Turbine airfoil clocking

Abstract

An assembly of airfoils in a compressor of a turbine engine that includes at least three axially stacked rows of airfoils: a middle airfoil row, a first upstream airfoil row, and a first downstream airfoil row. The middle airfoil row may be bordered on each side by the first upstream airfoil row, which comprises the first row of airfoils in the upstream direction from the middle airfoil row, and the first downstream airfoil row, which comprises the first row of airfoils in the downstream direction from the middle airfoil row. The first upstream airfoil row and the first downstream airfoil row may have substantially the same number of similarly shaped airfoils. The first upstream airfoil row and the first downstream airfoil row each may comprise a row of rotor blades, which rotate at substantially the same speed during operation. The middle airfoil row may comprise a row of stator blades, which remains substantially stationary during operation. At least 90% of the airfoils of the first upstream airfoil row and at least 90% of the airfoils of the first downstream airfoil row may comprise a clocking relationship of between 25% and 75% pitch.

1 . An assembly of airfoils in a compressor of a turbine engine, the assembly comprising at least three axially stacked rows of airfoils: a middle airfoil row, a first upstream airfoil row, and a first downstream airfoil row;
 wherein:
 the middle airfoil row is bordered on each side by the first upstream airfoil row, which comprises the first row of airfoils in the upstream direction from the middle airfoil row, and the first downstream airfoil row, which comprises the first row of airfoils in the downstream direction from the middle airfoil row; 
 the first upstream airfoil row and the first downstream airfoil row have substantially the same number of similarly shaped airfoils; 
 the first upstream airfoil row and the first downstream airfoil row each comprise a row of rotor blades, which rotate at substantially the same speed during operation; 
 the middle airfoil row comprises a row of stator blades, which remains substantially stationary during operation; and 
 at least 90% of the airfoils of the first upstream airfoil row and at least 90% of the airfoils of the first downstream airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
   
     
     
         2 . The assembly of airfoils according to  claim 1 , wherein substantially all of the airfoils of the first upstream airfoil row and substantially all of the airfoils of the first downstream airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
     
     
         3 . The assembly of airfoils according to  claim 1 , wherein at least 90% of the airfoils of the first upstream airfoil row and at least 90% of the airfoils of the first downstream airfoil row comprise a clocking relationship of between 25.5% and 74.5% pitch. 
     
     
         4 . The assembly of airfoils according to  claim 1 , wherein at least 90% of the airfoils of the first upstream airfoil row and at least 90% of the airfoils of the first downstream airfoil row comprise a clocking relationship of between 35% and 65% pitch. 
     
     
         5 . The assembly of airfoils according to  claim 1 , wherein at least 90% of the airfoils of the first upstream airfoil row and at least 90% of the airfoils of the first downstream airfoil row comprise a clocking relationship of between 45% and 55% pitch. 
     
     
         6 . The assembly of airfoils according to  claim 1 , wherein at least 90% of the airfoils of the first upstream airfoil row and at least 90% of the airfoils of the first downstream airfoil row comprise a clocking relationship of approximately 50% pitch. 
     
     
         7 . The assembly of airfoils according to  claim 1 , further comprising:
 a second upstream airfoil row, which borders the first upstream airfoil row and comprises the second row of airfoils in the upstream direction from the middle airfoil row; and   a third upstream airfoil row, which borders the second upstream airfoil row and comprises the third row of airfoils in the upstream direction from the middle airfoil row;   wherein:
 the third upstream airfoil row, the first upstream airfoil row, and the first downstream airfoil row have substantially the same number of similarly shaped airfoils; 
 the third upstream airfoil row, the first upstream airfoil row, and the first downstream airfoil row each comprise a row of rotor blades, which rotate at substantially the same speed during operation; 
 the second upstream airfoil row comprises a row of stator blades, which remain substantially stationary during operation; and 
 at least 90% of the airfoils of the third upstream airfoil row and at least 90% of the airfoils of the first upstream airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
   
     
     
         8 . The assembly of airfoils according to  claim 7 , wherein substantially all of the airfoils of the third upstream airfoil row and substantially all of the airfoils of the first upstream airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
     
     
         9 . The assembly of airfoils according to  claim 7 , wherein at least 90% of the airfoils of the third upstream airfoil row and at least 90% of the airfoils of the first upstream airfoil row comprise a clocking relationship of between 25.5% and 74.5% pitch. 
     
