US4550561A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method for improving the fuel efficiency of a gas turbine engine
Assignee: National Aeronautics and Space Administration
•
Filing: 1982-08-30
•
Granted: 1985-11-05
•
Expires: 2002-08-30
Abstract
Abstract An energy recovery system is provided for an aircraft gas turbine engine of the type in which some of the pneumatic energy developed by the engine is made available to support systems such as an environmental control system. In one such energy recovery system, some of the pneumatic energy made available to but not utilized by the support system is utilized to heat the engine fuel immediately prior to the consumption of the fuel by the engine. Some of the recovered energy may also be utilized to heat the fuel in the fuel tanks. Provision is made for multi-engine applications wherein energy recovered from one engine may be utilized by another one of the engines or systems associated therewith.
Inventors
- 👤 George A. Coffinberry
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 20:16
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/22; F02C7/224; F02C7/12; F02C7/14; F05; F05D; F05D2220/00; F05D2220/50; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
204 words
A method of recovering heat in a gas turbine engine which drives a fan in an aircraft, comprising: (a) tapping a first compressor bleed airstream, B1, having a first temperature; (b) tapping a second compressor bleed airstream, B2, having a second temperature higher than the first temperature; (c) transferring heat from B1 through a first heat exchanger and into an aquaeous heat transfer medium; (d) transferring heat from the aqueous medium of (c) into high-pressure fuel having a pressure exceeding 500 psig; (e) bypassing some of B1 past the first heat exchanger of (c) when the temperature of the fuel of (d) reaches a predetermined level to thereby reduce heating of the high-pressure fuel; (f) mixing B2 with both the B1 which passed through the first heat exchanger and with the B1 which bypassed the first heat exchanger in order to provide a mixed airstream; and (g) directing some of the mixed airstream of (f) to one or more of the following engine suport components: wing anti-icer, cowl anti-icer, cabin air conditioner, or engine starter for absorption of heat from the mixed airstream prior to the overboard disposal of any significant amounts of B1 or B2 or the mixed B1 and B2 of (f).
Claim 2
Independent Claim
204 words
A method of recovering heat in a gas turbine engine which drives a fan in an aircraft, comprising: (a) tapping a first compressor bleed airstream, B1, having a first temperature; (b) tapping a second compressor bleed airstream, B2, having a second temperature higher than the first temperature; (c) transferring heat from B1 through a first heat exchanger and into an aquaeous heat transfer medium; (d) transferring heat from the aqueous medium of (c) into high-pressure fuel having a pressure exceeding 500 psig; (e) bypassing some of B1 past the first heat exchanger of (c) when the temperature of the fuel of (d) reaches a predetermined level to thereby reduce heating of the high-pressure fuel; (f) mixing B2 with both the B1 which passed through the first heat exchanger and with the B1 which bypassed the first heat exchanger in order to provide a mixed airstream; and (g) directing some of the mixed airstream of (f) to one or more of the following engine suport components: wing anti-icer, cowl anti-icer, cabin air conditioner, or engine starter for absorption of heat from the mixed airstream prior to the overboard disposal of any significant amounts of B1 or B2 or the mixed B1 and B2 of (f).
Claim 3
Dependent Claim
43 words
A method according to claim 1 and further comprising the step of transferring heat out of the mixed airstream into the fan airstream when the heat absorbed by the fuel of (d) and by the components of (g) falls below a predetermined level.
Claim 4
Dependent Claim
20 words
A method according to claim 1 and further comprising the step of pressurizing the aquaeous heat transfer medium by B1.
Claim 5
Dependent Claim
33 words
A method according to claim 1 and further comprising the step of controlling the tapping of B2 such that substantially no B2 is tapped when the engine power output exceeds a predetermined level.
References Cited (Backward Citations)
US2637984A
Cited
US2691274A
Cited
GB741433A
Cited
GB742270A
Cited
GB781758A
Cited
GB797360A
Cited
GB859479A
Cited
US3158197A
Cited
US3547380A
Cited
US3537513A
Cited
US3623546A
Cited
GB1559828A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1988-11-04 | 1989-05-06 | 1989-11-05 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-11-04 | 1993-05-06 | 1993-11-05 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-11-04 | 1997-05-06 | 1997-11-05 | $7700.00 | Window Closed / Lapsed |