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1. 发明授权

EP3170581B1 DIE CAST TIP COVER AND METHOD OF MANAGING RADIAL DEFLECTION OF DIE CAST TIP 有权
公开(公告)号：EP3170581B1
公开(公告)日：2020-01-01
申请号：EP16199295.3
申请日：2016-11-17
申请人： United Technologies Corporation
发明人： SLAVENS, Thomas N. , LoRICCO, Nicholas M.
IPC分类号： B22D17/20

2. 发明公开

EP2993304A1 GAS TURBINE ENGINE COMPONENT WITH FILM COOLING HOLE 有权转让
标题翻译： GASTURBINENMOTORKOMPONENTE MITFILMKÜHLUNGSLOCH
公开(公告)号：EP2993304A1
公开(公告)日：2016-03-09
申请号：EP15184019.6
申请日：2015-09-07
申请人： United Technologies Corporation
发明人： MOORE, Sasha M. , MUSTO, Clifford J. , JENNINGS, Timothy J. , STEVENS, Thomas N. , QUACH, San , LoRICCO, Nicholas M. , McBRIEN, John , CLUM, Carey , WHITFIELD, Christopher
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F01D9/041 , F01D11/08 , F01D25/12 , F02C3/04 , F02C7/18 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/35 , F05D2260/202 , Y02T50/676
摘要： A gas turbine engine component includes a wall (94) that provides an exterior surface (79) and an interior flow path surface (124). The wall (94) has a wall thickness (104). A protrusion (106) is arranged on the wall (94) that extends a height (108) beyond the wall thickness (104) and provides a portion of the interior flow path surface (124). A film cooling hole (92) that has an inlet (100) is provided on the protrusion (106) and extends to an exit (102) on the exterior surface (79).
摘要翻译：燃气涡轮发动机部件包括提供外表面（79）和内部流路表面（124）的壁（94）。壁（94）具有壁厚（104）。突出部（106）布置在壁（94）上，其高度（108）延伸超过壁厚（104）并提供内部流动路径表面（124）的一部分。具有入口（100）的薄膜冷却孔（92）设置在突起（106）上并延伸到外表面（79）上的出口（102）。

3. 发明公开

EP3170581A1 DIE CAST TIP COVER AND METHOD OF MANAGING RADIAL DEFLECTION OF DIE CAST TIP 审中-公开
标题翻译：压铸头盖和管理压铸头径向变形的方法
公开(公告)号：EP3170581A1
公开(公告)日：2017-05-24
申请号：EP16199295.3
申请日：2016-11-17
申请人： United Technologies Corporation
发明人： SLAVENS, Thomas N. , LoRICCO, Nicholas M.
IPC分类号： B22D17/20
摘要： A die casting plunger tip assembly (24; 52) includes a first portion having a closed end (32) defining an outer surface (32a), and a tip cover (28; 50) disposed on the outer surface (32a) of the closed end (32).
摘要翻译：一种压铸柱塞头组件（24; 52）包括具有限定外表面（32a）的封闭端（32）的第一部分以及设置在封闭件的外表面（32a）上的顶盖（28; 50）结束（32）。

4. 发明授权

EP2993304B1 GAS TURBINE ENGINE COMPONENT WITH FILM COOLING HOLE 有权转让
公开(公告)号：EP2993304B1
公开(公告)日：2020-02-12
申请号：EP15184019.6
申请日：2015-09-07
申请人： United Technologies Corporation
发明人： MOORE, Sasha M. , MUSTO, Clifford J. , JENNINGS, Timothy J. , STEVENS, Thomas N. , QUACH, San , LoRICCO, Nicholas M. , McBRIEN, John , CLUM, Carey , WHITFIELD, Christopher
IPC分类号： F01D9/04 , F01D11/08 , F01D25/12 , F02C3/04 , F02C7/18 , F04D29/32 , F04D29/54 , F04D29/58 , F01D5/18

5. 发明公开

EP3508696A1 DOUBLE WALL TURBINE GAS TURBINE ENGINE VANE PLATFORM COOLING CONFIGURATION WITH BAFFLE IMPINGEMENT 有权转让
公开(公告)号：EP3508696A1
公开(公告)日：2019-07-10
申请号：EP19151054.4
申请日：2019-01-09
申请人： United Technologies Corporation
发明人： LoRICCO, Nicholas M. , MONGILLO Jr., Dominic J.
IPC分类号： F01D5/18 , F01D9/04
摘要： An airfoil (78) includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edge and in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage (90) is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform (76b). A airfoil skin cooling passage (98) is arranged in one of the pressure and suction side walls to form a hot side wall (100) and a cold side wall (102). The hot side wall (100) defines a portion of the exterior airfoil surface and the cold side wall (102) defines a portion of the core cooling passage (90). The airfoil skin cooling passage (98) extends to a platform skin cooling passage (108) arranged in the platform (76b). The platform skin cooling passage (108) is resupplied by a backside of the platform (76b).

