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公开(公告)号：US20150260048A1
公开(公告)日：2015-09-17
申请号：US14644709
申请日：2015-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven Bruce Gautschi , San Quach
IPC: F01D5/18
CPC classification number: F01D5/18 , F01D5/186 , F05D2240/127 , F05D2240/303 , F05D2250/25 , F05D2250/281 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/2212 , Y02T50/676
Abstract: One exemplary embodiment of this disclosure relates to a component for a gas turbine engine. The component includes a cooling hole having a wall with at least one helical groove formed in the wall.
Abstract translation: 本公开的一个示例性实施例涉及一种用于燃气涡轮发动机的部件。 该部件包括冷却孔，该冷却孔具有形成在壁中的至少一个螺旋槽的壁。
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公开(公告)号：US11156101B2
公开(公告)日：2021-10-26
申请号：US16858955
申请日：2020-04-27
Applicant: United Technologies Corporation
Inventor： San Quach , Tracy A. Propheter-Hinckley , Steven Bruce Gautschi
Abstract: A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.
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公开(公告)号：US10830096B2
公开(公告)日：2020-11-10
申请号：US14917434
申请日：2014-09-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Steven Bruce Gautschi
Abstract: A pivoting turbine vane has an airfoil, an inner bearing race and an outer bearing race, with the inner and outer bearing races on a pivot axis of the pivoting turbine vane. There are cooling air passages through at least one of the inner and outer bearing races to provide cooling air from a remote facing face of at least one of the inner and outer bearing races to an airfoil facing face of at least one of the inner and outer bearing races. A turbine section is also disclosed.
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公开(公告)号：US10821500B2
公开(公告)日：2020-11-03
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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公开(公告)号：US10648363B2
公开(公告)日：2020-05-12
申请号：US15856232
申请日：2017-12-28
Applicant: United Technologies Corporation
Inventor： Shawn M. McMahon , Christopher Whitfield , Nicholas M. LoRicco , Steven Bruce Gautschi , Vincent E. Simms , Justin M. Aniello , Thomas Allwood , Richard M. Salzillo , Jeffery Scott Hembree, Sr.
Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
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Patent Agency Ranking
公开(公告)号：US10533425B2
公开(公告)日：2020-01-14
申请号：US15856182
申请日：2017-12-28
Applicant: United Technologies Corporation
Inventor： Shawn M. McMahon , Christopher Whitfield , Nicholas M. LoRicco , Steven Bruce Gautschi , Vincent E. Simms , Justin M. Aniello , Thomas Allwood , Richard M. Salzillo , Jeffery Scott Hembree, Sr.
Abstract: A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.
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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：US10202903B2
公开(公告)日：2019-02-12
申请号：US14861601
申请日：2015-09-22
Applicant: United Technologies Corporation
Inventor： Shayan Ahmadian , Steven Bruce Gautschi , Mark F. Zelesky
Abstract: A particle separator for removing particles in a flow of air is provided. The particle separator having: a conduit for directing air towards a curved section of the conduit; and a drum in fluid communication with the conduit proximate to the curved section of the conduit, wherein particles in the air travelling towards the curved section will contact a surface of the drum.
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公开(公告)号：US20180274373A1
公开(公告)日：2018-09-27
申请号：US15995884
申请日：2018-06-01
Applicant: United Technologies Corporation
Inventor： San Quach , Tracy A. Propheter-Hinckley , Steven Bruce Gautschi
CPC classification number: F01D5/187 , F01D5/147 , F01D5/186 , F01D5/20 , F05D2220/32 , F05D2260/202 , F05D2260/221 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , Y02T50/676
Abstract: A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.
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公开(公告)号：US20180214941A1
公开(公告)日：2018-08-02
申请号：US15421502
申请日：2017-02-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lea Kennard Castle , Steven Bruce Gautschi , James Tilsley Auxier
Abstract: A method of forming a component includes the steps of placing a core into a mold and pouring a component material around the core. The component material is allowed to solidify. The core is then removed from within the material, leaving a component having at least a first and a second cavity formed by the core. A first filler material is moved into the first cavity, and a second filler material is moved into the second cavity. The component is inspected for the presence of an apparent residual core within the first cavity and the second cavity. The location is identified of the apparent residual core from the core based upon an identification of whether the location of the apparent residual core is in the first or second filler materials. A method of inspecting a component formed by investment casting is also disclosed.
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