USRE40500EExpiredUtility
Internal combustion engine
Est. expiryJul 25, 2020(expired)· nominal 20-yr term from priority
F02B 2075/025F01P 3/16F02F 1/40
65
PatentIndex Score
6
Cited by
63
References
167
Claims
Abstract
Improved internal combustion engine, particularly, an improved two-stroke, diesel aircraft engine. The invention includes a new wrist pin/connecting rod connection, a new cooling system for fuel injectors, a new cylinder head cooling arrangement, a new cooling jacket cross-feed arrangement, and a new combustion seal arrangement.
Claims
exact text as granted — not AI-modified1. An internal combustion engine, comprising:
an engine block at least partially defining a cylinder;
a cylinder head mounted on said cylinder; and
a cooling cap mounted on said cylinder head, wherein at least one of said cylinder head and said cooling cap includes a substantially annular coolant groove such that said cooling cap and said cylinder head define a substantially annular cooling passageway, said cooling cap also including inlet and outlet ports communicating with said cooling passageway so that cooling fluid can flow into said inlet port, through said cooling passageway, and out of said outlet port, thereby cooling said cylinder head.
2. An internal combustion engine according to claim 1 , wherein said cylinder head threads into a portion of said engine block, wherein said engine block includes a cooling jacket with an outlet and an inlet, and wherein said cooling cap is placed on said cylinder head with said inlet port in alignment with said cooling jacket outlet and with said outlet port in alignment with said cooling jacket inlet.
3. An internal combustion engine according to claim 2 , further comprising a transfer tube communicating between said inlet port and said cooling jacket outlet, and a transfer tube communicating between said outlet port and said cooling jacket inlet.
4. An internal combustion engine according to claim 1 , wherein said inlet port and said outlet port are not diametrically opposed around said cooling passageway, such that a first portion of said cooling passageway extends in one direction from said inlet port to said outlet port and a second portion of said cooling passageway extends in an opposite direction from said inlet port to said outlet port, said first portion being shorter in length than said second portion and said first portion also being restricted.
5. An internal combustion engine according to claim 1 , wherein said cooling cap is annular, and wherein said engine further comprises a plurality of clamping members spanning said cooling cap and securing said cooling cap to said cylinder head.
6. An internal combustion engine according to claim 5 , wherein each of said clamping members has opposite ends and is secured to said cylinder head by a pair of fasteners, with one fastener located adjacent one of said ends and the other fastener located adjacent the other of said ends.
7. An internal combustion engine according to claim 6 , wherein said fasteners thread into holes in said cylinder head, said cylinder head having therein a plurality of sets of holes such that each fastener can be located in a plurality of positions relative to said cylinder head.
8. An internal combustion engine according to claim 5 , wherein said engine further includes a fuel injector secured to said cylinder head by said clamping members.
9. An internal combustion engine according to claim 1 , wherein said engine is a two-stroke, diesel aircraft engine.
10. An internal combustion engine according to claim 1 , wherein said engine block includes a return port and a cooling jacket having an outlet, wherein said cooling cap is placed on said cylinder head with said inlet port in alignment with said cooling jacket outlet and with said outlet port in alignment with said return port.
11. An internal combustion engine according to claim 10 , further comprising a transfer tube communicating between said inlet port and said cooling jacket outlet, and a transfer tube communicating between said outlet port and said return port.
12. An internal combustion engine according to claim 1 , wherein cooling fluid flows into the inlet port, through the cooling passageway in a single direction, and out of the outlet.
13. An internal combustion engine according to claim 12 , wherein said coolant groove is blocked between the inlet and outlet ports of the cooling cap so as to substantially close the cooling passageway in the direction opposite said single direction between the inlet and outlet ports of the cooling cap, thereby causing the cooling fluid to flow in said single direction around the cooling passageway.
14. An internal combustion engine according to claim 13 , wherein said coolant groove is blocked by a projection that is located on the other of said cylinder head and said cooling cap and that extends into said coolant groove between the inlet and outlet ports of the cooling cap.
15. An internal combustion engine as set forth in claim 1 , wherein the engine is a two-stroke, diesel aircraft engine.
16. An internal combustion engine, comprising:
an engine block at least partially defining a cylinder, the engine block including a cooling jacket;
a cylinder head mounted on the cylinder; and
a cooling cap mounted on the cylinder head, wherein at least one of the cylinder head and the cooling cap has a coolant groove such that the cooling cap and the cylinder head define a cooling passageway, the cooling cap further having inlet and outlet ports communicating between the cooling passageway and the cooling jacket, such that cooling fluids flow into the inlet port, through the cooling passageway in a single direction, and out of the outlet port, thereby cooling the cylinder head.
17. An internal combustion engine as set forth in claim 16 , wherein the cooling passageway is annular, and wherein the engine further comprises a divider member positioned between the inlet and outlet ports of the cooling cap so as to substantially close the annular cooling passageway in one direction between the inlet and outlet ports of the cooling cap, thereby ensuring that the cooling fluid flows in an opposite direction around the cooling passageway.
18. An internal combustion engine as set forth in claim 16 , wherein the engine is a two-stroke, diesel aircraft engine.
19. An internal combustion engine according to claim 16 , wherein said coolant groove is blocked between the inlet and outlet ports of the cooling cap so as to substantially close the cooling passageway in the direction opposite said single direction between the inlet and outlet ports of the cooling cap, thereby causing the cooling fluid to flow in said single direction around the cooling passageway.
