公开(公告)号：US20180291760A1

公开(公告)日：2018-10-11

申请号：US15484166

申请日：2017-04-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ortiz ,  Matthew A. Devore ,  Lane Mikal Thornton ,  James D. Hill

IPC: F01D11/20 ,  F02C3/04 ,  F02C9/18 ,  F01D5/02

Abstract: A gas turbine engine comprises a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface defining a diffuser chamber radially outwardly of the combustor, and a cooling air chamber wall positioned outwardly of the diffuser chamber and the combustor, and radially inwardly of a second wall to define a cooling air chamber. The turbine section includes a high pressure turbine first stage blade having an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap taps air having been compressed by the compressor and is passed through a heat exchanger. Air downstream of the heat exchanger passes into the cooling chamber, and then to the blade outer air seal.

公开(公告)号：US20180291762A1

公开(公告)日：2018-10-11

申请号：US15484168

申请日：2017-04-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ortiz ,  Lane Mikal Thornton ,  Matthew A. Devore

IPC: F01D25/12 ,  F02C3/04 ,  F01D17/10 ,  F01D17/16 ,  F01D9/04 ,  F01D11/14

CPC classification number: F01D25/12 ,  F01D5/081 ,  F01D9/041 ,  F01D9/065 ,  F01D11/14 ,  F01D17/105 ,  F01D17/162 ,  F02C3/04 ,  F02C6/08 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2300/50212 ,  Y02T50/676

Abstract: A gas turbine engine comprises a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine first stage blade having an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap taps air having been compressed by the compressor, the tapped air being passed through a heat exchanger. A vane section has vanes downstream of the combustor, but upstream of the first stage blade, and the air downstream of the heat exchanger passes radially inwardly of the combustor, along an axial length of the combustor, and then radially outwardly through a hollow chamber in the vanes, and then across the blade outer air seal, to cool the blade outer air seal.

公开(公告)号：US11215061B2

公开(公告)日：2022-01-04

申请号：US16781729

申请日：2020-02-04

Applicant: United Technologies Corporation

Inventor： Anton G. Banks ,  Lane Mikal Thornton

IPC: F01D5/20

Abstract: Disclosed is a blade, having: a blade root; a blade body that extends radially from the blade root to a blade tip, the blade body having a pressure side and a suction side each extending from a leading edge of the blade body to a trailing edge of the blade body; a squealer pocket located in the blade tip; and a first wearable tip-rub-portion located radially above the squealer pocket, and extending between the pressure side and the suction side, the first wearable tip-rub-portion terminating at a first wearable tip-rub-portion distal end.

公开(公告)号：US10711640B2

公开(公告)日：2020-07-14

申请号：US15484168

申请日：2017-04-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ortiz ,  Lane Mikal Thornton ,  Matthew A. Devore

IPC: F01D17/16 ,  F01D25/12 ,  F02C3/04 ,  F01D17/10 ,  F01D9/04 ,  F01D11/14 ,  F02C6/08 ,  F01D5/08 ,  F01D9/06

Abstract: A gas turbine engine comprises a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine first stage blade having an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap taps air having been compressed by the compressor, the tapped air being passed through a heat exchanger. A vane section has vanes downstream of the combustor, but upstream of the first stage blade, and the air downstream of the heat exchanger passes radially inwardly of the combustor, along an axial length of the combustor, and then radially outwardly through a hollow chamber in the vanes, and then across the blade outer air seal, to cool the blade outer air seal.

公开(公告)号：US20210239009A1

公开(公告)日：2021-08-05

申请号：US16781729

申请日：2020-02-04

Applicant: United Technologies Corporation

Inventor： Anton G. Banks ,  Lane Mikal Thornton

IPC: F01D11/12 ,  F01D5/14 ,  F01D5/30

Abstract: Disclosed is a blade, having: a blade root; a blade body that extends radially from the blade root to a blade tip, the blade body having a pressure side and a suction side each extending from a leading edge of the blade body to a trailing edge of the blade body; a squealer pocket located in the blade tip; and a first wearable tip-rub-portion located radially above the squealer pocket, and extending between the pressure side and the suction side, the first wearable tip-rub-portion terminating at a first wearable tip-rub-portion distal end.

公开(公告)号：US20200248565A1

公开(公告)日：2020-08-06

申请号：US16267664

申请日：2019-02-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Anton G. Banks ,  Lane Mikal Thornton

IPC: F01D5/18

Abstract: A gas turbine engine blade according to an example of the present disclosure includes a blade including internal walls defining a blade cooling passage and a tip section at a radially outer end of the blade. The tip section includes a pocket protruding into the tip section from a radially outermost end of the tip section to a pocket floor. The blade further includes a pocket wall defined between the pocket floor and the radially outermost end of the tip section and including a tapered wall cooling passage.

公开(公告)号：US11008873B2

公开(公告)日：2021-05-18

申请号：US16267664

申请日：2019-02-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Anton G. Banks ,  Lane Mikal Thornton

IPC: F01D5/18

Abstract: A gas turbine engine blade according to an example of the present disclosure includes a blade including internal walls defining a blade cooling passage and a tip section at a radially outer end of the blade. The tip section includes a pocket protruding into the tip section from a radially outermost end of the tip section to a pocket floor. The blade further includes a pocket wall defined between the pocket floor and the radially outermost end of the tip section and including a tapered wall cooling passage.

公开(公告)号：US20190309685A1

公开(公告)日：2019-10-10

申请号：US15946251

申请日：2018-04-05

Applicant: United Technologies Corporation

Inventor： William P. Stillman ,  Lane Mikal Thornton ,  Matthew A. Devore ,  Gavin Hendricks

IPC: F02C7/18 ,  F02C3/06 ,  F02C7/30

Abstract: A gas turbine engine includes a compressor section, a combustor section downstream from the compressor section, and a turbine section downstream from the combustor section. The gas turbine engine also includes a water tank with an outlet, and an injector fluidically connected to the outlet of the water tank and to the turbine section. The injector is configured to direct steam from the water tank into the turbine section.