US3869862A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Fuel conservation system for multi-engine powered vehicle
Assignee: Avco Corp
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Filing: 1972-12-01
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Granted: 1975-03-11
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Expires: 1992-12-01
Abstract
Abstract A pair of gas turbine engines drive a main rotor assembly of a helicopter through a combined output gearbox. During low power requirement conditions of the helicopter''s flight regime, metered fuel flow to one of the engines is terminated and that engine driven by a connection, such as hydraulic or pneumatic, from the other engine. A pilot combustion is maintained in the combustor of the driven engine to insure that the engine may be rapidly brought to an operating condition upon demand.
Inventors
- 👤 Thomas A Dickey
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 20:04
CPC Classifications
F; F02; F02C; F02C6/00; F02C6/02
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
167 words
A fuel conservation system for a vehicle having a wide range of power requirements and normally powered simultaneously in the same direction by at least first and second gas turbine engines, each having a compressor rotor rotatable to pressurize air, a combustor receiving air from said compressor rotor and means for supplying metered fuel to said combustor, thereby enabling combustion and production of a motive gas stream, said engines being operable over relatively wide power ranges, said system comprising: means for selectively terminating metered flow of fuel to the combustor of said first engine; means connected to and deriving power from the second gas turbine engine for driving the compressor rotor of the first engine at an idle R.P.M. substantially below its normal operating R.P.M.; means for sustaining pilot combustion in a portion of the combustor of said first engine; whereby fuel consumption is significantly reduced during low vehicle power requirements and said first engine is in a state of readiness for rapid establishment of full power.
Claim 2
Dependent Claim
167 words
A fuel conservation system for a vehicle having a wide range of power requirements and normally powered simultaneously in the same direction by at least first and second gas turbine engines, each having a compressor rotor rotatable to pressurize air, a combustor receiving air from said compressor rotor and means for supplying metered fuel to said combustor, thereby enabling combustion and production of a motive gas stream, said engines being operable over relatively wide power ranges, said system comprising: means for selectively terminating metered flow of fuel to the combustor of said first engine; means connected to and deriving power from the second gas turbine engine for driving the compressor rotor of the first engine at an idle R.P.M. substantially below its normal operating R.P.M.; means for sustaining pilot combustion in a portion of the combustor of said first engine; whereby fuel consumption is significantly reduced during low vehicle power requirements and said first engine is in a state of readiness for rapid establishment of full power.
Claim 3
Dependent Claim
167 words
A fuel conservation system for a vehicle having a wide range of power requirements and normally powered simultaneously in the same direction by at least first and second gas turbine engines, each having a compressor rotor rotatable to pressurize air, a combustor receiving air from said compressor rotor and means for supplying metered fuel to said combustor, thereby enabling combustion and production of a motive gas stream, said engines being operable over relatively wide power ranges, said system comprising: means for selectively terminating metered flow of fuel to the combustor of said first engine; means connected to and deriving power from the second gas turbine engine for driving the compressor rotor of the first engine at an idle R.P.M. substantially below its normal operating R.P.M.; means for sustaining pilot combustion in a portion of the combustor of said first engine; whereby fuel consumption is significantly reduced during low vehicle power requirements and said first engine is in a state of readiness for rapid establishment of full power.
Claim 4
Dependent Claim
167 words
A fuel conservation system for a vehicle having a wide range of power requirements and normally powered simultaneously in the same direction by at least first and second gas turbine engines, each having a compressor rotor rotatable to pressurize air, a combustor receiving air from said compressor rotor and means for supplying metered fuel to said combustor, thereby enabling combustion and production of a motive gas stream, said engines being operable over relatively wide power ranges, said system comprising: means for selectively terminating metered flow of fuel to the combustor of said first engine; means connected to and deriving power from the second gas turbine engine for driving the compressor rotor of the first engine at an idle R.P.M. substantially below its normal operating R.P.M.; means for sustaining pilot combustion in a portion of the combustor of said first engine; whereby fuel consumption is significantly reduced during low vehicle power requirements and said first engine is in a state of readiness for rapid establishment of full power.
Claim 5
Dependent Claim
30 words
A system as in claim 1 wherein said driving means comprises an engageable mechanical connection between the output of said second engine to the bladed rotor of the first engine.
Claim 6
Dependent Claim
39 words
A system as in claim 1 wherein said driving means comprises a hydraulic pump connected to the second engine and a hydraulic motor hydraulically coupled to said pump and mechanically connected to the bladed rotor of the first engine.
Claim 7
Dependent Claim
52 words
A system as in claim 1 wherein said driving means comprises means for bleeding a portion of the pressurized air from the compressor rotor of said second engine and an air turbine pneumatically connected to said bleed means, said air turbine being mechanically connected to the bladed rotor of said first engine.
Claim 8
Dependent Claim
28 words
A system as in claim 1 for a helicopter having at least one main rotor driven from a transmission receiving rotational power inputs from said gas turbine engines.
Claim 9
Dependent Claim
26 words
A system as in claim 5 wherein said driving means comprises a mechanical connection between said main rotor and the bladed rotor of said first engine.
Claim 10
Dependent Claim
43 words
A system as in claim 5 wherein said driving means comprises a hydraulic pump mechanically connected to the second engine and a hydraulic motor hydraulically connected to said pump, said hydraulic motor being mechanically connected to the bladed rotor of said first engine.
Claim 11
Dependent Claim
48 words
A system as in claim 5 wherein said driving means comprises means for bleeding a portion of the pressurized air from said second engine and an air turbine pneumatically connected to said bleed means, said air turbine being mechanically connected to the bladed rotor of said first engine.
Claim 12
Dependent Claim
48 words
A system as in claim 1 wherein said means for sustaining pilot combustion comprises a fuel nozzle for injecting fuel into said combustor to maintain a combustible fuel/air mixture in a portion of said combustor and an igniter operable to ignite and maintain combustion of said fuel/air mixture.
References Cited (Backward Citations)
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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) | 1978-03-10 | 1978-09-09 | 1979-03-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-03-10 | 1982-09-09 | 1983-03-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-03-10 | 1986-09-09 | 1987-03-11 | $7700.00 | Window Closed / Lapsed |