公开(公告)号：US10329934B2

公开(公告)日：2019-06-25

申请号：US14880403

申请日：2015-10-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Ken F Blaney ,  Anthony B Swift ,  Neil L Tatman ,  Paul M Lutjen ,  Christopher M Jarochym

IPC: F01D11/08 ,  F01D9/06 ,  B22C9/10 ,  F01D11/12 ,  F01D25/24

Abstract: A casting core for a Blade Outer Air Seal includes a heat exchange cavity core section in communication with a first plenum section and a second plenum section, the first plenum and the second plenum section are of a thickness greater than the heat exchange cavity section.

公开(公告)号：US20160010482A1

公开(公告)日：2016-01-14

申请号：US14766469

申请日：2014-02-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Mark J Rogers ,  Mark Broomer ,  Craig R McGarrah ,  Timothy M Davis ,  Anthony B Swift ,  Russell E Keene ,  Carson A. Roy Thill ,  Timothy A. Dunbar

IPC: F01D11/08

CPC classification number: F01D11/08 ,  F01D25/246 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/10 ,  F05D2240/20 ,  F05D2240/55 ,  F05D2250/14

Abstract: An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture.

Abstract translation: 燃气涡轮发动机内的界面包括多个分段部件，每个部件具有多个孔的段凸缘，多个孔中的至少一个孔是第一槽孔。 具有环形凸缘的整个环形部件，其限定多个孔环，所述多个环形孔中的至少一个具有第二狭槽孔，所述第二狭缝孔横向于所述第一狭缝孔。

公开(公告)号：US09879558B2

公开(公告)日：2018-01-30

申请号：US14766469

申请日：2014-02-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Mark J Rogers ,  Mark Broomer ,  Craig R. McGarrah ,  Timothy M Davis ,  Anthony B Swift ,  Russell E Keene ,  Carson A. Roy Thill ,  Timothy A. Dunbar

IPC: F01D11/08 ,  F01D25/24

CPC classification number: F01D11/08 ,  F01D25/246 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/10 ,  F05D2240/20 ,  F05D2240/55 ,  F05D2250/14

Abstract: An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture.

公开(公告)号：US20170211415A1

公开(公告)日：2017-07-27

申请号：US15005061

申请日：2016-01-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Anthony B Swift ,  Ken F. Blaney ,  Paul M. Lutjen ,  Neil L. Tatman ,  Dominic J. Mongillo

IPC: F01D25/12 ,  F01D9/04 ,  F01D5/14 ,  F02C7/12 ,  F01D11/08

Abstract: A gas turbine engine component has a body extending between two circumferential sides, and between a leading edge and a trailing edge. A refractory metal core within the body forms at least one cooling circuit to utilize fluid to cool the body. When the refractory metal core is removed from the body, the at least one cooling circuit includes an inlet, an outlet, and a passage that varies in cross-sectional area between the inlet and outlet. A method of manufacturing a gas turbine engine, a method of manufacturing a core, and a refractory metal core are also disclosed.