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Patent Agency Ranking
公开(公告)号：US10208602B2
公开(公告)日：2019-02-19
申请号：US14697329
申请日：2015-04-27
Applicant: United Technologies Corporation
Inventor： Lane Thornton , Ryan Alan Waite , Peter Balawajder , Benjamin F. Hagan
Abstract: A film cooled component may comprise a cooling chamber and a first ligament centered about a first axis. The first ligament may be in fluid communication with the cooling chamber. A first meter may be disposed at an end of the first ligament. A first diffuser may extend from the first meter to a surface of the film cooled component. The first diffuser may comprise a first tapered sidewall oriented at an angle of between 5 degrees to 15 degrees relative to the first axis. The first diffuser may further comprise a first non-tapered sidewall oriented at an angle less than 5 degrees relative to the first axis.
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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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公开(公告)号：US20180066532A1
公开(公告)日：2018-03-08
申请号：US15810279
申请日：2017-11-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Lane Thornton
CPC classification number: F01D9/065 , F01D5/147 , F01D5/186 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/125 , F05D2240/307 , F05D2240/81 , F05D2250/75 , Y02T50/676
Abstract: An assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including a radial end, a first passageway having an outlet at the radial end, and a second passageway having an inlet at the radial end. The assembly further includes a cover having at least one turning cavity configured to direct fluid expelled from the outlet of the first passageway into the inlet of the second passageway.
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34.发明申请公开(公告)号：US20160298465A1
公开(公告)日：2016-10-13
申请号：US15101244
申请日：2014-12-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Charles Thistle , Lane Thornton
CPC classification number: F01D5/187 , F01D5/081 , F01D5/186 , F01D5/3007 , F01D25/12 , F05D2220/32 , F05D2230/50 , F05D2240/12 , F05D2240/35 , F05D2240/55 , F05D2260/202 , F05D2260/22141 , F23R3/002
Abstract: A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A pedestal is arranged in the cooling passage and interconnects the walls in a thickness direction that is transverse to the first direction. The pedestal is asymmetrical in the thickness direction.
Abstract translation: 燃气涡轮发动机部件包括间隔开的壁，其提供沿第一方向延伸的冷却通道。 在冷却通道中布置有基座，并且在横向于第一方向的厚度方向上将壁互连。 基座在厚度方向上是不对称的。
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公开(公告)号：US20160298462A1
公开(公告)日：2016-10-13
申请号：US14682207
申请日：2015-04-09
Applicant: United Technologies Corporation
Inventor： Lane Thornton , Thomas N. Slavens
CPC classification number: F01D5/186 , B22C9/24 , F01D9/041 , F01D11/08 , F01D25/12 , F02C3/00 , F02C7/18 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/22 , F05D2240/12 , F05D2240/30 , F05D2240/35 , F05D2260/202 , Y02T50/676
Abstract: A gas turbine engine component includes a wall which includes a first surface and a second surface opposing the first surface. A plurality of cooling passages extends between the first surface and the second surface each including a metering portion and a diffusion portion. The diffusion portion includes a cast or as-consolidated surface.
Abstract translation: 燃气涡轮发动机部件包括壁，该壁包括第一表面和与第一表面相对的第二表面。 多个冷却通道在第一表面和第二表面之间延伸，每个包括计量部分和扩散部分。 扩散部分包括铸造或固结表面。
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