THERMAL MANAGEMENT SYSTEM FOR DEICING AIRCRAFT WITH TEMPERATURE BASED FLOW RESTRICTOR
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United States of America
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Issued Date -
Sep 21, 2017
app pub date -
Mar 18, 2016
filing date -
Mar 18, 2016
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Abstract
Assemblies are provided for an aircraft with a gas turbine engine. One assembly includes a body such as an inlet nose lip of a nacelle for the gas turbine engine. This assembly also includes a thermal management system that includes a duct, a regulator and a flow restrictor. The thermal management system is configured to direct a flow of bleed gas through the duct from the gas turbine engine to the body for substantially preventing ice buildup on the body. The regulator is configured to affect the flow of bleed gas downstream of the regulator. The flow restrictor is configured to selectively restrict the flow of bleed gas through the duct when a temperature of the flow of bleed gas is greater than a threshold temperature.
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