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    • 2. 发明授权
    • Turbo recuperator device
    • 涡轮换热装置
    • US06978621B2
    • 2005-12-27
    • US10331342
    • 2002-12-31
    • Ronald Scott BunkerChellappa Balan
    • Ronald Scott BunkerChellappa Balan
    • F01D13/02F02C3/04F02C6/08F02C6/18F02C7/12F02C7/18
    • F02C6/08F01D13/02F02C3/04F02C6/18F02C7/12F02C7/18F05D2260/205
    • A device and method for recuperating a gas turbine engine comprises a compressor being configured to receive a coolant fluid stream, to compress the coolant fluid stream and to discharge the compressed coolant fluid stream to a turbine in fluid communication with the compressor. The compressed coolant fluid stream undergoing thermal exchange within the turbine, exit the turbine thereafter. A source of a working fluid stream is in fluid communication with the turbine. The working fluid stream is fluidly isolated from a portion of the coolant fluid stream and undergoing thermodynamic expansion through the turbine to extract energy therefrom. Where desired, the entire coolant fluid stream is fluidly isolated from the working fluid stream. At least a portion of the coolant fluid stream is channeled downstream of the turbine to supply a preheated process fluid stream to an adjacent system.
    • 一种用于回收燃气涡轮发动机的装置和方法,包括压缩机,其构造成接收冷却剂流体流,以压缩冷却剂流体流并将压缩的冷却剂流体流排放到与压缩机流体连通的涡轮机。 在涡轮机内进行热交换的压缩的冷却剂流体流随后离开涡轮机。 工作流体流的源与涡轮流体连通。 工作流体流与冷却剂流体流的一部分流体隔离,并通过涡轮进行热力学膨胀,以从其中提取能量。 如果需要,整个冷却剂流体流与工作流体流流体隔离。 冷却剂流体流的至少一部分被引导到涡轮机的下游,以向相邻的系统提供预热的过程流体流。
    • 8. 发明申请
    • Aircraft auxiliary gas turbine engine and method for operating
    • 飞机辅助燃气轮机及其操作方法
    • US20070175223A1
    • 2007-08-02
    • US11345950
    • 2006-02-02
    • Chellappa BalanKarl Sheldon
    • Chellappa BalanKarl Sheldon
    • F02C7/32
    • B64D41/00B64D2013/0611B64D2041/002F02C7/32F05D2220/50
    • A non-aircraft-propelling auxiliary gas turbine engine installable in an aircraft having a cabin adapted to be pressurized. The auxiliary gas turbine engine includes an auxiliary-gas-turbine-engine compressor having an inlet, wherein the inlet is adapted to receive pressurized air from the cabin. A method for operating a non-aircraft-propelling auxiliary gas turbine engine of an aircraft includes providing pressurized air from the cabin of the aircraft to an inlet of a compressor of the auxiliary gas turbine engine. The method includes providing compressed air from the compressor to a combustor of the auxiliary gas turbine engine and includes providing combustion gases from the combustor to a turbine of the auxiliary gas turbine engine, wherein the turbine is mechanically coupled to the compressor.
    • 可安装在具有适于加压的舱室的飞行器中的非飞机推进辅助燃气涡轮发动机。 辅助燃气涡轮发动机包括具有入口的辅助燃气涡轮发动机压缩机,其中入口适于从舱室接收加压空气。 用于操作飞行器的非飞机推进辅助燃气涡轮发动机的方法包括将来自飞机的舱室的加压空气提供给辅助燃气涡轮发动机的压缩机的入口。 该方法包括将压缩空气从压缩机提供给辅助燃气涡轮发动机的燃烧器,并且包括将来自燃烧器的燃烧气体提供给辅助燃气涡轮发动机的涡轮机,其中涡轮机械地联接到压缩机。