-
公开(公告)号：US20180209343A1
公开(公告)日：2018-07-26
申请号：US15410971
申请日：2017-01-20
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , William K. Ackermann , Brian Merry , Neil Terwilliger
CPC classification number: F02C7/185 , F02C3/04 , F02K3/06 , F05D2260/213 , Y02T50/676
Abstract: An intercooled cooling system for a gas turbine engine includes a heat exchanger in fluid communication with a cooling airflow source directed through the heat exchanger and an auxiliary compressor fluidly coupled to the heat exchanger via a discharge duct to compress the cooling airflow exiting the heat exchanger. A compressor discharge pathway directs a first portion of the cooling airflow from the auxiliary compressor to a first cooling location of the gas turbine engine, and a bypass pathway is fluidly coupled to the discharge duct between the heat exchanger and the auxiliary compressor to direct a second portion of the cooling airflow to a second cooling location of the gas turbine without passing through the auxiliary compressor.
-
公开(公告)号：US20180149036A1
公开(公告)日：2018-05-31
申请号：US15881240
申请日：2018-01-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.
-
33.发明授权公开(公告)号：US09835052B2
公开(公告)日：2017-12-05
申请号：US15478671
申请日：2017-04-04
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
IPC: F02C7/36 , F01D25/16 , F04D29/32 , F04D25/04 , F04D19/02 , F01D5/06 , F01D9/04 , F02C3/107 , F01D15/12 , F02C3/04 , F02K3/06
CPC classification number: F01D25/164 , F01D5/06 , F01D9/041 , F01D15/12 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/028 , F04D25/045 , F04D29/056 , F04D29/325 , F04D29/668 , F05D2220/32 , F05D2240/60 , F05D2260/40311
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, and a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
-
34.发明申请公开(公告)号：US20170298767A1
公开(公告)日：2017-10-19
申请号：US15478706
申请日：2017-04-04
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
IPC: F01D25/16 , F01D9/04 , F04D19/02 , F01D5/06 , F04D29/32 , F04D27/00 , F04D25/04 , F04D25/02 , F02C3/04 , F02K3/06
CPC classification number: F01D25/164 , F01D5/06 , F01D9/041 , F01D15/12 , F01D25/162 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/028 , F04D25/045 , F04D27/009 , F04D29/056 , F04D29/325 , F04D29/668 , F05D2220/32 , F05D2240/60 , F05D2260/40311
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
-
公开(公告)号：US20170276010A1
公开(公告)日：2017-09-28
申请号：US15606522
申请日：2017-05-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades supported by a fan shaft support defining a fan shaft support lateral and transverse stiffness. A gear system connected to the fan shaft including a ring gear defining a ring gear lateral and transverse stiffness, a gear mesh defining a gear mesh lateral and transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral and transverse stiffness is less than 12% of a respective one of the gear mesh lateral and transverse stiffness. A flexible support supports the gear system and defines a flexible support lateral and transverse stiffness. At least one of the flexible support lateral and transverse stiffness is less than 11% of a respective one of the fan shaft support lateral and transverse stiffness.
-
Patent Agency Ranking
36.发明申请公开(公告)号：US20170234159A1
公开(公告)日：2017-08-17
申请号：US15478671
申请日：2017-04-04
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
CPC classification number: F01D25/164 , F01D5/06 , F01D9/041 , F01D15/12 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/028 , F04D25/045 , F04D29/056 , F04D29/325 , F04D29/668 , F05D2220/32 , F05D2240/60 , F05D2260/40311
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, and a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
-
公开(公告)号：US20170167384A1
公开(公告)日：2017-06-15
申请号：US14967518
申请日：2015-12-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler , William K. Ackermann , Matthew R. Feulner , Om P. Sharma
CPC classification number: F02C7/18 , F01D5/08 , F02C3/04 , F02C7/143 , F02C7/185 , F02C9/18 , F02K3/06 , F04D27/0215 , F04D29/582 , F05D2220/32 , F05D2220/3219 , F05D2240/24 , F05D2260/205 , F05D2260/211 , F05D2260/213 , Y02T50/676
Abstract: A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
-
38.发明申请HIGH PRESSURE COMPRESSOR ROTOR THERMAL CONDITIONING USING OUTER DIAMETER GAS EXTRACTION 审中-公开高压压缩机使用外径气体提取的转子热调节公开(公告)号：US20160123176A1
公开(公告)日：2016-05-05
申请号：US14877965
申请日：2015-10-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William K. Ackermann , Matthew P. Forcier , Paul J. Hiester
Abstract: A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A radially outer housing surrounds an outer diameter of the blades. A lower pressure tap and a higher pressure tap tap air from two distinct locations within the compressor and radially outwardly through the outer housing. A valve selectively delivers at least one of the lower pressure tap and the higher pressure tap to the bore of the disc. A control for the valve is programmed to move the valve to a position delivering the higher pressure tap at a point prior to take-off when the compressor is mounted in a gas turbine engine on an aircraft. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.
