| 摘要 |
<p>A fuel control apparatus for a gas turbine engine, in which operational fuel is supplied to the engine through a primary metering valve responsive to movement of a power lever within a normal operational range, and a secondary, normally closed metering valve which is responsive to movement of said power lever within an emergency operational range in the event of a malfunction in the operation of the primary metering valve (electrical power failure, for instance).</p><p>The invention provides for automatic detection of a possible malfunction by a sensor (402) and automatic transfer of the fuel flow requirement from the primary metering valve (56) to the secondary metering valve (62) without moving the power lever (36) when the fuel flow requirement is below a predetermined level.</p><p>For use particularly in the control of aircraft turbine engines.</p> |
