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公开(公告)号：US10557366B2
公开(公告)日：2020-02-11
申请号：US15863152
申请日：2018-01-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christina G Ciamarra , Brian Barainca , Thurman Carlo Dabbs
Abstract: A blade outer air seal may comprise an arcuate segment. The arcuate segment may comprise an aft wall having a first radially extending protrusion at a circumferential end of the aft wall. A first hook may extend aft from the aft wall. A first gusset may extend from the first radially extending protrusion. A radial height of the first radially extending protrusion may be greater than a radial height of a second radially extending protrusion of the aft wall.
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公开(公告)号：US10533456B2
公开(公告)日：2020-01-14
申请号：US15605991
申请日：2017-05-26
Applicant: United Technologies Corporation
Inventor： Brian Barainca , Paul W. Baumann
Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud that extends about an axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body that extends from a first end portion. The first end portion is received in the first shroud opening and defines a pair of airfoil openings. At least one retention clip has an intermediate portion connecting a pair of elongated leg portions. The pair of elongated leg portions are received in the pair of airfoil openings such that the at least one retention clip limits movement of the airfoil relative to the first shroud. A method of assembling a stator assembly is also disclosed.
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公开(公告)号：US20200011191A1
公开(公告)日：2020-01-09
申请号：US16026638
申请日：2018-07-03
Applicant: United Technologies Corporation
Inventor： Thomas Freeman , Brian Barainca
IPC: F01D9/04
Abstract: A vane for use with a stator assembly is disclosed herein. The vane having: an upper mounting portion; a lower mounting portion; an airfoil body extending between the upper mounting portion and the lower mounting portion; a first integrally formed metal fillet located between the upper mounting portion and the airfoil body, the first integrally formed metal fillet defining a first mounting surface located between the upper mounting portion and first integrally formed metal fillet; and a second integrally formed metal fillet located between the lower mounting portion and the airfoil body, the second integrally formed metal fillet defining a second mounting surface located between the lower mounting portion and second integrally formed metal fillet.
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公开(公告)号：US20190368362A1
公开(公告)日：2019-12-05
申请号：US15995907
申请日：2018-06-01
Applicant: United Technologies Corporation
Inventor： Brian Barainca
IPC: F01D9/04
Abstract: A guide vane retention system for a gas turbine engine. The system includes an outer diameter shroud defining an aperture. Also included is a guide vane having a radially outer end extending through the aperture, the guide vane defining a slot proximate the radially outer end and positioned radially outwardly of the outer diameter shroud in an installed condition of the guide vane. Further included is a clip disposed within the slot of the guide vane. The clip includes a looped end. The clip also includes a first leg extending away from the looped end to a first free end. The clip further includes a second leg extending away from the looped end to a second free end.
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公开(公告)号：US20180340448A1
公开(公告)日：2018-11-29
申请号：US15605991
申请日：2017-05-26
Applicant: United Technologies Corporation
Inventor： Brian Barainca , Paul W. Baumann
CPC classification number: F01D25/246 , F01D5/3023 , F01D9/042 , F05D2250/75 , F05D2260/31 , F05D2260/36 , F05D2260/38
Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud that extends about an axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body that extends from a first end portion. The first end portion is received in the first shroud opening and defines a pair of airfoil openings. At least one retention clip has an intermediate portion connecting a pair of elongated leg portions. The pair of elongated leg portions are received in the pair of airfoil openings such that the at least one retention clip limits movement of the airfoil relative to the first shroud. A method of assembling a stator assembly is also disclosed.
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Patent Agency Ranking
公开(公告)号：US20180340432A1
公开(公告)日：2018-11-29
申请号：US15606191
申请日：2017-05-26
Applicant: United Technologies Corporation
Inventor： Brian Barainca , Dennis R. Tremblay , Steven J. Feigleson
Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an assembly axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines a pair of airfoil openings. A retention clip has an intermediate portion connecting a first leg portion and a second leg portion. The intermediate portion is compressible to position the first and second leg portions in the pair of airfoil openings such that the retention clip limits movement of the airfoil relative to the first shroud.
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公开(公告)号：US20210123354A1
公开(公告)日：2021-04-29
申请号：US16667501
申请日：2019-10-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sarah J. Zecha , Brian Barainca , Brian Duguay , Uriah C. Noble
IPC: F01D9/04
Abstract: An improved stator assembly for use in a gas-turbine engine is disclosed. The stator assembly may comprise a vane, an inner diameter (ID) ring, an outer diameter (OD) ring, a vane disposed between the ID ring and the OD ring, a potting component coupling the vane to at least one of the OD ring or the ID ring, and a potting embedded component disposed within the potting component. The potting embedded component may prevent disbond of the potting component during operation of the gas-turbine engine.
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公开(公告)号：US10830074B2
公开(公告)日：2020-11-10
申请号：US16026638
申请日：2018-07-03
Applicant: United Technologies Corporation
Inventor： Thomas Freeman , Brian Barainca
Abstract: A vane for use with a stator assembly is disclosed herein. The vane having: an upper mounting portion; a lower mounting portion; an airfoil body extending between the upper mounting portion and the lower mounting portion; a first integrally formed metal fillet located between the upper mounting portion and the airfoil body, the first integrally formed metal fillet defining a first mounting surface located between the upper mounting portion and first integrally formed metal fillet; and a second integrally formed metal fillet located between the lower mounting portion and the airfoil body, the second integrally formed metal fillet defining a second mounting surface located between the lower mounting portion and second integrally formed metal fillet.
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公开(公告)号：US10808559B2
公开(公告)日：2020-10-20
申请号：US15995907
申请日：2018-06-01
Applicant: United Technologies Corporation
Inventor： Brian Barainca
IPC: F01D9/04
Abstract: A guide vane retention system for a gas turbine engine. The system includes an outer diameter shroud defining an aperture. Also included is a guide vane having a radially outer end extending through the aperture, the guide vane defining a slot proximate the radially outer end and positioned radially outwardly of the outer diameter shroud in an installed condition of the guide vane. Further included is a clip disposed within the slot of the guide vane. The clip includes a looped end. The clip also includes a first leg extending away from the looped end to a first free end. The clip further includes a second leg extending away from the looped end to a second free end.
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公开(公告)号：US10724389B2
公开(公告)日：2020-07-28
申请号：US15645881
申请日：2017-07-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brian Barainca , Paul W. Baumann
Abstract: A gas turbine engine has a stator vane assembly. The stator vane assembly includes an inner diameter shroud, an outer diameter shroud located radially outward from the inner diameter shroud, a vane extending radially outward from the first inner diameter shroud to the outer diameter shroud. The wedge clip is positioned horizontally through the vane to prevent the vane from being dislodged from the stator vane assembly.
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