公开(公告)号：US10415419B2

公开(公告)日：2019-09-17

申请号：US15406324

申请日：2017-01-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Fanping Sun ,  Zaffir A. Chaudhry ,  Lee A. Hoffman ,  Hailing Wu ,  Seung Bum Kim ,  Michael G. McCaffrey ,  Joel H. Wagner

IPC: F01D11/22 ,  F01D11/18

Abstract: A system for modulating turbine blade tip clearance is provided. The system may comprise an actuation control system having at least one actuator configured to modulate turbine blade tip clearance between a turbine blade tip and a blade outer air seal (BOAS). Each actuator may be coupled to the BOAS. Each actuator may comprise a solid-state motion amplification device such as a flextensional actuator. The actuators may be configured to move the BOAS in a radial direction from a first position to a second position to control tip clearance.

公开(公告)号：US20190010823A1

公开(公告)日：2019-01-10

申请号：US15406324

申请日：2017-01-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Fanping Sun ,  Zaffir A. Chaudhry ,  Lee A. Hoffman ,  Hailing Wu ,  Seung Bum Kim ,  Michael G. McCaffrey ,  Joel H. Wagner

IPC: F01D11/22 ,  F01D11/18 ,  F03G7/06

CPC classification number: F01D11/22 ,  F01D11/18 ,  F05D2240/11 ,  F05D2300/505

Abstract: A system for modulating turbine blade tip clearance is provided. The system may comprise an actuation control system having at least one actuator configured to modulate turbine blade tip clearance between a turbine blade tip and a blade outer air seal (BOAS). Each actuator may be coupled to the BOAS. Each actuator may comprise a solid-state motion amplification device such as a flextensional actuator. The actuators may be configured to move the BOAS in a radial direction from a first position to a second position to control tip clearance.

公开(公告)号：US20180334909A1

公开(公告)日：2018-11-22

申请号：US16048466

申请日：2018-07-30

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky ,  Joel H. Wagner ,  Thomas N. Slavens

IPC: F01D5/18 ,  F23R3/00 ,  B22F3/105 ,  B23P15/26 ,  F01D5/14 ,  F02C7/18 ,  F01D25/24 ,  F01D25/12 ,  F01D25/08 ,  F01D11/08 ,  F01D9/02 ,  B33Y80/00 ,  B33Y70/00 ,  B33Y10/00

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure. A method for producing a component is also disclosed.

公开(公告)号：US10126175B2

公开(公告)日：2018-11-13

申请号：US14564774

申请日：2014-12-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Charles W. Haldeman ,  Andrew Consiglio ,  Mark F. Zelesky ,  Joel H. Wagner

IPC: G01J5/00 ,  G01K1/00 ,  F01D21/00 ,  F01D5/28 ,  F01D21/12

Abstract: A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade.

公开(公告)号：US20180306059A1

公开(公告)日：2018-10-25

申请号：US15495283

申请日：2017-04-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Ram Ranjan ,  James D. Hill ,  Glenn Levasseur ,  Joel H. Wagner

IPC: F01D25/14 ,  F01D5/06 ,  F01D25/12 ,  F01D25/24 ,  F28D15/02

CPC classification number: F01D25/14 ,  F05D2260/208 ,  F28D15/0266 ,  F28D15/0275 ,  F28D2021/0026

Abstract: A turbine casing may comprise a casing body a heat pipe disposed in the casing body. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be located forward the condensation section. The vaporization section may be located in a high pressure turbine region of the casing body. The condensation section may be located in a low pressure turbine region of the casing body.

公开(公告)号：US20170082027A1

公开(公告)日：2017-03-23

申请号：US14860167

申请日：2015-09-21

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky ,  Joel H. Wagner ,  Shayan Ahmadian

IPC: F02C7/18 ,  F01D5/08

Abstract: A tangential on-board injector (TOBI) for a gas turbine engine is provided. The TOBI includes a body having an entrance and an exit, the body having an outer curved wall and defining an air passageway between the entrance and the exit and a purge cavity configured on an exterior surface of the body with a purge cavity entry fluidly connecting the air passageway to the purge cavity. The purge cavity is configured such that particles in an airflow through the passageway will enter the purge cavity.

