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公开(公告)号：US10669888B2
公开(公告)日：2020-06-02
申请号：US16107270
申请日：2018-08-21
Applicant: United Technologies Corporation
Inventor： William K. Ackermann , Clifton J. Crawley, Jr. , Frederick M. Schwarz
IPC: F01D25/12 , F01D5/08 , F01D5/30 , F01D11/00 , F16J15/44 , F01D5/02 , F01D9/04 , F01D11/04 , F01D11/08 , F02C3/14 , F02C7/18
Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a bladed rotor assembly, a stator vane assembly, a fixed stator structure and a seal assembly. The bladed rotor assembly includes a rotor disk structure. The stator vane assembly is disposed adjacent the bladed rotor assembly. The fixed stator structure is connected to and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.
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公开(公告)号：US10094241B2
公开(公告)日：2018-10-09
申请号：US14830514
申请日：2015-08-19
Applicant: United Technologies Corporation
Inventor： William K. Ackermann , Clifton J. Crawley, Jr. , Frederick M. Schwartz
IPC: F01D25/12 , F01D5/08 , F01D5/30 , F01D11/00 , F16J15/44 , F01D5/02 , F01D9/04 , F01D11/04 , F01D11/08 , F02C3/14 , F02C7/18
Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a bladed rotor assembly, a stator vane assembly, a fixed stator structure and a seal assembly. The bladed rotor assembly includes a rotor disk structure. The stator vane assembly is disposed adjacent the bladed rotor assembly. The fixed stator structure is connected to and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.
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公开(公告)号：US20160201563A1
公开(公告)日：2016-07-14
申请号：US14914178
申请日：2014-09-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ethan K. Stearns , Clifton J. Crawley, Jr.
CPC classification number: F23K5/04 , F02C7/14 , F02C7/224 , F23K2301/204 , F23R3/28 , Y02T50/675
Abstract: A system is provided for a turbine engine that includes a fuel injector and an actuator. The system includes a fuel management system configured to receive fuel from a flow path. The fuel management system is also configured to provide a first portion of the fuel received from the flow path to the fuel injector at a first temperature, and a second portion of the fuel received from the flow path to the actuator at a second temperature different than the first temperature.
Abstract translation: 一种用于包括燃料喷射器和致动器的涡轮发动机的系统。 该系统包括配置成从流动路径接收燃料的燃料管理系统。 燃料管理系统还被配置为在第一温度下将从流动路径接收的燃料的第一部分提供给燃料喷射器，并且将燃料的第二部分从不同于第二温度的第二温度从流动路径接收到致动器 第一个温度。
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公开(公告)号：US10047677B2
公开(公告)日：2018-08-14
申请号：US14755036
申请日：2015-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jorn A. Glahn , Clifton J. Crawley, Jr. , Philip S. Stripinis , William K. Ackermann
IPC: F02C9/18 , F02C7/18 , F02C6/08 , F01D11/04 , F01D25/16 , F02C7/06 , F02C7/12 , F02C7/28 , F01D25/00
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. A buffer system includes a first circuit that supplies a first buffer supply air and a second circuit that supplies a second buffer supply air. The first circuit includes a first bleed air supply and a second bleed air supply. The second circuit includes a third bleed air supply and a fourth bleed air supply and at least one of the first circuit and the second circuit includes a variable area ejector.
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公开(公告)号：US20170107838A1
公开(公告)日：2017-04-20
申请号：US14884513
申请日：2015-10-15
Applicant: United Technologies Corporation
Inventor： Clifton J. Crawley, Jr. , Frederick M. Schwarz
CPC classification number: F01D11/02 , F01D5/082 , F01D5/3015 , F01D9/065 , F01D11/001 , F02C3/04 , F05D2240/55 , F05D2240/81 , Y02T50/676
Abstract: Aspects of the disclosure are directed to a gas turbine engine, comprising a sealing assembly that includes a non-contacting HALO seal, a ring constructed as a full ring and configured as a carrier of the seal, a sealing land configured to rotate and interface to the seal. In some embodiments, the engine further comprises a vane, where the ring is coupled to the vane.