20. An internal combustion two-stroke diesel engine for an aircraft, comprising:
an engine block at least partially defining a cylinder;
a cylinder head mounted on the cylinder;
a cooling cap mounted on the cylinder head;
one of the cylinder head and the cooling cap having therein an annular coolant groove such that the cooling cap and the cylinder head define therebetween a cooling passageway;
the cooling cap further having inlet and outlet ports communicating with the cooling passageway; and
the other of the cylinder head and the cooling cap having there on a divider member that is positioned between the inlet and outlet ports and that extends into the coolant groove so as to substantially close the cooling passageway in one direction between the inlet and outlet ports of the cooling cap, thereby ensuring that the cooling fluid flows in an opposite direction around the cooling passageway.
21. An internal combustion engine according to claim 1 , further comprising:
a piston reciprocally operable within the cylinder; a fireplate positioned between the cylinder head and the piston, the fireplate cooperating with the piston to define a combustion chamber; and a head spring positioned between the cylinder head and the fireplate, such that the head spring provides a downward force against the fireplate to offset an upward force created by combustion within the combustion chamber.
22. An internal combustion engine as set forth in claim 21 , wherein the cylinder head threads into a portion of the engine block.
23. An internal combustion engine as set forth in claim 21 , wherein the cylinder head has an annular groove which receives the head spring.
24. An internal combustion engine as set forth in claim 23 , wherein the fireplate has a recess which also receives the head spring.
25. An internal combustion engine as set forth in claim 21 , wherein the cylinder includes a shoulder against which the head spring forces the fireplate.
26. An internal combustion engine as set forth in claim 25 , further comprising a cylindrical sleeve positioned within the cylinder, wherein the piston reciprocally operates within the sleeve, and wherein the sleeve provides the shoulder.
27. An internal combustion engine as set forth in claim 26 , further comprising a gasket positioned between the fireplate and the shoulder of the sleeve.
28. An internal combustion engine as set forth in claim 27 , wherein the gasket is a copper gasket.
29. An internal combustion engine as set forth in claim 21 , wherein the head spring is annular.
30. An internal combustion engine as set forth in claim 21 , wherein the head spring is a belleville spring.
31. An internal combustion engine as set forth in claim 21 , wherein the engine is a two-stroke, diesel aircraft engine.
32. An internal combustion engine according to claim 1 , further comprising:
a cylindrical sleeve positioned within the cylinder, the sleeve including a shoulder, wherein the cylinder head is threadably mounted to a portion of the engine block and on the cylinder, the cylinder head having an annular groove; a piston reciprocally operable within the sleeve; a gasket supported on the shoulder of the sleeve; a fireplate positioned between the cylinder head and the gasket, the fireplate having a top side which includes a recess, and a bottom side which cooperates with the piston to define a combustion chamber; and a belleville spring positioned between the cylinder head and the fireplate such that the spring is received by the annular groove of the cylinder head and the recess of the fireplate, so that when the cylinder head is threaded into the engine block, the spring is compressed between the cylinder head and the fireplate to provide a downward force against the top side of the fireplate to offset an upward force created by combustion within the combustion chamber, thereby substantially ensuring that the fireplate remains in contact with the gasket, and the gasket remains in contact with the shoulder of the sleeve, to provide an appropriate combustion seal during operation of the engine.
33. An internal combustion engine as set forth in claim 32 , wherein the gasket is a copper gasket.
34. An internal combustion engine as set forth in claim 32 , wherein the engine is a two-stroke, diesel aircraft engine.
35. An internal combustion engine according to claim 1 , wherein the engine block at least partially defines a crankcase, the engine further comprising:
a crankshaft rotatably supported within said crankcase; a piston reciprocally operable within said cylinder; a connecting rod for operatively coupling said piston to said crankshaft, said connecting rod including a first end connected to said crankshaft and a second end which includes an arcuate portion; a wrist pin pivotally connected to said piston, said wrist pin having an annular wall including a cylindrical outer surface engaging said arcuate portion of said connecting rod, and said annular wall including a cylindrical inner surface; a wrist pin insert within said wrist pin; and a plurality of fasteners extending through said annular wall of said wrist pin and securing said arcuate portion of said connecting rod to said wrist pin insert, thereby securing said connecting rod to said wrist pin.
36. An internal combustion engine according to claim 35 , wherein said second end of said connecting rod does not completely encircle said wrist pin.
37. An internal combustion engine according to claim 35 , wherein said second end of said connecting rod has an arcuate extent of less than 180 °.
38. An internal combustion engine according to claim 35 , wherein said plurality of fasteners are threaded into said wrist pin insert.
39. An internal combustion engine according to claim 35 , wherein said wrist pin insert is cylindrical.
40. An internal combustion engine according to claim 35 , wherein said engine is a two-stroke, diesel aircraft engine.
41. An internal combustion engine according to claim 35 , wherein substantially an entire longitudinal portion of said outer surface of said wrist pin engages said piston.
42. An internal combustion engine according to claim 1 , wherein the engine block is a V-type engine block at least partially defining a first cylinder bank and a second cylinder bank, a first cooling jacket adjacent said first cylinder bank, and a second cooling jacket adjacent said second cylinder bank, said engine block further defining a cross-feed cooling passageway which extends between said first cooling jacket and said second cooling jacket, the engine further comprising:
a first thermostat in communication with said first cooling jacket; and a second thermostat in communication with said second cooling jacket; said cross-feed cooling passageway providing cooling fluid flow between said cooling jackets at least in the event of failure of one of said thermostats.
43. An internal combustion engine according to claim 42 , wherein said engine is a two-stroke, diesel aircraft engine.
44. An internal combustion engine according to claim 1 , wherein said engine block includes female threads concentric with said cylinder, and wherein said cylinder head includes male threads engaging said female threads on said engine block.
45. An internal combustion engine according to claim 16 , further comprising:
a piston reciprocally operable within the cylinder; a fireplate positioned between the cylinder head and the piston, the fireplate cooperating with the piston to define a combustion chamber; and a head spring positioned between the cylinder head and the fireplate, such that the head spring provides a downward force against the fireplate to offset an upward force created by combustion within the combustion chamber.
