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1. 发明公开

EP3412868A1 ADJUSTABLE FLOW SPLIT PLATFORM COOLING FOR GAS TURBINE ENGINE 有权转让
公开(公告)号：EP3412868A1
公开(公告)日：2018-12-12
申请号：EP18164398.2
申请日：2018-03-27
申请人： United Technologies Corporation
发明人： CLUM, Carey , GENERALE, Adam
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D25/12 , F01D5/187 , F01D9/041 , F01D17/105 , F02C3/04 , F05D2220/32 , F05D2240/12 , F05D2240/35 , F05D2240/81 , F05D2250/185 , F05D2260/20
摘要： A turbine assembly comprises a platform defining a platform cavity (125) cooled by a platform flow with a vane (90) extending from the platform. A platform-fed through cavity (126) is defined by the vane (90) and cooled by a first portion of the platform flow. A direct-fed through flow cavity (124) is defined in the vane (90) and cooled by a direct-fed through flow. The direct-fed through flow cavity (124) and the platform-fed through cavity (126) meet at an outlet (139) to expel an outgoing through flow from the outlet (139). A platform-fed serpentine cavity (128) is defined in the vane (90) and separated from the platform-fed through cavity (126) by a divider (130). The platform-fed serpentine cavity (128) is cooled by a second portion of the platform flow.

2. 发明公开

EP3409894A1 ADAPTIVE COVER FOR COOLING PATHWAY BY ADDITIVE MANUFACTURE 有权
公开(公告)号：EP3409894A1
公开(公告)日：2018-12-05
申请号：EP18164244.8
申请日：2018-03-27
申请人： General Electric Company
发明人： LACY, Benjamin Paul , MORGAN, Victor John
IPC分类号： F01D9/00 , B22F5/04
CPC分类号： F01D5/186 , B22F5/04 , F01D5/147 , F01D9/023 , F01D9/041 , F01D9/065 , F02K1/822 , F05D2230/30 , F05D2230/31 , F05D2240/11 , F05D2240/81 , F05D2260/202 , F05D2270/3032 , F23R3/002 , F23R3/06 , F23R2900/00018
摘要： A hot gas path component 52, 100 of an industrial machine includes an adaptive cover 210, 220 for a cooling pathway 170, 200. The component and adaptive cover 210, 220 are made by additive manufacturing. The component includes an outer surface 180 exposed to a working fluid having a high temperature; an internal cooling circuit 160; and a cooling pathway 170, 200 in communication with the internal cooling circuit 160 and extending towards the outer surface 180. The adaptive cover 210, 220 is positioned in the cooling pathway 170, 200 at the outer surface 180. The adaptive cover 210, 220 may include a heat transfer enhancing surface 230 at the outer surface 180 causing the adaptive cover 210, 220 to absorb heat faster than the outer surface 180.

3. 发明公开

EP3396108A1 METHOD OF PROVIDING COOLING STRUCTURE FOR A COMPONENT 有权
公开(公告)号：EP3396108A1
公开(公告)日：2018-10-31
申请号：EP18169573.5
申请日：2018-04-26
申请人： General Electric Company
发明人： MORGAN, Victor John , GERGELY, George Andrew
IPC分类号： F01D5/18 , B23P15/04
CPC分类号： B22F5/04 , B22D21/005 , B22D25/02 , B22F3/1055 , B22F3/24 , B22F5/009 , B22F2003/242 , B22F2998/10 , B23K15/0086 , B23K26/342 , B23K26/70 , B23K2101/001 , B23P15/04 , B33Y10/00 , B33Y80/00 , C22C19/057 , C22C19/07 , C22C30/02 , C23C26/00 , F01D5/18 , F01D5/186 , F01D5/188 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2230/21 , F05D2230/211 , F05D2230/22 , F05D2230/31 , F05D2230/60 , F05D2230/80 , F05D2230/90 , F05D2240/81 , F05D2300/175
摘要： A method of providing cooling structure for a component (10) comprising forming a first cavity in the component (10) and forming a first passageway in the first cavity in fluid communication with a second cavity (16) positioned inside the component (10), the second cavity (16) in fluid communication with a cooling air source. The method further includes forming a unitary insert (20) including a first surface and a second surface; the insert (20) having an inlet formed in the first surface and an outlet formed in the second surface and a second passageway in fluid communication with the inlet and the outle. The method further includes positioning the insert (20) in the first cavity into fluid communication with the first passageway, the first surface facing the first cavity and rigidly attaching the insert in the first cavity.

