Turbine airfoil clocking

Abstract

A method of operating a turbine engine, wherein the turbine engine includes at least three successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, and a third airfoil row. The first airfoil row and the third airfoil row both may comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row comprises the other. The method includes: configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least a portion of the airfoils of the first airfoil row and at least a portion of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch.

1 . A method of operating a turbine engine, wherein the turbine engine includes at least three successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, and a third airfoil row; wherein the first airfoil row and the third airfoil row both comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row comprises the other; the method comprising:
 configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least a portion of the airfoils of the first airfoil row and at least a portion of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch.   
   
   
       2 . The method according to  claim 1 , further comprising the step of configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
   
   
       3 . The method according to  claim 1 , further comprising the step of configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that substantially all of the airfoils of the first airfoil row and substantially all of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
   
   
       4 . The method according to  claim 1 , wherein:
 the turbine engine is configured such that there is substantially no relative motion between the first airfoil row and the third airfoil row during operation;   the turbine engine is configured such that the first airfoil row and the third airfoil row have substantially the same relative motion in relation to the second airfoil row during operation; and   the turbine engine is configured such that the first airfoil row and the third airfoil row have substantially the same number of airfoils.   
   
   
       5 . The method according to  claim 1 , wherein:
 the pitch comprises the circumferential distance between a point on an airfoil in an airfoil row and the same point on either of the neighboring airfoils in the same row; and   the clocking relationship of between 25% and 75% pitch provides that the circumferential position of an airfoil in the third airfoil row lags or leads the circumferential position of a corresponding airfoil in the first airfoil row by an offset of between 25% and 75% of the measurement of the pitch.   
   
   
       6 . The method according to  claim 1 , further comprising the step of configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least 90% the airfoils of the first airfoil row and at least 90% the airfoils of the third airfoil row comprise a clocking relationship of between 25.5% and 74.5% pitch. 
   
   
       7 . The method according to  claim 1 , further comprising the step of configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least 90% the airfoils of the first airfoil row and at least 90% the airfoils of the third airfoil row comprise a clocking relationship of between 35% and 65% pitch. 
   
   
       8 . The method according to  claim 1 , further comprising the step of configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least 90% the airfoils of the first airfoil row and at least 90% the airfoils of the third airfoil row comprise a clocking relationship of between 45% and 55% pitch. 
   
   
       9 . The method according to  claim 1 , further comprising the step of configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least 90% the airfoils of the first airfoil row and at least 90% the airfoils of the third airfoil row comprise a clocking relationship of approximately 50% pitch. 
   
   
       10 . The method according to  claim 1 , wherein the first airfoil row and the third airfoil row each comprises a row of stator blades and the second airfoil row comprises a row of rotor blades. 
   
   
       11 . The method according to  claim 1 , wherein the first airfoil row and the third airfoil row each comprises a row of rotor blades and the second airfoil row comprises a row of stator blades. 
   
   
       12 . The method according to  claim 1 , wherein the first airfoil row, the second airfoil row, and the third airfoil row comprise compressor airfoil rows. 
   
   
       13 . The method according to  claim 1 , wherein the first airfoil row, the second airfoil row, and the third airfoil row comprise turbine airfoil rows. 
   
   
       14 . The method according to  claim 1 , wherein the airfoils are configured to operate in a gas turbine engine. 
   
   
       15 . A method of operating a turbine engine, wherein the turbine engine includes at least five successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, a third airfoil row, a fourth airfoil row and a fifth airfoil row; wherein the first airfoil row and the third airfoil row and the fifth airfoil row each comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row and the fourth airfoil row comprise the other; the method comprising the steps of:
 configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch; and   configuring the airfoils of the third airfoil row and the airfoils of fifth airfoil row such that at least 90% the airfoils of the third airfoil row and at least 90% the airfoils of the fifth airfoil row comprise a clocking relationship of between 25% and 75% pitch.   
   
   
       16 . The method according to  claim 15 , further comprising the steps of:
 configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that substantially all of the airfoils of the first airfoil row and substantially all of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch; and   configuring the airfoils of the third airfoil row and the airfoils of fifth airfoil row such that at substantially all of airfoils of the third airfoil row and substantially all of the airfoils of the fifth airfoil row comprise a clocking relationship of between 25% and 75% pitch.   
   
   
       17 . The method according to  claim 15 , further comprising the steps of:
 configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 25.5% and 74.5% pitch; and   configuring the airfoils of the third airfoil row and the airfoils of fifth airfoil row such that at least 90% the airfoils of the third airfoil row and at least 90% the airfoils of the fifth airfoil row comprise a clocking relationship of between 25.5% and 74.5% pitch.   
   