     
         10 . The assembly of airfoils according to  claim 7 , wherein at least 90% of the airfoils of the third upstream airfoil row and at least 90% of the airfoils of the first upstream airfoil row comprise a clocking relationship of between 35% and 65% pitch. 
     
     
         11 . The assembly of airfoils according to  claim 7 , wherein at least 90% of the airfoils of the third upstream airfoil row and at least 90% of the airfoils of the first upstream airfoil row comprise a clocking relationship of between 45% and 55% pitch. 
     
     
         12 . The assembly of airfoils according to  claim 7 , wherein at least 90% of the airfoils of the third upstream airfoil row and at least 90% of the airfoils of the first upstream airfoil row comprise a clocking relationship of approximately 50% pitch. 
     
     
         13 . The assembly of airfoils according to  claim 1 , wherein:
 the first upstream airfoil row comprises a row of rotor blades in a fourteenth stage of the compressor;   the middle airfoil row comprises a row of stator blades in the fourteenth stage of the compressor; and   the first downstream airfoil row comprises a row of rotor blades in a fifteenth stage of the compressor.   
     
     
         14 . The assembly of airfoils according to  claim 13 , wherein the compressor comprises a F-Class Compressor manufactured by The General Electric Company of Schenectady, N.Y. and the turbine engine comprises one of a 7F Gas Turbine Engine and a 9F Gas Turbine Engine manufactured by The General Electric Company of Schenectady, N.Y. 
     
     
         15 . The assembly of airfoils according to  claim 13 , wherein the row of rotor blades in the fourteenth stage comprises 64 rotor blades and the row of rotor blades in the fifteenth stage comprises 64 rotor blades. 
     
     
         16 . The assembly of airfoils according to  claim 15 , wherein the row of stator blades in the fourteenth stage comprises 132 stator blades. 
     
     
         17 . The assembly of airfoils according to  claim 1 , wherein:
 the first upstream airfoil row comprises a row of rotor blades in a fifteenth stage of the compressor;   the middle airfoil row comprises a row of stator blades in the fifteenth stage of the compressor; and   the first downstream airfoil row comprises a row of rotor blades in a sixteenth stage of the compressor.   
     
     
         18 . The assembly of airfoils according to  claim 17 , wherein the compressor comprises a F-Class Compressor manufactured by The General Electric Company of Schenectady, N.Y. and the turbine engine comprises one of a 7F Gas Turbine Engine and a 9F Gas Turbine Engine manufactured by The General Electric Company of Schenectady, N.Y. 
     
     
         19 . The assembly of airfoils according to  claim 17 , wherein the row of rotor blades in the fifteenth stage comprises 64 rotor blades, and the row of rotor blades in the sixteenth stage comprises 64 rotor blades. 
     
     
         20 . The assembly of airfoils according to  claim 19 , wherein the row of stator blades in the fifteenth stage comprises 130 stator blades. 
     
     
         21 . The assembly of airfoils according to  claim 7 , wherein:
 the third upstream airfoil row comprises a row of rotor blades in a fourteenth stage of the compressor;   the second upstream airfoil row comprises a row of stator blades in the fourteenth stage of the compressor;   the first upstream airfoil row comprises a row of rotor blades in a fifteenth stage of the compressor;   the middle airfoil row comprises a row of stator blades in the fifteenth stage of the compressor; and   the first downstream airfoil row comprises a row of rotor blades in a sixteenth stage of the compressor.   
     
     
         22 . The assembly of airfoils according to  claim 21 , wherein the row of rotor blades in the fourteenth stage comprises 64 rotor blades, the row of rotor blades in the fifteenth stage comprises 64 rotor blades, and the row of rotor blades in the sixteenth stage comprises 64 rotor blades. 
     
     
         23 . The assembly of airfoils according to  claim 22 , wherein the row of stator blades in the fourteenth stage comprises 132 stator blades, and the row of stator blades in the fifteenth stage comprises 130 stator blades. 
     
