IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
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출원번호 |
US-0889005
(2010-09-23)
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등록번호 |
US-8684696
(2014-04-01)
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발명자
/ 주소 |
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출원인 / 주소 |
- Rolls-Royce North American Technologies, Inc.
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
0 인용 특허 :
14 |
초록
▼
One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique gas turbine engine main engine rotor. Still another embodiment is a unique method for assembling a gas turbine engine main engine rotor. Other embodiments include apparatuses, systems, devices, har
One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique gas turbine engine main engine rotor. Still another embodiment is a unique method for assembling a gas turbine engine main engine rotor. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine rotors. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
대표청구항
▼
1. A gas turbine engine, comprising: a main engine rotor having a first rotor component and a second rotor component, wherein the first rotor component includes a first face and a first channel; and wherein the second rotor component includes a second face and a second channel;a compression washer d
1. A gas turbine engine, comprising: a main engine rotor having a first rotor component and a second rotor component, wherein the first rotor component includes a first face and a first channel; and wherein the second rotor component includes a second face and a second channel;a compression washer disposed between the first face and the second face, wherein the compression washer is operative to mechanically load the first face against the second face; anda retaining ring,wherein the first face, the first channel, the second face and the second channel are positioned so that the compression washer is in a state of compression between the first face and the second face when the retaining ring is positioned in both the first channel and the second channel; andwherein the retaining ring reacts the mechanical loading produced by the compression of the compression washer. 2. The gas turbine engine of claim 1, wherein the main engine rotor includes a turbine rotor and a compressor rotor, and wherein the first rotor component is one of the turbine rotor and the compressor rotor. 3. The gas turbine engine of claim 2, wherein the main engine rotor includes a shaft operative to transmit power from the turbine rotor to drive the compressor rotor, and wherein the second rotor component is the shaft. 4. The gas turbine engine of claim 2, wherein the compressor rotor includes a plurality of compressor stages, and wherein the first rotor component is a first compressor stage and wherein the second rotor component is a second compressor stage. 5. The gas turbine engine of claim 1, wherein at least one of the first rotor component and the second rotor component includes an opening extending into the respective at least one of the first channel and the second channel. 6. The gas turbine engine of claim 5, wherein the opening is structured to admit a tool therein for displacement of the retaining ring. 7. The gas turbine engine of claim 1, further comprising a spring disposed in one of the first channel and the second channel, wherein the spring is positioned to place a spring load on the retaining ring. 8. The gas turbine engine of claim 7, wherein the spring is a circumferential wave washer. 9. A method for assembly and disassembly of a main engine rotor of a gas turbine engine, comprising: positioning a compression washer between at least one of a first face of a first rotor component of the main engine rotor and a second face of a second rotor component of the main engine rotor;positioning a retaining ring in one of a first groove of the first rotor component and a second groove of the second rotor component;assembling the first rotor component to the second rotor component;applying a clamp load to force the compression washer into a state of compression between the first face and the second face; anddisplacing the retaining ring so that the retaining ring is positioned in both the first groove and the second groove. 10. The method of claim 9, further comprising releasing the clamp load, wherein the retaining ring reacts the compression of the compression washer and retains the first rotor component in assembly with the second rotor component. 11. The method of claim 10, further comprising disassembling the first rotor component from the second rotor component by repositioning the retaining ring from being in both the first groove and the second groove to being in the one of the first groove and the second groove, and removing the first rotor component from the second rotor component. 12. The method of claim 11, wherein the repositioning of the retaining ring includes inserting a tool into an opening in one of the first groove and the second groove, and applying force to the retaining ring using the tool to displace the retaining ring. 13. The method of claim 10, further comprising positioning a spring in one of the first groove and the second groove, wherein the spring is positioned to place a spring load on the retaining ring. 14. The method of claim 10, wherein the main engine rotor includes a shaft operative to transmit power from a turbine rotor to drive a compressor rotor, and wherein one of the first rotor component and the second rotor component is the shaft. 15. The method of claim 10, wherein the main engine rotor includes a plurality of compressor stages, and wherein the first rotor component is one compressor stage and wherein the second rotor component is another compressor stage. 16. The method of claim 10, wherein the main engine rotor includes a compressor disk and a compressor spacer, and wherein the first rotor component is the disk and wherein the second rotor component is the spacer. 17. The method of claim 9, wherein the first rotor component is clamped to the second rotor component without the use of threads. 18. A system for assembling components of a gas turbine engine, comprising: a first component having a first face and a second face;a second component having a third face and a fourth face, wherein the third face is opposite the first face, and wherein the fourth face is opposite the third face;a compression washer disposed between the first face and the third face, wherein the compression washer is operative to mechanically load the first face against the third face; anda retaining ring,wherein the first face, the second face, the third face and the fourth face are positioned so that the compression washer is in a state of compression between the first face and the third face when the retaining ring is positioned between the second face and the fourth face; andwherein the retaining ring reacts the mechanical loading produced by the compression of the compression washer. 19. A gas turbine engine main engine rotor, comprising: a first rotor component;a second rotor component; andmeans for clamping the first rotor component to the second rotor component. 20. The gas turbine engine main engine rotor of claim 19, wherein the means for clamping includes a compression washer and a split retaining ring that jointly clamp together the first rotor component and the second rotor component.
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