Dynamic stability and mid axial preload control for a tie shaft coupled axial high pressure rotor
A middle support member is used to provide axial support and control to the tie shaft. The middle support member includes a high pressure compressor coupling nut that applies a preload that allows the high pressure compressor stack to be installed separately from the high pressure turbine rotor through a kickstand.
1. A turbine engine, comprising:
a first bearing on a first end of a unitary tie shaft;
an upstream hub threadably engaged with the tie shaft;
a compressor rotor stack supported by and operatively associated with the tie shaft and abutting the upstream hub;
a middle support member abutting the compressor rotor stack, the middle support member having a downstream hub and a soft spring kickstand;
a high pressure compressor coupling nut abutting the soft spring kickstand and threadably engaged with the tie shaft;
a turbine rotor stack operatively associated with the tie shaft and abutting the downstream hub;
a turbine rotor arm operatively associated with the turbine rotor stack and interferingly fitting with the tie shaft;
a high pressure turbine lock nut threadably engaged with the tie shaft and abutting the turbine rotor arm;
an intermediary sleeve interferingly fitting with the turbine rotor arm;
a second bearing having inner and outer races, the inner race interferingly fitting with an outside diameter of the intermediary sleeve; and
a downstream lock nut threadably engaged with the tie shaft and abutting the high pressure turbine lock nut.
2. The turbine engine of claim 1 wherein as the high pressure compressor coupling nut is tightened, the soft spring kickstand and the compressor rotor accept a secondary compression load and a portion of the tie shaft between the upstream hub and the high pressure compressor coupling nut accepts a secondary tension load.
3. The turbine engine of claim 1 , wherein the soft spring kickstand of the middle support member provides axial and radial reaction forces in the middle support member.
4. The turbine engine of claim 1 , wherein the high pressure compressor coupling nut applies a preload force to the compressor rotor stack.
5. The turbine engine of claim 4 , wherein the high pressure compressor coupling nut allows the compressor rotor stack to be installed separately from the high pressure turbine rotor.
6. The turbine engine of claim 1 , wherein the high pressure compressor coupling nut and the high pressure turbine lock nut apply preload forces to the compressor and turbine rotor stacks.
7. The turbine engine of claim 1 , wherein the tie shaft, turbine rotor arm, intermediate sleeve, and inner race interferingly fitting with one another creates a radial preload force.
8. The turbine engine of claim 7 , wherein the high pressure turbine lock nut is secured by the downstream lock nut and wherein the downstream lock nut is a low-profile locking ring.
9. The turbine engine of claim 1 , wherein the compressor rotor stack and the turbine rotor stack are provided with an axial preload via the consisting of the tie shaft.
10. A turbine engine, comprising:
a tie shaft, the tie shaft being one unitary piece;
a first bearing operatively associated with the tie shaft at a first end of the tie shaft;
a compressor rotor supported by and operatively associated with the tie shaft, the compressor rotor including a plurality of radially-extending compressor blades;
a combustor downstream of the compressor rotor which exhausts high speed air into a turbine having a high pressure turbine rotor;
an upstream hub upstream of and abutting the compressor rotor and threadably engaged with the tie shaft;
a middle support member between the compressor rotor and the turbine, the middle support member having a downstream hub and a soft spring kickstand;
a high pressure compressor coupling nut threadably engaged with the tie shaft and abutting and abutting the soft spring kickstand;
an aft high pressure turbine rotor support including:
a turbine rotor arm operatively associated with the high pressure turbine rotor and interferingly fitting with the tie shaft,
a high pressure turbine lock nut threadably engaged with the tie shaft and abutting the turbine rotor arm,
an intermediary sleeve interferingly fitting with the turbine rotor arm, and
a second bearing having inner and outer races, the inner race interferingly fitting with an outside diameter of the intermediary sleeve; and
a downstream lock nut threadably engaged with the tie shaft and abutting the aft high pressure turbine rotor support.
11. The turbine engine of claim 10 , wherein as the high pressure compressor coupling nut is tightened, the compressor rotor and the soft spring kickstand accept a secondary compression load and a portion of the tie shaft between the upstream hub and the high pressure compressor coupling nut accepts a secondary tension load.
12. The turbine engine of claim 10 , wherein the soft spring kickstand provides axial and radial reaction forces in the middle support member.
13. The turbine engine of claim 10 , wherein the high pressure compressor coupling nut applies a preload force to the compressor rotor.
14. The turbine engine of claim 13 , wherein the high pressure compressor coupling nut allows the plurality of radially-extending compressor blades to be installed separately from the high pressure turbine rotor.
15. The turbine engine of claim 10 , wherein the high pressure turbine lock nut applies a primary preload force to the compressor rotor and to the high pressure turbine rotor.
16. The turbine engine of claim 15 , wherein the tie shaft, turbine rotor arm, intermediate sleeve, and inner race interferingly fitting with one another produces a radial preload force.
17. The turbine engine of claim 10 , wherein the compressor rotor and the turbine are provided with an axial preload via the tie shaft.