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公开(公告)号：WO2015026416A2
公开(公告)日：2015-02-26
申请号：PCT/US2014/039710
申请日：2014-05-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： KNOWLTON, Robert , ASTERLIN, Max , RAPP, Brandon, M. , JARIWALA, Parth
IPC: F01D5/16
CPC classification number: F01D5/10 , F01D5/081 , F01D5/18 , F01D5/26 , F01D11/006 , F05D2240/57 , F05D2260/96 , Y02T50/676
Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.
Abstract translation: 描述了一种涡轮叶片减振器。 阻尼器具有限定内表面和相对的阻尼表面的轴向延伸主体。 主体还具有从内表面延伸到阻尼表面的边缘和延伸穿过主体的开槽孔。 开槽孔在内表面和阻尼表面之间延伸。 相邻的一对开槽孔具有细长的形状，从而形成纵向轴线，该纵向轴线在阻尼器表面的一点处相交。
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2.发明申请GAS TURBINE ENGINE COMPONENT WITH COMBINED MATE FACE AND PLATFORM COOLING 审中-公开气体涡轮发动机组件与组合的油面和平台冷却
公开(公告)号：WO2014186005A2
公开(公告)日：2014-11-20
申请号：PCT/US2014/015194
申请日：2014-02-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： LEWIS, Scott D. , RAPP, Brandon M. , BEATTIE, Jeffrey S. , HOUGH, Matthew Andrew , TELLER, Bret M. , JACQUES, Jeffrey Michael , ASTERLIN, Max
CPC classification number: F01D5/186 , F01D5/18 , F01D9/023 , F01D9/065 , F01D11/08 , F01D25/12 , F05D2240/11 , F05D2240/35 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y02T50/676
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
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尤其包括在前缘和后缘之间轴向延伸的平台，其周向地在第一配合面和第二配合面之间延伸，以及 包括气体路径表面和非气体通道表面。 该部件限定至少一个至少部分地在部件内部延伸的空腔。 第一多个冷却孔从所述至少一个空腔延伸到所述第一配合面和所述第二配合面中的至少一个，并且第二多个冷却孔从所述至少一个空腔或非气体通道表面延伸到 气路面。
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公开(公告)号：WO2014150342A1
公开(公告)日：2014-09-25
申请号：PCT/US2014/022990
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ASTERLIN, Max , BEATTIE, Jeffrey S. , GUNN, John R.
CPC classification number: B22D15/00 , B22C9/10 , B22D25/02 , B22D27/04 , B22D27/045 , C30B11/00 , C30B29/52 , F01D5/18 , F01D5/187 , F01D5/282 , F01D9/041 , F02C3/04 , F05D2220/30 , F05D2230/21 , F05D2230/211 , F05D2260/20 , F05D2260/204 , F05D2300/607 , F05D2300/608 , Y02T50/676
Abstract: A cast component includes a cast body that has a single crystal microstructure and an internal corner bounding an internal cavity. The single crystal microstructure defines a critical internal residual stress with respect to investment casting of the cast body using a refractory metal core beyond which the single crystal microstructure recrystallizes under a predetermined condition. The internal corner has a corner radius that is greater than a critical corner radius below which an amount of internal residual stress in the single crystal microstructure exceeds the critical internal residual stress. The internal cavity includes a cross section less than about 20 mils near the corner radius.
Abstract translation: 铸造组件包括具有单晶微结构的铸造体和包围内腔的内角。 单晶微结构定义了使用难熔金属芯相对于铸造体的熔模铸造的关键内部残余应力，超临界内的单晶微结构在预定条件下重结晶。 内角具有大于临界角半径的角半径，低于该半径时，单晶微结构中的内部残余应力的量超过临界内部残余应力。 内腔包括在拐角半径附近小于约20密耳的横截面。
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公开(公告)号：WO2014099136A1
公开(公告)日：2014-06-26
申请号：PCT/US2013/067395
申请日：2013-10-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： RABINOVICH, Albert , SHAH, Dilip M. , CETEL, Alan D. , MARCIN, John Joseph , ASTERLIN, Max
Abstract: A refractory metal core for forming internal features in a turbine engine component has a core formed from a refractory metal material; and the core has at least one blended surface on at least one edge of the core.
