-
公开(公告)号：US20180045120A1
公开(公告)日：2018-02-15
申请号：US15791825
申请日：2017-10-24
Applicant: United Technologies Corporation
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
-
公开(公告)号：US09816442B2
公开(公告)日：2017-11-14
申请号：US14573003
申请日：2014-12-17
Applicant: United Technologies Corporation
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
-
公开(公告)号：US09816436B2
公开(公告)日：2017-11-14
申请号：US14283610
申请日：2014-05-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jorn A. Glahn , William K. Ackermann , Clifton J. Crawley , Philip S. Stripinis
CPC classification number: F02C6/08 , F01D25/18 , F01D25/183 , F02C7/12 , F02C7/14 , F05D2260/601 , Y02T50/675
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft, a first bearing structure and a second bearing structure that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air.
-
公开(公告)号：US20170284305A1
公开(公告)日：2017-10-05
申请号：US15089806
申请日：2016-04-04
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , William K. Ackermann , Harold W. Hipsky
Abstract: An environmental control system for an aircraft includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with an aircraft engine, and a lower pressure tap to be associated with a lower pressure location in the main compressor section associated with the aircraft engine. The lower pressure location being at a lower pressure than said higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A turbine outlet receives airflow exhausted from the turbine section. A compressor outlet receives airflow exhausted from the compressor section. A combined outlet receives airflow from the turbine outlet and the compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft. A buffer air outlet communicates airflow to an engine buffer air system. The buffer air outlet receives airflow supplied to the turbocompressor. A gas turbine engine is also disclosed.
-
公开(公告)号：US20170226935A1
公开(公告)日：2017-08-10
申请号：US15485312
申请日：2017-04-12
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 defined 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 between 0.5 and 1.5.
-
Patent Agency Ranking
86.发明申请NON-CONTACT SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT WITH LINKAGE BETWEEN ADJACENT ROTORS 审中-公开非接触式密封组件用于旋转设备与相邻转子之间的连接公开(公告)号：US20170009596A1
公开(公告)日：2017-01-12
申请号：US14794516
申请日：2015-07-08
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , William K. Ackermann
Abstract: An assembly is provided for rotational equipment such as a gas turbine engine for an aircraft propulsion system. This assembly includes a stator, a rotor and a seal assembly. The rotor extends axially along a centerline. The rotor includes a linkage, a first rotor disk, and a second rotor disk. The linkage extends axially from the first rotor disk to the second rotor disk. The linkage is removably attached to the second rotor disk. The seal assembly is configured for sealing a gap radially between the stator and the linkage. The seal assembly includes a hydrostatic non-contact seal.
Abstract translation: 为旋转设备提供组件，例如用于飞行器推进系统的燃气涡轮发动机。 该组件包括定子，转子和密封组件。 转子沿中心线轴向延伸。 转子包括联动装置，第一转子盘和第二转子盘。 连杆从第一转子盘轴向延伸到第二转子盘。 连杆可拆卸地连接到第二转子盘。 密封组件被构造用于在定子和连接件之间径向密封间隙。 密封组件包括静压非接触式密封。
-
公开(公告)号：US20160376904A1
公开(公告)日：2016-12-29
申请号：US14754161
申请日：2015-06-29
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , William K. Ackermann
CPC classification number: F01D11/02 , F01D11/001 , F01D11/025 , F05D2220/323 , F05D2240/55 , F05D2240/56 , F05D2260/36 , F16J15/44 , F16J15/442
Abstract: An assembly is provided for rotational equipment. The assembly includes a circumferentially segmented stator and a rotor radially within the stator. The assembly also includes a seal assembly configured for substantially sealing a gap radially between the stator and the rotor. The seal assembly includes a carrier and a non-contact seal seated with the carrier. The carrier includes a plurality of discrete carrier segments circumferentially arranged around the non-contact seal.
Abstract translation: 为旋转设备提供组件。 组件包括周向分段的定子和径向在定子内的转子。 组件还包括密封组件，其被配置为基本上密封定子和转子之间径向的间隙。 密封组件包括载体和与载体一起安置的非接触式密封件。 载体包括围绕非接触式密封件周向布置的多个离散载体片段。
-
公开(公告)号：US20160230597A1
公开(公告)日：2016-08-11
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.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机的一部分尤其包括热隔离区域，以及第一转子盘和第二转子盘。 第一和第二转子盘中的每一个设置在热隔离区域内。
-
89.发明申请SYSTEM AND METHOD FOR CONTROLLING AN ENVIRONMENTAL CONDITION OF AN ENGINE ELECTRONIC COMPONENT 审中-公开用于控制发动机电子部件的环境条件的系统和方法公开(公告)号：US20160177781A1
公开(公告)日：2016-06-23
申请号：US14974808
申请日：2015-12-18
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Kurt J. Sobanski , Wesley K. Lord , William K. Ackermann
CPC classification number: F01D25/10 , F01D25/12 , F02C3/04 , F02C7/18 , F02C7/32 , F02K3/115 , F05D2260/202 , Y02T50/671 , Y02T50/675
Abstract: The present disclosure relates generally to a gas turbine engine that includes a fan configured to generate a fanstream and a fanstream duct configured to receive the fanstream flowing therethrough. An engine electronic component is positioned in flow communication with the fanstream. A heating element is positioned in the fanstream upstream from the engine electronic component and is operative to heat at least a portion of the fanstream in flow communication with the engine electronic component. The position of the engine electronic component passively thermally conditions the engine electronic component and the heating element actively thermally conditions the engine electronic component.
Abstract translation: 本公开一般涉及一种燃气涡轮发动机，其包括被配置为产生风扇流的风扇和被配置为接收流过其中的风扇流的风扇流管。 发动机电子部件被定位成与风扇流动地流动连通。 加热元件位于发动机电子部件上游的风扇流中，并且可操作地加热与发动机电子部件流动连通的风扇流的至少一部分。 发动机电子部件的位置被动地热调节发动机电子部件和加热元件，使发动机电子部件发热。
-
90.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：US20160115865A1
公开(公告)日：2016-04-28
申请号：US14927567
申请日：2015-10-30
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Daniel Bernard Kupratis , Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F02C3/107 , F01D25/162 , F02K3/06 , F05D2260/4031
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。
-
-
-
-
-
-
-
-
-
Search Results
124
records
(took 0.047 seconds)
