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公开(公告)号：US09976423B2
公开(公告)日：2018-05-22
申请号：US14862422
申请日：2015-09-23
Applicant: United Technologies Corporation
Inventor： San Quach , Christopher King , Steven Bruce Gautschi , David J. Candelori
CPC classification number: F01D5/186 , F01D5/141 , F05D2240/303 , F05D2240/305 , F05D2240/306 , F05D2250/324 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.
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公开(公告)号：US20180023407A1
公开(公告)日：2018-01-25
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
CPC classification number: F01D9/065 , F01D5/186 , F01D5/187 , F01D25/12 , F01D25/14 , F05D2240/126 , F05D2260/20 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/673 , Y02T50/676
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：US20170298762A1
公开(公告)日：2017-10-19
申请号：US14615509
申请日：2015-02-06
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ryan Alan Waite , Steven Bruce Gautschi , Benjamin F. Hagan
CPC classification number: F01D9/065 , F01D5/186 , F01D5/187 , F01D25/12 , F01D25/14 , F05D2240/126 , F05D2260/20 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/676
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 from the pressure and suction side walls into the airfoil cavity and engage the baffle. 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 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：US20160326883A1
公开(公告)日：2016-11-10
申请号：US15107493
申请日：2015-01-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lane Thornton , Matthew A. Devore , Dominic J. Mongillo , Steven Bruce Gautschi
IPC: F01D5/18
Abstract: A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.
Abstract translation: 燃气涡轮发动机部件包括具有从前缘延伸到后缘的吸力侧和压力侧的翼型件。 在前缘附近有多个冷却孔，冷却孔具有非圆形形状，具有较长的尺寸和较小的尺寸。 翼型件限定从径向外端到径向内端的径向方向，并且冷却孔的径向外部与径向外端间隔开，其具有更靠近平行于径向的较长尺寸。 与径向外侧冷却孔相比，更靠近具有较长尺寸的径向内端的径向内部冷却孔相对于径向更接近垂直。
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公开(公告)号：US20160177734A1
公开(公告)日：2016-06-23
申请号：US14862422
申请日：2015-09-23
Applicant: United Technologies Corporation
Inventor： San Quach , Christopher King , Steven Bruce Gautschi , David J. Candelori
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/141 , F05D2240/303 , F05D2240/305 , F05D2240/306 , F05D2250/324 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.
Abstract translation: 本文所述的系统和方法根据外部气体/流线流动方向适应喷头冷却孔的取向，位置和/或扩散角。 例如，在停滞线处于压力侧的区域中，喷头孔的突破基本上向后（例如主要朝向吸力侧）。 孔的位置和定位可以根据进入的气流的方向定向。
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Patent Agency Ranking
公开(公告)号：US20150300258A1
公开(公告)日：2015-10-22
申请号：US14689168
申请日：2015-04-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dominic J. Mongillo , San Quach , Steven Bruce Gautschi , Brandon S. Donnell , Anita L. Tracy , Yafet Girma
CPC classification number: F01D5/186 , F05D2250/18 , F05D2250/31 , F05D2250/32 , F05D2260/202 , Y02T50/676
Abstract: A component for a gas turbine engine according to an exemplary aspect of this disclosure includes a surface having a plurality of cooling holes. The surface includes a first region and a second region each having a plurality of cooling holes. The cooling holes within the first region are arranged differently than the cooling holes in the second region.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件包括具有多个冷却孔的表面。 表面包括第一区域和第二区域，每个具有多个冷却孔。 第一区域内的冷却孔的布置与第二区域中的冷却孔不同。
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公开(公告)号：US11078796B2
公开(公告)日：2021-08-03
申请号：US16220400
申请日：2018-12-14
Applicant: United Technologies Corporation
Inventor： Christopher Perron , Justin M. Aniello , Shawn M. McMahon , Ricardo Trindade , Steven Bruce Gautschi , David Barger , Brett Alan Bartling , Nicholas J. Madonna , Robin Prenter , Ryan Lundgreen , Christopher Cosher , Mohamed Hassan
Abstract: A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.
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公开(公告)号：US11008872B2
公开(公告)日：2021-05-18
申请号：US16220398
申请日：2018-12-14
Applicant: United Technologies Corporation
Inventor： Christopher Perron , Justin M. Aniello , Shawn M. McMahon , Ricardo Trindade , Steven Bruce Gautschi , David Barger , Brett Alan Bartling , Nicholas J. Madonna , Robin Prenter , Ryan Lundgreen , Christopher Cosher , Mohamed Hassan
Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.
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公开(公告)号：US10690346B2
公开(公告)日：2020-06-23
申请号：US15476431
申请日：2017-03-31
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Atul Kohli , Dustin W. Davis , Ricardo Trindade , Steven Bruce Gautschi , Brandon W. Spangler , Trevor Rudy , Benjamin Bellows , Dave J. Hyland , James B. Hoke , Stephen K. Kramer , Dennis M. Moura
Abstract: A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.
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公开(公告)号：US10670274B2
公开(公告)日：2020-06-02
申请号：US15699514
申请日：2017-09-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin D Bellows , Brandon W Spangler , David J Hyland , James B Hoke , Ricardo Trindade , Steven Bruce Gautschi
Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.
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