4. 发明授权

EP3002416B1 STATOR VANE, GAS TURBINE PROVIDED WITH SAME, METHOD FOR MANUFACTURING STATOR VANE, AND METHOD FOR MODIFYING STATOR VANE 有权
公开(公告)号：EP3002416B1
公开(公告)日：2018-10-31
申请号：EP15807779.2
申请日：2015-03-19
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： OKAJIMA Yoshifumi , KUWABARA Masamitsu
IPC分类号： F01D5/18 , F01D25/24 , F01D9/04 , F01D9/02 , F02C7/00 , F02C7/18
CPC分类号： F01D5/186 , F01D9/02 , F01D9/04 , F01D9/042 , F01D25/24 , F01D25/246 , F02C7/00 , F02C7/18 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/80 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/30
摘要： A retainer (91) that protrudes from an inner shroud (61) of a vane (40f) to a radially inner side and extends in a circumferential direction (Dc) is formed with an opening (92) that passes through the retainer (91) in an axial direction (Da) and defines a space through which air flows. A width (Wo) of the opening (92) in the circumferential direction (Dc) is wider than a width (Ww) of a vane body (41) in the circumferential direction (Dc) at a radially inner end of the vane body (41) at a position of the retainer (91) in the axial direction (Da).

5. 发明公开

EP3388632A1 COMPONENT FOR A GAS TURBINE ENGINE AND CORRESPONDING TURBOFAN ENGINE 审中-公开
公开(公告)号：EP3388632A1
公开(公告)日：2018-10-17
申请号：EP18173342.9
申请日：2013-02-13
申请人： United Technologies Corporation
发明人： XU, JinQuan
IPC分类号： F01D5/18 , F01D9/06 , F23R3/00 , F23R3/06
CPC分类号： F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R3/06 , F23R2900/00018 , F23R2900/03042 , Y02T50/673 , Y02T50/676
摘要： A component for a gas turbine engine includes a wall and a cooling hole. The wall has a first surface and a second surface. The second surface is exposed to hot gas flow. The cooling hole extends through the wall. The cooling hole includes a metering section extending from an inlet in the first surface of the wall to a transition, a diffusing section extending from the transition to an outlet in the second surface of the wall, a cusp extending from the transition along the metering section of the cooling hole toward the inlet.

6. 发明授权

EP2947280B1 TURBINE NOZZLES AND COOLING SYSTEMS FOR COOLING SLIP JOINTS THEREIN 有权转让
公开(公告)号：EP2947280B1
公开(公告)日：2018-10-17
申请号：EP15158094.1
申请日：2015-03-06
申请人： Honeywell International Inc.
发明人： Crosatti, Lorenzo , Riahi, Ardeshir , Tucker, Bradley Reed , Kanjiyani, Shezan
IPC分类号： F01D25/24 , F01D9/04 , F01D9/06
CPC分类号： F01D9/02 , F01D9/04 , F01D9/042 , F01D9/065 , F01D25/12 , F01D25/246 , F05D2220/32 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： Turbine nozzles (110) and cooling systems for cooling slip joints (206) therein are provided. The turbine nozzle has an endwall (103), a vane (102) coupled to the endwall, a slip joint (206), and a plurality of airfoil quenching holes (160) that cooperate with a plurality of endwall cooling holes (150). The vane comprises a leading edge (126) and a trailing edge (128) interconnected by a pressure sidewall (122) and a suction sidewall (128) and an end portion (140). The slip joint (206) is between the end portion(140) and the endwall (103). The airfoil quenching holes (160) are defined through the pressure sidewall (122) in the end portion. The endwall cooling holes (150) are defined through the endwall along the pressure sidewall (122) and in proximity to the leading edge (126). The airfoil quenching holes (160) and endwall cooling holes (150) are disposed adjacent the slip joint (150).

7. 发明授权

EP2019187B1 Apparatus and methods for providing vane platform cooling 有权
公开(公告)号：EP2019187B1
公开(公告)日：2018-10-17
申请号：EP08252422.4
申请日：2008-07-16
申请人： United Technologies Corporation
发明人： Surace, Raymond , Milliken, Andrew D. , Kaufman, Eleanor D. , Abdel-Messeh, William
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81
摘要： Apparatus and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform (300) includes: providing a cooling channel (306) on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface (304) and a channel cover (312), the channel cover being spaced from the cooling surface and located such that the cooling surface is positioned between a gas flow path of the vane and the channel cover; and directing a flow of cooling air through the cooling channel such that heat is extracted from the cooling surface of the platform by the flow of cooling air.

