公开(公告)号：US10914187B2

公开(公告)日：2021-02-09

申请号：US15700288

申请日：2017-09-11

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Joseph F. Englehart ,  Graham Ryan Philbrick ,  ChaiDee Woods Brown

IPC: F01D5/20 ,  F01D11/24 ,  F01D25/12

Abstract: An active clearance control manifold assembly includes multiple arcuate manifold segments each having multiple circumferential channels axially spaced apart from one another. The circumferential channels include cooling holes facing radially inward. A tube at least partially circumscribes and fluidly interconnects the manifold segments.

公开(公告)号：US20170107830A1

公开(公告)日：2017-04-20

申请号：US14886201

申请日：2015-10-19

Applicant: United Technologies Corporation

Inventor： Joseph F. Englehart ,  Edward F. Pietraszkiewicz ,  Wieslaw A. Chlus ,  David M. Konopka ,  Luke A. Hmiel ,  Kenneth Boucher

IPC: F01D5/18 ,  F02C3/04 ,  F02C7/18 ,  F01D5/14

Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.

公开(公告)号：US10815812B2

公开(公告)日：2020-10-27

申请号：US15920819

申请日：2018-03-14

Applicant: United Technologies Corporation

Inventor： Daniel Barak ,  Joseph F. Englehart

IPC: F01D11/16 ,  F01D25/24 ,  F01D11/08

Abstract: A blade outer air seal (BOAS) is provided. The BOAS comprising: a seal body having a forward side, an aft side opposite the forward side, a radially inward side, and a radially outward side opposite the radially inward side; and a relief gap within the seal body to allow a portion of the radially inward side to expand into the relief gap when the seal body is heated.

公开(公告)号：US20190078457A1

公开(公告)日：2019-03-14

申请号：US15700264

申请日：2017-09-11

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Joseph F. Englehart ,  Christopher Carter Venable ,  Michael G. McCaffrey

IPC: F01D11/14 ,  F16J15/16

Abstract: A gas turbine engine sealing system includes a case including forward and aft hooks. The aft hook arranged radially outward of the forward hook. A blade outer air seal has a J-hook that receives the aft hook and includes an end received by the forward hook.

公开(公告)号：US20190032505A1

公开(公告)日：2019-01-31

申请号：US15920819

申请日：2018-03-14

Applicant: United Technologies Corporation

Inventor： Daniel Barak ,  Joseph F. Englehart

IPC: F01D11/16

Abstract: A blade outer air seal (BOAS) is provided. The BOAS comprising: a seal body having a forward side, an aft side opposite the forward side, a radially inward side, and a radially outward side opposite the radially inward side; and a relief gap within the seal body to allow a portion of the radially inward side to expand into the relief gap when the seal body is heated.

公开(公告)号：US20190078459A1

公开(公告)日：2019-03-14

申请号：US15700372

申请日：2017-09-11

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Joseph F. Englehart ,  Graham Ryan Philbrick

IPC: F01D11/24 ,  F01D17/06 ,  F01D17/08 ,  F01D25/12 ,  F02C9/18

Abstract: A method of controlling a power turbine running clearance between blade tips and a case structure. The method includes the step of adjusting an active clearance control system fluid flow based upon a power turbine speed to obtain a desired running clearance in a power turbine.

公开(公告)号：US20190078458A1

公开(公告)日：2019-03-14

申请号：US15700288

申请日：2017-09-11

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Joseph F. Englehart ,  Graham Ryan Philbrick ,  ChaiDee Woods Brown

IPC: F01D11/24 ,  F01D25/12

Abstract: An active clearance control manifold assembly includes multiple arcuate manifold segments each having multiple circumferential channels axially spaced apart from one another. The circumferential channels include cooling holes facing radially inward. A tube at least partially circumscribes and fluidly interconnects the manifold segments.

公开(公告)号：US20180328214A1

公开(公告)日：2018-11-15

申请号：US15623208

申请日：2017-06-14

Applicant: UNiTED TECHNOLOGIES CORPORATION

Inventor： Daniel Barak ,  Joseph F. Englehart

IPC: F01D11/12 ,  F02C3/04 ,  F01D5/12 ,  F01D9/04 ,  F04D29/32 ,  F04D29/54 ,  F04D29/08

Abstract: A blade outer air seal (BOAS) assembly includes a rotor blade configured to rotate about an axis. The BOAS assembly also includes a BOAS positioned radially outward from the rotor blade and having a forward-facing BOAS face. The BOAS assembly also includes a shroud block positioned radially outward from the BOAS, having an aft-facing shroud face, and being configured to support the BOAS. The BOAS assembly also includes a first bellows seal extending from the forward-facing BOAS face to the aft-facing shroud face and configured to reduce fluid leakage radially between the BOAS and the shroud block.

公开(公告)号：US10677070B2

公开(公告)日：2020-06-09

申请号：US14886201

申请日：2015-10-19

Applicant: United Technologies Corporation

Inventor： Joseph F. Englehart ,  Edward F. Pietraszkiewicz ,  Wieslaw A. Chlus ,  David M. Konopka ,  Luke A. Hmiel ,  Kenneth Boucher

IPC: F02C1/00 ,  F01D5/18 ,  F01D5/14 ,  F02C3/04 ,  F02C7/18

Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.

公开(公告)号：US10533446B2

公开(公告)日：2020-01-14

申请号：US15623208

申请日：2017-06-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel Barak ,  Joseph F. Englehart

IPC: F01D11/14 ,  F01D11/16 ,  F01D11/08 ,  F01D11/00 ,  F16J15/08

Abstract: A blade outer air seal (BOAS) assembly includes a rotor blade configured to rotate about an axis. The BOAS assembly also includes a BOAS positioned radially outward from the rotor blade and having a forward-facing BOAS face. The BOAS assembly also includes a shroud block positioned radially outward from the BOAS, having an aft-facing shroud face, and being configured to support the BOAS. The BOAS assembly also includes a first bellows seal extending from the forward-facing BOAS face to the aft-facing shroud face and configured to reduce fluid leakage radially between the BOAS and the shroud block.