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公开(公告)号：US20190176228A1
公开(公告)日：2019-06-13
申请号：US16275468
申请日：2019-02-14
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Lane Thornton , Sasha M. Moore , Nicholas M. LoRicco
Abstract: A gas turbine engine includes a structure that has walls that provide a cooling passage and a cooling surface. A non-ferrous obstruction is relative to the walls. The obstruction includes a portion spaced from the cooling surface to provide a gap which is configured to receive a cooling fluid.
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公开(公告)号：US09714580B2
公开(公告)日：2017-07-25
申请号：US14907461
申请日：2014-07-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Sasha M. Moore , Nicholas M. LoRicco
CPC classification number: F01D11/008 , F01D11/006 , F04D29/083 , F04D29/542 , F05D2220/32 , F05D2240/55 , F05D2250/75 , F16J15/06 , F16J15/062 , F16J15/0887
Abstract: This disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal provided between the mate face of the first engine component and the mate face of the second engine component. The seal includes least one trough.
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公开(公告)号：US20190218916A1
公开(公告)日：2019-07-18
申请号：US16365943
申请日：2019-03-27
Applicant: United Technologies Corporation
Inventor： Sarah Riley , Sasha M. Moore , Jeffrey R. Levine
CPC classification number: F01D5/186 , F01D5/189 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/122 , F05D2240/124 , F05D2240/30 , F05D2260/201 , F05D2260/202 , Y02T50/672 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.
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公开(公告)号：US10253634B2
公开(公告)日：2019-04-09
申请号：US14892713
申请日：2014-04-25
Applicant: United Technologies Corporation
Inventor： Sarah Riley , Sasha M. Moore , Jeffrey R. Levine
Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.
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公开(公告)号：US20160177767A1
公开(公告)日：2016-06-23
申请号：US14907461
申请日：2014-07-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Sasha M. Moore , Nicholas M. LoRicco
CPC classification number: F01D11/008 , F01D11/006 , F04D29/083 , F04D29/542 , F05D2220/32 , F05D2240/55 , F05D2250/75 , F16J15/06 , F16J15/062 , F16J15/0887
Abstract: This disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal provided between the mate face of the first engine component and the mate face of the second engine component. The seal includes least one trough.
Abstract translation: 本公开涉及一种包括第一发动机部件和第二发动机部件的燃气涡轮发动机。 第一发动机部件具有与第二发动机部件的配合面相邻的配合面。 发动机还包括设置在第一发动机部件的配合面与第二发动机部件的配合面之间的密封件。 密封件包括至少一个槽。
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Patent Agency Ranking
6.发明申请公开(公告)号：US20150375297A1
公开(公告)日：2015-12-31
申请号：US14766061
申请日：2014-01-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Lane Thornton , Sasha M. Moore , Nicholas M. LoRicco
CPC classification number: B22D19/0072 , B22C9/04 , B22C9/103 , F01D5/187 , F01D9/023 , F05D2230/211 , F05D2250/185 , F23R3/002 , Y02T50/676
Abstract: A method of manufacturing a component that includes providing a core structure, casting a component about the core structure, removing a first portion of the core structure from the cast component, and leaving a second portion of the core structure in the cast component to provide a reduced cross-section in the cast component.
Abstract translation: 一种制造组件的方法，所述方法包括提供芯结构，围绕所述芯结构铸造部件，从所述铸造部件移除所述芯结构的第一部分，以及将所述芯结构的第二部分留在所述铸造部件中，以提供 减少铸件中的横截面积。
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公开(公告)号：US20180245470A1
公开(公告)日：2018-08-30
申请号：US15966049
申请日：2018-04-30
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, JR. , Jeffrey R. Levine , Kyle C. Lana , Sasha M. Moore
CPC classification number: F01D5/186 , F01D5/187 , F01D5/20 , F05D2240/307 , F05D2260/2214 , F05D2260/22141 , Y02T50/673 , Y02T50/676
Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform extending from a root section, an airfoil section extending radially from the platform to an airfoil tip, a plurality of cooling passages defined in an external wall of the airfoil tip, the plurality of cooling passages extending radially between the airfoil tip and a cavity in the airfoil section bounded by the external wall, and each of the plurality of cooling passages defining an inlet port along the cavity and an exit port adjacent the airfoil tip, and at least one internal feature within each of the plurality of cooling passages that meter flow to the respective exit port.
