公开(公告)号：US10662791B2

公开(公告)日：2020-05-26

申请号：US16161194

申请日：2018-10-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael S. Stevens ,  David Richard Griffin

IPC: F01D9/04 ,  F01D25/24 ,  F01D25/12 ,  F01D5/22 ,  F01D11/00 ,  F01D11/08 ,  F01D9/06 ,  F02C7/20 ,  F02C3/14 ,  F23R3/60

Abstract: A support ring for a gas turbine engine includes a main body portion extending circumferentially about a center axis, a radially extending portion extending radially inward from the main body portion and having a plurality of openings, and a plurality of anti-rotation tabs extending radially inward from the main body portion and axially spaced from the radially extending portion.

公开(公告)号：US20190353043A1

公开(公告)日：2019-11-21

申请号：US15982714

申请日：2018-05-17

Applicant: United Technologies Corporation

Inventor： Michael S. Stevens ,  Christine F. McGinnis ,  Major D. Jones ,  Judith F. Brooks ,  Brian Duguay ,  Tomasz Pelic

IPC: F01D9/04 ,  F01D9/02 ,  F02K3/06

Abstract: A heat shield vane support may have a structure including at least one of a cylindrical and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face and may comprise a flange extending circumferentially about the aft face radially inward from the inboard diameter, a plurality of anti-rotation features distributed circumferentially about the inboard diameter extending radially inward from the inboard diameter and extending axially with respect to the cylindrical structure between a forward edge and an aft edge defining a length L, and a plurality of teeth distributed circumferentially about the forward face and extending axially from the forward face.

公开(公告)号：US10393024B2

公开(公告)日：2019-08-27

申请号：US15250304

申请日：2016-08-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael S. Stevens ,  Brian C. McLaughlin

IPC: F02C7/18 ,  F04D29/54 ,  F01D5/08

Abstract: A multi-air stream cooling system is provided. The multi-air stream cooling system may comprise an inner vane support, a flow guide, and a fastened inner duct. The inner vane support may partially define a first airflow path. The flow guide may couple to the inner vane support and may partially define a second airflow path. The fastened inner duct may couple to the flow guide and may partially define a third airflow path. The inner vane support may comprise a discharge slot to allow a first airflow into a blade rim cavity. The flow guide may comprise a tangential onboard injector (TOBI) to provide a second airflow through a cover plate. The flow guide may also comprise a bypass passage configured to enable a third airflow from the third airflow path.

公开(公告)号：US10132193B2

公开(公告)日：2018-11-20

申请号：US14911287

申请日：2014-08-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Ken F. Blaney ,  Michael S. Stevens

IPC: F01D25/12 ,  F01D5/08 ,  F04D29/58 ,  F02C7/18 ,  F01D9/02 ,  F01D25/24 ,  F01D25/14 ,  F02C6/08

Abstract: A duct assembly according to an exemplary aspect of the present disclosure includes, among other things, a casing body that extends between a flange and a wall, a first discrete cooling passage formed in the casing body and a second discrete cooling passage circumferentially spaced from the first discrete cooling passage. At least one of the first discrete cooling passage and the second discrete cooling passage includes an axial portion and a tangential portion configured to turn a cooling fluid communicated in each of the first and second discrete cooling passages.

公开(公告)号：US10088049B2

公开(公告)日：2018-10-02

申请号：US14704634

申请日：2015-05-05

Applicant: United Technologies Corporation

Inventor： Timothy M. Davis ,  Michael S. Stevens

IPC: F16J15/08 ,  F01D11/00

Abstract: A seal assembly that may be for turbine engine includes first and second rings with a convoluted seal resiliently compressed there-between. The seal may define a gap for receipt of a thermally resistant shield that may also reduce wear of the seal. The seal may include a hole for the flow of cooling air and the shield may be porous so as not to obstruct the cooling air flow for cooling of the seal.

公开(公告)号：US20180058329A1

公开(公告)日：2018-03-01

申请号：US15250304

申请日：2016-08-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael S. Stevens ,  Brian C. McLaughlin

IPC: F02C7/18 ,  F04D29/54

CPC classification number: F02C7/18 ,  F01D5/082 ,  F04D29/54 ,  Y02T50/676

Abstract: A multi-air stream cooling system is provided. The multi-air stream cooling system may comprise an inner vane support, a flow guide, and a fastened inner duct. The inner vane support may partially define a first airflow path. The flow guide may couple to the inner vane support and may partially define a second airflow path. The fastened inner duct may couple to the flow guide and may partially define a third airflow path. The inner vane support may comprise a discharge slot to allow a first airflow into a blade rim cavity. The flow guide may comprise a tangential onboard injector (TOBI) to provide a second airflow through a cover plate. The flow guide may also comprise a bypass passage configured to enable a third airflow from the third airflow path.