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公开(公告)号：US20200291790A1
公开(公告)日：2020-09-17
申请号：US16415199
申请日：2019-05-17
Applicant: United Technologies Corporation
Inventor： Steven Taffet , Brandon S. Donnell , Daniel C. Nadeau , Russell Deibel , San Quach
Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.
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公开(公告)号：US10689988B2
公开(公告)日：2020-06-23
申请号：US14683408
申请日：2015-04-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven Bruce Gautschi , San Quach , Tracy A Propheter-Hinckley
Abstract: A component for a gas turbine engine includes a root with a neck that extends into a fir tree with at least one tooth, the root includes a feed passage in communication with a multiple of cooling passages that extend through the neck and fir tree.
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公开(公告)号：US20200024970A1
公开(公告)日：2020-01-23
申请号：US16397180
申请日：2019-04-29
Applicant: United Technologies Corporation
Inventor： Eric A. Hudson , Tracy A. Propheter-Hinckley , San Quach , Matthew A. Devore
Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.
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公开(公告)号：US10385699B2
公开(公告)日：2019-08-20
申请号：US14632485
申请日：2015-02-26
Applicant: United Technologies Corporation
Inventor： San Quach , Ryan Alan Waite , Christopher King , Steven Bruce Gautschi
Abstract: An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.
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公开(公告)号：US10370980B2
公开(公告)日：2019-08-06
申请号：US15039918
申请日：2014-11-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven Taffet , Brandon S. Donnell , Daniel C. Nadeau , Russell Deibel , San Quach
Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.
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Patent Agency Ranking
公开(公告)号：US20190078445A1
公开(公告)日：2019-03-14
申请号：US15700990
申请日：2017-09-11
Applicant: United Technologies Corporation
Inventor： San Quach , Jeffrey T. Morton
IPC: F01D5/18
Abstract: An airfoil includes an airfoil body having a pressure side and a suction side that each radially extend between a first radial boundary end and a second radial boundary end and each axially extend between a leading edge and a trailing edge. The airfoil body defines a plurality of first skin core passages disposed proximate the suction side and radially extend from the first radial boundary end towards the second radial boundary end, and a plurality of second skin core passages that radially extend toward the second radial boundary end and circumferentially extend towards the suction side proximate the second radial boundary end.
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公开(公告)号：US10196900B2
公开(公告)日：2019-02-05
申请号：US14882899
申请日：2015-10-14
Applicant: United Technologies Corporation
Inventor： Christopher King , San Quach
Abstract: A turbomachine component includes a body defining an interior cooling channel in fluid communication with the exterior of the body for fluid communication with a cooling flow source. At least one flow modifying pedestal is disposed within the interior cooling channel extending in a first direction. The flow modifying pedestal includes at least one flow feature that extends from the pedestal in a second direction.
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公开(公告)号：US10190420B2
公开(公告)日：2019-01-29
申请号：US14618912
申请日：2015-02-10
Applicant: United Technologies Corporation
Inventor： Christopher King , San Quach , Steven Bruce Gautschi
Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a reference plane extending in a spanwise direction along a surface of the internal wall, a first cavity and a second cavity separated by the internal wall, and a plurality of crossover passages within the internal wall and connecting the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The passage axis of each of the plurality of crossover passages is arranged at a radial angle relative to a localized region of the reference plane such that the radial angle of at least some of the plurality of crossover passages differs in the spanwise direction.
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公开(公告)号：US20190017390A1
公开(公告)日：2019-01-17
申请号：US15997943
申请日：2018-06-05
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Steven Bruce Gautschi , San Quach
Abstract: A method of manufacturing a component for a gas turbine engine according to an exemplary aspect of the present disclosure includes forming the component with a first manufacturing technique to include a first cavity and a second cavity, and a microcircuit in fluid communication with the first cavity, the component including an outer wall and a ribbed portion or a bulged portion extending from the outer wall. The exemplary method includes forming a plunged hole with a second manufacturing technique different from the first manufacturing technique to intersect at least a portion of the microcircuit and extend into the ribbed portion or the bulged portion.
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公开(公告)号：US20180281051A1
公开(公告)日：2018-10-04
申请号：US15960857
申请日：2018-04-24
Applicant: United Technologies Corporation
Inventor： Lane Thornton , San Quach , Steven Bruce Gautschi
Abstract: In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component. A method of molding a gas turbine engine component is also disclosed.
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