46. An internal combustion engine as set forth in claim 45 , wherein the cylinder head threads into a portion of the engine block.
47. An internal combustion engine as set forth in claim 45 , wherein the cylinder head has an annular groove which receives the head spring.
48. An internal combustion engine as set forth in claim 47 , wherein the fireplate has a recess which also receives the head spring.
49. An internal combustion engine as set forth in claim 45 , wherein the cylinder includes a shoulder against which the head spring forces the fireplate.
50. An internal combustion engine as set forth in claim 49 , further comprising a cylindrical sleeve positioned within the cylinder, wherein the piston reciprocally operates within the sleeve, and wherein the sleeve provides the shoulder.
51. An internal combustion engine as set forth in claim 50 , further comprising a gasket positioned between the fireplate and the shoulder of the sleeve.
52. An internal combustion engine as set forth in claim 51 , wherein the gasket is a copper gasket.
53. An internal combustion engine as set forth in claim 45 , wherein the head spring is annular.
54. An internal combustion engine as set forth in claim 45 , wherein the head spring is a belleville spring.
55. An internal combustion engine as set forth in claim 45 , wherein the engine is a two-stroke, diesel aircraft engine.
56. An internal combustion engine according to claim 16 , further comprising:
a cylindrical sleeve positioned within the cylinder, the sleeve including a shoulder, wherein the cylinder head is threadably mounted to a portion of the engine block and on the cylinder, the cylinder head having an annular groove; a piston reciprocally operable within the sleeve; a gasket supported on the shoulder of the sleeve; a fireplate positioned between the cylinder head and the gasket, the fireplate having a top side which includes a recess, and a bottom side which cooperates with the piston to define a combustion chamber; and a belleville spring positioned between the cylinder head and the fireplate such that the spring is received by the annular groove of the cylinder head and the recess of the fireplate, so that when the cylinder head is threaded into the engine block, the spring is compressed between the cylinder head and the fireplate to provide a downward force against the top side of the fireplate to offset an upward force created by combustion within the combustion chamber, thereby substantially ensuring that the fireplate remains in contact with the gasket, and the gasket remains in contact with the shoulder of the sleeve, to provide an appropriate combustion seal during operation of the engine.
57. An internal combustion engine as set forth in claim 56 , wherein the gasket is a copper gasket.
58. An internal combustion engine as set forth in claim 56 , wherein the engine is a two-stroke, diesel aircraft engine.
59. An internal combustion engine according to claim 16 , wherein the engine block at least partially defines a crankcase, the engine further comprising:
a crankshaft rotatably supported within said crankcase; a piston reciprocally operable within said cylinder; a connecting rod for operatively coupling said piston to said crankshaft, said connecting rod including a first end connected to said crankshaft and a second end which includes an arcuate portion; a wrist pin pivotally connected to said piston, said wrist pin having an annular wall including a cylindrical outer surface engaging said arcuate portion of said connecting rod, and said annular wall including a cylindrical inner surface; a wrist pin insert within said wrist pin; and a plurality of fasteners extending through said annular wall of said wrist pin and securing said arcuate portion of said connecting rod to said wrist pin insert, thereby securing said connecting rod to said wrist pin.
60. An internal combustion engine according to claim 59 , wherein said second end of said connecting rod does not completely encircle said wrist pin.
61. An internal combustion engine according to claim 59 , wherein said second end of said connecting rod has an arcuate extent of less than 180 °.
62. An internal combustion engine according to claim 59 , wherein said plurality of fasteners are threaded into said wrist pin insert.
63. An internal combustion engine according to claim 59 , wherein said wrist pin insert is cylindrical.
64. An internal combustion engine according to claim 59 , wherein said engine is a two-stroke, diesel aircraft engine.
65. An internal combustion engine according to claim 59 , wherein substantially an entire longitudinal portion of said outer surface of said wrist pin engages said piston.
66. An internal combustion engine according to claim 16 , wherein the engine block is a V-type engine block at least partially defining a first cylinder bank and a second cylinder bank, a first cooling jacket adjacent said first cylinder bank, and a second cooling jacket adjacent said second cylinder bank, said engine block further defining a cross-feed cooling passageway which extends between said first cooling jacket and said second cooling jacket, the engine further comprising:
a first thermostat in communication with said first cooling jacket; and a second thermostat in communication with said second cooling jacket; said cross-feed cooling passageway providing cooling fluid flow between said cooling jackets at least in the event of failure of one of said thermostats.
67. An internal combustion engine according to claim 66 , wherein said engine is a two-stroke, diesel aircraft engine.
68. An internal combustion engine according to claim 16 , wherein said engine block including female threads concentric with said cylinder, and wherein said cylinder head includes male threads engaging said female threads on said engine block.
69. An internal combustion engine according to claim 20 , comprising:
a piston reciprocally operable within the cylinder; a fireplate positioned between the cylinder head and the piston, the fireplate cooperating with the piston to define a combustion chamber; and a head spring positioned between the cylinder head and the fireplate, such that the head spring provides a downward force against the fireplate to offset an upward force created by combustion within the combustion chamber.
70. An internal combustion engine as set forth in claim 69 , wherein the cylinder head threads into a portion of the engine block.
71. An internal combustion engine as set forth in claim 69 , wherein the cylinder head has an annular groove which receives the head spring.
72. An internal combustion engine as set forth in claim 71 , wherein the fireplate has a recess which also receives the head spring.
73. An internal combustion engine as set forth in claim 69 , wherein the cylinder includes a shoulder against which the head spring forces the fireplate.
74. An internal combustion engine as set forth in claim 73 , further comprising a cylindrical sleeve positioned within the cylinder, wherein the piston reciprocally operates within the sleeve, and wherein the sleeve provides the shoulder.
