Geared architecture for high speed and small volume fan drive turbine

Abstract

A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades. A fan shaft support supports the fan shaft and a gear system is connected to the fan shaft. The gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness. At least one of said gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.

What is claimed is: 
     
         1 . A gas turbine engine, comprising:
 a fan shaft driving a fan having fan blades;   a fan shaft support that supports said fan shaft;   a gear system connected to said fan shaft, said gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness and a reduction ratio greater than 2.3;   a gear system input to said gear system defining a gear system input lateral stiffness and a gear system input transverse stiffness; and   wherein at least one of said gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.   
     
     
         2 . The gas turbine engine of  claim 1 , further comprising a bypass ratio greater than ten (10). 
     
     
         3 . The gas turbine engine of  claim 2 , further comprising a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1 and a two stage high pressure turbine, wherein said low pressure turbine pressure ratio is a ratio of a pressure measured prior to said inlet as related to a pressure at said outlet prior to any exhaust nozzle. 
     
     
         4 . The gas turbine engine of  claim 2 , further comprising a low corrected fan tip speed less than about 1150 ft/second, wherein said low corrected fan tip speed is an actual fan tip speed at an ambient temperature divided by [(Tram °R)/(518.7°R)]0.5, where T represents said ambient temperature in degrees Rankine. 
     
     
         5 . The gas turbine engine of  claim 2 , wherein said gear system input lateral stiffness is less than 5% of said gear mesh lateral stiffness. 
     
     
         6 . The gas turbine engine of  claim 5 , wherein gear system input transverse stiffness is less than 5% of said gear mesh transverse stiffness. 
     
     
         7 . The gas turbine engine of  claim 6 , wherein said fan shaft support defines a fan shaft support lateral stiffness and said gear system input lateral stiffness is less than 11% of said fan shaft support lateral stiffness. 
     
     
         8 . The gas turbine engine of  claim 7 , further comprising a flexible support supporting the gear system defining a flexible support transverse stiffness and said fan shaft support defines a fan shaft support transverse stiffness, wherein said flexible support transverse stiffness is less than 11% of said fan shaft support transverse stiffness. 
     
     
         9 . The gas turbine engine of  claim 8 , further comprising a mid-turbine frame including a plurality of airfoils extending into a flow path. 
     
     
         10 . The gas turbine engine of  claim 5 , further comprising a two stage high pressure turbine and a low fan pressure ratio of less than 1.45 and said low fan pressure ratio is measured across the fan blades alone. 
     
     
         11 . The gas turbine engine of  claim 10 , further comprising a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1, wherein said low pressure turbine pressure ratio is a ratio of a pressure measured prior to said inlet as related to a pressure at said outlet prior to any exhaust nozzle. 
     
     
         12 . The gas turbine engine of  claim 11 , wherein said fan shaft support defines a fan shaft support transverse stiffness and said gear system input transverse stiffness is less than 11% of said fan shaft support transverse stiffness and said gear system input both transfers torque and facilitates segregation of vibrations. 
     
     
         13 . The gas turbine engine of  claim 11 , further comprising a low corrected fan tip speed less than about 1150 ft/second, wherein said low corrected fan tip speed is an actual fan tip speed at an ambient temperature divided by [(Tram °R)/(518.7°R)]0.5, where T represents said ambient temperature in degrees Rankine. 
     
     
         14 . A gas turbine engine, comprising:
 a fan shaft driving a fan having fan blades;   a fan shaft support that supports said fan shaft;   a gear system connected to said fan shaft, said gear system includes a gear mesh defining a gear mesh transverse stiffness and a reduction ratio greater than 2.3;   a gear system input connected to said fan shaft defining a gear system input transverse stiffness, wherein said gear system input transverse stiffness is less than 5% of said gear mesh transverse stiffness; and   a low fan pressure ratio of less than 1.45 and said low fan pressure ratio is measured across the fan blades alone.   
     
     
         15 . The gas turbine engine of  claim 14 , further comprising a two stage high pressure turbine and a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1, wherein said low pressure turbine pressure ratio is a ratio of a pressure measured prior to said inlet as related to a pressure at said outlet prior to any exhaust nozzle. 
     
