发明名称 Gas turbine engines including broadband damping systems and methods for producing the same
摘要 Gas turbine engine, broadband damping systems, and methods for producing broadband-damped gas turbine engine are provided. In one embodiment, the gas turbine engine includes an engine case, a rotor assembly mounted within the engine case for rotation about a rotational axis, and a broadband damping system disposed between the rotor assembly and the engine case. The broadband damping system includes a first set of three parameter axial dampers angularly spaced around the rotational axis, and a second set of three parameter axial dampers angularly spaced around the rotational axis and coupled in parallel with the first set of three parameter axial dampers. The first and second sets of three parameter axial dampers are tuned to provide peak damping at different rotational frequencies to increase the damping bandwidth of the broadband damping system during operation of the gas turbine engine.
申请公布号 US8992161(B2) 申请公布日期 2015.03.31
申请号 US201113219287 申请日期 2011.08.26
申请人 Honeywell International Inc. 发明人 Hindle Timothy;Hadden Steven;Davis Torey
分类号 F01D25/06;F01D25/04 主分类号 F01D25/06
代理机构 Ingrassia Fisher & Lorenz, P.C. 代理人 Ingrassia Fisher & Lorenz, P.C.
主权项 1. A gas turbine engine, comprising: an engine case; a rotor assembly mounted within the engine case for rotation about a rotational axis and having a first critical mode; and a broadband damping system disposed between the rotor assembly and the engine case, the broadband damping system comprising: a first set of three parameter axial dampers angularly spaced around the rotational axis; anda second set of three parameter axial dampers angularly spaced around the rotational axis and coupled in parallel with the first set of three parameter axial dampers, the first and second sets of three parameter axial dampers tuned to provide peak damping at different rotational frequencies to increase the damping bandwidth of the broadband damping system during operation of the gas turbine engine; wherein the first set of three parameter axial dampers is tuned to provide peak damping at a frequency less than the frequency at which the first critical mode occurs, and wherein the second set of three parameter axial dampers is tuned to provide peak damping at a frequency greater than the frequency at which the first critical mode occurs.
地址 Morristown NJ US