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公开(公告)号：US20200024967A1
公开(公告)日：2020-01-23
申请号：US16052730
申请日：2018-08-02
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Kevin D. Tracy , Dominic J. Mongillo, JR.
Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body having a leading edge and a trailing edge extending in a radial direction, a cooling cavity defined within the airfoil body at the trailing edge, and a plurality of angled pedestals arranged along the trailing edge, wherein the plurality of angled pedestals define a plurality of angled trailing edge slots therebetween. Adjacent angled pedestals of the plurality of angled pedestals define a meter section of a respective angled trailing edge slot and a diffuser section of the respective angled trailing edge slot, wherein the meter section is defined by parallel sides of the adjacent angled pedestals, wherein the parallel sides of the adjacent angled pedestals are oriented at a bleed direction that is less than 90° with respect to a feed direction through the cooling cavity.
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公开(公告)号：US10465542B2
公开(公告)日：2019-11-05
申请号：US15708603
申请日：2017-09-19
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ryan Alan Waite , Steven Bruce Gautschi , Benjamin F. Hagan
Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend between at least one of the pressure and suction side walls into the airfoil cavity to support the baffle relative to the at least one of the pressure and suction side walls. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through the at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.
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公开(公告)号：US10337334B2
公开(公告)日：2019-07-02
申请号：US14961685
申请日：2015-12-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Atul Kohli
Abstract: A component of a gas turbine engine, the component having: an internal cooling cavity extending through an interior of the component; a baffle insert configured to be inserted into the internal cooling cavity; 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, wherein the plurality of trip strips and the at least one rib are spaced from an interior surface of the internal cooling cavity.
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公开(公告)号：US10267163B2
公开(公告)日：2019-04-23
申请号：US15584106
申请日：2017-05-02
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic J. Mongillo
Abstract: Turn caps for airfoils of gas turbine engines having a first pressure-side turn passage extending from a respective inlet to a respective outlet within the turn cap, a first suction-side turn passage extending from a respective inlet to a respective outlet within the turn cap, and a merging chamber fluidly connected to the outlets of the first pressure-side turn passage and the first suction-side turn passage, wherein each of the first suction-side turn passage and the first pressure-side turn passage turn a direction of fluid flow from a first direction to a second direction such that a fluid flow exiting the first suction-side turn passage and the first pressure-side turn passage are aligned when entering the merging chamber.
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公开(公告)号：US10240470B2
公开(公告)日：2019-03-26
申请号：US14911148
申请日：2014-06-30
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan , Ryan A. Waite , Brandon W. Spangler , Steven B. Gautschi
Abstract: A vane structure includes an airfoil section with a first inner airfoil wall surface and a second inner airfoil wall surface. A baffle is mounted within the airfoil section between the first inner airfoil wall surface and the second inner airfoil wall surface.
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Patent Agency Ranking
公开(公告)号：US20190048726A1
公开(公告)日：2019-02-14
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：US20180347919A1
公开(公告)日：2018-12-06
申请号：US15608795
申请日：2017-05-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Atul Kohli
CPC classification number: F01D9/065 , F05D2240/126
Abstract: Disclosed is a module for a gas turbine engine, the module including: a disk rotatable about an engine central axis and a vane fixedly disposed upstream of the disk, the vane being hollow and including a vane cavity, the vane cavity having a vane longitudinal span between a vane upstream opening and vane downstream opening, the vane including: a baffle fixedly supported within the vane cavity, the baffle having a hollow interior and having a baffle longitudinal span between a baffle upstream surface and a baffle downstream surface, the baffle longitudinal span being less than the vane longitudinal span to define a partial space eater baffle; wherein a baffle opening area fluidly connects the vane cavity to the baffle interior, and the baffle opening area is between 5.0×10̂−5 square inches and 1.5×10̂−3 square inches.
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公开(公告)号：US10047629B2
公开(公告)日：2018-08-14
申请号：US14763719
申请日：2013-01-28
Applicant: United Technologies Corporation
Abstract: An assembly for a turbine engine includes a plurality of vane segments. The vane segments are fastened together and form an adjustable stator vane that pivots about a variable vane axis. The adjustable stator vane includes a stator vane body, a shaft and a flange. The stator vane body extends axially between a first end and a second end, and includes an airfoil, a body surface and a cavity. The body surface is located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially at least partially around the inlet, and radially from the stator vane body. A first of the vane segments includes the flange. A second of the vane segments includes at least a portion of the airfoil.
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公开(公告)号：US20180223676A1
公开(公告)日：2018-08-09
申请号：US15426082
申请日：2017-02-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic J. Mongillo, JR.
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/189 , F01D9/02 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/21 , F05D2240/125 , F05D2240/126 , F05D2240/81 , F05D2250/185 , F05D2260/221
Abstract: Turn caps for airfoils of gas turbine engines including cavity sidewalls, a first turn cap divider extending between the cavity sidewalls and defining a turning cavity between the first turn cap divider and the cavity sidewalls, and a second turn cap divider disposed radially inward within the turning cavity. A first turning path is defined between the first turn cap divider and the second turn cap divider and a second turning path is defined radially inward of the second turn cap divider and a merging chamber is formed in the turn cap wherein fluid flows through the first turning path and the second turning path are merged, the merging chamber, the first turning path, and the second turning path forming the turning cavity.
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公开(公告)号：US20180209286A1
公开(公告)日：2018-07-26
申请号：US15416394
申请日：2017-01-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Carey Clum , Matthew A. Devore
CPC classification number: F01D9/065 , F01D5/187 , F02C7/18 , F05D2220/32 , F05D2240/122 , F05D2260/20 , F05D2260/202 , F05D2260/2212 , Y02T50/676
Abstract: A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. Another internal channel in body receives the upstream supply pressure and provides a downstream supply pressure. At least one axial rib separates an internal area adjacent to the trailing edge into a plurality of individual cavities. At least one pressure regulating feature is located at an entrance to at least one individual cavity entrance to control downstream supply pressure to the trailing edge. Exits formed in the trailing edge communicate with an exit pressure. The rib and pressure regulating features cooperate such that the downstream supply pressure mimics the exit pressure along the radial span. A method of manufacturing a gas turbine engine component and a method of controlling flow in a gas turbine engine component are also disclosed.
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