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公开(公告)号：US20180347465A1
公开(公告)日：2018-12-06
申请号：US15608547
申请日：2017-05-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul W. Baumann , Brian Barainca , Rolf Thorsen , Mark E. Simonds , Gary F. Fowler , Hector M. Pinero
CPC classification number: F02C7/055 , F01D5/24 , F01D11/122 , F01D21/045 , F02C7/045 , F02C7/05
Abstract: An outer diameter shroud for retaining a stator of a gas turbine engine having an axis includes an annular body positioned around the axis, extending in an axial direction, and defining a plurality of slots each configured to receive a portion- of one of a plurality of stators. The outer diameter shroud further includes a shroud flange coupled to the annular body, extending in a direction perpendicular to the annular body, and configured to be fastened to a case of the gas turbine engine.
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公开(公告)号：US10767503B2
公开(公告)日：2020-09-08
申请号：US15618903
申请日：2017-06-09
Applicant: United Technologies Corporation
Inventor： Brian Barainca , Gary F. Fowler
Abstract: A stator assembly for 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 retention aperture. A retention clip includes a body and at least one locking feature. The body extends between opposed clip end portions. The at least one locking feature is compressibly received through the retention aperture, and the least one locking feature is decompressible from the body to define a ramp sloping towards one of the clip end portions to limit movement of the airfoil relative to the first shroud when in the installed position.
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公开(公告)号：US10557412B2
公开(公告)日：2020-02-11
申请号：US15608547
申请日：2017-05-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul W. Baumann , Brian Barainca , Rolf Thorsen , Mark E. Simonds , Gary F. Fowler , Hector M. Pinero
Abstract: An outer diameter shroud for retaining a stator of a gas turbine engine having an axis includes an annular body positioned around the axis, extending in an axial direction, and defining a plurality of slots each configured to receive a portion of one of a plurality of stators. The outer diameter shroud further includes a shroud flange coupled to the annular body, extending in a direction perpendicular to the annular body, and configured to be fastened to a case of the gas turbine engine.
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公开(公告)号：US20190010816A1
公开(公告)日：2019-01-10
申请号：US15645881
申请日：2017-07-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brian Barainca , Paul W. Baumann
IPC: F01D9/04
CPC classification number: F01D9/042 , F01D9/041 , F04D29/542 , F04D29/644 , F05D2220/32 , F05D2230/60 , F05D2230/644 , F05D2240/125 , F05D2260/36
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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公开(公告)号：US20180340449A1
公开(公告)日：2018-11-29
申请号：US15606005
申请日：2017-05-26
Applicant: United Technologies Corporation
Inventor： Brian Barainca , Gary F. Fowler
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 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 at least one airfoil opening. At least one retention clip has an arcuate portion extending from a first elongated leg portion. The first elongated leg portion and the arcuate portion are received through the at least one airfoil opening such that the at least one retention clip limits movement of the airfoil relative to the first shroud.
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Patent Agency Ranking
公开(公告)号：US20210140375A1
公开(公告)日：2021-05-13
申请号：US16677090
申请日：2019-11-07
Applicant: United Technologies Corporation
Inventor： Sarah J. Zecha , Brian Barainca
Abstract: A stator vane assembly of a gas turbine engine includes a stator shroud having a plurality of shroud openings formed therein. The stator shroud defines a flowpath surface. The assembly includes a plurality of stator vanes, one stator vane of the plurality of stator vanes installed in each shroud opening of the stator shroud. A volume of potting material is located in the plurality of shroud openings to retain the stator vanes thereat. One or more retainers are located at a back surface of the stator shroud opposite the flowpath surface to restrict circumferential movement of the plurality of stator vanes relative to the stator shroud.
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公开(公告)号：US10590783B2
公开(公告)日：2020-03-17
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：US20190218928A1
公开(公告)日：2019-07-18
申请号：US15873496
申请日：2018-01-17
Applicant: United Technologies Corporation
Inventor： Christina G. Ciamarra , Brian Barainca , Thurman Carlo Dabbs
IPC: F01D11/10
CPC classification number: F01D11/10 , F01D9/042 , F01D11/005 , F01D11/08 , F01D11/22 , F01D25/246 , F05D2240/55 , F05D2260/30 , F05D2260/96
Abstract: An assembly for use in a turbine section of a gas turbine engine, the assembly including: a blade outer air seal having a forward end and opposite aft end and a pair of opposing sides extending between the forward end and the opposite aft end; a blade outer air seal support, the blade outer air seal support having a rail with at least one scalloped opening, the rail engaging a hook located at the forward end of the blade outer air seal when the blade outer air seal is secured to the blade outer air seal support, wherein two points of contact are made between the hook and the rail of the blade outer air seal support when the blade outer air seal is secured to the blade outer air seal support; and a vane platform, that receives and supports a rail of the blade outer air seal, the rail being located at the aft end of the blade outer air seal and the rail extends continuously between the pair of opposing sides of the blade outer air seal, wherein a single point of contact is made between the rail of the blade outer air seal and the vane platform when the blade outer air seal is secured to the vane platform.
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公开(公告)号：US20190211701A1
公开(公告)日：2019-07-11
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：US20180355737A1
公开(公告)日：2018-12-13
申请号：US15618903
申请日：2017-06-09
Applicant: United Technologies Corporation
Inventor： Brian Barainca , Gary F. Fowler
Abstract: A stator assembly for 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 retention aperture. A retention clip includes a body and at least one locking feature. The body extends between opposed clip end portions. The at least one locking feature is compressibly received through the retention aperture, and the least one locking feature is decompressible from the body to define a ramp sloping towards one of the clip end portions to limit movement of the airfoil relative to the first shroud when in the installed position.
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