公开(公告)号：US20160305664A1

公开(公告)日：2016-10-20

申请号：US15195383

申请日：2016-06-28

Applicant: United Technologies Corporation

Inventor： Joel H. Wagner ,  Paul M. Lutjen

IPC: F23R3/16 ,  F23R3/00 ,  F23R3/50 ,  F23C3/00

CPC classification number: F23R3/16 ,  F23C3/00 ,  F23R3/002 ,  F23R3/50

Abstract: A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The inner wall and the outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions.

Abstract translation: 具有输入端和输出端的燃烧器衬套包括环形内壁和环形外壁。 内壁和外壁中的至少一个是三维轮廓。 内壁和外壁形成燃烧室，其轮廓在室内形成交替的膨胀和收缩区域，使得燃烧气体在周向和轴向上流动。

公开(公告)号：US20150367412A1

公开(公告)日：2015-12-24

申请号：US14744450

申请日：2015-06-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Joel H. Wagner ,  John R. Farris ,  John Joseph Marcin

IPC: B22D29/00 ,  B22C9/10

CPC classification number: B22C9/106 ,  B22D29/001 ,  B22D29/002

Abstract: A method of forming an engine component according to an exemplary aspect of the present disclosure includes, among other things, introducing molten metal into a cavity between a shell and a casting article in the shell. The casting article includes a ceramic portion and a plurality of fibers. The method further includes separately removing the ceramic portion and the fibers from an interior of the component.

Abstract translation: 根据本公开的示例性方面的形成发动机部件的方法包括：将熔融金属引入壳体和外壳中的铸件之间的空腔中。 铸造制品包括陶瓷部分和多根纤维。 该方法还包括从部件的内部分离地去除陶瓷部分和纤维。

公开(公告)号：US20150360338A1

公开(公告)日：2015-12-17

申请号：US14741056

申请日：2015-06-16

Applicant: United Technologies Corporation

Inventor： John P. Rizzo, JR. ,  Alan C. Barron ,  Joel H. Wagner

IPC: B24B19/14 ,  F01D5/14 ,  B24B49/16 ,  B24B49/14 ,  B24B19/26 ,  B24B49/12

CPC classification number: B24B19/14 ,  B24B17/00 ,  B24B19/009 ,  B24B19/26 ,  B24B27/0038 ,  B24B49/12 ,  B24B49/14 ,  B24B49/16 ,  B25J11/0065 ,  F01D5/005 ,  F01D5/141 ,  F05D2220/32 ,  F05D2230/14 ,  Y02T50/673

Abstract: An abrasive profiling tool that may be part of a robotic machining system for machining a trailing edge of an airfoil, includes a shank extending along a rotational axis, a bearing guide rotationally secured to a distal end of the shank for riding upon the airfoil; and an abrasive profiler projecting radially and rigidly outward from the shank for grinding at least the trailing edge as the shank rotates. The profiler may include a round-over portion for grinding the trailing edge and a chamfered blending portion for grinding adjacent surfaces of the airfoil to produce a smooth transition from the adjacent surfaces and to the trailing edge.

Abstract translation: 可以是用于加工翼型件的后缘的机器人加工系统的一部分的磨料轮廓工具包括沿着旋转轴线延伸的柄部，转动地固定到柄的远端以用于骑在翼型上的轴承导向件; 以及从柄部径向和刚性地向外突出的研磨轮廓仪，用于当柄旋转时至少研磨后缘。 轮廓仪可以包括用于研磨后缘的圆形部分和用于研磨翼型件的相邻表面的倒角混合部分，以产生从相邻表面到后缘的平滑过渡。