75. An internal combustion engine as set forth in claim 74 , further comprising a gasket positioned between the fireplate and the shoulder of the sleeve.
76. An internal combustion engine as set forth in claim 75 , wherein the gasket is a copper gasket.
77. An internal combustion engine as set forth in claim 69 , wherein the head spring is annular.
78. An internal combustion engine as set forth in claim 69 , wherein the head spring is a belleville spring.
79. An internal combustion engine as set forth in claim 69 , wherein the engine is a two-stroke, diesel aircraft engine.
80. An internal combustion engine according to claim 20 , comprising:
a cylindrical sleeve positioned within the cylinder, the sleeve including a shoulder, wherein the cylinder head is threadably mounted to a portion of the engine block and on the cylinder, the cylinder head having an annular groove; a piston reciprocally operable within the sleeve; a gasket supported on the shoulder of the sleeve; a fireplate positioned between the cylinder head and the gasket, the fireplate having a top side which includes a recess, and a bottom side which cooperates with the piston to define a combustion chamber; and a belleville spring positioned between the cylinder head and the fireplate such that the spring is received by the annular groove of the cylinder head and the recess of the fireplate, so that when the cylinder head is threaded into the engine block, the spring is compressed between the cylinder head and the fireplate to provide a downward force against the top side of the fireplate to offset an upward force created by combustion within the combustion chamber, thereby substantially ensuring that the fireplate remains in contact with the gasket, and the gasket remains in contact with the shoulder of the sleeve, to provide an appropriate combustion seal during operation of the engine.
81. An internal combustion engine as set forth in claim 80 , wherein the gasket is a copper gasket.
82. An internal combustion engine as set forth in claim 80 , wherein the engine is a two-stroke, diesel aircraft engine.
83. An internal combustion engine according to claim 20 , wherein the engine block at least partially defines a crankcase, the engine further comprising:
a crankshaft rotatably supported within said crankcase; a piston reciprocally operable within said cylinder; a connecting rod for operatively coupling said piston to said crankshaft, said connecting rod including a first end connected to said crankshaft and a second end which includes an arcuate portion; a wrist pin pivotally connected to said piston, said wrist pin having an annular wall including a cylindrical outer surface engaging said arcuate portion of said connecting rod, and said annular wall including a cylindrical inner surface; a wrist pin insert within said wrist pin; and a plurality of fasteners extending through said annular wall of said wrist pin and securing said arcuate portion of said connecting rod to said wrist pin insert, thereby securing said connecting rod to said wrist pin.
84. An internal combustion engine according to claim 83 , wherein said second end of said connecting rod does not completely encircle said wrist pin.
85. An internal combustion engine according to claim 83 , wherein said second end of said connecting rod has an arcuate extent of less than 180 °.
86. An internal combustion engine according to claim 83 , wherein said plurality of fasteners are threaded into said wrist pin insert.
87. An internal combustion engine according to claim 83 , wherein said wrist pin insert is cylindrical.
88. An internal combustion engine according to claim 83 , wherein said engine is a two-stroke, diesel aircraft engine.
89. An internal combustion engine according to claim 83 , wherein substantially an entire longitudinal portion of said outer surface of said wrist pin engages said piston.
90. An internal combustion engine according to claim 20 , wherein the engine block is a V-type engine block at least partially defining a first cylinder bank and a second cylinder bank, a first cooling jacket adjacent said first cylinder bank, and a second cooling jacket adjacent said second cylinder bank, said engine block further defining a cross-feed cooling passageway which extends between said first cooling jacket and said second cooling jacket, the engine further comprising:
a first thermostat in communication with said first cooling jacket; and a second thermostat in communication with said second cooling jacket; said cross-feed cooling passageway providing cooling fluid flow between said cooling jackets at least in the event of failure of one of said thermostats.
91. An internal combustion engine according to claim 90 , wherein said engine is a two-stroke, diesel aircraft engine.
92. An internal combustion engine according to claim 20 , wherein said engine block includes female threads concentric with said cylinder, and wherein said cylinder head including male threads engaging said female threads on said engine block.
93. An internal combustion engine, comprising:
an engine block at least partially defining a cylinder; a cylinder head mounted to the engine block; a piston reciprocally operable within the cylinder; a fireplate positioned between the cylinder head and the piston, the fireplate cooperating with the piston to define a combustion chamber; and a head spring positioned between the cylinder head and the fireplate, such that the head spring provides a downward force against the fireplate to offset an upward force created by combustion within the combustion chamber.
94. An internal combustion engine as set forth in claim 93 , wherein the cylinder head threads into a portion of the engine block.
95. An internal combustion engine as set forth in claim 93 , wherein the cylinder head has an annular groove which receives the head spring.
96. An internal combustion engine as set forth in claim 95 , wherein the fireplate has a recess which also receives the head spring.
97. An internal combustion engine as set forth in claim 93 , wherein the cylinder includes a shoulder against which the head spring forces the fireplate.
98. An internal combustion engine as set forth in claim 97 , further comprising a cylindrical sleeve positioned within the cylinder, wherein the piston reciprocally operates within the sleeve, and wherein the sleeve provides the shoulder.
99. An internal combustion engine as set forth in claim 98 , further comprising a gasket positioned between the fireplate and the shoulder of the sleeve.
100. An internal combustion engine as set forth in claim 99 , wherein the gasket is a copper gasket.
101. An internal combustion engine as set forth in claim 93 , wherein the head spring is annular.
102. An internal combustion engine as set forth in claim 93 , wherein the head spring is a belleville spring.
103. An internal combustion engine as set forth in claim 93 , wherein the engine is a two-stroke, diesel aircraft engine.
