US4354345A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Fuel heating system for gas turbine engine
Assignee: RTX Corp
•
Filing: 1980-04-29
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Granted: 1982-10-19
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Expires: 2000-04-29
Abstract
Abstract To accommodate fuel having higher freezing points the continuous bypass flow of fuel from the fuel control is selectively diverted to pick up the rejected heat from the engine's lubrication system to heat the fuel in the aircraft fuel tank.
Inventors
- 👤 Raymond A. Dreisbach, Jr.
- 👤 James G. Griffin
- 👤 Edward F. Cole
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 14:35
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/12; F02C7/14; F02C7/22; F02C7/224; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
181 words
A system for heating the fuel in a fuel tank for aircraft which system includes a lubrication system for a jet engine, a fuel control that meters fuel to said engine and a heat exchanger that places the fuel and lubricant of said lubrication systems in indirect heat exchange relation, a pump for pressurizing the fuel prior to being admitted to the fuel control which receives an excess of fuel over that being metered to the engine, and a bypass diverting fuel from said engine continuously flowing said excess fuel, said fuel heating system including another heat exchanger having the lubricant connected in series with said heat exchanger, means for interconnecting said excess fuel to said other heat exchanger so as to place said fuel in indirect heat exchange relation with said lubricant, conduit means leading said heated fuel from said other heat exchanger into said fuel tank, means for selectively turning on and off the flow of bypass fuel to said other heat exchanger and said bypass continuously communicating with the inlet of said pump independently of said selective means.
Claim 2
Independent Claim
181 words
A system for heating the fuel in a fuel tank for aircraft which system includes a lubrication system for a jet engine, a fuel control that meters fuel to said engine and a heat exchanger that places the fuel and lubricant of said lubrication systems in indirect heat exchange relation, a pump for pressurizing the fuel prior to being admitted to the fuel control which receives an excess of fuel over that being metered to the engine, and a bypass diverting fuel from said engine continuously flowing said excess fuel, said fuel heating system including another heat exchanger having the lubricant connected in series with said heat exchanger, means for interconnecting said excess fuel to said other heat exchanger so as to place said fuel in indirect heat exchange relation with said lubricant, conduit means leading said heated fuel from said other heat exchanger into said fuel tank, means for selectively turning on and off the flow of bypass fuel to said other heat exchanger and said bypass continuously communicating with the inlet of said pump independently of said selective means.
Claim 3
Dependent Claim
43 words
A system as in claim 1 including conduit means interconnecting the inlet of said pump and said other heat exchanger with said fuel bypass, selector valve means for shutting the flow of fuel in said conduit means solely to said other heat exchanger.
Claim 4
Dependent Claim
40 words
A system as in claim 2 including an actuator positioning said selector valve means to an on and off position, and means responsive to the temperature of the fuel downstream of said other heat exchanger for controlling said actuator means.
Claim 5
Dependent Claim
198 words
Means for selectively heating fuel in aircraft fuel tanks in which the aircraft includes an engine powering the aircraft and a lubrication system for said engine, the lubrication system including means for leading lubricant into and out of said engine and a first heat exchanger in indirect heat exchange with the fuel being metered to the engine and said lubricant, a fuel control for metering fuel to said engine which has a continuous flow of excess fuel bypassing said engine, a pump for pressurizing fuel from said fuel tank leading fuel to said fuel control, conduit means continuously conducting said excess fuel to said pump inlet, a second heat exchanger having connection means to the lubrication system and being in series relationship with said first heat exchanger, additional conduit means interconnecting said conduit means and said second heat exchanger, a valve in said additional conduit means for controlling a portion of excess fuel to said second heat exchanger to be in indirect heat exchange relation with said lubricant, means responsive to the temperature of fuel discharging from said second heat exchanger for controlling said valve to selectively admit said portion of excess fuel to said second heat exchanger.
Claim 6
Dependent Claim
198 words
Means for selectively heating fuel in aircraft fuel tanks in which the aircraft includes an engine powering the aircraft and a lubrication system for said engine, the lubrication system including means for leading lubricant into and out of said engine and a first heat exchanger in indirect heat exchange with the fuel being metered to the engine and said lubricant, a fuel control for metering fuel to said engine which has a continuous flow of excess fuel bypassing said engine, a pump for pressurizing fuel from said fuel tank leading fuel to said fuel control, conduit means continuously conducting said excess fuel to said pump inlet, a second heat exchanger having connection means to the lubrication system and being in series relationship with said first heat exchanger, additional conduit means interconnecting said conduit means and said second heat exchanger, a valve in said additional conduit means for controlling a portion of excess fuel to said second heat exchanger to be in indirect heat exchange relation with said lubricant, means responsive to the temperature of fuel discharging from said second heat exchanger for controlling said valve to selectively admit said portion of excess fuel to said second heat exchanger.
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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) | 1985-10-18 | 1986-04-19 | 1986-10-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1989-10-18 | 1990-04-19 | 1990-10-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1993-10-18 | 1994-04-19 | 1994-10-19 | $7700.00 | Window Closed / Lapsed |