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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
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SCHWARZ, Frederick M. , STAUBACH, Joseph Brent
CPC classification number: F02C3/107 , F02C7/36 , F02K3/06 , F05D2260/40311 , Y02T50/671
Abstract: 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.
Abstract translation: 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。
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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
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SNAPE, Nathan , STAUBACH, Joseph Brent , SCHWARZ, Frederick M.
Abstract: 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.
Abstract translation: 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。
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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
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SCHWARZ, Frederick M. , STAUBACH, Joseph Brent
CPC classification number: F02K3/06 , F02C7/36 , F05D2260/40311
Abstract: 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.
Abstract translation: 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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公开(公告)号：EP3587765A1
公开(公告)日：2020-01-01
申请号：EP19173793.1
申请日：2019-05-10
Applicant: United Technologies Corporation
Inventor： SUCIU, Gabriel L. , CHANDLER, Jesse M. , STAUBACH, Joseph Brent , MERRY, Brian D. , LORD, Wesley K.
Abstract: A gas turbine engine (20; 120) includes a main compressor section (20). A tap (110) is fluidly connected downstream of the main compressor section (24). A heat exchanger (112; 122; 130) is fluidly connected downstream of the tap (110). An auxiliary compressor unit (114; 140; 312) is fluidly connected downstream of the heat exchanger (112; 122; 130). The auxiliary compressor unit (114; 140; 312) is configured to compress air cooled by the heat exchanger (112; 122; 130) with an overall auxiliary compressor unit pressure ratio between 1.1 and 6.0. An intercooling system for a gas turbine engine is also disclosed.
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公开(公告)号：EP3489488A1
公开(公告)日：2019-05-29
申请号：EP18208970.6
申请日：2018-11-28
Applicant: United Technologies Corporation
Inventor： STAUBACH, Joseph Brent , SNAPE, Nathan , SCHWARZ, Frederick M. , LENTS, Charles E. , IKEDA, Michael K.
Abstract: A lower pressure tap (46) is connected to a first heat exchanger (48) to be cooled by cooling air, and then to a selection valve (52). The selection valve (52) selectively delivers the lower pressure tap air to a boost compressor (44). The lower pressure tap air downstream of the boost compressor (44) is connected to cool the at least one turbine (32). The selection valve (52) also selectively delivers a portion of the lower pressure tap air across a first cooling turbine (78), and to a line (79) associated with an air delivery system for a cabin (80) on an associated aircraft. A portion of the air downstream of the first cooling turbine (78) is connected to a second cooling turbine (84), and air downstream of the second cooling turbine (84) is connected for use in a cold loop (88).
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Patent Agency Ranking
公开(公告)号：EP3483418A1
公开(公告)日：2019-05-15
申请号：EP18205264.7
申请日：2018-11-08
Applicant: United Technologies Corporation
Inventor： SNAPE, Nathan , STAUBACH, Joseph Brent , SCHWARZ, Frederick M.
Abstract: A first cooling stage (210) is fluidly coupled to a bleed port (145) of a compressor (24) to receive and cool bleed air with the air stream (275) to produce a cool bleed air. A cooling pump (105) receives and increases a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage (215) is fluidly coupled to the pump (105) to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A valve (196) is downstream of the first cooling stage (210), the valve selectively delivering air into a mixing chamber (180) where it is mixed with air from a tap (165) that is compressed to a higher pressure than the air from the bleed port (145), and the valve (196) also selectively supplying air from the first cooling stage (210) to a use (290) on an aircraft associated with the gas turbine engine (20).
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7.发明公开COOLING AIR INTERCOOLING WITH DUAL PASS HEAT EXCHANGER 审中-公开KÜHLLUFT-ZWISCHENKÜHLUNGMITDOPPELDURCHGANGSWÄRMETAUSCHER
公开(公告)号：EP3085923A1
公开(公告)日：2016-10-26
申请号：EP16166707.6
申请日：2016-04-22
Applicant: United Technologies Corporation
Inventor： SUCIU, Gabriel L. , CHANDLER, Jesse M. , STAUBACH, Joseph Brent , MERRY, Brian D. , LORD, Wesley K.