     
         16 . The gas turbine engine of  claim 15 , further comprising a low corrected fan tip speed less than about 1150 ft/second, wherein said low corrected fan tip speed is an actual fan tip speed at an ambient temperature divided by [(Tram °R)/(518.7°R)]0.5, where T represents said ambient temperature in degrees Rankine. 
     
     
         17 . The gas turbine engine of  claim 16 , wherein said fan shaft support defines a fan shaft support lateral stiffness and said gear system input lateral stiffness is less than 11% of said fan shaft support lateral stiffness. 
     
     
         18 . The gas turbine engine of  claim 17 , further comprising a bypass ratio greater than ten (10). 
     
     
         19 . The gas turbine engine of  claim 14 , further comprising a low corrected fan tip speed less than about 1150 ft/second, wherein said low corrected fan tip speed is an actual fan tip speed at an ambient temperature divided by [(Tram °R)/(518.7°R)]0.5, where T represents said ambient temperature in degrees Rankine. 
     
     
         20 . A gas turbine engine, comprising:
 a fan shaft driving a fan having fan blades;   a fan shaft support that supports said fan shaft;   a gear system connected to said fan shaft, said gear system a gear mesh defining a gear mesh transverse stiffness and a gear mesh lateral stiffness, and a reduction ratio greater than 2.3;   a gear system input connected to said fan shaft defining a gear system input later stiffness and a gear system input transverse stiffness; and   wherein said gear system input transverse stiffness is less than 5% of said gear mesh transverse stiffness and said gear system input lateral stiffness is less than 5% of said gear mesh lateral stiffness.   
     
     
         21 . The gas turbine engine of  claim 20 , further comprising a two stage high pressure turbine and a low fan pressure ratio of less than 1.45 and said low fan pressure ratio is measured across the fan blades alone. 
     
     
         22 . The gas turbine engine of  claim 21 , further comprising a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1, wherein said low pressure turbine pressure ratio is a ratio of a pressure measured prior to said inlet as related to a pressure at said outlet prior to any exhaust nozzle. 
     
     
         23 . The gas turbine engine of  claim 22 , further comprising a low corrected fan tip speed less than about 1150 ft/second, wherein said low corrected fan tip speed is an actual fan tip speed at an ambient temperature divided by [(Tram °R)/(518.7°R)]0.5, where T represents said ambient temperature in degrees Rankine. 
     
     
         24 . The gas turbine engine of  claim 23 , further comprising a bypass ratio greater than ten (10). 
     
     
         25 . The gas turbine engine of  claim 24 , wherein said fan shaft support defines a fan shaft support lateral stiffness and said gear system input lateral stiffness is less than 11% of said fan shaft support lateral stiffness. 
     
     
         26 . The gas turbine engine of  claim 24 , further comprising a mid-turbine frame including at least one airfoil extending into a flow path. 
     
     
         27 . The gas turbine engine of  claim 21 , further comprising a low corrected fan tip speed less than about 1150 ft/second, wherein said low corrected fan tip speed is an actual fan tip speed at an ambient temperature divided by [(Tram °R)/(518.7°R)]0.5, where T represents said ambient temperature in degrees Rankine. 
     
     
         28 . The gas turbine engine of  claim 20 , further comprising a high speed spool including a two stage high pressure turbine, and a low speed spool including a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1, wherein said low pressure turbine pressure ratio is a ratio of a pressure measured prior to said inlet as related to a pressure at said outlet prior to any exhaust nozzle. 
     
     
         29 . The gas turbine engine of  claim 28 , wherein said gear system includes a planet carrier and said fan shaft is mounted to said planet carrier, and further comprising a low corrected fan tip speed less than about 1150 ft/second, wherein said low corrected fan tip speed is an actual fan tip speed at an ambient temperature divided by [(Tram °R)/(518.7°R)]0.5, where T represents said ambient temperature in degrees Rankine. 
     
     
         30 . The gas turbine engine of  claim 29 , further comprising at least one bearing system, and a three stage low pressure compressor, wherein said high speed spool includes an outer shaft and said low speed spool includes an inner shaft, and said inner shaft and outer shaft are concentric and rotate in coordination with said at least one bearing system about a longitudinal axis of said engine.