104. An internal combustion engine according to claim 93 , wherein the cylinder head cooperates with said cylinder and said piston to define a combustion chamber, the engine further comprising:
a fuel injection system including: a fuel injector for injecting fuel into said combustion chamber, said fuel injector having a fuel inlet port, a fuel outlet port, a fuel passage communicating between said fuel inlet port and said fuel outlet port, a cooling fuel inlet port, a leak-off fuel outlet port, and a cooling fuel passage communicating between said cooling fuel inlet port and said leak-off fuel outlet port; a fuel pump; a fuel supply line communicating between said fuel pump and said fuel inlet port; a bypass fuel line communicating between said fuel pump and said cooling fuel inlet port, such that overflow fuel from said fuel pump flows through said bypass fuel line, into said cooling fuel inlet port, through said cooling fuel passage and out of said leak-off fuel outlet port, thereby cooling said fuel injector, wherein the overflow fuel is recirculated from said leak-off fuel outlet port back to said fuel pump; and a fuel filter placed upstream of said fuel pump such that the overflow fuel recirculated to said fuel pump flows through said fuel filter prior to reaching said fuel pump, and such that the overflow fuel which cools said fuel injector is warmed as it flows through said fuel injector, thereby heating the fuel which flows through said fuel filter to substantially prevent ice build-up on said fuel filter during cold weather.
105. An internal combustion engine as set forth in claim 104 , wherein the cylinder head threads into a portion of the engine block.
106. An internal combustion engine as set forth in claim 104 , wherein the cylinder head has an annular groove which receives the head spring.
107. An internal combustion engine as set forth in claim 106 , wherein the fireplate has a recess which also receives the head spring.
108. An internal combustion engine as set forth in claim 104 , wherein the cylinder includes a shoulder against which the head spring forces the fireplate.
109. An internal combustion engine as set forth in claim 108 , further comprising a cylindrical sleeve positioned within the cylinder, wherein the piston reciprocally operates within the sleeve, and wherein the sleeve provides the shoulder.
110. An internal combustion engine as set forth in claim 109 , further comprising a gasket positioned between the fireplate and the shoulder of the sleeve.
111. An internal combustion engine as set forth in claim 110 , wherein the gasket is a copper gasket.
112. An internal combustion engine as set forth in claim 104 , wherein the head spring is annular.
113. An internal combustion engine as set forth in claim 104 , wherein the head spring is a belleville spring.
114. An internal combustion engine as set forth in claim 104 , wherein the engine is a two-stroke, diesel aircraft engine.
115. An internal combustion engine, comprising:
an engine block at least partially defining a cylinder; a cylindrical sleeve positioned within the cylinder, the sleeve including a shoulder; a cylinder head threadably mounted to a portion of the engine block and on the cylinder, the cylinder head having an annular groove; a piston reciprocally operable within the sleeve; a gasket supported on the shoulder of the sleeve; a fireplate positioned between the cylinder head and the gasket, the fireplate having a top side which includes a recess, and a bottom side which cooperates with the piston to define a combustion chamber; and a belleville spring positioned between the cylinder head and the fireplate such that the spring is received by the annular groove of the cylinder head and the recess of the fireplate, so that when the cylinder head is threaded into the engine block, the spring is compressed between the cylinder head and the fireplate to provide a downward force against the top side of the fireplate to offset an upward force created by combustion within the combustion chamber, thereby substantially ensuring that the fireplate remains in contact with the gasket, and the gasket remains in contact with the shoulder of the sleeve, to provide an appropriate combustion seal during operation of the engine.
116. An internal combustion engine as set forth in claim 115 , wherein the gasket is a copper gasket.
117. An internal combustion engine as set forth in claim 115 , wherein the engine is a two-stroke, diesel aircraft engine.
118. An internal combustion engine according to claim 115 , wherein the cylinder head cooperates with said cylinder and said piston to define a combustion chamber, the engine further comprising:
a fuel injection system including: a fuel injector for injecting fuel into said combustion chamber, said fuel injector having a fuel inlet port, a fuel outlet port, a fuel passage communicating between said fuel inlet port and said fuel outlet port, a cooling fuel inlet port, a leak-off fuel outlet port, and a cooling fuel passage communicating between said cooling fuel inlet port and said leak-off fuel outlet port; a fuel pump; a fuel supply line communicating between said fuel pump and said fuel inlet port; a bypass fuel line communicating between said fuel pump and said cooling fuel inlet port, such that overflow fuel from said fuel pump flows through said bypass fuel line, into said cooling fuel inlet port, through said cooling fuel passage and out of said leak-off fuel outlet port, thereby cooling said fuel injector, wherein the overflow fuel is recirculated from said leak-off fuel outlet port back to said fuel pump; and a fuel filter placed upstream of said fuel pump such that the overflow fuel recirculated to said fuel pump flows through said fuel filter prior to reaching said fuel pump, and such that the overflow fuel which cools said fuel injector is warmed as it flows through said fuel injector, thereby heating the fuel which flows through said fuel filter to substantially prevent ice build-up on said fuel filter during cold weather.
119. An internal combustion engine as set forth in claim 118 , wherein the gasket is a copper gasket.
120. An internal combustion engine as set forth in claim 118 , wherein the engine is a two-stroke, diesel aircraft engine.
121. An internal combustion engine according to claim 115 , wherein the cylinder head cooperates with said cylinder and said piston to define a combustion chamber, the engine further comprising:
a fuel injection system including: a fuel injector for injecting fuel into said combustion chamber, said fuel injector including a fuel injector nut, and a fuel injector body threaded into said fuel injector nut so as to define with said fuel injector nut a space into which leak-off fuel normally flows, said fuel injector body having therein a fuel inlet port, a cooling fuel inlet port, a leak-off fuel outlet port, an upstream cooling fuel passage portion between said cooling fuel inlet port and said space, and a downstream cooling fuel passage portion between said space and said leak-off fuel outlet port, and said fuel injector also including a fuel outlet port, and a fuel passage communicating between said fuel inlet port and said fuel outlet port; a fuel pump; a fuel supply line communicating between said fuel pump and said fuel inlet port; a bypass fuel line communicating between said fuel pump and said cooling fuel inlet port, such that overflow fuel from said fuel pump flows through said bypass fuel line, into said cooling fuel inlet port, through said upstream cooling fuel passage portion and into said space, where the overflow fuel commingles with leak-off fuel in said space, through said downstream cooling fuel passage portion and out of said leak-off fuel outlet port, thereby cooling said fuel injector; and a fuel return line conducting the overflow fuel from said leak-off fuel outlet port back to said fuel pump.
