发明名称 Thermally actuated venting system for a compartment of an aircraft gas turbine engine
摘要 <p>A thermally actuated venting system (12) includes a thermally actuated vent (46) for opening a vent outlet (48) in a gas turbine engine (10) associated compartment (11) with a passive thermal actuator (54) located in the compartment (11) based on a temperature of the compartment (11). Outlet (48) may be located at or near a top (50) of a core engine compartment (13), a fan compartment (11), or a pylon compartment (21). Actuator (54) may be operably connected to a hinged door (52) of vent (46) for opening outlet (48). Actuator (54) may be actuated by a phase change material (110) disposed in a chamber (94) and having a liquid state below a predetermined actuation temperature and a gaseous state above the predetermined actuation temperature. Actuator (54) may include a thermal fuse (120) for closing door (52) during a fire. Thermal fuse (120) may include at least a portion of piston rod (98) or a cylinder wall (116) of actuator (54) being made of a fuse material having a melting point substantially above the predetermined actuation temperature.</p>
申请公布号 EP2333288(A2) 申请公布日期 2011.06.15
申请号 EP20100191341 申请日期 2010.11.16
申请人 GENERAL ELECTRIC COMPANY 发明人 DIAZ, CARLOS ENRIQUE;LABORIE, DANIEL JEAN-LOUIS;GEARY, STEPHEN DENNIS
分类号 F02K1/38;B64D29/00;F01D25/14;F02K1/82 主分类号 F02K1/38
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