US4157010A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine with power modulation capability
Assignee: General Electric Co
•
Filing: 1977-06-03
•
Granted: 1979-06-05
•
Expires: 1997-06-03
Abstract
Abstract A device is provided for increasing the power output of a gas turbine engine at the low ambient inlet temperatures which would otherwise produce a decrease in power. The device includes a conduit for bypassing a portion of the compressor discharge air around the combustor whereupon it is reintroduced back into the engine downstream of the compressor-driving turbine and upstream of the power turbine, if any. A valve is provided to increase the bypass flow rate through the conduit at low ambient temperatures, the increasing bypass flow permitting the engine to operate at a higher fuel flow and cycle temperatures for the same compressor mass flow. The increased temperature with the same mass flow rate results in an increase in power.
Inventors
- 👤 Edward D. Sailer
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 02:00
CPC Classifications
F; F02; F02C; F02C3/00; F02C3/04; F02C3/10; F02C9/00; F02C9/16; F02C9/18; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
138 words
In a gas turbine engine having a compressor for pressurizing a flow of air, a combustor in which compressed air is mixed with fuel and combusted, a turbine driven by the hot gases of combustion and drivingly connected to said compressor, and a separate power turbine said engine characterized by a predetermined relationship of power output versus compressor inlet ambient temperature at maximum compressor flow, a device for modulating the engine power output at a low ambient temperature comprising means for bypassing a portion of the air discharged from the compressor around the combustor and for reintroducing the portion into the cycle between the compressor and power turbines, means for modulating the bypass flow rate, and a throttle for modulating fuel flow rate, the resulting power level thereby exceeding the predetermined relationship at the same low ambient temperature.
Claim 2
Dependent Claim
138 words
In a gas turbine engine having a compressor for pressurizing a flow of air, a combustor in which compressed air is mixed with fuel and combusted, a turbine driven by the hot gases of combustion and drivingly connected to said compressor, and a separate power turbine said engine characterized by a predetermined relationship of power output versus compressor inlet ambient temperature at maximum compressor flow, a device for modulating the engine power output at a low ambient temperature comprising means for bypassing a portion of the air discharged from the compressor around the combustor and for reintroducing the portion into the cycle between the compressor and power turbines, means for modulating the bypass flow rate, and a throttle for modulating fuel flow rate, the resulting power level thereby exceeding the predetermined relationship at the same low ambient temperature.
Claim 3
Dependent Claim
238 words
A gas turbine engine comprising: a core engine having a compressor for pressurizing a flow of air, a combustor in which pressurized air is mixed with fuel and combusted, and a core engine turbine driven by the hot gases of combustion and drivingly connected to the compressor; a power turbine downstream of said core engine and independently driven by the hot gases of combustion exiting the core engine turbine; said engine possessing an operating characteristic whereby power turbine work extraction increases as compressor inlet temperature decreases until a relatively low inlet temperature level is obtained while contemporaneously maintaining a rated power turbine inlet temperature through an increase of the fuel flow rate into the combustor, the power turbine work extraction thereafter decreasing with further reductions in compressor inlet temperature as a result of compressor airflow and stall margin limitations; said engine further comprising means for increasing the power turbine work extraction at compressor inlet temperatures below the relatively low inlet temperature level including means for bypassing a portion of the air discharged from the compressor around the core engine turbine and for introducing the bypass portion into the engine cycle between the core engine turbine and the power turbine; means for increasing the fuel flow rate into the combustor contemporaneous with the passage of the bypass flow; and means for modulating the bypass flow rate such that an increasing rate is associated with increased power turbine work extraction.
Claim 4
Dependent Claim
238 words
A gas turbine engine comprising: a core engine having a compressor for pressurizing a flow of air, a combustor in which pressurized air is mixed with fuel and combusted, and a core engine turbine driven by the hot gases of combustion and drivingly connected to the compressor; a power turbine downstream of said core engine and independently driven by the hot gases of combustion exiting the core engine turbine; said engine possessing an operating characteristic whereby power turbine work extraction increases as compressor inlet temperature decreases until a relatively low inlet temperature level is obtained while contemporaneously maintaining a rated power turbine inlet temperature through an increase of the fuel flow rate into the combustor, the power turbine work extraction thereafter decreasing with further reductions in compressor inlet temperature as a result of compressor airflow and stall margin limitations; said engine further comprising means for increasing the power turbine work extraction at compressor inlet temperatures below the relatively low inlet temperature level including means for bypassing a portion of the air discharged from the compressor around the core engine turbine and for introducing the bypass portion into the engine cycle between the core engine turbine and the power turbine; means for increasing the fuel flow rate into the combustor contemporaneous with the passage of the bypass flow; and means for modulating the bypass flow rate such that an increasing rate is associated with increased power turbine work extraction.
Claim 5
Dependent Claim
130 words
In a method of increasing the temperature of a gas flow entering a power turbine disposed downstream of a core engine having a compressor for pressurizing a flow of air, a combustor in which pressurized air is mixed with fuel and combusted, and a core engine turbine driven by the hot gas flow of combustion products and drivingly connected to the compressor, the steps of: bypassing a portion of the compressor discharge air around the core engine turbine; increasing the rate of fuel flow into the combustor to increase the fuel-air ratio within the combustor; reintroducing the bypass air into the engine cycle between the core engine turbine and the power turbine while contemporaneously maintaining the compressor discharge airflow substantially constant; thereby increasing the power output of the power turbine.
Claim 6
Dependent Claim
130 words
In a method of increasing the temperature of a gas flow entering a power turbine disposed downstream of a core engine having a compressor for pressurizing a flow of air, a combustor in which pressurized air is mixed with fuel and combusted, and a core engine turbine driven by the hot gas flow of combustion products and drivingly connected to the compressor, the steps of: bypassing a portion of the compressor discharge air around the core engine turbine; increasing the rate of fuel flow into the combustor to increase the fuel-air ratio within the combustor; reintroducing the bypass air into the engine cycle between the core engine turbine and the power turbine while contemporaneously maintaining the compressor discharge airflow substantially constant; thereby increasing the power output of the power turbine.
References Cited (Backward Citations)
US2312995A
Cited
US2257982A
Cited
US2608055A
Cited
US2738645A
Cited
US2703477A
Cited
US3041822A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1982-06-04 | 1982-12-04 | 1983-06-05 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-06-04 | 1986-12-04 | 1987-06-05 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-06-04 | 1990-12-04 | 1991-06-05 | $7700.00 | Window Closed / Lapsed |