6. 发明公开

EP3290638A1 COOLED TURBINE VANE WITH ALTERNATELY ORIENTATED FILM COOLING HOLE ROWS 有权转让
标题翻译：带有取向膜取向冷却孔排的冷却式涡轮叶片
公开(公告)号：EP3290638A1
公开(公告)日：2018-03-07
申请号：EP17189120.3
申请日：2017-09-01
申请人： United Technologies Corporation
发明人： LoRICCO, Nicholas M. , SALZILLO, Jr., Richard M. , DeGRAY, Jeffrey J. , BOEKE, Mark A.
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2260/202 , F05D2260/221 , Y02T50/676
摘要： A cooled component (62) for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis (A) of the gas turbine engine. The internal ribs are disposed within an internal cavity (110) defining cooling air passages within the cooled component (62). A plurality of cooling holes (84, 85) are arranged in rows (80) with axial orientations alternating between a radially outboard bias directing cooling air radially outward and a radially inboard bias directing cooling air radially inward. Each of the cooling holes (84, 85) includes an internal opening in communication with one of the cooling air passages and an external opening open to an outer surface of the cooled component. The external opening of each of the plurality of cooling holes (84, 85) is disposed on a side opposite the internal rib relative to a corresponding internal opening.
摘要翻译：用于燃气涡轮发动机的冷却部件（62）包括基本平行于燃气涡轮发动机的纵向轴线（A）延伸的多个内部肋。内肋布置在限定冷却部件（62）内的冷却空气通道的内腔（110）内。多个冷却孔（84,85）排成行（80），其中轴向取向在径向向外偏压引导冷却空气径向向外和径向向内偏压引导冷却空气径向向内之间交替。每个冷却孔（84,85）包括与冷却空气通道之一连通的内部开口和通向冷却部件的外表面的外部开口。多个冷却孔（84,85）中的每个冷却孔的外部开口相对于相应的内部开口布置在与内部肋相对的一侧上。

7. 发明公开

EP3012407A1 FILM HOLE WITH PROTRUDING FLOW ACCUMULATOR 有权转让
标题翻译： FILMKHHLLOCH MIT VORSTEHENDEMSTRÖMUNGSAKKUMULATOR
公开(公告)号：EP3012407A1
公开(公告)日：2016-04-27
申请号：EP15190346.5
申请日：2015-10-19
申请人： United Technologies Corporation
发明人： MUSTO, Clifford J. , LoRICCO, Nicholas M. , SLAVENS, Thomas N. , JENNINGS, Timothy J. , CLUM, Carey , MOORE, Sasha M. , McBRIEN, John , QUACH, San , WHITFIELD, Christopher
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , B22C9/10 , B33Y10/00 , B33Y80/00 , F01D5/187 , F05D2230/21 , F05D2230/22 , F05D2230/31 , F05D2240/127 , F05D2260/202 , F05D2260/2212 , Y02T50/676
摘要： A wall (204; 302; 402; 502) of a gas turbine engine component/part is provided. The wall (204; 302; 402; 502) may comprise an external surface (207; 301; 403; 503) adjacent a gas path (222; 322; 416; 518) and an internal surface (205; 303; 401; 501) adjacent an internal flow path (220; 320; 412; 512). A film hole (213; 304; 404; 504) may have an inlet (214; 308) at the internal surface (205; 303; 401; 501) and an outlet (212; 306) at the external surface (207; 301; 403; 503). A flow accumulator (206; 312; 406; 506) adjacent the inlet (214; 308) may protrude from the internal surface (205; 303; 401; 501). A method of making an engine component is also provided and comprises the step of forming a component wall (204; 302; 402; 502) comprising an accumulator (206; 312; 406; 506) on an internal surface (205; 303; 401; 501) and a film hole (213; 304; 404; 504) defined by the component wall (204; 302; 402; 502). The film hole (213; 304; 404; 504) may include an opening adjacent the accumulator (206; 312; 406; 506) and defined by the internal surface (205; 303; 401; 501).
摘要翻译：提供了一种燃气涡轮发动机部件/部件的壁（204; 302; 402; 502）。所述壁（204; 302; 402; 502）可包括邻近气体路径（222; 322; 416; 518）和内表面（205; 303; 401; 501）的外表面（207; 301; 403; ）相邻于内部流动路径（220; 320; 412; 512）。薄膜孔（213; 304; 404; 504）可以在内表面（205; 303; 401; 501）处具有入口（214; 308）和外表面（207,301）处的出口（212; 306） ; 403; 503）。邻近入口（214; 308）的流动蓄能器（206; 312; 406; 506）可从内表面（205; 303; 401; 501）突出。还提供了制造发动机部件的方法，包括在内表面（205; 303; 401）上形成包括蓄能器（206; 312; 406; 506）的部件壁（204; 302; 402; 502） ; 501）和由所述部件壁（204; 302; 402; 502）限定的薄膜孔（213; 304; 404; 504）。薄膜孔（213; 304; 404; 504）可以包括邻近储存器（206; 312; 406; 506）并由内表面（205; 303; 401; 501）限定的开口。

8. 发明授权

EP3012407B1 FILM HOLE WITH PROTRUDING FLOW ACCUMULATOR 有权转让
公开(公告)号：EP3012407B1
公开(公告)日：2020-03-04
申请号：EP15190346.5
申请日：2015-10-19
申请人： United Technologies Corporation
发明人： MUSTO, Clifford J. , LoRICCO, Nicholas M. , SLAVENS, Thomas N. , JENNINGS, Timothy J. , CLUM, Carey , MOORE, Sasha M. , McBRIEN, John , QUACH, San , WHITFIELD, Christopher
IPC分类号： F01D5/18 , B22C9/10

9. 发明公开

EP3498979A1 COOLED AIRFOIL 有权转让
公开(公告)号：EP3498979A1
公开(公告)日：2019-06-19
申请号：EP18213716.6
申请日：2018-12-18
申请人： United Technologies Corporation
发明人： LoRICCO, Nicholas M. , GAUTSCHI, Steven Bruce
IPC分类号： F01D9/06 , F01D5/18
摘要： An airfoil (78) includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges (82, 84). The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform (76a, 76b). A skin core cooling passage (98a, 98b) is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the skin core cooling passage (98a, 98b). The skin core cooling passage (98a, 98b) is divided by a wall into two discrete first and second skin core cooling passages (98b, 98a) each supplied with cooling fluid from opposing sides.

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