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公开(公告)号：US10323525B2
公开(公告)日：2019-06-18
申请号：US14903467
申请日：2014-06-17
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic J. Mongillo, Jr.
Abstract: A gas turbine engine component includes a structure having a wall that provides an exterior surface. A first cooling passage is arranged adjacent to and interiorly of the wall. A second cooling passage is arranged in the wall and provides a first fluid flow direction. A resupply channel is arranged in the wall and is fluidly interconnected to the second cooling passage. A resupply hole fluidly interconnects the first cooling passage and the resupply channel. The resupply channel is transverse relative to the second cooling passage to provide a second fluid flow direction that extends from the resupply hole to the second cooling passage.
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公开(公告)号：US10253635B2
公开(公告)日：2019-04-09
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
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：US09995165B2
公开(公告)日：2018-06-12
申请号：US14735415
申请日：2015-06-10
Applicant: United Technologies Corporation
Inventor： Christopher R. Joe , Paul M. Lutjen , Dominic J. Mongillo, Jr.
CPC classification number: F01D11/08 , F05D2230/90 , F05D2250/292 , F05D2260/202 , Y02T50/676
Abstract: A blade outer air seal member includes a distinct body that has two circumferential sides, a leading edge and a trailing edge, and a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side. The ceramic coating includes a forward coating portion and an aft coating portion. The gas path side has a bare area axially separating the forward coating portion and the aft coating portion. The bare area excludes any of the ceramic coating. One or more cooling passages have an outlet that opens at the bare area. The cooling passage extends in the body in an axial direction under the ceramic coating.
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公开(公告)号：US09284845B2
公开(公告)日：2016-03-15
申请号：US14250166
申请日：2014-04-10
Applicant: United Technologies Corporation
IPC: F01D5/20
CPC classification number: F01D5/20 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: An airfoil comprises pressure and suction surfaces extending from a root section to a tip section of the airfoil. The airfoil also comprises a leading edge and trailing edge defining a chord length therebetween. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall, the tip shelf wall being spaced between the pressure surface and the suction surface. A squealer pocket is formed along the tip section between the tip shelf wall and a squealer tip wall extending from the suction surface. The tip shelf extends from within 10% of the cord length measured from the leading edge to within 10% of the chord length measured from the trailing edge. The squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate less than 85% of the chord length measured from the trailing edge.
Abstract translation: 翼型件包括从根部延伸到翼型的尖端部分的压力和吸力表面。 翼型件还包括在其间限定弦长的前缘和后缘。 沿着压力表面和尖端搁板壁之间的尖端部分形成尖端搁板，顶部搁板壁在压力表面和吸力表面之间分开。 沿尖端搁架壁和从抽吸面延伸的尖叫尖端壁之间的尖端部分形成一个尖叫口袋。 尖端架从从前缘测量的绳索长度的10％范围内延伸到从后缘测量的弦长的10％以内。 尖叫口袋从前缘测量的弦长的10％范围内延伸，以终止从后缘测得的弦长的85％以下。
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