Fuel systems for aircraft gas turbine engines专利检索-失速控制风能专利检索查询-专利查询网

Fuel systems for aircraft gas turbine engines

阅读：268发布：2022-02-17

专利汇可以提供Fuel systems for aircraft gas turbine engines专利检索，专利查询，专利分析的服务。并且In an aircraft having a gas-turbine engine, one or more main jet nozzles directed downwardly to provide weight-supporting thrust for the aircraft, a plurality of stabilising nozzles, duct-means for feeding air at pressure from the engine compressor to the stabilising nozzles, and a pilot''s adjustable valve means for adjusting air flow from the stabilising nozzles to control the attitude of the aircraft, the provision of a fuel system for the engine comprising, a source of fuel at pressure, a constant speed fuel flow control to feed fuel from the source to the engine for constant and slowly varying speeds, an acceleration fuel flow control to feed fuel from the source to the engine during engine acceleration at a rate ensuring safe acceleration without compressor stall, an auxiliary fuel flow control and control means for said auxiliary fuel flow control responsive to air flow to one or more stabilising nozzles to supply extra fuel flow to the engine during engine acceleration over and above the fuel flow supplied by the acceleration fuel flow control.，下面是Fuel systems for aircraft gas turbine engines专利的具体信息内容。

权利要求

2. A fuel system as claimed in claim 1 including compensating means for said auxiliary fuel flow control responsive to compressor delivery pressure.

3. A fuel system as claimed in claim 2 wherein said compensating means is also responsive to engine speed.

4. A fuel system as claimed in claim 1 wherein said control means for said auxiliary fuel flow control includes a proportional device arranged to supply fuel flow in accordance with the air flow rate selected for the stabilising nozzles.

5. A fuel system as claimed in claim 1 wherein the acceleration fuel flow control comprises a main variable throttle through which fuel flows to the engine, first adjustment means for the main throttle controlled by at least one engine air pressure, a by-pass valve connected to by-pass fuel from upstream of the thorttle, and pressure drop means responsive to pressure drop at the throttle to adjust the by-pass valve so that the remaining fuel flow passing through the throttle to the engine gives a predetermined pressure drop at the throttle.

6. A fuel system as claimed in claim 5 wherein the said pressure drop means includes engine driven flyweights arranged to apply a force proportional to the square of engine speed to the pressure drop means to ensure that fuel flow to the engine through the main throttle generates a pressure drop proportional to the square of engine speed.

7. A fuel system as claimed in claim 6 wherein the auxiliary fuel flow control comprises an auxiliary variable throttle connected in parallel with the said main variable throttle, and auxiliary adjustment means for the auxiliary throttle responsive to the air flow rate within the duct means to adjust the auxiliary throttle so that the extra fuel flow to the engine permitted by the auxiliary throttle is in accordance with the air flow rate within the duct means.

8. A fuel system as claimed in claim 7 wherein the said means responsive to air flow within the duct means comprises a pair of opposed bellows, one connected to receive engine compressor delivery pressure and the other connected to receive pressure from the duct means whereby the bellows generates a force proportional to pressure drop between the engine compressor and the duct means, and servo means for adjusting the auxiliary throttle in accordance with said force.

9. A fuel system as claimed in claim 7 including an engine-driven flyweight device driven at a speed proportional to engine speed, manually-adjustable spring means acting on the flyweight device to oppose centrifugal movement, manually-operable means for adjusting the load of the spring means, second adjustment means for the main throttle responsive to centrifugal movement of the flyweight device, discriminator means responsive to the first and the second adjustment means to connect the adjustment to adjust the main throttle which will result in the lower fuel flow to the engine.

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Fuel systems for aircraft gas turbine engines

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