122. An internal combustion engine as set forth in claim 121 , wherein the gasket is a copper gasket.
123. An internal combustion engine as set forth in claim 121 , wherein the engine is a two-stroke, diesel aircraft engine.
124. A method of assembling a cylinder head to an engine block of an internal combustion engine to create a combustion seal, the method comprising the acts of:
positioning a piston, which is reciprocally operable within a cylinder of the engine, in its top dead center position; positioning a fireplate within the cylinder above the piston to create a predetermined combustion chamber volume between the fireplate and the piston; threading the cylinder head into the engine block until the cylinder head contacts the fireplate, thereby defining a final assembly position for the cylinder head with respect to the engine block; marking the final assembly position of the cylinder head; unthreading the cylinder head from the engine block; positioning a head spring between the cylinder head and the fireplate; and threading the cylinder head into the engine block a second time until the cylinder head is located in the final assembly position, such that threading the cylinder head into the engine block the second time compresses the head spring between the cylinder head and the fireplate so that the head spring provides a downward force against the fireplate to offset an upward force created by combustion within the combustion chamber.
125. A method as set forth in claim 124 , further comprising the act of positioning a gasket on a shoulder of a sleeve positioned within the cylinder, the gasket being located between the shoulder of the sleeve and the fireplate, the piston being reciprocally operable within the sleeve, and the gasket being appropriately sized to obtain the predetermined combustion chamber volume.
126. A method as set forth in claim 125 , wherein the gasket is a copper gasket.
127. A method as set forth in claim 124 , wherein the head spring is a belleville spring.
128. A method as set forth in claim 124 , wherein the engine is a two-stroke, diesel aircraft engine.
129. An internal combustion engine, comprising:
a V-type engine block at least partially defining a first cylinder bank and a second cylinder bank, a first cooling jacket adjacent said first cylinder bank, and a second cooling jacket adjacent said second cylinder bank, said engine block further defining a cross-feed cooling passageway which extends between said first cooling jacket and said second cooling jacket; a first thermostat in communication with said first cooling jacket; and a second thermostat in communication with said second cooling jacket; said cross-feed cooling passageway configured to allow cooling fluid flow from one of said first and second cooling jackets to the other of said first and second cooling jackets through said cross-feed cooling passageway at least in the event of failure of one of said thermostats.
130. An internal combustion engine according to claim 129 , wherein said engine is a two-stroke, diesel aircraft engine.
131. An internal combustion engine according to claim 129 , wherein said cross-feed cooling passageway is drilled through a portion of said V-type engine block.
132. A method of assembling a cylinder head to an engine block of an internal combustion engine to create a combustion seal, the internal combustion engine including an engine block at least partially defining a cylinder, a cylinder head mounted on the cylinder, and a cooling cap mounted on the cylinder head, wherein at least one of the cylinder head and the cooling cap includes a substantially annular coolant groove such that the cooling cap and the cylinder head define a substantially annular cooling passageway, the cooling cap also including inlet and outlet ports communicating with the cooling passageway so that cooling fluid can flow into the inlet port, through the cooling passageway, and out of the outlet port, thereby cooling the cylinder head, the method comprising the acts of:
positioning a piston, which is reciprocally operable within the cylinder of the engine, in its top dead center position; positioning a fireplate within the cylinder above the piston to create a predetermined combustion chamber volume between the fireplate and the piston; threading the cylinder head into the engine block until the cylinder head contacts the fireplate, thereby defining a final assembly position for the cylinder head with respect to the engine block; marking the final assembly position of the cylinder head; unthreading the cylinder head from the engine block; positioning a head spring between the cylinder head and the fireplate; and threading the cylinder head into the engine block a second time until the cylinder head is located in the final assembly position, such that threading the cylinder head into the engine block the second time compresses the head spring between the cylinder head and the fireplate so that the head spring provides a downward force against the fireplate to offset an upward force created by combustion within the combustion chamber.
133. A method as set forth in claim 132 further comprising the act of positioning a gasket on a shoulder of a sleeve positioned within the cylinder, the gasket being located between the shoulder of the sleeve and the fireplate, the piston being reciprocally operable within the sleeve, and the gasket being appropriately sized to obtain the predetermined combustion chamber volume.
134. A method as set forth in claim 133 , wherein the gasket is a copper gasket.
135. A method as set forth in claim 132 , wherein the head spring is a belleville spring.
136. A method as set forth in claim 132 , wherein the engine is a two-stroke, diesel aircraft engine.
137. A method of assembling a cylinder head to an engine block of an internal combustion engine to create a combustion seal, the internal combustion engine including an engine block at least partially defining a cylinder, a cylinder head mounted on the cylinder, and a cooling cap mounted on the cylinder head, wherein at least one of the cylinder head and the cooling cap has a coolant groove such that the cooling cap and the cylinder head define a cooling passageway, the cooling cap further having inlet and outlet ports communicating with the cooling passageway, such that cooling fluid flows into the inlet port, through the cooling passageway in a single direction, and out of the outlet port, thereby cooling the cylinder head, the method comprising the acts of:
positioning a piston, which is reciprocally operable within the cylinder of the engine, in its top dead center position; positioning a fireplate within the cylinder above the piston to create a predetermined combustion chamber volume between the fireplate and the piston; threading the cylinder head into the engine block until the cylinder head contacts the fireplate, thereby defining a final assembly position for the cylinder head with respect to the engine block; marking the final assembly position of the cylinder head; unthreading the cylinder head from the engine block; positioning a head spring between the cylinder head and the fireplate; and threading the cylinder head into the engine block a second time until the cylinder head is located in the final assembly position, such that threading the cylinder head into the engine block the second time compresses the head spring between the cylinder head and the fireplate so that the head spring provides a downward force against the fireplate to offset an upward force created by combustion within the combustion chamber.