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公开(公告)号：US20160230564A1
公开(公告)日：2016-08-11
申请号：US14619343
申请日：2015-02-11
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, JR. , Jeffrey R. Levine , Kyle C. Lana , Sasha M. Moore
CPC classification number: F01D5/186 , F01D5/187 , F01D5/20 , F05D2240/307 , F05D2260/2214 , F05D2260/22141 , Y02T50/673 , Y02T50/676
Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform, an airfoil tip, and an airfoil section between the platform and the airfoil tip. The airfoil section has a cavity spaced radially from the airfoil tip and a plurality of cooling passages radially between the cavity and the airfoil tip. Each of the plurality of cooling passages defines an exit port adjacent the airfoil tip. An internal feature within each of the plurality of cooling passages is configured to meter flow to the exit port.
Abstract translation: 根据本公开的示例的涡轮叶片包括平台，翼型末端以及平台和翼型顶端之间的翼型部分。 机翼部分具有与翼型件末端径向间隔开的空腔和在空腔和翼型端之间径向放置的多个冷却通道。 多个冷却通道中的每一个限定了与翼型件末端相邻的出口。 多个冷却通道内的每个内部特征被配置成计量到出口的流量。
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公开(公告)号：US20160201475A1
公开(公告)日：2016-07-14
申请号：US14854606
申请日：2015-09-15
Applicant: United Technologies Corporation
Inventor： Sasha M. Moore , Timothy J. Jennings , Thomas N. Slavens , Clifford J. Musto , Nicholas M. LoRicco , Carey Clum , John McBrien , Christopher Whitfield , San Quach
CPC classification number: F01D5/187 , F01D5/186 , F01D9/041 , F01D9/065 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2240/12 , F05D2240/127 , F05D2240/30 , F05D2240/81 , F05D2260/202 , F23R2900/03041 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.
Abstract translation: 燃气涡轮发动机部件包括具有围绕内部空腔的壁的主体。 墙壁与内部和外部表面相对。 内表面具有多个冷却剂入口，并且外表面具有限定在其中的冷却剂出口。 冷却剂导管在冷却剂入口和冷却剂出口之间延伸，并且被构造和适于在冷却剂中引导二次流动涡流，所述冷却剂穿过冷却剂管道以及在组件主体的外表面的一部分上的粘附冷却剂膜中。
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公开(公告)号：US20160177738A1
公开(公告)日：2016-06-23
申请号：US14831997
申请日：2015-08-21
Applicant: United Technologies Corporation
Inventor： Sasha M. Moore , Clifford J. Musto , Timothy J. Jennings , Thomas N. Slavens , San Quach , Nicholas M LoRicco , John McBrien , Carey Clum , Christopher Whitfield
IPC: F01D5/18 , F01D11/08 , F01D25/12 , F02C7/18 , F04D29/54 , F04D29/58 , F02C3/04 , F01D9/04 , F04D29/32
Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. The wall has a wall thickness. A protrusion is arranged on the wall that extends a height beyond the wall thickness and provides a portion of the interior flow path surface. A film cooling hole that has an inlet is provided on the protrusion and extends to an exit on the exterior surface.
Abstract translation: 燃气涡轮发动机部件包括提供外表面和内部流路表面的壁。 墙壁有壁厚。 突出部设置在壁上，其高度超过壁厚，并提供内部流路表面的一部分。 具有入口的薄膜冷却孔设置在突起上并延伸到外表面上的出口。
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