US3777489A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Combustor casing and concentric air bleed structure
Assignee: General Electric Co
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Filing: 1972-06-01
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Granted: 1973-12-11
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Expires: 1992-06-01
Abstract
Abstract Combustor casing and bleed structure provides a concentric flow path for compressor discharge and intermediate stage air from a turbofan engine compressor to an outer cowling defining the fan flow path. Concentric tubes are respectively mounted to a support cone, which includes a plurality of outlet guide vanes, and to an outer casing, which partially defines the fan flow path. External piping is thus limited to the concentric tubes and potential losses due to interference with the fan flow are avoided.
Inventors
- 👤 A George
- 👤 K Johnson
- 👤 P Kepf
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 10:04
CPC Classifications
F; F02; F02C; F02C9/00; F02C9/16; F02C9/18; F01; F01D; F01D9/00; F01D9/06; F01D9/065; F02C6/00; F02C6/04; F02C6/06; F02C6/08; F04; F04D; F04D29/00; F04D29/40; F04D29/52; F04D29/54; F04D29/541; F04D29/545; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
104 words
In a gas turbine engine which includes an axial flow, multistage compressor, a combustor and a turbine, compressor air bleed structure comprising: a first air delivery tube, a second air delivery tube, concentric with and surrounding said first tube so as to define a passageway between the outer surface of said first tube and the inner surface of said second tube, means for delivering air from the discharge end of the compressor to said first tube, means for delivering air from an intermediate stage of the compressor to said second tube, and means for preventing flow between said first tube and said second tube.
Claim 2
Dependent Claim
104 words
In a gas turbine engine which includes an axial flow, multistage compressor, a combustor and a turbine, compressor air bleed structure comprising: a first air delivery tube, a second air delivery tube, concentric with and surrounding said first tube so as to define a passageway between the outer surface of said first tube and the inner surface of said second tube, means for delivering air from the discharge end of the compressor to said first tube, means for delivering air from an intermediate stage of the compressor to said second tube, and means for preventing flow between said first tube and said second tube.
Claim 3
Dependent Claim
51 words
Compressor air bleed structure as recited in claim 1 wherein the gas turbine engine comprises a turbOfan engine having an outer cowling which defines the inner bounds of a fan flow path which surrounds said compressor, and said first and second tubes each extend from the compressor to the outer cowling.
Claim 4
Dependent Claim
32 words
Compressor air bleed structure as recited in claim 1 further including a support cone located at the downstream end of the compressor, and said first tube is mounted to said support cone.
Claim 5
Dependent Claim
38 words
Compressor air bleed structure as recited in claim 3 wherein said support cone additionally supports an integral diffuser/outlet guide vane casting adapted to receive air from the discharge end of the compressor and deliver same to the combustor.
Claim 6
Dependent Claim
61 words
Compressor air bleed structure as recited in claim 4 wherein said diffuser casting includes at least one diffuser wall which defines a portion of a flow path for the compressor discharge flow, and said support cone surrounds said diffuser wall and thereby defines an annular plenum which receives a portion of the air flowing from the discharge end of the compressor.
Claim 7
Dependent Claim
51 words
Compressor air bleed structure as recited in claim 5 wherein the gas turbine engine comprises a turbofan engine having an outer cowling which defines the inner bounds of a fan flow path which surrounds said compressor, and said first and second tubes each extend from the compressor to the outer cowling.
Claim 8
Dependent Claim
44 words
Compressor air bleed structure as recited in claim 6 wherein the turbofan engine additionally includes an outer casing means which partially surrounds the compressor and defines a portion of the fan flow path, and said second tube is mounted to said outer casing means.
Claim 9
Dependent Claim
40 words
Compressor air bleed structure as recited in claim 7 wherein the turbofan engine includes a combustor casing which surrounds the combustor, and said combustor casing and said outer casing means cooperate to define a passageway for said intermediate stage air.
Claim 10
Dependent Claim
57 words
Compressor air bleed structure as recited in claim 5 wherein said diffuser casting further includes at least one conical-shaped extending arm, said arm is connected to and extends from said diffuser wall, and said arm is provided with at least one orifice adapted to permit a portion of the compressor discharge flow to pass to said plenum.
Claim 11
Dependent Claim
19 words
Compressor air bleed structure as recited in claim 9 wherein said outer casing means is mounted to said arm.
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) | 1976-12-10 | 1977-06-11 | 1977-12-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-12-10 | 1981-06-11 | 1981-12-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-12-10 | 1985-06-11 | 1985-12-11 | $7700.00 | Window Closed / Lapsed |