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公开(公告)号：JP2002364305A
公开(公告)日：2002-12-18
申请号：JP2002137990
申请日：2002-05-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KOHLI ATUL , WAGNER JOEL H , AGGARWALA ANDREW S
Abstract: PROBLEM TO BE SOLVED: To provide a film cooling system with high cost performance for facilitating the sideways expansion and secure adhesion of a cooling jet 70 over a high temperature face 24 of an article. SOLUTION: The article having a wall with the high temperature face 24 such as a blade or vane of a turbine engine comprises a recess 48 characterized by a descending side face 52 and an ascending side face 54. A cooling hole 6 bored on the wall 24 includes an outlet located on the ascending side face 54. When the article is operated, the cooling jet 70 is discharged from the outlet and a primary fluid flow F flowing on the ascending side face 54 is locally over-accelerated by the recess 48. The local over-acceleration of the primary fluid flow F turns the cooling jet 70 to flow on the high temperature face 24 to facilitate sideways expansion of the jet and formation of a protective cooling film continuing sideways together with the expanded jet.
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公开(公告)号：WO2013165507A3
公开(公告)日：2014-01-16
申请号：PCT/US2013025705
申请日：2013-02-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GLEINER MATTHEW S , KOHLI ATUL , ZELESKY MARK F
CPC classification number: F01D5/186 , F01D9/065 , F05D2240/81 , F05D2250/324 , F05D2250/73 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/00018 , F23R2900/03042 , Y02T50/676 , Y10T29/49323
Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section.
Abstract translation: 燃气涡轮发动机部件包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 漫射部分包括从计量部分纵向分散的第一凸角和邻近第一凸角的第二凸角并且从计量部分纵向和横向发散。
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公开(公告)号：WO2013165502A3
公开(公告)日：2014-01-03
申请号：PCT/US2013025680
申请日：2013-02-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KOHLI ATUL , GLEINER MATTHEW S , ZELESKY MARK F , XU JINQUAN
CPC classification number: F23R3/06 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge.
Abstract translation: 燃气涡轮发动机包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 扩散部分包括从计量部分纵向和横向分叉的第一凸角，从计量部分纵向和横向分开的第二凸角，位于出口处的上游端，位于与上游端相对的出口处的后缘， 第一和第二侧壁。 每个侧壁具有沿着上游端和后缘之间的出口延伸的边缘。 每个边缘从上游端横向分开，并在到达后缘之前横向会聚。
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公开(公告)号：WO2013165509A2
公开(公告)日：2013-11-07
申请号：PCT/US2013025711
申请日：2013-02-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KOHLI ATUL , GLEINER MATTHEW S
CPC classification number: F01D5/18 , F01D5/186 , F01D5/187 , F01D9/065 , F05D2240/81 , F05D2250/73 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe, a second lobe and a transition region. The first lobe diverges longitudinally and laterally from the metering section and has a first shape. The second lobe is generally opposite the first lobe and diverges longitudinally and laterally from the metering section and has a second shape different from the first shape. The transition region is positioned between the first and second lobes and includes a downstream end adjacent the outlet.
Abstract translation: 经受高温气体流动的燃气涡轮发动机部件包括具有第一和第二壁表面以及延伸穿过该壁的冷却孔的壁。 冷却孔包括位于第一壁表面处的入口，位于第二壁表面处的出口，从入口向下游延伸的计量部分以及从计量部分延伸至出口的扩散部分。 扩散部分包括第一叶片，第二叶片和过渡区域。 第一叶从计量部分纵向和横向分叉并具有第一形状。 第二叶片大体上与第一叶片相对并且从计量部分纵向和横向分叉并且具有不同于第一形状的第二形状。 过渡区位于第一和第二叶片之间并包括邻近出口的下游端。
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公开(公告)号：DE60218776D1
公开(公告)日：2007-04-26
申请号：DE60218776
申请日：2002-05-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KOHLI ATUL , WAGNER JOEL H , AGGARWALA ANDREW S
Abstract: The invention resides in a film cooled article such as a turbine engine blade or vane, having a wall with a hot surface (26) to be film cooled. The hot surface (26) includes a depression (48) featuring a descending flank (52) and an ascending flank (54) . Coolant holes (60) , which penetrate through the wall, have discharge openings residing on the ascending flank (54) . During operation, the depression locally over-accelerates a primary fluid stream F flowing over the ascending flank while coolant jets (70) concurrently issue from the discharge openings. The local over-acceleration of the primary fluid deflects the jets onto the hot surface and spatially constrains the jets thus encouraging them to spread out laterally and coalesce into a laterally continuous, protective coolant film. In one embodiment, the depression (48) is a trough (50) . In another embodiment, the depression is a dimple (72) .