138. A method as set forth in claim 137 , further comprising the act of positioning a gasket on a shoulder of a sleeve positioned within the cylinder, the gasket being located between the shoulder of the sleeve and the fireplate, the piston being reciprocally operable within the sleeve, and the gasket being appropriately sized to obtain the predetermined combustion chamber volume.
139. A method as set forth in claim 138 , wherein the gasket is a copper gasket.
140. A method as set forth in claim 137 , wherein the head spring is a belleville spring.
141. A method as set forth in claim 137 , wherein the engine is a two-stroke, diesel aircraft engine.
142. A method of assembling a cylinder head to an engine block of an internal combustion engine to create a combustion seal, the internal combustion engine including an engine block at least partially defining a cylinder, a cylinder head mounted on the cylinder, a cooling cap mounted on the cylinder head, one of the cylinder head and the cooling cap having therein an annular coolant groove such that the cooling cap and the cylinder head define therebetween a cooling passageway, the cooling cap further having inlet and outlet ports communicating with the cooling passageway, and the other of the cylinder head and the cooling cap having there on a divider member that is positioned between the inlet and outlet ports and that extends into the coolant groove so as to substantially close the cooling passageway in one direction between the inlet and outlet ports of the cooling cap, thereby ensuring that the cooling fluid flows in an opposite direction around the cooling passageway, the method comprising the acts of:
positioning a piston, which is reciprocally operable within the cylinder of the engine, in its top dead center position; positioning a fireplate within the cylinder above the piston to create a predetermined combustion chamber volume between the fireplate and the piston; threading the cylinder head into the engine block until the cylinder head contacts the fireplate, thereby defining a final assembly position for the cylinder head with respect to the engine block; marking the final assembly position of the cylinder head; unthreading the cylinder head from the engine block; positioning a head spring between the cylinder head and the fireplate; and threading the cylinder head into the engine block a second time until the cylinder head is located in the final assembly position, such that threading the cylinder head into the engine block the second time compresses the head spring between the cylinder head and the fireplate so that the head spring provides a downward force against the fireplate to offset an upward force created by combustion within the combustion chamber.
143. A method as set forth in claim 142 further comprising the act of positioning a gasket on a shoulder of a sleeve positioned within the cylinder, the gasket being located between the shoulder of the sleeve and the fireplate, the piston being reciprocally operable within the sleeve, and the gasket being appropriately sized to obtain the predetermined combustion chamber volume.
144. A method as set forth in claim 143 , wherein the gasket is a copper gasket.
145. A method as set forth in claim 142 , wherein the head spring is a belleville spring.
146. A method as set forth in claim 142 , wherein the engine is a two-stroke, diesel aircraft engine.
147. A method of assembling a cylinder head to an engine block of an internal combustion engine to create a combustion seal, the internal combustion engine including an engine block at least partially defining a cylinder, a piston reciprocally operable within said cylinder, a cylinder head cooperating with said cylinder and said piston to define a combustion chamber, and a fuel injection system including a fuel injector for injecting fuel into said combustion chamber, said fuel injector having a fuel inlet port, a fuel outlet port, a fuel passage communicating between said fuel inlet port and said fuel outlet port, a cooling fuel inlet port, a leak-of fuel outlet port, and a cooling fuel passage communicating between said cooling fuel inlet port and said leak-off fuel outlet port, a fuel pump, a fuel supply line communicating between said fuel pump and said fuel inlet port, a bypass fuel line communicating between said fuel pump and said cooling fuel inlet port, such that overflow fuel from said fuel pump flows through said bypass fuel line, into said cooling fuel inlet port, through said cooling fuel passage and out of said leak-off fuel outlet port, thereby cooling said fuel injector, wherein the overflow fuel is recirculated from said leak-off fuel outlet port back to said fuel pump, and a fuel filter placed upstream of said fuel pump such that the overflow fuel recirculated to said fuel pump flows through said fuel filter prior to reaching said fuel pump, and such that the overflow fuel which cools said fuel injector is warmed as it flows through said fuel injector, thereby heating the fuel which flows through said fuel filter to substantially prevent ice build-up on said fuel filter during cold weather, the method comprising the acts of:
positioning a piston, which is reciprocally operable within a cylinder of the engine, in its top dead center position; positioning a fireplate within the cylinder above the piston to create a predetermined combustion chamber volume between the fireplate and the piston; threading the cylinder head into the engine block until the cylinder head contacts the fireplate, thereby defining a final assembly position for the cylinder head with respect to the engine block; marking the final assembly position of the cylinder head; unthreading the cylinder head from the engine block; positioning a head spring between the cylinder head and the fireplate; and threading the cylinder head into the engine block a second time until the cylinder head is located in the final assembly position, such that threading the cylinder head into the engine block the second time compresses the head spring between the cylinder head and the fireplate so that the head spring provides a downward force against the fireplate to offset an upward force created by combustion within the combustion chamber.
148. A method as set forth in claim 147 , further comprising the act of positioning a gasket on a shoulder of a sleeve positioned within the cylinder, the gasket being located between the shoulder of the sleeve and the fireplate, the piston being reciprocally operable within the sleeve, and the gasket being appropriately sized to obtain the predetermined combustion chamber volume.
