Patent US3584459A successfully refreshed from Google Patents.
US3584459A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine with combustion chamber bypass for fuel-air ratio control and turbine cooling
Assignee: Motors Liquidation Co
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Filing: 1968-09-12
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Granted: 1971-06-15
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Expires: 1988-09-12
Abstract
Abstract A gas turbine engine which may otherwise be of conventional configuration, single or plural shaft, regenerative or nonregenerative, is provided with a controlled bypass from the compressor to the turbine bypassing the combustion apparatus. Flow through this bypass is controlled so as to maintain the fuel-air ratio in the combustion chamber substantially constant notwithstanding variations in fuel flow and airflow with the load carried by the engine. Control of flow through the bypass may respond to setting of the fuel control device, to compressor discharge pressure, or to burner outlet temperature.
Inventors
- 👤 Charles A Amann
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 20:40
CPC Classifications
F; F02; F02C; F02C9/00; F02C9/16; F02C9/18
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
145 words
A gas turbine engine comprising, in combination, a compressor, a turbine connected to drive the compressor, and combustion apparatus of fixed geometry with a combustion zone, a dilution zone downstream from the combustion zone, an outlet for motive fluid from the dilution zone into the turbine inlet, and means connecting each of the said zones unvaryingly to the compressor outlet for supply of air to the zones, in combination with an air conduit from the compressor outlet to the turbine inlet bypassing the said combustion apparatus, a regulating valve in the air conduit, and means to operate the valve so as to bypass air in such quantities as to maintain the ratio of total air supplied to both of the combustion and dilution zones of the combustion apparatus to the fuel supplied to the combustion apparatus substantially invariant with variations in load on the engine.
Claim 2
Dependent Claim
145 words
A gas turbine engine comprising, in combination, a compressor, a turbine connected to drive the compressor, and combustion apparatus of fixed geometry with a combustion zone, a dilution zone downstream from the combustion zone, an outlet for motive fluid from the dilution zone into the turbine inlet, and means connecting each of the said zones unvaryingly to the compressor outlet for supply of air to the zones, in combination with an air conduit from the compressor outlet to the turbine inlet bypassing the said combustion apparatus, a regulating valve in the air conduit, and means to operate the valve so as to bypass air in such quantities as to maintain the ratio of total air supplied to both of the combustion and dilution zones of the combustion apparatus to the fuel supplied to the combustion apparatus substantially invariant with variations in load on the engine.
Claim 3
Dependent Claim
19 words
An engine as recited in claim 1 in which the last-recited means includes means controlled by motive fluid temperature.
Claim 4
Dependent Claim
19 words
An engine as recited in claim 1 in which the last-recited means includes means controlled by compressor discharge pressure.
Claim 5
Dependent Claim
43 words
An engine as recited in claim 1 including a regenerator for heating the motive fluid by extracting heat from exhaust gas before entry of the motive fluid into the combustion apparatus and in which the said air conduit is supplied through the regenerator.
Claim 6
Dependent Claim
46 words
An engine as recited in claim 1 in which the turbine inlet includes a flow-directing nozzle having vanes and a shroud, the air conduit bypassing the combustion apparatus extends to the said nozzle, and means are provided for cooling the turbine nozzle with the bypassed air.
Claim 7
Dependent Claim
124 words
A gas turbine engine comprising, in combination, a compressor, a turbine connected to drive the compressor, combustion apparatus of fixed geometry connected for flow of motive fluid from the compressor outlet to the turbine inlet, the turbine inlet including a flow-directing nozzle having vanes and a shroud, an air conduit from the compressor outlet to the turbine nozzle bypassing the combustion apparatus, a regulating valve in the air conduit, means to operate the valve so as to bypass air past the combustion apparatus to the turbine nozzle in such quantities as to maintain the fuel-air ratio in the combustion apparatus substantially invariant with variations in load on the engine, and means to flow the bypassed air through the turbine nozzle to cool the nozzle.
Claim 8
Dependent Claim
124 words
A gas turbine engine comprising, in combination, a compressor, a turbine connected to drive the compressor, combustion apparatus of fixed geometry connected for flow of motive fluid from the compressor outlet to the turbine inlet, the turbine inlet including a flow-directing nozzle having vanes and a shroud, an air conduit from the compressor outlet to the turbine nozzle bypassing the combustion apparatus, a regulating valve in the air conduit, means to operate the valve so as to bypass air past the combustion apparatus to the turbine nozzle in such quantities as to maintain the fuel-air ratio in the combustion apparatus substantially invariant with variations in load on the engine, and means to flow the bypassed air through the turbine nozzle to cool the nozzle.
Claim 9
Dependent Claim
28 words
An engine as recited in claim 6 including also means to control the valve so as to supply bypassed air for turbine cooling at high engine power levels.
Claim 10
Dependent Claim
152 words
A gas turbine engine comprising, in combination, a compressor a turbine connected to drive the compressor, combustion apparatus of fixed geometry connected for flow of motive from the compressor outlet to the turbine inlet, the turbine inlet including a flow-directing nozzle having vanes and a shroud, an air conduit from the compressor outlet to the turbine nozzle bypassing the combustion apparatus, a regulating valve in the air conduit, means to operate the valve so as to bypass air past the combustion apparatus to the turbine nozzle in such quantities as to maintain the fuel-air ratio in the combustion apparatus substantially invariant with variations in load on the engine, the nozzle shroud and vanes being hollow, the air conduit leading into the nozzle shroud, the air flowing through the shroud and vanes, and the outlet means for the air from the nozzle being defined into the motive fluid path upstream of the vanes.
Claim 11
Dependent Claim
152 words
A gas turbine engine comprising, in combination, a compressor a turbine connected to drive the compressor, combustion apparatus of fixed geometry connected for flow of motive from the compressor outlet to the turbine inlet, the turbine inlet including a flow-directing nozzle having vanes and a shroud, an air conduit from the compressor outlet to the turbine nozzle bypassing the combustion apparatus, a regulating valve in the air conduit, means to operate the valve so as to bypass air past the combustion apparatus to the turbine nozzle in such quantities as to maintain the fuel-air ratio in the combustion apparatus substantially invariant with variations in load on the engine, the nozzle shroud and vanes being hollow, the air conduit leading into the nozzle shroud, the air flowing through the shroud and vanes, and the outlet means for the air from the nozzle being defined into the motive fluid path upstream of the vanes.
References Cited (Backward Citations)
No citation records indexed.
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-06-14 | 1974-12-14 | 1975-06-15 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-06-14 | 1978-12-14 | 1979-06-15 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-06-14 | 1982-12-14 | 1983-06-15 | $7700.00 | Window Closed / Lapsed |