US4268221A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Compressor structure adapted for active clearance control
Assignee: RTX Corp
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Filing: 1979-03-28
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Granted: 1981-05-19
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Expires: 1999-03-28
Abstract
Abstract A compressor structure for a gas turbine engine capable of enhanced active clearance control within the compressor is disclosed. Various construction details which enable the discharge of cooling air against the compressor case and which minimize thermal distortion of the case are developed. The concepts are applied to a longitudinally split compressor case and include an external bleed manifold of circular cross section which extends across the longitudinal split in the case. Cooling air is dischargeable beneath the manifold to cool the case structure. Heat shields are provided in access ports to the manifold to inhibit heat transfer to the compressor case at the local regions of the ports.
Inventors
- 👤 William G. Monsarrat
- 👤 William F. Neal
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 13:19
CPC Classifications
F; F01; F01D; F01D25/00; F01D25/08; F01D25/14; F01D11/00; F01D11/08; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
120 words
In an axial flow gas turbine engine of the type having rotor and stator elements and wherein the stator element includes a longitudinally split compressor case, the improvement comprising: a compressor case having an integrally formed manifold of circular cross section extending circumferentially about the exterior of the case and across the longitudinal split in the case and having a plurality of circumferentially spaced ports extending into the manifold from the interior of the case; a liner extending through each of said ports for shielding the case from medium gases flowing into the manifold; and means for thermally controlling the diameter of the case including apparatus capable of discharging cooling air against the case beneath the circular cross section manifold.
Claim 2
Dependent Claim
120 words
In an axial flow gas turbine engine of the type having rotor and stator elements and wherein the stator element includes a longitudinally split compressor case, the improvement comprising: a compressor case having an integrally formed manifold of circular cross section extending circumferentially about the exterior of the case and across the longitudinal split in the case and having a plurality of circumferentially spaced ports extending into the manifold from the interior of the case; a liner extending through each of said ports for shielding the case from medium gases flowing into the manifold; and means for thermally controlling the diameter of the case including apparatus capable of discharging cooling air against the case beneath the circular cross section manifold.
Claim 3
Dependent Claim
54 words
The invention according to claim 1 wherein said apparatus for discharging cooling air against the case beneath the circular cross section manifold includes a tube extending circumferentially about the case in substantially parallel relationship to the manifold and having a plurality of orifices adapted to direct cooling air against the case beneath the manifold.
Claim 4
Dependent Claim
48 words
The invention according to claim 2 wherein said case has an inwardly extending hook for support of stator vanes and outer air seals within the engine case wherein said hook is located beneath the bleed manifold and is coolable by said means for discharging air against the case.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1984-05-18 | 1984-11-17 | 1985-05-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-05-18 | 1988-11-17 | 1989-05-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-05-18 | 1992-11-17 | 1993-05-19 | $7700.00 | Window Closed / Lapsed |