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1. 发明申请

WO2015105594A2 ULTRA HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE 审中-公开
标题翻译：超高压总成比例气体涡轮发动机
公开(公告)号：WO2015105594A2
公开(公告)日：2015-07-16
申请号：PCT/US2014/067529
申请日：2014-11-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SCHWARZ, Frederick M. , STAUBACH, Joseph Brent
IPC分类号： F02C3/04 , F02C3/06
CPC分类号： F02C3/107 , F02C7/36 , F02K3/06 , F05D2260/40311 , Y02T50/671
摘要： A gas turbine engine comprises a first turbine positioned upstream of a second intermediate turbine and a third turbine positioned downstream of the first and second turbines. A fan and three compressors, with an upstream one of the compressors connected to rotate with the fan rotor, and the third turbine driving the upstream compressor and the fan both through a gear reduction. A second intermediate compressor is driven by the second intermediate turbine rotor, and a third compressor downstream of the first and second compressors is driven by the first turbine rotor.
摘要翻译：燃气涡轮发动机包括位于第二中间涡轮机的上游的第一涡轮机和位于第一和第二涡轮机下游的第三涡轮机。一个风扇和三个压缩机，其上游的一个压缩机连接成与风扇转子一起旋转，第三个涡轮通过齿轮减速器驱动上游压缩机和风扇。第二中间压缩机由第二中间涡轮转子驱动，第一和第二压缩机下游的第三压缩机由第一涡轮转子驱动。

2. 发明申请

WO2018089458A1 INTERCOOLED COOLED COOLING INTEGRATED AIR CYCLE MACHINE 审中-公开
标题翻译：中冷式冷却集成式空气循环机
公开(公告)号：WO2018089458A1
公开(公告)日：2018-05-17
申请号：PCT/US2017/060587
申请日：2017-11-08
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SNAPE, Nathan , STAUBACH, Joseph Brent , SCHWARZ, Frederick M.
IPC分类号： F02C7/18 , F02C9/18
摘要： A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A is valve downstream of the first cooling stage, the valve selectively delivering air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the air from the bleed port, and the valve also selectively supplying air from the first cooling stage to a use on an aircraft associated with the gas turbine engine. A method is also disclosed.
摘要翻译：第一冷却阶段流体联接到压缩机的排放端口以接收并冷却排放的空气与空气流以产生冷的排出空气。冷却泵接收并增加冷排气的压力以产生加压的冷排气。第二冷却阶段流体联接到泵以接收和冷却加压的冷排气以产生中冷的冷却空气。 A是第一冷却阶段下游的阀，该阀选择性地将空气输送到混合室中，在混合室中与来自被压缩到比来自排放端口的空气更高的压力的抽头的空气混合，并且该阀还选择性地供应空气从第一冷却阶段到在与燃气涡轮发动机相关联的飞机上的使用。还公开了一种方法。

3. 发明申请

WO2015112231A2 GEARED TURBOFAN WITH THREE TURBINE SECTIONS 审中-公开
标题翻译：带有三个涡轮分段的齿轮涡轮增压器
公开(公告)号：WO2015112231A2
公开(公告)日：2015-07-30
申请号：PCT/US2014/064490
申请日：2014-11-07
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SCHWARZ, Frederick M. , STAUBACH, Joseph Brent
IPC分类号： F02C3/073 , F02K3/06
CPC分类号： F02K3/06 , F02C7/36 , F05D2260/40311
摘要： A gas turbine engine comprises a fan rotor configured to be driven by a fan drive turbine through a first shaft and a gear reduction. The fan rotor is configured to deliver air into a bypass duct as bypass air and to deliver core air flow into a core engine where it reaches an upstream compressor rotor. The upstream compressor rotor is configured to be driven through a second shaft by an intermediate turbine rotor. A downstream compressor rotor is configured to be driven by an upstream turbine rotor through a third shaft. An overall pressure ratio across the upstream and downstream compressor rotors is greater than or equal to about 35.0 and less than or equal to about 75.0.
摘要翻译：燃气涡轮发动机包括风扇转子，该风扇转子构造成通过第一轴和齿轮减速器由风扇驱动涡轮驱动。风扇转子被配置为将空气作为旁路空气输送到旁路管道中并且将核心空气流输送到核心发动机中，在那里它到达上游压缩机转子。上游压缩机转子构造成由中间涡轮机转子驱动通过第二轴。下游压缩机转子构造成通过第三轴由上游涡轮机转子驱动。跨越上游和下游压缩机转子的整体压力比大于或等于约35.0且小于或等于约75.0。

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