     
         24 . In a compressor of a turbine engine, the compressor comprising at least three axially stacked rows of airfoils: a middle airfoil row, a first upstream airfoil row, and a first downstream airfoil row; wherein the middle airfoil row is bordered on each side by the first upstream airfoil row, which comprises the first row of airfoils in the upstream direction from the middle airfoil row, and the first downstream airfoil row, which comprises the first row of airfoils in the downstream direction from the middle airfoil row; wherein the first upstream airfoil row and the first downstream airfoil row have substantially the same number of similarly shaped airfoils; wherein the first upstream airfoil row and the first downstream airfoil row each comprise a row of rotor blades, which rotate at substantially the same speed during operation; and wherein the middle airfoil row comprises a row of stator blades, which remains substantially stationary during operation; a method of operating a turbine engine, the method comprising:
 configuring the airfoils of the first upstream airfoil row and the airfoils of first downstream airfoil row such that at least 90% the airfoils of the first upstream airfoil row and at least 90% the airfoils of the first downstream airfoil row comprise a clocking relationship of between 25% and 75% pitch.   
     
     
         25 . The method according to  claim 24 , further comprising the step of configuring the airfoils of the first upstream airfoil row and the airfoils of first downstream airfoil row such that substantially all of the airfoils of the first upstream airfoil row and substantially all of the airfoils of the first downstream airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
     
     
         26 . The method according to  claim 24 , further comprising the step of configuring the airfoils of the first upstream airfoil row and the airfoils of first downstream airfoil row such that at least 90% the airfoils of the first upstream airfoil row and at least 90% the airfoils of the first downstream airfoil row comprise a clocking relationship of between 35% and 65% pitch. 
     
     
         27 . The method according to  claim 24 , further comprising the step of configuring the airfoils of the first upstream airfoil row and the airfoils of first downstream airfoil row such that at least 90% the airfoils of the first upstream airfoil row and at least 90% the airfoils of the first downstream airfoil row comprise a clocking relationship of between 45% and 55% pitch. 
     
     
         28 . The method according to  claim 24 , further comprising the step of configuring the airfoils of the first upstream airfoil row and the airfoils of first downstream airfoil row such that at least 90% the airfoils of the first upstream airfoil row and at least 90% the airfoils of the first downstream airfoil row comprise a clocking relationship of approximately 50% pitch. 
     
     
         29 . The method according to  claim 24 , wherein:
 a second upstream airfoil row borders the first upstream airfoil row and comprises the second row of airfoils in the upstream direction from the middle airfoil row;   a third upstream airfoil row borders the second upstream airfoil row and comprises the third row of airfoils in the upstream direction from the middle airfoil row;   the third upstream airfoil row, the first upstream airfoil row, and the first downstream airfoil row have substantially the same number of similarly shaped airfoils;   the third upstream airfoil row, the first upstream airfoil row, and the first downstream airfoil row each comprise a row of rotor blades, which rotate at substantially the surface speed during operation; and   the second upstream airfoil row comprises a row of stator blades, which remain substantially stationary during operation;   further comprising the step of configuring the airfoils of the third upstream airfoil row and the airfoils of first upstream airfoil row such that at least 90% the airfoils of the third upstream airfoil row and at least 90% the airfoils of the first upstream airfoil row comprise a clocking relationship of between 25% and 75% pitch.   
     
     
         30 . The method according to  claim 29 , further comprising the step of configuring the airfoils of the third upstream airfoil row and the airfoils of first upstream airfoil row such that substantially all of the airfoils of the third upstream airfoil row and substantially all of the airfoils of the first upstream airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
     
     
         31 . The method according to  claim 29 , further comprising the step of configuring the airfoils of the third upstream airfoil row and the airfoils of first upstream airfoil row such that at least 90% the airfoils of the third upstream airfoil row and at least 90% the airfoils of the first upstream airfoil row comprise a clocking relationship of between 35% and 65% pitch. 
     
     
         32 . The method according to  claim 29 , further comprising the step of configuring the airfoils of the third upstream airfoil row and the airfoils of first upstream airfoil row such that at least 90% the airfoils of the third upstream airfoil row and at least 90% the airfoils of the first upstream airfoil row comprise a clocking relationship of approximately 50% pitch. 
     
