Dual valve apparatus for aircraft engine ice protection and related methods
First Claim
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1. A thermal anti-ice system in an aircraft comprising:
- a controlled valve configured to receive air from a compressor bleed port of an engine of the aircraft;
a self-regulating valve fluidly connected between the controlled valve and an inlet of the engine;
a first pressure sensor configured to sense pressure between the valves; and
a second pressure sensor configured to sense pressure between the self-regulating valve and the inlet.
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Abstract
A thermal anti-ice system in an aircraft. A controlled valve receives air from a compressor bleed port of an engine of the aircraft. A self-regulating valve is fluidly connected between the controlled valve and an inlet of the engine. A first pressure sensor senses pressure between the valves. A second pressure sensor senses pressure between the self-regulating valve and the inlet. The system can be used to de-ice aircraft inlet lip skins made of composite materials that have comparatively lower design temperatures than other comparable materials.
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Citations
28 Claims
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1. A thermal anti-ice system in an aircraft comprising:
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a controlled valve configured to receive air from a compressor bleed port of an engine of the aircraft; a self-regulating valve fluidly connected between the controlled valve and an inlet of the engine; a first pressure sensor configured to sense pressure between the valves; and a second pressure sensor configured to sense pressure between the self-regulating valve and the inlet. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A thermal anti-ice system in an aircraft comprising:
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a controlled valve configured to receive air from a compressor bleed port of an engine of the aircraft; a self-regulating valve in series with the controlled valve and through which air travels from the controlled valve to an inlet of the engine; a first pressure sensor configured to sense pressure between the valves; and a second pressure sensor configured to sense pressure between the self-regulating valve and the inlet; the pressure sensors configured to provide values for evaluating performance of the valves. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17, 18, 19, 20)
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21. A control-module-performed method of providing thermal anti-icing in an aircraft, the method comprising:
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controlling a valve that receives air from a compressor bleed port of an engine of the aircraft and is fluidly connected with an inlet of the engine through a self-regulating valve; receiving a first input representing pressure in a fluid connection between the controlled valve and the self-regulating valve; receiving a second input representing pressure in a fluid connection between the self-regulating valve and the inlet; the controlling performed based on the first and second inputs. - View Dependent Claims (22, 23, 24, 25, 26, 27, 28)
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Specification