Abstract translation: 用于在涡轮发动机部件中形成内部特征的耐火金属芯具有由难熔金属材料形成的芯; 并且芯在芯的至少一个边缘上具有至少一个混合表面。
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Patent Agency Ranking
公开(公告)号：EP3004557A2
公开(公告)日：2016-04-13
申请号：EP14837891.2
申请日：2014-05-28
Applicant: United Technologies Corporation
Inventor： KNOWLTON, Robert , ASTERLIN, Max , RAPP, Brandon, M. , JARIWALA, Parth
CPC classification number: F01D5/10 , F01D5/081 , F01D5/18 , F01D5/26 , F01D11/006 , F05D2240/57 , F05D2260/96 , Y02T50/676
Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.
Abstract translation: 描述了涡轮叶片减振器。 阻尼器具有限定内表面和相对的阻尼表面的轴向延伸主体。 主体还具有从内表面延伸到阻尼表面的边缘和延伸穿过主体的开槽孔。 开槽孔在内表面和阻尼表面之间延伸。 相邻的一对槽孔具有细长的形状，其限定纵向轴线，所述纵向轴线在阻尼器的表面处的点处相交。
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公开(公告)号：EP3004557B1
公开(公告)日：2020-07-29
申请号：EP14837891.2
申请日：2014-05-28
Applicant: United Technologies Corporation
Inventor： KNOWLTON, Robert , ASTERLIN, Max , RAPP, Brandon, M. , JARIWALA, Parth
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公开(公告)号：EP2956627B1
公开(公告)日：2018-07-25
申请号：EP14797049.5
申请日：2014-02-07
Applicant: United Technologies Corporation
Inventor： LEWIS, Scott D. , RAPP, Brandon M. , BEATTIE, Jeffrey S. , HOUGH, Matthew Andrew , TELLER, Bret M. , JACQUES, Jeffrey Michael , ASTERLIN, Max
CPC classification number: F01D5/186 , F01D5/18 , F01D9/023 , F01D9/065 , F01D11/08 , F01D25/12 , F05D2240/11 , F05D2240/35 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y02T50/676
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
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公开(公告)号：EP2969314A1
公开(公告)日：2016-01-20
申请号：EP14767376.8
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： ASTERLIN, Max , BEATTIE, Jeffrey S. , GUNN, John R.
CPC classification number: B22D15/00 , B22C9/10 , B22D25/02 , B22D27/04 , B22D27/045 , C30B11/00 , C30B29/52 , F01D5/18 , F01D5/187 , F01D5/282 , F01D9/041 , F02C3/04 , F05D2220/30 , F05D2230/21 , F05D2230/211 , F05D2260/20 , F05D2260/204 , F05D2300/607 , F05D2300/608 , Y02T50/676
Abstract: A cast component includes a cast body that has a single crystal microstructure and an internal corner bounding an internal cavity. The single crystal microstructure defines a critical internal residual stress with respect to investment casting of the cast body using a refractory metal core beyond which the single crystal microstructure recrystallizes under a predetermined condition. The internal corner has a corner radius that is greater than a critical corner radius below which an amount of internal residual stress in the single crystal microstructure exceeds the critical internal residual stress. The internal cavity includes a cross section less than about 20 mils near the corner radius.
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9.发明公开
公开(公告)号：EP2956627A2
公开(公告)日：2015-12-23
申请号：EP14797049.5
申请日：2014-02-07
Applicant: United Technologies Corporation
Inventor： LEWIS, Scott D. , RAPP, Brandon M. , BEATTIE, Jeffrey S. , HOUGH, Matthew Andrew , TELLER, Bret M. , JACQUES, Jeffrey Michael , ASTERLIN, Max
CPC classification number: F01D5/186 , F01D5/18 , F01D9/023 , F01D9/065 , F01D11/08 , F01D25/12 , F05D2240/11 , F05D2240/35 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y02T50/676
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
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