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公开(公告)号：US20090288628A1
公开(公告)日：2009-11-26
申请号：US12154192
申请日：2008-05-21
IPC分类号： F02P7/00
CPC分类号： F16C19/52 , F16C17/24 , F16C2360/23 , H02K11/40
摘要： A thrust-producing engine includes an engine structure, a rotor that is electrically isolated from the engine structure, and an electrical conductor connected to the engine structure. The electrical conductor is in electrical contact with the engine structure and the rotor as the rotor rotates relative to the electrical conductor and the engine structure to reduce electrical arcing between the engine structure and the rotor.
摘要翻译： 推力发动机包括发动机结构，与发动机结构电隔离的转子和连接到发动机结构的电导体。 当转子相对于电导体和发动机结构旋转时，电导体与发动机结构和转子电接触，以减少发动机结构和转子之间的电弧。
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公开(公告)号：US09624870B2
公开(公告)日：2017-04-18
申请号：US13637619
申请日：2011-03-27
CPC分类号： F02K3/075 , F02C3/113 , F02C7/32 , F02C7/36 , F02K3/06 , F02K3/077 , F05D2260/40 , F05D2260/4023 , F05D2260/40311 , F16D21/06 , F16D47/04 , Y02T50/671
摘要： An adaptive fan system for a variable cycle turbofan engine having at least one turbine, includes a shaft structured to receive mechanical power from a turbine in the variable cycle turbofan engine and a first fan stage that is coupled directly to the shaft and is driven directly by the shaft. A transmission system is coupled to the shaft and a second fan stage is coupled to the shaft via the transmission system and is driven by the shaft via the transmission system. The transmission system is structured to selectively vary a speed between high and low speeds at which power is supplied from the shaft to the second fan stage relative to at least one of the shaft and the first fan stage, wherein the first fan stage and the second fan stage are configured to rotate in the same direction and at the same high speed to increase the mechanical power of the turbine.
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公开(公告)号：US20130199156A1
公开(公告)日：2013-08-08
申请号：US13637619
申请日：2011-03-27
CPC分类号： F02K3/075 , F02C3/113 , F02C7/32 , F02C7/36 , F02K3/06 , F02K3/077 , F05D2260/40 , F05D2260/4023 , F05D2260/40311 , F16D21/06 , F16D47/04 , Y02T50/671
摘要： One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique variable cycle gas turbine engine. Another embodiment is a unique adaptive fan system for a variable cycle turbofan engine having at least one turbine. Another embodiment is a unique method for operating a variable cycle gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and related systems.
摘要翻译： 本发明的一个实施例是独特的燃气轮机。 另一个实施例是独特的可变循环燃气涡轮发动机。 另一个实施例是用于具有至少一个涡轮机的可变循环涡轮风扇发动机的独特的自适应风扇系统。 另一个实施例是用于操作可变循环燃气涡轮发动机的独特方法。 其他实施例包括用于燃气涡轮发动机和相关系统的装置，系统，装置，硬件，方法和组合。
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公开(公告)号：US08596076B1
公开(公告)日：2013-12-03
申请号：US12649636
申请日：2009-12-30
IPC分类号： F02C3/13
CPC分类号： F02C3/13
摘要： The present invention provides a variable pressure ratio gas turbine. In an embodiment, the engine is configured to selectively bypass all or a portion of a high pressure compressor and a high pressure turbine. In an embodiment, during bypass operation, all or a portion of the flow that would otherwise pass through the high pressure compressor and the high pressure turbine may be routed through a respective compressor bypass duct and turbine bypass duct.
摘要翻译： 本发明提供一种可变压力比燃气轮机。 在一个实施例中，发动机构造成选择性地绕过高压压缩机和高压涡轮机的全部或一部分。 在一个实施例中，在旁路操作期间，否则将通过高压压缩机和高压涡轮机的流量的全部或一部分可以通过相应的压缩机旁通管道和涡轮机旁通管路。
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公开(公告)号：US08863529B2
公开(公告)日：2014-10-21
申请号：US12650878
申请日：2009-12-31
申请人： Matthew J. Starr
发明人： Matthew J. Starr
CPC分类号： F02C6/08 , F01D17/141 , F02C9/18 , F04D19/02 , F04D19/028 , F04D27/0223 , F04D27/023 , F05D2260/4023
摘要： A compressor of a gas turbine engine may have a bypass that routes a compressed air flow from within the compressor and directs the compressed air flow to a combustor. The bypass may have an inlet positioned just ahead of a downstream stage of the compressor and an outlet positioned to route the compressed air flow from the bypass to a diffuser or directly to a combustor. A valve may be used within the bypass and may be located near the inlet, near the outlet, or both. The valve may have the form of an annular sleeve in some embodiments and may be actuated with an actuator. The various arrangements allow for a compressor having a variable compression ratio.
摘要翻译： 燃气涡轮发动机的压缩机可以具有旁路，其将压缩空气流从压缩机内引导并将压缩空气流引导到燃烧器。 旁路可以具有位于压缩机的下游级的前方的入口和设置成将压缩空气流从旁路引导到扩散器或直接传送到燃烧器的出口。 可以在旁路内使用阀门，并且可以位于入口附近，靠近出口处或两者。 在一些实施例中，阀可以具有环形套筒的形式，并且可以由致动器致动。 各种布置允许具有可变压缩比的压缩机。
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公开(公告)号：US20100223903A1
公开(公告)日：2010-09-09
申请号：US12650878
申请日：2009-12-31
申请人： Matthew J. Starr
发明人： Matthew J. Starr
IPC分类号： F02K3/04
CPC分类号： F02C6/08 , F01D17/141 , F02C9/18 , F04D19/02 , F04D19/028 , F04D27/0223 , F04D27/023 , F05D2260/4023
摘要： A compressor of a gas turbine engine may have a bypass that routes a compressed air flow from within the compressor and directs the compressed air flow to a combustor. The bypass may have an inlet positioned just ahead of a downstream stage of the compressor and an outlet positioned to route the compressed air flow from the bypass to a diffuser or directly to a combustor. A valve may be used within the bypass and may be located near the inlet, near the outlet, or both. The valve may have the form of an annular sleeve in some embodiments and may be actuated with an actuator. The various arrangements allow for a compressor having a variable compression ratio.
摘要翻译： 燃气涡轮发动机的压缩机可以具有旁路，其将压缩空气流从压缩机内引导并将压缩空气流引导到燃烧器。 旁路可以具有位于压缩机的下游级的前方的入口和设置成将压缩空气流从旁路引导到扩散器或直接传送到燃烧器的出口。 可以在旁路内使用阀门，并且可以位于入口附近，靠近出口处或两者。 在一些实施例中，阀可以具有环形套筒的形式，并且可以由致动器致动。 各种布置允许具有可变压缩比的压缩机。
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