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公开(公告)号：US11092017B2
公开(公告)日：2021-08-17
申请号：US16594156
申请日：2019-10-07
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Allan N. Arisi
Abstract: An airfoil includes an airfoil wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The airfoil wall circumscribes an internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an inlet orifice through the inner portion of the airfoil wall to receive cooling air from the internal core cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The outer portion of the airfoil wall has a protrusion in the cooling passage network that faces toward the inlet orifice.
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公开(公告)号：US11085325B2
公开(公告)日：2021-08-10
申请号：US16033356
申请日：2018-07-12
Applicant: United Technologies Corporation
Inventor： Michael F. Blair , Tracy A. Propheter-Hinckley , Mark F. Zelesky
Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.
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公开(公告)号：US11002153B2
公开(公告)日：2021-05-11
申请号：US16031057
申请日：2018-07-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Alberto A. Mateo , Tracy A. Propheter-Hinckley , San Quach
Abstract: A balance bracket for a diffuser case of gas turbine engine is disclosed. In various embodiments, the balance bracket includes a first portion configured for mounting to a first boss on the diffuser case, a second portion configured for mounting to a second boss on the diffuser case, the second portion spaced a distance from the first portion, and a first undulating portion positioned intermediate the first portion and the second portion.
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公开(公告)号：US20210071684A1
公开(公告)日：2021-03-11
申请号：US16564478
申请日：2019-09-09
Applicant: United Technologies Corporation
Inventor： Robert R. Mayer , Peter F. Gero , Tracy A. Propheter-Hinckley
Abstract: An assembly is provided for a variable vane arrangement of a turbine engine. A platform extends circumferentially about a centerline and radially relative to the centerline between a first platform side and a second platform side. The platform includes a plurality of variable vane receptacles arranged in an annular array about the axial centerline, which variable vane receptacles include a first variable vane receptacle. The first variable vane receptacle is configured with a recess, a bore and a shelf. The recess extends longitudinally along a variable vane pivot axis into the platform from the first platform side to the shelf. The bore extends longitudinally along the variable vane pivot axis into the platform from the shelf. An insert includes a sleeve and a plate. The sleeve lines at least a portion of the bore. The plate is located within the recess adjacent the shelf.
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205.发明授权公开(公告)号：US10914320B2
公开(公告)日：2021-02-09
申请号：US15112032
申请日：2015-01-23
Applicant: United Technologies Corporation
Abstract: A blade is provided for a gas turbine engine. The blade includes an airfoil portion with at least one internal cavity and a damper located within the internal cavity. The damper includes a cantilever spring arm. A fan blade is provided for a gas turbine engine. The fan blade includes an airfoil portion with at least one internal cavity; and a damper located within the internal cavity. The damper includes a cantilever spring arm that terminates with a rub surface pad adjacent to a friction bridge between a concave pressure side and a convex suction side of the airfoil portion. A method is also provided for damping a blade of a gas turbine engine. The method includes deflecting a cantilever spring arm to contact a rub surface pad with a friction bridge between a concave pressure side and a convex suction side of an airfoil portion of the blade.
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Patent Agency Ranking
公开(公告)号：US20210033027A1
公开(公告)日：2021-02-04
申请号：US16527422
申请日：2019-07-31
Applicant: United Technologies Corporation
Inventor： Scott A. Kovach , Tracy A. Propheter-Hinckley
IPC: F02C7/18
Abstract: A method of fabricating a baffle for a gas turbine engine component includes providing a baffle that has a baffle wall that circumscribes an open interior region, the baffle wall defining two datum features, wherein at least one of the two datum features is semi-spherical, establishing a fixed reference position of the baffle in a fixture by engaging the two datum features with two corresponding locators on the fixture, and performing at least one operation on the baffle that is dependent upon the reference position.
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公开(公告)号：US10907479B2
公开(公告)日：2021-02-02
申请号：US15972429
申请日：2018-05-07
Applicant: United Technologies Corporation
Inventor： Timothy J. Jennings , Tracy A. Propheter-Hinckley , Kyle C. Lana
Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a leading edge and a trailing edge in an axial direction, between a pressure side and a suction side in a circumferential direction, and between a root and a tip in a radial direction, a first transitioning leading edge cavity located proximate the leading edge proximate the root of the airfoil body and transitioning axially toward the trailing edge as the first transitioning leading edge cavity extends radially toward the tip, and a second transitioning leading edge cavity located aft of the first transitioning leading edge cavity proximate the root of the airfoil body and transitioning axially toward the leading edge as the second transitioning leading edge cavity extends radially toward the tip. The second transitioning leading edge cavity includes an impingement sub-cavity and a film sub-cavity along the leading edge and proximate the tip.
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公开(公告)号：US20200378343A1
公开(公告)日：2020-12-03
申请号：US16425016
申请日：2019-05-29
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Tracy A. Propheter-Hinckley
Abstract: A passive centrifugal valve for a gas turbine engine. The passive centrifugal valve includes an inner section with a flow control inlet orifice, a cantilevered valve adjacent to the flow control inlet orifice, and an outer section with a seal land geometry that operates to at least partially support the cantilevered valve in response to a first centrifugal force that deflects the cantilevered valve away from the flow control inlet orifice.
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公开(公告)号：US20200347741A1
公开(公告)日：2020-11-05
申请号：US16806168
申请日：2020-03-02
Applicant: United Technologies Corporation
Inventor： Jonathan Ortiz , Raymond Surace , Renee J. Jurek , Tracy A. Propheter-Hinckley
Abstract: A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.
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公开(公告)号：US20200332663A1
公开(公告)日：2020-10-22
申请号：US16594379
申请日：2019-10-07
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Allan N. Arisi
Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends, and the airfoil wall circumscribes an internal core cavity. An arced rib extends from the first side to the second side and divides the internal core cavity into a forward cavity and an aft cavity. A cooling passage network is embedded in the airfoil wall aft of the rib and between inner and outer portions of the airfoil wall. The network includes a cooling passage leading edge and a cooling passage trailing edge. The aft core cavity has a central cavity section and a cavity lobe. The cavity lobe projects between the rib and the cooling passage leading edge.
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