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公开(公告)号：US20210062667A1
公开(公告)日：2021-03-04
申请号：US16571678
申请日：2019-09-16
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, JR. , Brandon W. Spangler , Lane Thornton
Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.
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公开(公告)号：US10822963B2
公开(公告)日：2020-11-03
申请号：US16210696
申请日：2018-12-05
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Adam P. Generale
Abstract: A component for a gas turbine engine includes a interleaved structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs. The second multiple of structural rib span segments that extend from the second sidewall, the first multiple of structural rib span segments interleaved with the second multiple of structural rib span segments to form an interleaved structural rib that extends between the first sidewall and the second sidewall.
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公开(公告)号：US10808552B2
公开(公告)日：2020-10-20
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：US10787913B2
公开(公告)日：2020-09-29
申请号：US16177933
申请日：2018-11-01
Applicant: United Technologies Corporation
Inventor： Daniel P. Preuss , Brandon W. Spangler
Abstract: An airfoil for a gas turbine engine includes axial flow and radial flow cooling circuits defined within an airfoil body. A baffle disposed in spaced relation to an inner surface of the airfoil has a plurality of impingement cooling holes configured to direct a cooling fluid at an inner surface of the airfoil body and an axial extent from the leading edge defined by an aft wall, with the axial extent being substantially constant between the inner and outer end walls and defined by a plane perpendicular to an engine axis. A first radially-extending rib is angled with respect to the baffle to define a first passage between the first rib and the baffle that tapers in cross-sectional area between the inner end wall and the outer end wall, becoming larger in cross-sectional area in a direction of cooling fluid flow through the first passage.
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公开(公告)号：US20200263563A1
公开(公告)日：2020-08-20
申请号：US16700513
申请日：2019-12-02
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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Patent Agency Ranking
公开(公告)号：US10697309B2
公开(公告)日：2020-06-30
申请号：US15961930
申请日：2018-04-25
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson , Brandon W. Spangler
IPC: F01D5/18
Abstract: Components for gas turbine engines are provided. The components include a platform, a first airfoil extending from the platform, a first cavity located within the first airfoil, the first cavity includes a forward portion and an aft portion separated by a divider, a cover plate attached to the platform on a side opposite the airfoil, wherein a platform cavity is defined between the cover plate and the platform and wherein the first cavity is fluidly connected to the platform cavity through a first cavity inlet, and a first cavity separating rail dividing the platform cavity into a first platform forward cavity and a first platform aft cavity, wherein the first platform forward cavity is fluidly connected to the aft portion of the first cavity and the first platform aft cavity is fluidly connected to the forward portion of the first cavity.
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公开(公告)号：US20200182152A1
公开(公告)日：2020-06-11
申请号：US16210393
申请日：2018-12-05
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic Mongillo , Allan N. Arisi
Abstract: A component for a gas turbine engine includes a wall portion that includes an interior surface and an exterior surface. At least one cooling circuit is defined by the wall portion and includes a plurality of pedestals that extend across the cooling circuit. A width of the cooling circuit increases or decreases in a downstream direction. At least one cooling fluid inlet extends through the interior surface and is in fluid communication with the cooling circuit. At least one cooling fluid outlet extends through the exterior surface and is in fluid communication with the cooling circuit.
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公开(公告)号：US10662783B2
公开(公告)日：2020-05-26
申请号：US16116351
申请日：2018-08-29
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
Abstract: A gas turbine engine component includes an airfoil defined by a leading edge, a trailing edge, a pressure sidewall, and a suction sidewall. An internal cavity extends radially through the airfoil and is partially defined by an inner surface of the pressure sidewall and an inner surface of the suction sidewall. A baffle is disposed within the internal cavity, and includes a baffle wall conformal with adjacent surfaces of the internal cavity, a divider separating a forward chamber and an aft chamber, and a plurality of orifices extending through the baffle wall at the forward chamber. At least one axial rib is disposed between the baffle wall and the internal cavity, and is positioned at a discrete spanwise location of the airfoil.
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公开(公告)号：US20200149413A1
公开(公告)日：2020-05-14
申请号：US16660093
申请日：2019-10-22
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Edwin Otero
Abstract: A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.
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公开(公告)号：US20200072060A1
公开(公告)日：2020-03-05
申请号：US16116351
申请日：2018-08-29
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
IPC: F01D5/18
Abstract: A gas turbine engine component includes an airfoil defined by a leading edge, a trailing edge, a pressure sidewall, and a suction sidewall. An internal cavity extends radially through the airfoil and is partially defined by an inner surface of the pressure sidewall and an inner surface of the suction sidewall. A baffle is disposed within the internal cavity, and includes a baffle wall conformal with adjacent surfaces of the internal cavity, a divider separating a forward chamber and an aft chamber, and a plurality of orifices extending through the baffle wall at the forward chamber. At least one axial rib is disposed between the baffle wall and the internal cavity, and is positioned at a discrete spanwise location of the airfoil.
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