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US4711085A Expired / Lapsed US ⏱️ 0.0 years remaining

Gas turbine engine fuel systems

Assignee: Rolls Royce PLC
•
Filing: 1986-02-18
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Granted: 1987-12-08
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Expires: 2006-02-18
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Abstract

Abstract A fuel system for a gas turbine engine is arranged to schedule fuel flow between primary and secondary fuel injectors in order to obtain good ignition and light round when the engine is operating on diesel fuel. The system includes either two solenoid valves in parallel with flow restrictors or a single solenoid operated valve and two flow restrictors. The two valves or the diverter valve schedule the fuel flow so that at engine start up, the flow to the primary and secondary fuel injectors is according to requirement proportioned. At a certain engine speed the flow to the secondary fuel injectors is reduced to purge flow and the major part of the fuel flow passes to the primary fuel injectors.

Inventors

  • 👤 Michael R. Lyons

Bibliographic Details

Application Number —
Jurisdiction US
Data Source google_patents
Last Synchronized 2026-10-29 15:27
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/34; F02; F02C; F02C7/00; F02C7/22; F02C7/228; F02C7/26; F02C7/264; F02C9/00; F02C9/26; F02C9/32; F02C9/34

Claims Analysis

Total Claims: 4
Claim 1
Independent Claim 159 words
A fuel system for a gas turbine engine comprising: at least one primary fuel injector; at least one secondary fuel injector; a primary fuel supply line operatively connected to said at least one primary fuel injector; a secondary fuel supply line operatively connected to said secondary fuel injector; means for supplying fuel to said primary fuel supply line and to said secondary fuel supply line; fuel flow restricting means in each of said primary and said secondary fuel supply lines; and valve means operatively connected to said fuel supply means and to said primary and secondary fuel supply lines downstream of said fuel flow restricting means in each, said valve means comprising a solenoid valve arranged in parallel with said flow restricting means in each of said primary and secondary fuel supply lines where said valve means is selectively operable to direct fuel to bypass said fuel flow restricting means in one of said primary and secondary fuel lines.
Claim 2
Dependent Claim 159 words
A fuel system for a gas turbine engine comprising: at least one primary fuel injector; at least one secondary fuel injector; a primary fuel supply line operatively connected to said at least one primary fuel injector; a secondary fuel supply line operatively connected to said secondary fuel injector; means for supplying fuel to said primary fuel supply line and to said secondary fuel supply line; fuel flow restricting means in each of said primary and said secondary fuel supply lines; and valve means operatively connected to said fuel supply means and to said primary and secondary fuel supply lines downstream of said fuel flow restricting means in each, said valve means comprising a solenoid valve arranged in parallel with said flow restricting means in each of said primary and secondary fuel supply lines where said valve means is selectively operable to direct fuel to bypass said fuel flow restricting means in one of said primary and secondary fuel lines.
Claim 3
Dependent Claim 66 words
A fuel system as claimed in claim 1 in which said flow restricting means in said primary fuel supply line is confined when said valve means is operated to direct a supply of fuel to said secondary fuel supply line such that fuel flows to each of said at least one primary fuel injector and said at least one secondary fuel injector are substantially the same.
Claim 4
Dependent Claim 47 words
A fuel system as claimed in claim 1 in which said valve means is a diverter valve arranged to receive fuel from said fuel supply means and to discharge fuel to one of said primary and secondary fuel supply lines downstream of said flow restricting means therein.

References Cited (Backward Citations)

US3283502A Cited
US3319418A Cited
US3335567A Cited
US4062183A Cited
US3991558A Cited
US4417439A Cited

USPTO Annuity & Maintenance Windows

Annuity Stage Window Opens Payment Deadline Surcharge Period Until Estimated Fee Status
3.5 Years (Year 4) 1990-12-07 1991-06-08 1991-12-08 $2000.00 Window Closed / Lapsed
7.5 Years (Year 8) 1994-12-07 1995-06-08 1995-12-08 $3760.00 Window Closed / Lapsed
11.5 Years (Year 12) 1998-12-07 1999-06-08 1999-12-08 $7700.00 Window Closed / Lapsed

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