149. A method as set forth in claim 148 , wherein the gasket is a copper gasket.
150. A method as set forth in claim 147 , wherein the head spring is a belleville spring.
151. A method as set forth in claim 147 , wherein the engine is a two-stroke, diesel aircraft engine.
152. An internal combustion engine according to claim 93 , wherein the cylinder head cooperates with said cylinder and said piston to define a combustion chamber, the engine further comprising:
a fuel injection system including: a fuel injector for injecting fuel into said combustion chamber, said fuel injector including a fuel injector nut, and a fuel injector body threaded into said fuel injector nut so as to define within said fuel injector nut a space into which leak-off fuel normally flows, said fuel injector body having therein a fuel inlet port, a cooling fuel inlet port, a leak-off fuel outlet port, an upstream cooling fuel passage portion between said cooling fuel inlet port and said space, and a downstream cooling fuel passage portion between said space and said leak-off fuel outlet port, and said fuel injector also including a fuel outlet port, and a fuel passage communicating between said fuel inlet port and said fuel outlet port; a fuel pump; a fuel supply line communicating between said fuel pump and said fuel inlet port; a bypass fuel line communicating between said fuel pump and said cooling fuel inlet port, such that overflow fuel from said fuel pump flows through said bypass fuel line, into said cooling fuel inlet port, through said upstream cooling fuel passage portion and into said space, where the overflow fuel commingles with leak-off fuel in said space, through said downstream cooling fuel passage portion and out of said leak-off fuel outlet port, thereby cooling said fuel injector; and a fuel return line conducting the overflow fuel from said leak-off fuel outlet port back to said fuel pump.
153. An internal combustion engine as set forth in claim 152 , wherein the cylinder head threads into a portion of the engine block.
154. An internal combustion engine as set forth in claim 152 , wherein the cylinder head has an annular groove which receives the head spring.
155. An internal combustion engine as set forth in claim 154 , wherein the fireplate has a recess which also receives the head spring.
156. An internal combustion engine as set forth in claim 152 , wherein the cylinder includes a shoulder against which the head spring forces the fireplate.
157. An internal combustion engine as set forth in claim 156 , further comprising a cylindrical sleeve positioned within the cylinder, wherein the piston reciprocally operates within the sleeve, and wherein the sleeve provides the shoulder.
158. An internal combustion engine as set forth in claim 157 , further comprising a gasket positioned between the fireplate and the shoulder of the sleeve.
159. An internal combustion engine as set forth in claim 158 , wherein the gasket is a copper gasket.
160. An internal combustion engine as set forth in claim 152 , wherein the head spring is annular.
161. An internal combustion engine as set forth in claim 152 , wherein the head spring is a belleville spring.
162. An internal combustion engine as set forth in claim 152 , wherein the engine is a two-stroke, diesel aircraft engine.
163. A method of assembling a cylinder head to an engine block of an internal combustion engine to create a combustion seal, the internal combustion engine including an engine block at least partially defining a cylinder, a piston reciprocally operable within said cylinder, a cylinder head cooperating with said cylinder and said piston to define a combustion chamber, and a fuel injection system including, a fuel injector for injecting fuel into said combustion chamber, said fuel injector including a fuel injector nut, and a fuel injector body threaded into said fuel injector nut so as to define within said fuel injector nut a space into which leak-off fuel normally flows, said fuel injector body having therein a fuel inlet port, a cooling fuel inlet port, a leak-off fuel outlet port, an upstream cooling fuel passage portion between said cooling fuel inlet port and said space, and a downstream cooling fuel passage portion between said space and said leak-off fuel outlet port, and said fuel injector also including a fuel outlet port, and a fuel passage communicating between said fuel inlet port and said fuel outlet port, a fuel pump, a fuel supply line communicating between said fuel pump and said fuel inlet port, a bypass fuel line communicating between said fuel pump and said cooling fuel inlet port, such that overflow fuel from said fuel pump flows through said bypass fuel line, into said cooling fuel inlet port, through said upstream cooling fuel passage portion and into said space, where the overflow fuel commingles with leak-off fuel in said space, through said downstream cooling fuel passage portion and out of said leak-off fuel outlet port, thereby cooling said fuel injector, and a fuel return line conducting the overflow fuel from said leak-off fuel outlet port back to said fuel pump, the method comprising the acts of:
positioning a piston, which is reciprocally operable within the cylinder of the engine, in its top dead center position; positioning a fireplate within the cylinder above the piston to create a predetermined combustion chamber volume between the fireplate and the piston; threading the cylinder head into the engine block until the cylinder head contacts the fireplate, thereby defining a final assembly position for the cylinder head with respect to the engine block; marking the final assembly position of the cylinder head; unthreading the cylinder head from the engine block; positioning a head spring between the cylinder head and the fireplate; and threading the cylinder head into the engine block a second time until the cylinder head is located in the final assembly position, such that threading the cylinder head into the engine block the second time compresses the head spring between the cylinder head and the fireplate so that the head spring provides a downward force against the fireplate to offset an upward force created by combustion within the combustion chamber.
164. A method as set forth in claim 163 , further comprising the act of positioning a gasket on a shoulder of a sleeve positioned within the cylinder, the gasket being located between the shoulder of the sleeve and the fireplate, the piston being reciprocally operable within the sleeve, and the gasket being appropriately sized to obtain the predetermined combustion chamber volume.
165. A method as set forth in claim 164 , wherein the gasket is a copper gasket.
166. A method as set forth in claim 163 , wherein the head spring is a belleville spring.
167. A method as set forth in claim 163 , wherein the engine is a two-stroke, diesel aircraft engine.Cited by (0)
No later patents cite this yet.
References (0)
No backward citations on record.