US4017207A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine
Assignee: Rolls Royce PLC
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Filing: 1975-10-28
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Granted: 1977-04-12
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Expires: 1995-10-28
Abstract
Abstract A duct wall embracing the turbine of a gas turbine engine is cooled by impingement of air jets on to the outside of the wall. For control of the air flow the wall is surrounded by a chamber divided into inlet and outlet regions by a partition having spaced apart portions projecting towards the wall. The air jets emerge from nozzle openings in the free ends of the projections. Air rebounding from the wall enters the spaces between the projections and so does not interfere with the flow of fresh air thereby raising the efficiency of the heat exchange.
Inventors
- 👤 John Kenneth Alexander Bell
- 👤 John Rodney Dyson Fuller
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 12:52
CPC Classifications
F; F01; F01D; F01D11/00; F01D11/08; F05; F05D; F05D2260/00; F05D2260/20; F05D2260/201; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
136 words
A gas turbine engine comprising an annular duct for combustion products, means defining an annular cooling air chamber surrounding the duct, a wall common to the chamber and the duct, a source of pressurized cooling air, an annular array of nozzles arranged in the chamber and connected to be supplied by said cooling air source, the nozzles being direced for axial spaced jets of air emanating therefrom to impinge on to and return from said wall, the nozzles being arranged in rows parallel to the axis of said chamber, an outlet at one axial end of the means defining the chamber for the returned air, and said axial rows of nozzles being circumferentially spaced apart to define, between next adjacent ones of said rows, axially extending spaces accomodating the flow of returning air to said outlet.
Claim 2
Dependent Claim
136 words
A gas turbine engine comprising an annular duct for combustion products, means defining an annular cooling air chamber surrounding the duct, a wall common to the chamber and the duct, a source of pressurized cooling air, an annular array of nozzles arranged in the chamber and connected to be supplied by said cooling air source, the nozzles being direced for axial spaced jets of air emanating therefrom to impinge on to and return from said wall, the nozzles being arranged in rows parallel to the axis of said chamber, an outlet at one axial end of the means defining the chamber for the returned air, and said axial rows of nozzles being circumferentially spaced apart to define, between next adjacent ones of said rows, axially extending spaces accomodating the flow of returning air to said outlet.
Claim 3
Dependent Claim
88 words
A gas turbine engine according to claim 1 further comprising: a partition dividing said chamber into an inlet region spaced from the wall and an outlet region open to the wall, the partition having circumferentially spaced apart projection portions projecting toward the wall to define therebetween said axially extending spaces, the partition being defined by spaced apart tubes extending generally parallel to the wall, the interior of the tubes defining said inlet region, portions of the tubes facing the wall defining said projection portions and containing said nozzles.
Claim 4
Dependent Claim
67 words
A gas turbine engine according to claim 1 further comprising: a partition dividing said chamber into an inlet region spaced from the wall and an outlet region open toward the wall, the partition having spaced apart projection portions projecting toward the wall to define therebetween said axially extending spaces, the partition is defined by a corrugated sheet, the corrugations defining said projection portions and containing said nozzles.
Claim 5
Dependent Claim
48 words
A gas turbine engine according to calim 1 comprising a turbine rotor having an annular array of blades, said wall being situated annularly around said array, and said outlet being defined by an opening in the wall leading into the duct in a position upstream of the blades.
Claim 6
Dependent Claim
48 words
A gas turbine engine according to calim 1 comprising a turbine rotor having an annular array of blades, said wall being situated annularly around said array, and said outlet being defined by an opening in the wall leading into the duct in a position upstream of the blades.
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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) | 1980-04-11 | 1980-10-11 | 1981-04-12 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-04-11 | 1984-10-11 | 1985-04-12 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-04-11 | 1988-10-11 | 1989-04-12 | $7700.00 | Window Closed / Lapsed |