-
公开(公告)号：US09920652B2
公开(公告)日：2018-03-20
申请号：US14617339
申请日：2015-02-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , William K. Ackermann , James D. Hill , Brian D. Merry
CPC classification number: F01D25/14 , F01D5/081 , F01D5/082 , F01D25/12 , F05D2220/3212 , F05D2240/24 , F05D2240/55 , F05D2260/20 , F05D2260/201 , F05D2260/213
Abstract: A section of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a thermally isolated area, and a first rotor disk and a second rotor disk. Each of the first and second rotor disks are provided within the thermally isolated area.
-
公开(公告)号：US20170306855A1
公开(公告)日：2017-10-26
申请号：US15440412
申请日：2017-02-23
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.
-
公开(公告)号：US20170218849A1
公开(公告)日：2017-08-03
申请号：US15484441
申请日：2017-04-11
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.
-
公开(公告)号：US20170159572A1
公开(公告)日：2017-06-08
申请号：US15437104
申请日：2017-02-20
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.
-
公开(公告)号：US20170051621A1
公开(公告)日：2017-02-23
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
CPC classification number: F01D11/02 , F01D5/082 , F01D5/087 , F01D5/3015 , F01D9/041 , F01D9/065 , F01D11/001 , F01D11/122 , F05D2220/36 , F05D2240/55 , F05D2250/41 , F05D2260/20 , F16J15/442 , Y02T50/671 , Y02T50/673 , Y02T50/676
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.
Abstract translation: 为旋转设备提供组件。 这些组件中的一个包括第一叶片转子组件，第二叶片转子组件，定子叶片组件，定子结构和密封组件。 第二叶片转子组件包括转子盘结构。 定子叶片组件轴向地位于第一和第二叶片转子组件之间。 定子结构与定子叶片组件中的径向配合。 密封组件被构造用于密封定子结构和转子盘结构之间的间隙，其中密封组件包括非接触式密封。
-
Patent Agency Ranking
16.发明申请GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES 审中-公开具有高速低压涡轮部分和轴承支持特性的气体涡轮发动机公开(公告)号：US20160053679A1
公开(公告)日：2016-02-25
申请号：US14932251
申请日：2015-11-04
Applicant: United Technologies Corporation
CPC classification number: F02C7/06 , F01D25/162 , F02C7/20 , F02K3/06
Abstract: A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a fan drive turbine section and a second turbine section. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. The second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is faster than the first speed.
Abstract translation: 根据本公开的示例的燃气涡轮发动机的涡轮部分包括风扇驱动涡轮部分和第二涡轮机部分。 风扇驱动涡轮部分在第一出口处具有第一出口区域，并且构造成以第一速度旋转。 第二涡轮部分在第二出口处具有第二出口区域，并且构造成以比第一速度快的第二速度旋转。
-
17.发明申请公开(公告)号：US20160053634A1
公开(公告)日：2016-02-25
申请号：US14930819
申请日：2015-11-03
Applicant: United Technologies Corporation
CPC classification number: F01D25/162 , F02C3/067 , F02C7/06 , F02C7/36 , F02K3/06 , F02K3/072 , F02K3/075 , F05D2260/40311
Abstract: A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a fan drive turbine section and a second turbine section. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. The second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is faster than the first speed.
-
18.发明申请公开(公告)号：US20140234079A1
公开(公告)日：2014-08-21
申请号：US14260557
申请日：2014-04-24
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 flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.
Abstract translation: 燃气涡轮发动机包括用于风扇驱动齿轮系统的柔性安装座。 一个非常高速的风扇驱动涡轮驱动风扇驱动齿轮系统。
-
公开(公告)号：US08747055B2
公开(公告)日：2014-06-10
申请号：US13974136
申请日：2013-08-23
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
IPC: F01D15/12
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 flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.
-
20.发明申请公开(公告)号：US20130336791A1
公开(公告)日：2013-12-19
申请号：US13974136
申请日：2013-08-23
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
IPC: F01D15/12
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 flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.
Abstract translation: 燃气涡轮发动机包括用于风扇驱动齿轮系统的柔性安装座。 一个非常高速的风扇驱动涡轮驱动风扇驱动齿轮系统。
-
-
-
-
-
-
-
-
-
Search Results
124
records
(took 0.032 seconds)
