US3888602A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Stress restraining ring for compressor rotors
Assignee: RTX Corp
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Filing: 1974-06-05
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Granted: 1975-06-10
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Expires: 1994-06-05
Abstract
Abstract The integral wing flange of a compressor disk is surrounded at its free end by an annular restraining ring which, in a preferred embodiment, has a smaller free state inner diameter than the outer diameter of the wing flange, thereby exerting a compressive force on the wing flange. The outer diameter of the restraining ring fits into a snap diameter of the next adjacent disk. During engine operation the wing flange deflects and creeps, but not as much as it would have without the restraining ring due to the initial compressive force. Also, when the two adjacent disks are disassembled the restraining ring prevents the flange from springing outwardly as much due to the creep thereby reducing the interference fit between the two disks when it is time to reassemble them.
Inventors
- 👤 Arnold Douglas Nichols
- 👤 Cornelius Vickers Sundt
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 00:03
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/02; F01D5/06
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
181 words
An axial flow compressor for a gas turbine engine comprising: an upstream compressor disk made from a first material and including an integral, axially extending wing flange having a downstream end, said downstream end including a radially outwardly facing cylindrical surface; a downstream compressor disk made from a second material adjacent and connected to said upstream compressor disk and including means defining an inner snap diameter surface; and a restraining ring disposed on said downstream end and having an outer snap diameter surface and a radially inwardly facing cylindrical surface, said radially inwardly facing cylindrical surface abutting said radially outwardly facing cylindrical surface, said radially inwardly facing cylindrical surface having a free state diameter no greater than the free state diameter of said radially outwardly facing cylindrical surface, said outer snap diameter surface abutting said inner snap diameter surface, said restraining ring having the characteristic that it is stiff relative to the stiffness of said wing flange, said wing flange having the characteristic that it creeps during engine operation, said second material having a creep strength higher than said first material.
Claim 2
Dependent Claim
181 words
An axial flow compressor for a gas turbine engine comprising: an upstream compressor disk made from a first material and including an integral, axially extending wing flange having a downstream end, said downstream end including a radially outwardly facing cylindrical surface; a downstream compressor disk made from a second material adjacent and connected to said upstream compressor disk and including means defining an inner snap diameter surface; and a restraining ring disposed on said downstream end and having an outer snap diameter surface and a radially inwardly facing cylindrical surface, said radially inwardly facing cylindrical surface abutting said radially outwardly facing cylindrical surface, said radially inwardly facing cylindrical surface having a free state diameter no greater than the free state diameter of said radially outwardly facing cylindrical surface, said outer snap diameter surface abutting said inner snap diameter surface, said restraining ring having the characteristic that it is stiff relative to the stiffness of said wing flange, said wing flange having the characteristic that it creeps during engine operation, said second material having a creep strength higher than said first material.
Claim 3
Dependent Claim
23 words
The axial flow compressor according to claim 1 wherein said second material has a coefficient to thermal expansion higher than said first material.
Claim 4
Dependent Claim
32 words
The axial flow compressor according to claim 2 wherein the free state diameter of said inwardly facing cylindrical surface is less than the free state diameter of said outwardly facing cylindrical surface.
Claim 5
Dependent Claim
22 words
The axial flow compressor according to claim 3 wherein said restraining ring has the characteristic that it is elastic throughout engine operation.
References Cited (Backward Citations)
US3688371A
Cited
US3617150A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-06-09 | 1978-12-09 | 1979-06-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-06-09 | 1982-12-09 | 1983-06-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-06-09 | 1986-12-09 | 1987-06-10 | $7700.00 | Window Closed / Lapsed |