公开(公告)号：US20210317748A1

公开(公告)日：2021-10-14

申请号：US16844625

申请日：2020-04-09

Applicant: United Technologies Corporation

Inventor： Jon E. Sobanski ,  Howard J. Liles

IPC: F01D11/00 ,  F01D9/02

Abstract: A gas turbine engine support system includes a vane arc segment, a vane support arc segment piece configured to engage the vane arc segment, and a seal disposed radially between the vane arc segment and the vane support arc segment piece. The seal includes first and second seal sections. The first seal section has a floor wall and first and second side walls that project from the floor wall. The first and second side walls converge to define a disjointed corner. The second seal section nests with the first seal section and seals the disjointed corner.

公开(公告)号：US20210148241A1

公开(公告)日：2021-05-20

申请号：US16689529

申请日：2019-11-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Howard J. Liles ,  Bryan P. Dube ,  Bryan H. Farrar

IPC: F01D9/04

Abstract: An airfoil assembly includes an airfoil. The airfoil has first and second platforms and an airfoil between the first and second platforms. A support ring is configured to retain the first platform. The support ring has a lip which extends radially inward from the support ring. The lip is configured to engage an axial face of the first platform. The lip has a primary retention feature and a secondary retention feature. The primary and secondary retention features are configured to retain the first face of the first platform with respect to the annular ring. A support structure for an airfoil and a method of retaining an airfoil assembly are also disclosed.

公开(公告)号：US20210071534A1

公开(公告)日：2021-03-11

申请号：US16562557

申请日：2019-09-06

Applicant: United Technologies Corporation

Inventor： Adam P. Generale ,  Howard J. Liles

IPC: F01D5/14

Abstract: A gas turbine engine airfoil includes an airfoil section that has an airfoil wall and a rib that are formed of a ceramic matrix composite. The airfoil wall circumscribes an internal cavity for receiving cooling air. The airfoil wall defines leading and trailing ends and first and second sides that join the leading and trailing ends. The rib connects the first and second sides. A metallic shield is disposed in the internal cavity and at least partially encloses the rib to shield the rib from the cooling air.

公开(公告)号：US20210001511A1

公开(公告)日：2021-01-07

申请号：US16503905

申请日：2019-07-05

Applicant: United Technologies Corporation

Inventor： Lei Jin ,  Zachary P. Konopaske ,  Ryan M. Brodeur ,  Howard J. Liles ,  Bryan H. Farrar ,  Andrew J. Lazur

IPC: B28B1/093 ,  B28B1/00 ,  B28B11/08 ,  C04B35/14

Abstract: A method of forming a ceramic matrix composite component with cooling channels includes embedding a plurality of wires into a preform structure, densifying the preform structure with embedded wires, and removing the plurality of wires to create a plurality of corresponding channels within the densified structure.

公开(公告)号：US10724387B2

公开(公告)日：2020-07-28

申请号：US16184701

申请日：2018-11-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Bryan H. Farrar ,  Howard J. Liles ,  Michael G McCaffrey ,  Andrew J. Lazur

IPC: F01D5/14 ,  F01D9/04 ,  F01D5/28 ,  B29C70/24 ,  B29L31/08

Abstract: A stator vane may comprise an airfoil extending between a first platform and a second platform, a first shear tube may extend through the airfoil and relatively orthogonal to the first platform and the second platform, wherein the first shear tube extends through the first platform and the second platform. In various embodiments, a second shear tube may extend through the airfoil into the first platform and the second platform parallel the first shear tube.

公开(公告)号：US11187096B2

公开(公告)日：2021-11-30

申请号：US16677262

申请日：2019-11-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Bryan H. Farrar ,  Howard J. Liles

IPC: F01D9/04 ,  F01D11/00 ,  F01D25/12

Abstract: A gas turbine engine includes a plurality of airfoil vanes situated in a circumferential row about an engine central axis. Each of the plurality of airfoil vanes include a first platform, and a second platform, and an airfoil section therebetween. A face of the first platform includes a trailing edge recess and a leading edge recess. The trailing edge recess and leading edge recesses of adjacent ones of the first platforms together define a slot. A sealing element situated in each slot. The sealing element has a geometry that tracks the geometry of the slot such that the seal is trapped in the slot by a form-fit relationship in circumferential and axial dimensions by a form-fit relationship between the sealing element and the slot. A method of sealing a plurality of airfoil vanes is also disclosed.

公开(公告)号：US20210317786A1

公开(公告)日：2021-10-14

申请号：US16844596

申请日：2020-04-09

Applicant: United Technologies Corporation

Inventor： Jon E. Sobanski ,  Howard J. Liles

IPC: F02C7/20

Abstract: A gas turbine engine support system includes a support arc segment piece that defines radially inner and outer sides, axially forward and aft sides, and first and second circumferential mate face sides. The radially inner side has a radially open socket that is configured to engage a mating component and transmit loads from the mating component. The radially open socket is elongated in an axial direction with respect to the axially forward and aft sides The support arc segment piece has radial and axial reaction surfaces that are configured, respectively, to transmit radial and axial components of the loads from the mating component.

公开(公告)号：US10975706B2

公开(公告)日：2021-04-13

申请号：US16250804

申请日：2019-01-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Bryan H. Farrar ,  Andrew J. Lazur ,  Howard J. Liles ,  Bryan P. Dube

IPC: F01D5/28 ,  F01D5/14 ,  F01D9/04 ,  F04D29/64 ,  F01D25/24 ,  F04D29/54 ,  F01D5/18

Abstract: A stator vane may comprise an airfoil extending between a first platform and a second platform, the airfoil including a core extending relatively orthogonal to the first platform and the second platform, at least one of the first platform or second platform comprising a frustic load transmission feature, wherein the frustic load transmission feature comprises at least a first angular surface disposed proximate a platform edge, wherein the first angular surface is defined by a non-orthogonal angle θ with respect to an outer platform surface.

公开(公告)号：US20210102469A1

公开(公告)日：2021-04-08

申请号：US16592884

申请日：2019-10-04

Applicant: United Technologies Corporation

Inventor： Jon E. Sobanski ,  Howard J. Liles ,  Bryan H. Farrar ,  Cheng Gao

IPC: F01D5/28

Abstract: A vane arc segment includes a continuous airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The airfoil section has a pressure side and a suction side. The first platform defines axially-sloped suction and pressure side circumferential mate faces, first and second axial sides, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along at least a portion the axially-sloped suction side circumferential mate face.

公开(公告)号：US11092015B2

公开(公告)日：2021-08-17

申请号：US16562557

申请日：2019-09-06

Applicant: United Technologies Corporation

Inventor： Adam P. Generale ,  Howard J. Liles

IPC: F01D5/18 ,  F01D5/14

Abstract: A gas turbine engine airfoil includes an airfoil section that has an airfoil wall and a rib that are formed of a ceramic matrix composite. The airfoil wall circumscribes an internal cavity for receiving cooling air. The airfoil wall defines leading and trailing ends and first and second sides that join the leading and trailing ends. The rib connects the first and second sides. A metallic shield is disposed in the internal cavity and at least partially encloses the rib to shield the rib from the cooling air.