公开(公告)号：US20180328228A1

公开(公告)日：2018-11-15

申请号：US15919832

申请日：2018-03-13

Applicant: United Technologies Corporation

Inventor： Joseph F. Englehart ,  Craig R. McGarrah

IPC: F01D25/28 ,  F01D9/04

CPC classification number: F01D9/042 ,  F01D11/005 ,  F05D2240/12 ,  F05D2240/55 ,  F05D2260/30

Abstract: A vane assembly includes an outer platform, an inner platform, and a vane. The inner platform has an inner flange that includes a first face, a second face disposed opposite the first face, a third face extending from the first face towards the second face, and a fourth face extending from the third face towards a tip of the inner flange. The third face and the fourth face at least partially define a first notch.

公开(公告)号：US10753222B2

公开(公告)日：2020-08-25

申请号：US15700264

申请日：2017-09-11

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Joseph F. Englehart ,  Christopher Carter Venable ,  Michael G. McCaffrey

IPC: F01D11/14 ,  F01D25/24 ,  F16J15/08 ,  F01D11/08 ,  F16J15/16 ,  F01D11/12

Abstract: A gas turbine engine sealing system includes a case including forward and aft hooks. The aft hook arranged radially outward of the forward hook. A blade outer air seal has a J-hook that receives the aft hook and includes an end received by the forward hook.

公开(公告)号：US20190078514A1

公开(公告)日：2019-03-14

申请号：US15700328

申请日：2017-09-11

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Joseph F. Englehart ,  Graham Ryan Philbrick ,  Henry K. Webster ,  Richard Seleski ,  ChaiDee Woods Brown ,  Michael G. McCaffrey

IPC: F02C7/05 ,  F01D11/24 ,  F02C7/18 ,  B64D33/02

Abstract: A turbine section for a gas turbine engine includes blade outer air seals and stator vanes that provide a core flow path. A turbine case supports blade outer air seals and stator vanes. An annular cavity is provided between an interior surface of the turbine case and the blade outer air seals and the stator vanes. A hole extends through the turbine case from an exterior surface to the interior surface. The annular cavity extends axially to an exit. A manifold circumscribes the exterior surface of the turbine case and provides an annular space therebetween. The annular space is in fluid communication with the exit of the annular cavity via the hole.

公开(公告)号：US20190024525A1

公开(公告)日：2019-01-24

申请号：US15841792

申请日：2017-12-14

Applicant: United Technologies Corporation

Inventor： Daniel Barak ,  Joseph F. Englehart

IPC: F01D11/08

Abstract: A disclosed gas turbine engine includes a shroud block including a mounting slot, a blade outer air seal supported within the mounting slot and a seal disposed within the mounting slot providing a seal between the blade outer air seal and the mounting slot. An anti-rotation tab is attached to the shroud block within the mounting slot for constraining movement of the seal within the mounting slot.