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Patent Agency Ranking
公开(公告)号：US10107126B2
公开(公告)日：2018-10-23
申请号：US14830437
申请日：2015-08-19
Applicant: United Technologies Corporation
Inventor： William K. Ackermann , Clifton J. Crawley, Jr. , Frederick M. Schwarz
Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a first bladed rotor assembly, a second bladed rotor assembly, a stator vane assembly, a stator structure and a seal assembly. The second bladed rotor assembly includes a rotor disk structure. The stator vane assembly is axially between the first and the second bladed rotor assemblies. The stator structure is mated with and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.
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公开(公告)号：US10060280B2
公开(公告)日：2018-08-28
申请号：US14884513
申请日：2015-10-15
Applicant: United Technologies Corporation
Inventor： Clifton J. Crawley, Jr. , Frederick M. Schwarz
CPC classification number: F01D11/02 , F01D5/082 , F01D5/3015 , F01D9/065 , F01D11/001 , F02C3/04 , F05D2240/55 , F05D2240/81 , Y02T50/676
Abstract: Aspects of the disclosure are directed to a gas turbine engine, comprising a sealing assembly that includes a non-contacting HALO seal, a ring constructed as a full ring and configured as a carrier of the seal, a sealing land configured to rotate and interface to the seal. In some embodiments, the engine further comprises a vane, where the ring is coupled to the vane.
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公开(公告)号：US09027353B2
公开(公告)日：2015-05-12
申请号：US14219070
申请日：2014-03-19
Applicant: United Technologies Corporation
Inventor： Jorn A. Glahn , Clifton J. Crawley, Jr. , Philip S. Stripinis , William K. Ackermann
IPC: F02C6/08 , F01D25/00 , F02C7/18 , F01D11/04 , F01D25/16 , F02C7/06 , F02C7/12 , F02C7/28 , F02C9/18
CPC classification number: F02C9/18 , F01D11/04 , F01D25/00 , F01D25/16 , F02C6/08 , F02C7/06 , F02C7/12 , F02C7/18 , F02C7/28 , F05D2260/601 , Y02T50/675 , Y10T29/49229
Abstract: A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure.
Abstract translation: 燃气涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器，与燃烧器流体连通的涡轮机部分，经由齿轮架构被涡轮部分驱动的风扇部分和缓冲系统， 将缓冲空气传送到燃气涡轮发动机的一部分。 缓冲系统包括第一回路，其被配置为选择性地混合具有第一压力的第一排放空气供应源和第二排气源，其具有大于第一压力的第二压力，以提供具有中间压力的第一缓冲器供应空气， 第一压力和第二压力。
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公开(公告)号：US10087782B2
公开(公告)日：2018-10-02
申请号：US14773876
申请日：2014-03-12
Applicant: United Technologies Corporation
Inventor： Cheng-Zhang Wang , Jorn A. Glahn , David F. Cloud , Peter M. Munsell , Clifton J. Crawley, Jr. , Robert Newman , Michelle Diana Stearns
Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.
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公开(公告)号：US09097138B2
公开(公告)日：2015-08-04
申请号：US14044282
申请日：2013-10-02
Applicant: United Technologies Corporation
Inventor： Jorn A. Glahn , Clifton J. Crawley, Jr. , Philip S. Stripinis , William K. Ackermann
IPC: F02C6/08 , F01D25/00 , F02C7/18 , F01D11/04 , F01D25/16 , F02C7/06 , F02C7/12 , F02C7/28 , F02C9/18
CPC classification number: F02C9/18 , F01D11/04 , F01D25/00 , F01D25/16 , F02C6/08 , F02C7/06 , F02C7/12 , F02C7/18 , F02C7/28 , F05D2260/601 , Y02T50/675 , Y10T29/49229
Abstract: A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a buffer system. The buffer system can include a first circuit that supplies a first buffer supply air and a second circuit that supplies a second buffer supply air. The first circuit can include a first bleed air supply a second bleed air supply and at least one of an ejector and a valve. The second circuit can include a third bleed air supply, a fourth bleed air supply and at least one of an ejector and a valve.
Abstract translation: 燃气涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器，与燃烧器流体连通的涡轮机部分和缓冲系统。 缓冲系统可以包括提供第一缓冲器供应空气的第一电路和供应第二缓冲器供应空气的第二电路。 第一回路可以包括第一排放空气源和第二排放空气源，以及喷射器和阀中的至少一个。 第二回路可以包括第三排气供应源，第四排放空气源以及喷射器和阀门中的至少一个。
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