   
       18 . The method according to  claim 15 , further comprising the steps of:
 configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 35% and 65% pitch; and   configuring the airfoils of the third airfoil row and the airfoils of fifth airfoil row such that at least 90% the airfoils of the third airfoil row and at least 90% the airfoils of the fifth airfoil row comprise a clocking relationship of between 35% and 65% pitch.   
   
   
       19 . The method according to  claim 15 , further comprising the steps of:
 configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 45% and 55% pitch; and   configuring the airfoils of the third airfoil row and the airfoils of fifth airfoil row such that at least 90% the airfoils of the third airfoil row and at least 90% the airfoils of the fifth airfoil row comprise a clocking relationship of between 45% and 55% pitch.   
   
   
       20 . The method according to  claim 15 , further comprising the steps of:
 configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of approximately 50% pitch; and   configuring the airfoils of the third airfoil row and the airfoils of fifth airfoil row such that at least 90% the airfoils of the third airfoil row and at least 90% the airfoils of the fifth airfoil row comprise a clocking relationship of approximately 50% pitch.   
   
   
       21 . An assembly of airfoils in a turbine engine, the assembly comprising at least three successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, and a third airfoil row;
 wherein:
 the first airfoil row and the third airfoil row each comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row comprises the other; and 
 at least a portion of the airfoils of the first airfoil row and at least a portion of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
   
   
   
       22 . The assembly of airfoils according to  claim 21 , wherein at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
   
   
       23 . The assembly of airfoils according to  claim 21 , wherein substantially all of the airfoils of the first airfoil row and substantially all of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
   
   
       24 . The assembly of airfoils according to  claim 21 , wherein:
 the turbine engine is configured such that there is substantially no relative motion between the first airfoil row and the third airfoil row during operation;   the turbine engine is configured such that the first airfoil row and the third airfoil row have substantially the same relative motion in relation to the second airfoil row during operation; and   the turbine engine is configured such that the first airfoil row and the third airfoil row have substantially the same number of airfoils.   
   
   
       25 . The assembly of airfoils according to  claim 24 , wherein:
 the pitch comprises the circumferential distance between a point on an airfoil in an airfoil row and the same point on either of the neighboring airfoils in the same row; and   the clocking relationship of between 25% and 75% pitch provides that the circumferential position of an airfoil in the third airfoil row lags or leads the circumferential position of a corresponding airfoil in the first airfoil row by an offset of between 25% and 75% of the measurement of the pitch.   
   
   
       26 . The assembly of airfoils according to  claim 21 , wherein at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 25.5% and 74.5% pitch. 
   
   
       27 . The assembly of airfoils according to  claim 21 , wherein at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 35% and 65% pitch. 
   
   
       28 . The assembly of airfoils according to  claim 21 , wherein at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 45% and 55% pitch. 
   
   
       29 . The assembly of airfoils according to  claim 21 , wherein at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of approximately 50% pitch. 
   
   
       30 . An assembly of airfoils in a turbine engine, the assembly comprising at least five successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, a third airfoil row, a fourth airfoil row, and a fifth airfoil row;
 wherein:
 the first airfoil row, the third airfoil row, and the fifth airfoil row each comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row and the fourth airfoil row each comprise the other; 
 at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch; and 
 at least 90% of the airfoils of the third airfoil row and at least 90% of the airfoils of the fifth airfoil row comprise a clocking relationship of between 25% and 75% pitch. 
   
   
   
       31 . The assembly of airfoils according to  claim 30 , wherein:
 substantially all of the airfoils of the first airfoil row and substantially all of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch; and   substantially all of the airfoils of the third airfoil row and substantially all of the airfoils of the fifth airfoil row comprise a clocking relationship of between 25% and 75% pitch.   
   
   
       32 . The assembly of airfoils according to  claim 30 , wherein:
 at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 25.5% and 74.5% pitch; and   at least 90% of the airfoils of the third airfoil row and at least 90% of the airfoils of the fifth airfoil row comprise a clocking relationship of between 25.5% and 74.5% pitch.   
   
   
       33 . The assembly of airfoils according to  claim 30 , wherein:
 at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 35% and 65% pitch; and   at least 90% of the airfoils of the third airfoil row and at least 90% of the airfoils of the fifth airfoil row comprise a clocking relationship of between 35% and 65% pitch.   
   
   
       34 . The assembly of airfoils according to  claim 30 , wherein:
 at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of between 45% and 55% pitch; and   at least 90% of the airfoils of the third airfoil row and at least 90% of the airfoils of the fifth airfoil row comprise a clocking relationship of between 45% and 55% pitch.   
   
   
       35 . The assembly of airfoils according to  claim 30 , wherein:
 at least 90% of the airfoils of the first airfoil row and at least 90% of the airfoils of the third airfoil row comprise a clocking relationship of approximately 50% pitch; and   at least 90% of the airfoils of the third airfoil row and at least 90% of the airfoils of the fifth airfoil row comprise a clocking relationship of approximately 50% pitch.