US4062183A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Fuel supply system for a gas turbine engine
Assignee: Rolls Royce PLC
•
Filing: 1976-05-24
•
Granted: 1977-12-13
•
Expires: 1996-05-24
Abstract
Abstract In order to improve the start-up of a gas turbine engine, a control system is provided which fills part of the fuel manifold with compressed air during start-up so as to prevent fuel flowing to all the burners and thereby to improve the performance of the remaining burners.
Inventors
- 👤 David Omri Davies
- 👤 Bruce Ernest Mills
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 12:29
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/22; F02C7/232; F02C7/228; Y; Y10; Y10T; Y10T137/00; Y10T137/8593; Y10T137/87249
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
181 words
A fuel supply system for a gas turbine engine having compressor means, combustion chamber and turbine means in flow series: a plurality of burners for injecting fuel into the combustion chamber; fuel manifold means operatively connected to each of said burners for sypplying fuel thereto; a source of compressed gas; a compressed gas operated starting device operatively connected to the compressor means and/or turbine means for starting the engine; duct means operatively connected to the source of compressed gas and to said compressed gas operated starting device and said fuel manifold means respectively, said duct means being arranged to supply compressed gas to said starting device for operating the same and to supply compressed gas to said fuel manifold means to act directly against fuel flowing therethrough to prevent fuel from being supplied to a predetermined number of burners; and valve means in said duct means upstream of the connection of the duct means to said starting device and upstream of the connection to said fuel manifold means for simultaneously supplying compressed gas to the starting device and the manifold means.
Claim 2
Dependent Claim
181 words
A fuel supply system for a gas turbine engine having compressor means, combustion chamber and turbine means in flow series: a plurality of burners for injecting fuel into the combustion chamber; fuel manifold means operatively connected to each of said burners for sypplying fuel thereto; a source of compressed gas; a compressed gas operated starting device operatively connected to the compressor means and/or turbine means for starting the engine; duct means operatively connected to the source of compressed gas and to said compressed gas operated starting device and said fuel manifold means respectively, said duct means being arranged to supply compressed gas to said starting device for operating the same and to supply compressed gas to said fuel manifold means to act directly against fuel flowing therethrough to prevent fuel from being supplied to a predetermined number of burners; and valve means in said duct means upstream of the connection of the duct means to said starting device and upstream of the connection to said fuel manifold means for simultaneously supplying compressed gas to the starting device and the manifold means.
Claim 3
Dependent Claim
32 words
A fuel supply system as claimed in claim 1 including a pressure regulating valve in said duct means for controlling a maximum pressure of compressed gas delivered to said fuel manifold means.
Claim 4
Dependent Claim
60 words
A fuel supply system as claimed in claim 1 including a non-return valve in said duct means adjacent the connection of the same to said fuel manifold means whereby compressed gas and/or fuel in said fuel manifold means, when its pressure is greater than pressure of the compressed gas in said duct means, is prevented from entering said duct means.
Claim 5
Dependent Claim
44 words
A fuel supply system as claimed in claim 3 including a fail-safe control means operatively connected in said duct means intermediate said non-return valve and said compressed gas starting device for preventing fuel from flowing to said starting device should said non-return valve fail.
Claim 6
Dependent Claim
51 words
A fuel supply system as claimed in claim 4 in which said fail-safe control means includes a pressure responsive relief valve having a discharge outlet, said pressure responsive relief valve being operative to an open postion when pressure of fuel in said duct means is greater than pressure of compressed gas.
Claim 7
Dependent Claim
23 words
A fuel supply system as claimed in claim 5 including a drain tank operatively connected to said discharge outlet of said relief valve.
Claim 8
Dependent Claim
34 words
A fuel supply system as claimed in claim 5 including an outlet to atmosphere having a pre-determined gravity head means, said outlet to atmosphere being connected to said discharge outlet of said relief valve.
Claim 9
Dependent Claim
41 words
A fuel supply system as claimed in claim 7 in which said duct means upstream of said relief valve has a gravity head means greater than said gravity head means in said outlet to atmosphere from said pressure responsive relief valve.
Claim 10
Dependent Claim
41 words
A fuel supply system as claimed in claim 8 in which said gravity head means in the outlet to atmosphere is an inverted U-shaped duct, and in which said gravity head means in said duct means is an inverted U-shaped duct.
References Cited (Backward Citations)
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Cited
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US3158998A
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US3149463A
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US3288447A
Cited
US3498056A
Cited
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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) | 1980-12-12 | 1981-06-13 | 1981-12-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-12-12 | 1985-06-13 | 1985-12-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-12-12 | 1989-06-13 | 1989-12-13 | $7700.00 | Window Closed / Lapsed |