Fuel control system for gas turbine engine
Patent
·
OSTI ID:7348150
A fuel control system is described for a gas turbine engine with a gas generator turbine and a separate work turbine. A positive-displacement pump is driven by the engine, and a spill valve responsive to a servo pressure signal delivers fuel from the downstream side of the pump. A pilot valve is responsible to an electrical signal which controls the servo pressure signal, and a flow restrictor in series with the pilot valve defines the servo pressure signal from engine operating parameters. The pilot valve can be isolated from the restrictor by a valve in parallel with the pilot valve, the valve being controlled by the servo pressure signal.
- Assignee:
- Lucas Aerospace Ltd.
- Patent Number(s):
- US 3958415
- OSTI ID:
- 7348150
- Country of Publication:
- United States
- Language:
- English
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