US3908361A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Seal between relatively moving components of a fluid flow machine
Assignee: Rolls Royce PLC
•
Filing: 1973-12-14
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Granted: 1975-09-30
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Expires: 1993-12-14
Abstract
Abstract A seal at the downstream end of a compressor of a gas turbine engine is formed between a rotor element of the compressor and a stationary element carried by the combustion chamber inner casing, the combustion chamber inner casing is mounted at its downstream end rigidly to the engine casing so that the upstream end is free to move under the influence of both pressure and temperature changes within the engine the seal being adapted to compensate for relative movement between the compressor rotor and the combustion chamber inner casing.
Inventors
- 👤 Terence Edward Gouven Gardiner
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 14:36
CPC Classifications
F; F01; F01D; F01D11/00; F01D11/02
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
168 words
A gas turbine engine having a casing, a rotor, and a seal therebetween, said seal comprising a first sealing member carried by a part of the rotor and a second sealing member carried by an element of the casing and spaced from the first sealing member to define a sealing clearance therebetween, wherein the rotor part is adapted to move under various engine running conditions to vary the sealing clearance, means are provided for fixing the casing to static structure at one end away from the casing element, and at the other end there is provided a joint between the casing element and static structure which allows freedom of movement of said casing element in the direction of movement of the rotor, means being provided for producing a pressure differential across said casing element which varies with the engine running conditions and which causes movement of the casing element in said direction to follow movement of the rotor part to maintain said sealing clearance in a pre-determined range.
Claim 2
Dependent Claim
168 words
A gas turbine engine having a casing, a rotor, and a seal therebetween, said seal comprising a first sealing member carried by a part of the rotor and a second sealing member carried by an element of the casing and spaced from the first sealing member to define a sealing clearance therebetween, wherein the rotor part is adapted to move under various engine running conditions to vary the sealing clearance, means are provided for fixing the casing to static structure at one end away from the casing element, and at the other end there is provided a joint between the casing element and static structure which allows freedom of movement of said casing element in the direction of movement of the rotor, means being provided for producing a pressure differential across said casing element which varies with the engine running conditions and which causes movement of the casing element in said direction to follow movement of the rotor part to maintain said sealing clearance in a pre-determined range.
Claim 3
Dependent Claim
29 words
A gas turbine engine according to claim 1, wherein said joint is a sliding joint and a further seal is provided between the casing element and the static structure.
Claim 4
Dependent Claim
25 words
A gas turbine engine according to claim 1, wherein the casing element is a resilient member capable of deflection under variations of the pressure differential.
Claim 5
Dependent Claim
57 words
A gas turbine engine according to claim 1, wherein the gas turbine engine has a combustion chamber, and a compressor rotor, and wherein said casing forms the inner casing thereof and said casing element is the upstream end wall of the casing, said first sealing member being carried on the downstream end part of the compressor rotor.
Claim 6
Dependent Claim
49 words
A gas turbine engine according to claim 1, wherein the gas turbine engine has a combustion chamber casing and a compressor rotor, and wherein one of the sealing members is mounted on said compressor rotor and the other of the sealing members is mounted on said combustion chamber casing.
Claim 7
Dependent Claim
51 words
A gas turbine engine according to claim 4 including means defining chambers on opposite sides of said combustion chamber casing and having means for supplying engine working fluid at different pressures to the said chambers thereby to produce said differential pressure across at least said front end wall of the casing.
Claim 8
Dependent Claim
45 words
A gas turbine engine according to claim 4 and in which the said front end wall comprises bi-metallic means responsive to temperature variations of the front end wall under different engine operating Conditions for flexing towards or away from the said rotor mounted sealing member.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-09-29 | 1979-03-31 | 1979-09-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-09-29 | 1983-03-31 | 1983-09-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-09-29 | 1987-03-31 | 1987-09-30 | $7700.00 | Window Closed / Lapsed |