公开(公告)号：US20160003077A1

公开(公告)日：2016-01-07

申请号：US14770112

申请日：2014-03-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Anton G. Banks ,  Andy Turko

IPC: F01D11/00 ,  F01D25/24

CPC classification number: F01D11/003 ,  F01D9/041 ,  F01D11/005 ,  F01D25/24 ,  F01D25/246 ,  F05D2240/12 ,  F05D2250/611 ,  F05D2260/941 ,  Y02T50/672

Abstract: A stator vane seal assembly for a gas turbine engine that includes a vane that has a rail with a scallop that extends axially through the rail. A scallop seal obstructs the scallop.

Abstract translation: 一种用于燃气涡轮发动机的定子叶片密封组件，其包括叶片，所述叶片具有轴向延伸穿过轨道的扇形轨道。 扇贝密封件阻塞扇贝。

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：US10450880B2

公开(公告)日：2019-10-22

申请号：US15228573

申请日：2016-08-04

Applicant: United Technologies Corporation

Inventor： Anton G. Banks ,  Leah M. Collins ,  Gary J. Larson ,  Thomas P. Dziuba ,  Scott A. Kovach

IPC: F01D9/06 ,  F01D9/02 ,  F01D25/00 ,  F02K3/06 ,  F01D5/18

Abstract: A baffle assembly includes a collar with a port and a baffle positioned in the port. The baffle includes two ends, a hollow body, and a weld connecting the baffle to the collar, and the collar continuously surrounds the body of the baffle.

公开(公告)号：US20180058236A1

公开(公告)日：2018-03-01

申请号：US15244203

申请日：2016-08-23

Applicant: United Technologies Corporation

Inventor： Anton G. Banks ,  Christopher Corcoran ,  Bryan P. Dube

IPC: F01D11/00 ,  F02C3/04 ,  F01D5/02 ,  F01D5/30 ,  F04D29/32 ,  F04D29/08

Abstract: A rim seal for a rotor of a gas turbine engine includes a seal portion extending circumferentially across a rim cavity of a rotor, the sealing portion configured to seal the rim cavity and a first foot portion extending radially inwardly from a first end of the sealing portion. A rotor assembly for a gas turbine engine includes a rotor disc and a plurality of rotor blades secured to the rotor disc defining a rim cavity between the rotor disc and a rim portion of the plurality of rotor blades. A rim seal is located in the rim cavity and includes a seal portion extending circumferentially across the rim cavity, the sealing portion configured to seal the rim cavity. The seal portion has an increasing radial thickness with increasing distance from a first end of the rim seal and from a second end opposite the first end.

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：US20190113232A1

公开(公告)日：2019-04-18

申请号：US15782423

申请日：2017-10-12

Applicant: United Technologies Corporation

Inventor： Anton G. Banks ,  Tracy A. Propheter-Hinckley, JR.

IPC: F23R3/26 ,  F02C9/18

CPC classification number: F23R3/26 ,  F01D17/105 ,  F02C9/18 ,  F02C9/22 ,  F23R3/02

Abstract: A combustor section of a gas turbine engine includes a combustor having a combustor inlet, and a combustor bypass passage having a passage inlet located upstream of the combustor inlet. The combustor bypass passage is configured to divert a selected bypass airflow around the combustor. A combustor bypass valve is located at the combustor bypass passage to control the selected bypass airflow along the combustor bypass passage. A method of operating a gas turbine engine, includes urging a core airflow from a compressor section toward a combustor section, flowing a first portion of the core airflow into the combustor section via a combustor inlet, and flowing a second portion of the core airflow into a combustor bypass passage via a combustor bypass valve, thereby bypassing the combustor with the second portion of the core airflow.

公开(公告)号：US09739754B2

公开(公告)日：2017-08-22

申请号：US14449813

申请日：2014-08-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Anton G. Banks ,  Steven Taffet ,  Christopher Laxton

IPC: G01N29/265

CPC classification number: G01N29/265 ,  G01N2291/044 ,  G01N2291/101 ,  G01N2291/2638 ,  G01N2291/2693

Abstract: The present disclosure relates generally to a transducer position guide. The transducer position guide may be attached to a component to be measured, such as an airfoil, and controls a path traversed by the transducer during a measurement process.

公开(公告)号：US11473433B2

公开(公告)日：2022-10-18

申请号：US16043257

申请日：2018-07-24

Applicant: United Technologies Corporation

Inventor： Anton G. Banks ,  Alan C. Barron

IPC: F01D5/28 ,  F01D5/14 ,  F01D5/18

Abstract: An airfoil for a gas turbine engine includes a substrate portion extending from an airfoil leading edge to an airfoil trailing edge portion. The airfoil trailing edge portion includes a flared portion wherein a substrate portion thickness increases along a camber line of the airfoil, and a trailing edge defined as a full constant radius extending from a pressure side of the airfoil to a suction side of the airfoil. A coating portion includes a coating applied over at least a portion of the substrate portion.

公开(公告)号：US10830438B2

公开(公告)日：2020-11-10

申请号：US15782423

申请日：2017-10-12

Applicant: United Technologies Corporation

Inventor： Anton G. Banks ,  Tracy A. Propheter-Hinckley

IPC: F02C6/08 ,  F23R3/26 ,  F02C9/18 ,  F23R3/02 ,  F01D17/10 ,  F02C9/22 ,  F01D17/16 ,  F04D27/02 ,  F23R3/04 ,  F23R3/10 ,  F02C7/18

Abstract: A combustor section of a gas turbine engine includes a combustor having a combustor inlet, and a combustor bypass passage having a passage inlet located upstream of the combustor inlet. The combustor bypass passage is configured to divert a selected bypass airflow around the combustor. A combustor bypass valve is located at the combustor bypass passage to control the selected bypass airflow along the combustor bypass passage. A method of operating a gas turbine engine, includes urging a core airflow from a compressor section toward a combustor section, flowing a first portion of the core airflow into the combustor section via a combustor inlet, and flowing a second portion of the core airflow into a combustor bypass passage via a combustor bypass valve, thereby bypassing the combustor with the second portion of the core airflow.