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公开(公告)号：US10577947B2
公开(公告)日：2020-03-03
申请号：US14961644
申请日：2015-12-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Atul Kohli
Abstract: A baffle insert for a component of a gas turbine engine is provided. The baffle insert having: a plurality of trip strips extending upwardly from an exterior surface of the baffle insert; and at least one rib extending upwardly from the exterior surface of the baffle insert.
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公开(公告)号：US10544682B2
公开(公告)日：2020-01-28
申请号：US15675899
申请日：2017-08-14
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
Abstract: Airfoils and methods of making the same, the airfoils having an airfoil body radially extending from a first end to a second end and axially extending from a leading edge to a trailing edge, the airfoil body defining an airfoil cavity therein, the airfoil cavity defined by a cavity wall having at least one smooth portion, at least one expansion seal installed within the airfoil cavity, the at least one expansion seal dividing the airfoil cavity into at least a first sub-cavity and a second sub-cavity, wherein the at least one expansion seal engages with the smooth portion of the cavity wall by an expansion force that biases ends of the at least one expansion seal into contact with the smooth portion of the cavity wall.
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公开(公告)号：US20190383149A1
公开(公告)日：2019-12-19
申请号：US16010776
申请日：2018-06-18
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic J. Mongillo, JR.
Abstract: A gaspath component for a gas turbine engine includes a platform having at least one internal cooling passage. The at least one internal cooling passage has a plurality of trip strips extending into the cooling passage from at least one internal surface of the cooling passage. Each of the trip strips is defined by a z-shaped configuration.
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公开(公告)号：US10415428B2
公开(公告)日：2019-09-17
申请号：US15884500
申请日：2018-01-31
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Corey D. Anderson
IPC: F04F5/16 , F04F5/46 , F04D17/16 , F04D25/06 , F04D25/08 , F04D25/16 , F04D29/42 , F04D29/66 , F01D11/00 , F01D5/08 , F01D5/06 , F01D25/12 , F02C3/04 , F16J15/16 , F16J15/447 , F01D9/04 , F02C3/06
Abstract: A component for a gas turbine engine according to example of the present disclosure includes a body that has an airfoil extending between a radially inner platform and a radially outer platform, and that has an internal cavity within the airfoil. A baffle is disposed within the internal cavity. The baffle defines first and second baffle cavities that are separated by a baffle dividing wall extending between the radially inner platform and the radially outer platform. An impingement plate is spaced apart from one of the radially inner and outer platforms, includes a first opening that provides fluid communication between a first chamber and the first baffle cavity, and includes a plurality of second openings that are smaller than the first opening and provide fluid communication between the first chamber and the second baffle cavity via a second chamber.
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公开(公告)号：US10378364B2
公开(公告)日：2019-08-13
申请号：US15806224
申请日：2017-11-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Edwin Otero , David R. Pack
Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.
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Patent Agency Ranking
公开(公告)号：US20190234234A1
公开(公告)日：2019-08-01
申请号：US15884473
申请日：2018-01-31
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson , Brandon W. Spangler
Abstract: An exemplary gas turbine engine includes a turbine section positioned about an engine central longitudinal axis. The turbine section includes a component with a platform providing a lip, a rail extending radially from the platform and at an axial location spaced from an outer axial extension of the lip. An inner face of the rail and a surface of the platform at least partially provide a cavity. At least one opening extends from the inner face to an outer face of the rail opposite the inner face to provide fluid communication from the cavity to the lip.
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公开(公告)号：US10329932B2
公开(公告)日：2019-06-25
申请号：US14635168
申请日：2015-03-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Gina Cavallo
Abstract: An airfoil includes an airfoil body extending from an inner diameter platform to an opposed outer diameter platform along a longitudinal axis. The airfoil body defines a leading edge and a trailing edge and has a cavity defined between the leading edge, the trailing edge, the inner diameter platform and the outer diameter platform. The cavity includes an airfoil protrusion extending inward from an inner surface of the airfoil body. The airfoil includes a baffle body within the cavity extending along a baffle body axis. The baffle body has a baffle protrusion extending along a central protrusion axis at an angle with respect to the baffle body axis. The end of the baffle protrusion abuts an end of the airfoil protrusion. A flow path is defined between the inner surface of the airfoil body and the outer surface of the baffle body.
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公开(公告)号：US10323525B2
公开(公告)日：2019-06-18
申请号：US14903467
申请日：2014-06-17
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic J. Mongillo, Jr.
Abstract: A gas turbine engine component includes a structure having a wall that provides an exterior surface. A first cooling passage is arranged adjacent to and interiorly of the wall. A second cooling passage is arranged in the wall and provides a first fluid flow direction. A resupply channel is arranged in the wall and is fluidly interconnected to the second cooling passage. A resupply hole fluidly interconnects the first cooling passage and the resupply channel. The resupply channel is transverse relative to the second cooling passage to provide a second fluid flow direction that extends from the resupply hole to the second cooling passage.
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公开(公告)号：US20190136699A1
公开(公告)日：2019-05-09
申请号：US15806224
申请日：2017-11-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Edwin Otero , David R. Pack
CPC classification number: F01D5/187 , F01D5/186 , F01D5/188 , F02C7/18 , F04D29/324 , F04D29/542 , F05D2220/323 , F05D2240/126 , F05D2240/301 , F05D2250/11 , F05D2250/131 , F05D2260/22141
Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.
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公开(公告)号：US20180371926A1
公开(公告)日：2018-12-27
申请号：US16105607
申请日：2018-08-20
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
Abstract: A vane includes a vane body extending from a root to an opposed tip along a longitudinal axis and first and second baffle bodies. The vane body defines a leading edge and a trailing edge, and a cavity defined between the leading edge, the trailing edge, the root and the tip. The vane body includes at least one vane rib defined between the leading edge and the trailing edge inside the cavity. The first baffle body is defined in one of a leading edge portion and a trailing edge portion of the cavity. The second baffle body is defined in a middle portion of the cavity.
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