8. 发明授权

EP3184739B1 MULTI-WALL BLADE WITH COOLING CIRCUIT 有权
公开(公告)号：EP3184739B1
公开(公告)日：2018-10-03
申请号：EP16203125.6
申请日：2016-12-09
申请人： General Electric Company
发明人： SMITH, Aaron Ezekiel , FOSTER, Gregory Thomas
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/202 , F05D2260/204 , Y02T50/676
摘要： A cooling system according to an embodiment includes: a leading edge cooling circuit (30) including a pressure side (8) serpentine circuit and a suction side (10) serpentine circuit; a first mid-blade cooling circuit including a suction side (10) serpentine circuit; a second mid-blade cooling circuit including a pressure side (8) serpentine circuit; a trailing edge (16) cooling circuit; and at least one air feed for supplying cooling air (32, 34, 36, 50, 52, 60, 132, 232, 332) to the leading edge (14, 16) cooling circuit, the first mid-blade cooling circuit, the second mid-blade cooling circuit, and the trailing edge (16) cooling circuit.

9. 发明授权

EP3061910B1 GAS TURBINE ENGINE AIRFOIL AND CORRESPONDING METHOD OF FORMING 有权转让
公开(公告)号：EP3061910B1
公开(公告)日：2018-09-26
申请号：EP16157737.4
申请日：2016-02-26
申请人： United Technologies Corporation
发明人： BOEKE, Mark A. , SALZILLO, Richard , DEGRAY, Jeffrey J. , GREGG, Shawn J.
IPC分类号： F01D5/14 , F01D5/18 , F01D9/06
CPC分类号： F01D5/189 , F01D5/141 , F01D5/147 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/20 , F05D2230/60 , F05D2240/126 , F05D2240/301 , F05D2240/81 , F05D2260/221 , Y02T50/676
摘要： An airfoil (68) includes an airfoil wall (110, 112) including an exterior airfoil surface and at least partially defines an airfoil cavity (104). A fillet (102A, 102B) is on the exterior airfoil surface (98, 100). A recess (114) is in an interior surface of the airfoil wall (110, 112) adjacent the fillet (102A, 102B). A baffle tube (116) is located in the airfoil cavity (104) spaced from the recess (114).

10. 发明授权

EP3186485B1 COOLING CONCEPT FOR TURBINE BLADES OR VANES 有权
公开(公告)号：EP3186485B1
公开(公告)日：2018-07-04
申请号：EP15750321.0
申请日：2015-08-05
申请人： Siemens Aktiengesellschaft
发明人： MUGGLESTONE, Jonathan
IPC分类号： F01D25/12 , F01D9/04 , F01D5/18
CPC分类号： F01D5/187 , F01D5/188 , F01D5/189 , F01D9/041 , F01D25/12 , F05D2240/12 , F05D2240/30 , F05D2240/81 , F05D2260/201 , F05D2260/205
摘要： The present invention relates to a turbine assembly (10, 10a, 10b) comprising a basically hollow aerofoil (12) having at least a main cavity (14) with at least an impingement tube (16, 16b), which is insertable inside the main cavity (14) of the hollow aerofoil (12) and is used for impingement cooling of at least an inner surface (18) of the main cavity (14), and with at least a platform (20, 20'), which is arranged at a radial end (22, 22') of the hollow aerofoil (12), and with at least a cooling chamber (24, 24') used for cooling of at least the platform (20, 20') and which is arranged relative to the hollow aerofoil (12) on an opposed site of the at least one platform (20, 20') and wherein the at least one cooling chamber (24, 24') is limited at a first radial end (26, 26') by at least one a wall segment (28, 28') of the platform (20, 20') and at an opposed radial second end (30, 30') from at least a cover plate (32, 32'), and wherein the impingement tube (16, 16b) extends in span wise direction (34) at least completely through the cooling chamber (24, 24') from the platform (20, 20') to the cover plate (32, 32'). To minimised aerofoil cooling feed temperatures and increase impingement cooling effectiveness the impingement tube (16, 16b) restricts a sub-cavity (36) of the main cavity (14) and wherein the at least one wall segment (28, 28') of the at least one platform (20, 20') comprises at least one entry aperture (38, 38'; 38a, 38a') for a cooling medium (40) to enter through the at least one entry aperture (38, 38'; 38a, 38a') from the at least one cooling chamber (24, 24') of the at least one platform (20, 20') into the sub-cavity (36) of the hollow aerofoil (12).

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