Abstract: A gas turbine engine (100) comprises a main compressor section having a downstream most end (82), and more upstream locations. A turbine section has a high pressure turbine (117). A tap (110) taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger (112) and then to a cooling compressor (114). The cooling compressor (114) compresses air downstream of the heat exchanger (112), and delivers air into the high pressure turbine (117). The heat exchanger (112) has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor (114). An intercooling system for a gas turbine engine (100) is also disclosed.
Abstract translation: 燃气涡轮发动机（100）包括具有下游最末端（82）的主压缩机部分和更多的上游位置。 涡轮部分具有高压涡轮机（117）。 抽头（110）从压缩机部分中的上游位置中的至少一个抽吸空气，将抽头的空气通过热交换器（112），然后传递到冷却压缩机（114）。 冷却压缩机（114）压缩热交换器（112）下游的空气，并将空气输送到高压涡轮机（117）中。 热交换器（112）具有至少两次通过，其中一个通过径向向外通过空气，并且第二通道将空气径向向内返回到压缩机（114）。 还公开了一种用于燃气涡轮发动机（100）的中间冷却系统。
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公开(公告)号：EP3085923B1
公开(公告)日：2020-05-27
申请号：EP16166707.6
申请日：2016-04-22
Applicant: United Technologies Corporation
Inventor： SUCIU, Gabriel L. , CHANDLER, Jesse M. , STAUBACH, Joseph Brent , MERRY, Brian D. , LORD, Wesley K.
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9.发明公开COOLING AIR INTERCOOLING WITH COOLING AIR TAPPED FROM PLURAL LOCATIONS 审中-公开KÜHLLUFT-ZWISCHENKÜHLUNG麻省理工学院KÜHLLUFTABGEZAPFUNGVON MEHREREN ORTEN
公开(公告)号：EP3085924A1
公开(公告)日：2016-10-26
申请号：EP16166724.1
申请日：2016-04-22
Applicant: United Technologies Corporation
Inventor： SUCIU, Gabriel L. , CHANDLER, Jesse M. , STAUBACH, Joseph Brent , MERRY, Brian D.
CPC classification number: F04D29/5826 , F01D25/12 , F02C3/13 , F02C6/08 , F02C7/143 , F02C7/185 , F02C9/18 , F04D29/5833 , F05D2220/3212 , F05D2220/3217 , F05D2220/3219 , F05D2260/211 , F05D2260/213 , F05D2260/606 , F05D2270/3062 , Y02T50/675
Abstract: A gas turbine engine (121) comprises a main compressor section having a high pressure compressor (141) with a downstream most end (140), and more upstream locations (126). A turbine section has a high pressure turbine (144). A first tap taps air from at least one of the more upstream locations (126) in the main compressor section, passes the tapped air through a heat exchanger (122) and then to a cooling compressor (124). The cooling compressor (124) compresses air downstream of the heat exchanger (122). A second tap taps air from a location closer to the downstream most end (140) than the location(s) (126) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine (144). An intercooling system for a gas turbine engine (121) is also disclosed.
Abstract translation: 燃气涡轮发动机（121）包括主压缩机部分，其具有具有下游最末端（140）的高压压缩机（141）和更多的上游位置（126）。 涡轮部分具有高压涡轮机（144）。 第一分接头从主压缩机部分中的更上游位置（126）中的至少一个上抽出空气，将抽头的空气通过热交换器（122），然后传递到冷却压缩机（124）。 冷却压缩机124将热交换器122的下游的空气压缩。 第二分接头从第一分接头的位置（126）更接近下游最末端（140）的位置敲击空气。 第一和第二抽头混合在一起并被输送到高压涡轮机（144）中。 还公开了一种用于燃气涡轮发动机（121）的中间冷却系统。
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公开(公告)号：EP3084173A2
公开(公告)日：2016-10-26
申请号：EP14880333.1
申请日：2014-11-07
Applicant: United Technologies Corporation
Inventor： SCHWARZ, Frederick M. , STAUBACH, Joseph Brent
CPC classification number: F02K3/06 , F02C7/36 , F05D2260/40311
Abstract: 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.
Abstract translation: 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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