     
         33 . The method according to  claim 24 , wherein:
 the first upstream airfoil row comprises a row of rotor blades in a fourteenth stage of the compressor;   the middle airfoil row comprises a row of stator blades in the fourteenth stage of the compressor; and   the first downstream airfoil row comprises a row of rotor blades in a fifteenth stage of the compressor.   
     
     
         34 . The method according to  claim 33 , wherein the compressor comprises a F-Class Compressor manufactured by The General Electric Company of Schenectady, N.Y. and the turbine engine comprises one of a 7F Gas Turbine Engine and a 9F Gas Turbine Engine manufactured by The General Electric Company of Schenectady, N.Y. 
     
     
         35 . The method according to  claim 33 , wherein the row of rotor blades in the fourteenth stage comprises 64 rotor blades and the row of rotor blades in the fifteenth stage comprises 64 rotor blades. 
     
     
         36 . The method according to  claim 35 , wherein the row of stator blades in the fourteenth stage comprises 132 stator blades. 
     
     
         37 . The method according to  claim 24 , wherein:
 the first upstream airfoil row comprises a row of rotor blades in a fifteenth stage of the compressor;   the middle airfoil row comprises a row of stator blades in the fifteenth stage of the compressor; and   the first downstream airfoil row comprises a row of rotor blades in a sixteenth stage of the compressor.   
     
     
         38 . The method according to  claim 37 , wherein the row of rotor blades in the fifteenth stage comprises 64 rotor blades, and the row of rotor blades in the sixteenth stage comprises 64 rotor blades. 
     
     
         39 . The method according to  claim 38 , wherein the row of stator blades in the fifteenth stage comprises 130 stator blades. 
     
     
         40 . The method according to  claim 29 , wherein:
 the third upstream airfoil row comprises a row of rotor blades in a fourteenth stage of the compressor;   the second upstream airfoil row comprises a row of stator blades in the fourteenth stage of the compressor;   the first upstream airfoil row comprises a row of rotor blades in a fifteenth stage of the compressor;   the middle airfoil row comprises a row of stator blades in the fifteenth stage of the compressor; and   the first downstream airfoil row comprises a row of rotor blades in a sixteenth stage of the compressor.   
     
     
         41 . The method according to  claim 40 , wherein the row of rotor blades in the fourteenth stage comprises 64 rotor blades, the row of rotor blades in the fifteenth stage comprises 64 rotor blades, and the row of rotor blades in the sixteenth stage comprises 64 rotor blades. 
     
     
         42 . The method according to  claim 41 , wherein the row of stator blades in the fourteenth stage comprises 132 stator blades, and the row of stator blades in the fifteenth stage comprises 130 stator blades. 
     
     
         43 . In a compressor of a gas turbine engine, the compressor comprising at least six axially stacked rows of airfoils: a first row of rotor blades followed by a first row of stator blades followed by a second row of rotor blades followed by a second row of stator blades followed by a third row of rotor blades followed by a third row of stator blades; wherein the first row of rotor blades, the second row of rotor blades, and the third row of rotor blades have substantially the same number of similarly shaped rotor blades, which, during operation, rotate at substantially the same speed; a method of operating a turbine engine, the method comprising the steps of:
 configuring the airfoils of the first row of rotor blades and the airfoils of the second row of rotor blades such that substantially all of the airfoils of the first row of rotor blades and substantially all of the airfoils of the second row of rotor blades comprise a clocking relationship of between 25% and 75% pitch; and   configuring the airfoils of the second row of rotor blades and the airfoils of the third row of rotor blades such that substantially all of the airfoils of the second row of rotor blades and substantially all of the airfoils of the third row of rotor blades comprise a clocking relationship of between 25% and 75% pitch.   
     
     
         44 . The method according to  claim 43 , further comprising the step of
 configuring the airfoils of the first row of rotor blades and the airfoils of the second row of rotor blades such that substantially all of the airfoils of the first row of rotor blades and substantially all of the airfoils of the second row of rotor blades comprise a clocking relationship of approximately 50% pitch; and   configuring the airfoils of the second row of rotor blades and the airfoils of the third row of rotor blades such that substantially all of the airfoils of the second row of rotor blades and substantially all of the airfoils of the third row of rotor blades comprise a clocking relationship of approximately 50% pitch.