US4697238A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Integrated fuel management system
Assignee: Teledyne Technologies Inc
•
Filing: 1984-02-10
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Granted: 1987-09-29
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Expires: 2004-02-10
Abstract
Abstract A low cost, integrated, aircraft fuel management system. A system control unit receives engine variable signals and provides a signal to a motor control unit which thereby controls a variable speed motor. The motor drives a positive displacement pump which delivers and meters fuel to a slinger type turbine engine capable of handling slurry fuels. In a preferred embodiment, compressor discharge pressure (CDP) is supplied to the airframe fuel reservoir thereby pressurizing the fuel supply and minimizing the power requirements of the motor driving the fuel pump.
Inventors
- 👤 Dennis E. Barbeau
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 14:31
CPC Classifications
F; F02; F02P; F02P15/00; F02P15/001; F02P15/003; F02C; F02C7/00; F02C7/22; F02C9/00; F02C9/26; F02C9/30
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
118 words
An aircraft fuel management system to regulate fuel from an airframe reservoir, said system comprising: an aircraft turbine engine having a combustor providing propulsion for the aircraft; a fuel pump receiving fuel from the reservoir and supplying fuel to the turbine engine; a motor controlling said pump so as to provide fuel to said turbine engine; means for sensing at least one engine condition; means responsive to said sensing means for controlling fuel flow to said turbine engine, and wherein said pump and said motor are of the constant speed type and further comprising valve means for controlling the fuel flow rate to said turbine engine and wherein said controlling means modulates the position of said valve means.
Claim 2
Dependent Claim
118 words
An aircraft fuel management system to regulate fuel from an airframe reservoir, said system comprising: an aircraft turbine engine having a combustor providing propulsion for the aircraft; a fuel pump receiving fuel from the reservoir and supplying fuel to the turbine engine; a motor controlling said pump so as to provide fuel to said turbine engine; means for sensing at least one engine condition; means responsive to said sensing means for controlling fuel flow to said turbine engine, and wherein said pump and said motor are of the constant speed type and further comprising valve means for controlling the fuel flow rate to said turbine engine and wherein said controlling means modulates the position of said valve means.
Claim 3
Dependent Claim
41 words
The invention as defined in claim 1 and further comprising a compressor driven by said turbine wherein the reservoir is pressurized by said compressor to provide fuel flow to said turbine engine thereby reducing the power required to drive said pump.
Claim 4
Dependent Claim
33 words
The invention as defined in claim 1 wherein said sensing means comprises: first means for sensing engine inlet total temperature; second means for sensing engine speed; and third means for sensing pump speed.
Claim 5
Dependent Claim
34 words
The invention as defined in claim 3 and further comprising stationary supply tube means for supplying fuel to said rotating shaft and means for sealing fuel flow from said tube means to said shaft.
Claim 6
Dependent Claim
28 words
The invention as defined in claim 1 and further comprising first means for generating an airframe demand signal, said controlling means being responsive to said first generating means.
Claim 7
Dependent Claim
33 words
The invention as defined in claim 1 wherein said engine further comprises a rotating shaft receiving fuel from said pump, said shaft having at least one slinger hole releasing fuel to said combustor.
Claim 8
Dependent Claim
14 words
The invention as defined in claim 1 wherein said controlling means comprises a microprocessor.
Claim 9
Dependent Claim
31 words
The invention as defined in claim 1 and further comprising second means for generating a signal to start said engine and means responsive to said second means for starting said engine.
Claim 10
Dependent Claim
19 words
The invention as defined in claim 1 wherein said sensing means also senses the position of said valve means.
References Cited (Backward Citations)
US3098632A
Cited
US3261571A
Cited
US3275061A
Cited
US3279522A
Cited
US3389602A
Cited
US3443778A
Cited
US3758764A
Cited
US3946551A
Cited
US4038817A
Cited
US4115998A
Cited
US4033115A
Cited
US4159625A
Cited
US4208871A
Cited
US4188781A
Cited
US4294069A
Cited
US4215412A
Cited
DE2841750A1
Cited
US4248042A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1990-09-28 | 1991-03-30 | 1991-09-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1994-09-28 | 1995-03-30 | 1995-09-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1998-09-28 | 1999-03-30 | 1999-09-29 | $7700.00 | Window Closed / Lapsed |