Pin to reduce relative rotational movement of disk and spacer of turbine engine

Abstract

An axial compressor of a turbine engine includes a plurality of disk and spacer pairs oriented along a common axis of rotation. Each of a disk and a spacer of the disk and spacer pairs has a contacting face defining an engagement between the disk and the spacer. The contacting face of each of the disk and the spacer includes a recessed area. A pin has a stem received within the recessed area of the disk and a head received within the recessed area of the spacer. The head of the pin includes at least two flats corresponding to complementary surfaces of the recessed area of the spacer.

What is claimed is: 
     
       1. An axial compressor of a turbine engine, including:
 a plurality of disk and spacer pairs oriented along a common axis of rotation, each of a disk and a spacer of the disk and spacer pairs having a contacting face defining an engagement between the disk and the spacer; 
 the contacting face of each of the disk and the spacer including a recessed area; and 
 a pin having a stem received within the recessed area of the disk and a head received within the recessed area of the spacer; 
 the head of the pin including at least two flats corresponding to complementary surfaces of the recessed area of the spacer. 
 
     
     
       2. The axial compressor of  claim 1 , wherein the disk and the spacer have a thermal interference engagement. 
     
     
       3. The axial compressor of  claim 1 , wherein the head of the pin has a hexagonal shape. 
     
     
       4. The axial compressor of  claim 3 , wherein the recessed area of the spacer has a shape corresponding to the hexagonal shape of the head of the pin. 
     
     
       5. The axial compressor of  claim 3 , wherein the stem of the pin has a cylindrical shape. 
     
     
       6. The axial compressor of  claim 5 , wherein the recessed area of the disk has a shape corresponding to the cylindrical shape of the stem of the pin. 
     
     
       7. The axial compressor of  claim 3 , wherein the pin has a passage therethrough oriented along a longitudinal axis of the pin. 
     
     
       8. The axial compressor of  claim 1 , further including a plurality of recessed areas spaced about each of the disk and the spacer, and four pins configured for receipt within the plurality of recessed areas. 
     
     
       9. The axial compressor of  claim 1 , further including a predetermined clearance between a top surface of the head of the pin and an inner surface of the recessed area of the spacer. 
     
     
       10. A method of operating a turbine engine, including steps of:
 rotating a disk and spacer pair of a plurality of disk and spacer pairs about a common axis of rotation; 
 engaging a contacting face of a disk of the disk and spacer pairs with a contacting face of a spacer of the disk and spacer pairs during rotation; and 
 restricting relative rotation of the disk and the spacer using a pin having a stem received within a recessed area of the disk and a head received within a recessed area of the spacer; 
 wherein the restricting step includes contacting at least two flats of the head of the pin with complementary surfaces of the recessed area of the spacer. 
 
     
     
       11. The method of  claim 10 , further including forming a thermal interference engagement of the disk and the spacer during operation of the turbine engine. 
     
     
       12. The method of  claim 11 , further including performing a hot shutdown of the turbine engine, and reducing a predetermined clearance between a top surface of the head of the pin and an inner surface of the recessed area of the spacer. 
     
     
       13. The method of  claim 10 , further including engaging a hexagonally shaped head of the pin with the complementary surfaces of the recessed area of the spacer. 
     
     
       14. The method of  claim 10 , wherein the restricting step includes engaging four pins with four recessed areas spaced about each of the disk and the spacer. 
     
     
       15. A turbine engine, including:
 an axial compressor, including:
 a plurality of disk and spacer pairs oriented along a common axis of rotation, each of a disk of the disk and spacer pairs and a spacer of the disk and spacer pairs having a contacting face defining an engagement between the disk and the spacer, the contacting face of each of the disk and the spacer including a recessed area; and 
 a pin having a stem received within the recessed area of the disk and a hexagonally shaped head received within the recessed area of the spacer. 
 
 
     
     
       16. The turbine engine of  claim 15 , wherein the pin has a passage therethrough oriented along a longitudinal axis of the pin. 
     
     
       17. The turbine engine of  claim 15 , wherein the stem of the pin has a cylindrical shape. 
     
     
       18. The turbine engine of  claim 15 , wherein the disk and the spacer have a thermal interference engagement. 
     
     
       19. The turbine engine of  claim 15 , further including a predetermined clearance between a top surface of the head of the pin and an inner surface of the recessed area of the spacer. 
     
     
       20. The turbine engine of  claim 15 , further including a plurality of recessed areas spaced about each of the disk and the spacer, and four pins configured for receipt within the plurality of recessed areas.