公开(公告)号：EP3030751A2

公开(公告)日：2016-06-15

申请号：EP14852521.5

申请日：2014-08-05

Applicant: United Technologies Corporation

Inventor： HOUGH, Matthew Andrew ,  BEATTIE, Jeffrey S. ,  PROPHETER-HINCKLEY, Tracy A. ,  QUACH, San

IPC: F01D5/18 ,  F01D5/08

CPC classification number: F01D25/12 ,  F01D5/12 ,  F01D5/187 ,  F01D9/041 ,  F01D11/006 ,  F01D11/08 ,  F04D29/324 ,  F04D29/38 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2230/30 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/2212 ,  F05D2300/13 ,  F05D2300/20 ,  Y02T50/676

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a component. The component includes a platform having a mateface on a circumferential side thereof. The platform including a core passageway configured to communicate fluid to the mateface.

公开(公告)号：EP3719261A1

公开(公告)日：2020-10-07

申请号：EP20166506.4

申请日：2020-03-27

Applicant: United Technologies Corporation

Inventor： MCCAFFREY, Michael G. ,  HOUGH, Matthew Andrew ,  RIVERO, Pedro

IPC: F01D9/04 ,  F01D9/06 ,  F01D25/24 ,  F01D25/26

Abstract: A hot fairing structure (102) for a pre-diffuser (100) includes a ring-strut-ring structure (118) that comprises a multiple of hollow struts (200), and a multiple of diffusion passage ducts (124) attached to the ring-strut-ring structure (118). A pre-diffuser (100) for a gas turbine engine (20) includes an exit guide vane ring (104) having a multiple of exit guide vanes (108) defined around an engine longitudinal axis (A), a ring-strut-ring structure (118) adjacent to the exit guide vane ring (104) to form a multiple of diffusion passages (120) defined around the engine longitudinal axis (A), an inlet to each of the multiple of diffusion passages (120) smaller than an exit from each of the multiple diffusion passages (120) through the ring-strut-ring structure (118), and a diffusion passage duct (124) attached to the ring-strut-ring structure (118) at the exit from each of the multiple diffusion passages (120).

公开(公告)号：EP3719260A1

公开(公告)日：2020-10-07

申请号：EP20166838.1

申请日：2020-03-30

Applicant: United Technologies Corporation

Inventor： MCCAFFREY, Michael G. ,  HOUGH, Matthew Andrew ,  RIVERO, Pedro

IPC: F01D9/02 ,  F01D9/04 ,  F01D11/00

Abstract: A hot fairing structure (102) for a pre-diffuser (100) includes a ring-strut-ring structure (118) that comprises a multiple of hollow struts (200) and a multiple of inlets to a respective diffusion passage (120), one of the multiple of inlets formed between each one of the multiple of hollow struts (200) located between two diffusion passages (120).

公开(公告)号：EP3047112B1

公开(公告)日：2018-11-14

申请号：EP14859577.0

申请日：2014-08-21

Applicant: United Technologies Corporation

Inventor： HOUGH, Matthew Andrew ,  CORCORAN, Christopher ,  BEATTIE, Jeffrey S.

IPC: F01D11/00 ,  F01D5/18 ,  F01D5/22 ,  F01D11/02

CPC classification number: F01D11/006 ,  F01D5/22 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/75 ,  F05D2260/22141

Abstract: A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.

公开(公告)号：EP3047105A2

公开(公告)日：2016-07-27

申请号：EP14853976.0

申请日：2014-08-28

Applicant: United Technologies Corporation

Inventor： HOUGH, Matthew Andrew ,  BEATTIE, Jeffrey S.

IPC: F01D5/18 ,  F01D25/12 ,  F02C7/18

CPC classification number: F01D5/187 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212

Abstract: A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform and a first cooling hole that extends between a mate face of the platform and the second cooling core.

公开(公告)号：EP2971556A1

公开(公告)日：2016-01-20

申请号：EP14779530.6

申请日：2014-03-07

Applicant: United Technologies Corporation

Inventor： RAPP, Brandon M. ,  HOUGH, Matthew Andrew

IPC: F01D5/26 ,  F01D5/12 ,  F02C7/00

CPC classification number: F01D5/26 ,  F01D5/02 ,  F01D5/12 ,  F01D5/22 ,  F01D5/3007 ,  F01D5/326 ,  F01D11/006 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2250/71 ,  F05D2250/73 ,  F05D2260/96

Abstract: A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge.

Abstract translation: 用于燃气涡轮发动机转子组件的阻尼密封件具有带前缘，后缘，压力侧和吸力侧的轴向伸长的主体。 细长体包括在前缘处在压力侧上形成的第一扩大部分和在靠近后缘的吸力侧上形成的第二扩大部分。