Pin to reduce relative rotational movement of disk and spacer of turbine engine
AssigneeSolar Turbines Incorporated
InventorKenneth Gregory Thomas
Life of this patent
Estimating the term…
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.
Claims20
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.
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.
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.
Dependencies are inferred from the claim text.