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公开(公告)号：US11377965B2
公开(公告)日：2022-07-05
申请号：US15450087
申请日：2017-03-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Shawn J. Gregg , Dominic J. Mongillo , Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer
Abstract: A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.
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公开(公告)号：US20160160656A1
公开(公告)日：2016-06-09
申请号：US14957731
申请日：2015-12-03
Applicant: United Technologies Corporation
Inventor： Russell J. Bergman , Jason B. Moran , Mohammed Ennacer
CPC classification number: F01D25/12 , F01D9/041 , F05D2240/12 , F05D2240/81 , F05D2250/74 , F05D2260/202 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. At least one of the inner and outer platforms includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1 for the inner platform or Table 2 for the outer platform. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).
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公开(公告)号：US10107140B2
公开(公告)日：2018-10-23
申请号：US14957686
申请日：2015-12-03
Applicant: United Technologies Corporation
Inventor： Mohammed Ennacer , Russell J. Bergman , Jason B. Moran
Abstract: A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. The airfoil includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in one of Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).
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Patent Agency Ranking
公开(公告)号：US20160194966A1
公开(公告)日：2016-07-07
申请号：US14957686
申请日：2015-12-03
Applicant: United Technologies Corporation
Inventor： Russell J. Bergman , Jason B. Moran , Mohammed Ennacer
CPC classification number: F01D25/12 , F01D5/186 , F01D9/041 , F01D9/065 , F05D2250/74 , F05D2260/202 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. The airfoil includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in one of Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).
Abstract translation: 涡轮机翼段包括通过至少一个翼型件连接的内平台和外平台。 翼型件包括通过间隔开的第一和第二侧连接以提供外部翼面表面的前缘和后缘。 翼型件包括具有大致符合表1和表2中所示的笛卡尔坐标的外部突出点的膜冷却孔。笛卡尔坐标由轴向坐标，圆周坐标和径向坐标提供， 相对于零坐标，并且膜冷却孔相对于0.20英寸（5.0mm）的指定坐标具有径向表面公差。
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公开(公告)号：US10301966B2
公开(公告)日：2019-05-28
申请号：US14957731
申请日：2015-12-03
Applicant: United Technologies Corporation
Inventor： Mohammed Ennacer , Russell J. Bergman , Jason B. Moran
Abstract: A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. At least one of the inner and outer platforms includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1 for the inner platform or Table 2 for the outer platform. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).
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公开(公告)号：US20160160654A1
公开(公告)日：2016-06-09
申请号：US14953745
申请日：2015-11-30
Applicant: United Technologies Corporation
Inventor： Mohammed Ennacer , Russell J. Bergman , Jason B. Moran
CPC classification number: F01D25/12 , F01D9/041 , F05D2240/12 , F05D2240/81 , F05D2250/74 , F05D2260/202 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. At least one of the inner and outer platforms includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1 for the inner platform or Table 2 for the outer platform. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).
Abstract translation: 涡轮机翼段包括通过至少一个翼型件连接的内平台和外平台。 翼型件包括通过间隔开的第一和第二侧连接以提供外部翼面表面的前缘和后缘。 内平台和外平台中的至少一个包括膜冷却孔，其具有基本符合表1中针对内平台或外平台的表2所示的笛卡尔坐标的外部突出点。 相对于零坐标，笛卡尔坐标由轴向坐标，圆周坐标和径向坐标提供。 薄膜冷却孔相对于0.20英寸（5.0mm）的指定坐标具有径向表面公差。
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公开(公告)号：US10443434B2
公开(公告)日：2019-10-15
申请号：US14953745
申请日：2015-11-30
Applicant: United Technologies Corporation
Inventor： Mohammed Ennacer , Russell J. Bergman , Jason B. Moran
Abstract: A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. At least one of the inner and outer platforms includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1 for the inner platform or Table 2 for the outer platform. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).
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公开(公告)号：US20170175631A1
公开(公告)日：2017-06-22
申请号：US15450087
申请日：2017-03-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Shawn J. Gregg , Dominic J. Mongillo , Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer
CPC classification number: F01D5/188 , F01D5/187 , F01D5/189 , F01D9/041 , F01D25/12 , F02C7/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/126 , F05D2240/30 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.
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