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Patent Agency Ranking
公开(公告)号：WO2015088699A1
公开(公告)日：2015-06-18
申请号：PCT/US2014065430
申请日：2014-11-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEWIS SCOTT D , KOHLI ATUL , PRAISNER THOMAS J
CPC classification number: F01D11/08 , F01D5/12 , F01D5/143 , F01D9/02 , F01D11/006 , F05D2220/32 , F05D2240/11 , F05D2240/80 , F05D2250/192 , F05D2250/231
Abstract: An array of components in a gas turbine engine includes first and second structures respectively including first and second surfaces that are arranged adjacent to one another to provide a gap. The first and second surfaces respectively have first and second rounded edges at the gap that are arranged in staggered relationship relative to one another.
Abstract translation: 燃气涡轮发动机中的部件阵列包括第一和第二结构，第一和第二结构分别包括彼此相邻布置以提供间隙的第一和第二表面。 第一和第二表面分别在间隙处具有第一和第二圆形边缘，这些边缘相对于彼此以交错关系布置。
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公开(公告)号：WO2013165510A3
公开(公告)日：2014-01-09
申请号：PCT/US2013025715
申请日：2013-02-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： XU JINQUAN , ZELESKY MARK F , KOHLI ATUL , GLEINER MATTHEW S
CPC classification number: F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , Y02T50/676 , Y10T29/49323
Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet at the first wall surface, an outlet at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally from the metering section, a third lobe adjacent the second lobe and diverging longitudinally and laterally from the metering section, and a transition region having an end adjacent the outlet and a portion that extends between the lobes and the outlet. The first and third lobes each include a curved outer portion.
Abstract translation: 燃气涡轮发动机部件包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 冷却孔包括在第一壁表面处的入口，在第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 扩散部分包括从计量部分纵向和横向分散的第一凸角，与第一凸角相邻并且从计量部分纵向发散的第二凸角，邻近第二凸角并从计量部分纵向和横向发散的第三凸角，以及 过渡区域具有邻近出口的端部和在凸角和出口之间延伸的部分。 第一和第三瓣每个包括弯曲的外部部分。
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公开(公告)号：DE60218776T2
公开(公告)日：2007-12-06
申请号：DE60218776
申请日：2002-05-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KOHLI ATUL , WAGNER JOEL H , AGGARWALA ANDREW S
Abstract: The invention resides in a film cooled article such as a turbine engine blade or vane, having a wall with a hot surface (26) to be film cooled. The hot surface (26) includes a depression (48) featuring a descending flank (52) and an ascending flank (54) . Coolant holes (60) , which penetrate through the wall, have discharge openings residing on the ascending flank (54) . During operation, the depression locally over-accelerates a primary fluid stream F flowing over the ascending flank while coolant jets (70) concurrently issue from the discharge openings. The local over-acceleration of the primary fluid deflects the jets onto the hot surface and spatially constrains the jets thus encouraging them to spread out laterally and coalesce into a laterally continuous, protective coolant film. In one embodiment, the depression (48) is a trough (50) . In another embodiment, the depression is a dimple (72) .
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公开(公告)号：SG138539A1
公开(公告)日：2008-01-28
申请号：SG2007040470
申请日：2007-06-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KOHLI ATUL , STAUBACH JOSEPH B , DOLL STEPHEN D
Abstract: A cooling hole for a gas turbine engine component has a bi-lobed shape to improve cooling effectiveness. The gas turbine engine component has a first outer surface and a second outer surface separated from each other by a thickness. The cooling hole extends through the thickness from a first opening at the first outer surface to a second opening at the second outer surface. The first and second openings are defined by shapes that are different from each other. One of the first and second openings has the bi- lobed shape.
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公开(公告)号：EP2815103A4
公开(公告)日：2016-01-06
申请号：EP13784334
申请日：2013-02-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KOHLI ATUL , GLEINER MATTHEW S , ZELESKY MARK F , XU JINQUAN
CPC classification number: F23R3/06 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge.
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