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THERMAL MANAGEMENT SYSTEM FOR DEICING AIRCRAFT WITH TEMPERATURE BASED FLOW RESTRICTOR
THERMAL MANAGEMENT SYSTEM FOR DEICING AIRCRAFT WITH TEMPERATURE BASED FLOW RESTRICTOR
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机译:基于温度的流量限制器的传导飞机热管理系统
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摘要
Assemblies are provided for an aircraft with a gas turbine engine (12). One assembly includes a body (18) such as an inlet nose lip (18) of a nacelle (14) for the gas turbine engine (12). This assembly also includes a thermal management system (16) that includes a duct (58), a regulator (60) and a flow restrictor (62). The thermal management system (16) is configured to direct a flow of bleed gas through the duct (58) from the gas turbine engine (12) to the body (18) for substantially preventing ice buildup on the body (18). The regulator (60) is configured to affect the flow of bleed gas downstream of the regulator (60). The flow restrictor (62) is configured to selectively restrict the flow of bleed gas through the duct (58) when a temperature of the flow of bleed gas is greater than a threshold temperature (Tthreshold).
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