Abstract translation: 用于燃气涡轮发动机的压缩机包括具有叶片和盘的压缩机转子，其具有径向地位于盘的内侧的孔。 径向外壳围绕叶片的外径。 来自压缩机内的两个不同位置的较低压力抽头和较高压力的抽头抽风，并通过外壳径向向外。 选择性地将低压抽头和较高压力抽头中的至少一个输送到盘的孔。 编程该阀门的控制，以便当压缩机安装在飞机上的燃气涡轮发动机中时，将阀移动到在起飞前的某一点处传送高压龙头的位置。 还公开了一种燃气涡轮发动机和操作燃气涡轮发动机的方法。
-
39.发明申请METHOD AND APPARATUS FOR HANDLING PRE-DIFFUSER AIRFLOW FOR USE IN ADJUSTING A TEMPERATURE PROFILE 审中-公开用于处理预扩散器气流的方法和装置用于调节温度剖面公开(公告)号：US20160010554A1
公开(公告)日：2016-01-14
申请号：US14771055
申请日：2014-02-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , William K. Ackermann
Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold in communication with said mid-span pre-diffuser inlet and said combustor section.
Abstract translation: 提供了一种燃气涡轮发动机，其包括压缩机部分，燃烧器部分，扩散器壳体模块和歧管。 扩散器壳模块包括在从所述压缩机部分到所述燃烧器部分的环形流动路径内的多个支柱，其中所述多个支柱中的至少一个限定了与所述环形流动路径连通的中跨预扩散器入口。 与所述中跨预扩散器入口和所述燃烧器部分连通的歧管。
-
公开(公告)号：US20160003163A1
公开(公告)日：2016-01-07
申请号：US14751274
申请日：2015-06-26
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , William K. Ackermann
IPC: F02C7/36
CPC classification number: F02C7/36 , F01D5/142 , F01D5/225 , F05D2220/327 , F05D2260/40311 , Y02T50/671 , Y02T50/673
Abstract: A turbine section for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan drive turbine including a fan drive duct, the fan drive turbine being configured to drive a fan section through a geared architecture at a speed that is less than an input speed to the geared architecture. A fan drive turbine includes a fan drive duct, the fan drive turbine being configured to drive a fan section through a geared architecture at a speed that is less than an input speed to the geared architecture. At least one upstream turbine is configured to drive at least one compressor. The at least one upstream turbine includes a turbine duct defining a conical flow path having a conical inlet defined by a first diameter and a conical outlet defined by a second diameter greater than the first diameter. The conical outlet is in fluid communication with the fan drive duct downstream of the conical outlet. At least one row of shrouded rotor blades defines at least a portion of the conical flow path. A method of designing a gas turbine engine is also disclosed.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的涡轮机部分包括除了别的以外的包括风扇驱动管道的风扇驱动涡轮机，所述风扇驱动涡轮机构造成通过齿轮架构驱动风扇部分， 速度小于齿轮架构的输入速度。 风扇驱动涡轮机包括风扇驱动管道，所述风扇驱动涡轮机构造成以低于所述齿轮架构的输入速度的速度通过齿轮架构驱动风扇部分。 至少一个上游涡轮被配置成驱动至少一个压缩机。 所述至少一个上游涡轮机包括限定具有由第一直径限定的锥形入口和由大于第一直径的第二直径限定的锥形出口的锥形流动路径的涡轮机管道。 锥形出口与锥形出口下游的风扇驱动管道流体连通。 至少一排被覆盖的转子叶片限定了锥形流动路径的至少一部分。 还公开了一种设计燃气涡轮发动机的方法。
-
-
-
-
-
-
-
-
-
Search Results
124
records
(took 0.026 seconds)
