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61. 发明申请

US20150361922A1 HEAT EXCHANGER DESIGNS USING VARIABLE GEOMETRIES AND CONFIGURATIONS 审中-公开
标题翻译：热交换器设计使用可变几何和配置
公开(公告)号：US20150361922A1
公开(公告)日：2015-12-17
申请号：US14304020
申请日：2014-06-13
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Jorge D. Alvarez , Douglas Michael Czaplicki , Karl Fleer , Mark C. Morris , Donald G. Godfrey
IPC分类号： F02K3/115
CPC分类号： F28F9/0268 , B33Y80/00 , F01D25/02 , F02C7/047 , F02C7/185 , F04D27/009 , F04D29/582 , F05D2260/213 , F05D2260/2214 , F28D9/0081 , F28D9/02 , F28D2021/0021 , F28F2215/04 , Y02T50/675
摘要： A heat exchanger may include at least one fluid passageway adjacent a heat transfer plate and a plurality of heat transfer elements positioned in the at least one fluid passageway and joined with the heat transfer plate. The heat transfer elements may be positioned with first spacings therebetween at an inlet end of the at least one fluid passageway. The heat transfer elements may be positioned with second spacings therebetween at an outlet end of the at least one fluid passageway. The first spacings may be smaller than the second spacings.
摘要翻译：热交换器可以包括邻近传热板的至少一个流体通道和定位在至少一个流体通道中并与传热板接合的多个传热元件。传热元件可以在其至少一个流体通道的入口端处之间以第一间隔定位。传热元件可以在至少一个流体通道的出口端处以第二间隔定位。第一间隔可以小于第二间隔。

62. 发明申请

US20150330228A1 AIRFOIL TIP POCKET WITH AUGMENTATION FEATURES 审中-公开
标题翻译： AIRFOIL TIP POCKET WITH AUGMENTATION特点
公开(公告)号：US20150330228A1
公开(公告)日：2015-11-19
申请号：US14704022
申请日：2015-05-05
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： San QUACH , Tracy A. PROPHETER-HINCKLEY , Steven Bruce GAUTSCHI
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/187 , F01D5/147 , F01D5/186 , F01D5/20 , F05D2220/32 , F05D2260/202 , F05D2260/221 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , Y02T50/676
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge. The airfoil extends to a tip. A tip pocket is formed in the tip and terminates prior to the trailing edge. A heat transfer augmentation device is formed in the tip pocket.
摘要翻译：根据本公开的示例性方面的部件包括除了别的以外的翼型件，其包括在前缘和后缘处在一起相遇的压力侧壁和抽吸侧壁。翼型件延伸到尖端。尖端口形成在尖端中并且在后缘之前终止。传热增强装置形成在尖端口袋中。

63. 发明授权

US09133717B2 Cooling structure of turbine airfoil 有权
标题翻译：涡轮机翼的冷却结构
公开(公告)号：US09133717B2
公开(公告)日：2015-09-15
申请号：US12812227
申请日：2009-01-08
申请人： Chiyuki Nakamata , Takashi Yamane , Yoshitaka Fukuyama , Takahiro Bamba
发明人： Chiyuki Nakamata , Takashi Yamane , Yoshitaka Fukuyama , Takahiro Bamba
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F01D5/186 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2260/201 , F05D2260/205 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141
摘要： A cooling structure of a turbine airfoil cools a turbine airfoil (10) exposed to hot gas (1), using cooling air (2) of a temperature lower than that of the hot gas. The turbine airfoil (10) includes an external surface (11), an internal surface (12) opposite to the external surface, a plurality of film-cooling holes (13) blowing the cooling air from the internal surface toward the external surface to film-cool the external surface, and a plurality of heat-transfer promoting projections (14) integrally formed with the internal surface and protruding inwardly from the internal surface. The turbine airfoil further includes a hollow cylindrical insert (20) which is positioned inside the internal surface of the turbine airfoil and to which the cooling air is supplied. The insert has a plurality of impingement holes (21) for impingement-cooling the internal surface (12).
摘要翻译：涡轮翼型件的冷却结构使用比热气体的温度低的冷却空气（2）冷却暴露于热气体（1）的涡轮机翼型件（10）。涡轮机翼（10）包括外表面（11），与外表面相对的内表面（12），多个薄膜冷却孔（13），其将冷却空气从内表面向外表面吹向薄膜 - 冷却外表面，以及多个传热促进突起（14），其与内表面整体形成并从内表面向内突出。涡轮机翼片还包括中空圆柱形插入件（20），该中空圆柱形插入件位于涡轮机翼片的内表面内部，并且供应冷却空气。插入件具有用于冲击冷却内表面（12）的多个冲击孔（21）。

64. 发明授权

US09127560B2 Cooled turbine blade and method for cooling a turbine blade 有权
标题翻译：冷却涡轮叶片和冷却涡轮叶片的方法
公开(公告)号：US09127560B2
公开(公告)日：2015-09-08
申请号：US13308927
申请日：2011-12-01
申请人： Matthew Durham Collier , Anthony Louis Giglio , Gayathri Puram
发明人： Matthew Durham Collier , Anthony Louis Giglio , Gayathri Puram
IPC分类号： F01D5/08 , F01D5/18 , F01D5/22
CPC分类号： F01D5/187 , F01D5/225 , F05D2260/201 , F05D2260/204 , F05D2260/205 , F05D2260/2214 , Y02T50/673 , Y02T50/676
摘要： A cooled turbine blade comprises a root for fixing the blade to rotor, an airfoil extending along a radial axis from the root, and a tip shroud disposed at a radially outward end of the airfoil. The tip shroud extends in a circumferential direction from the airfoil and defines, within itself, a core plenum and a peripheral plenum. The airfoil defines an aft airfoil cooling passage that extends radially through the airfoil proximate a trailing edge portion of the airfoil. The airfoil also defines an aft cooling inlet for providing an aft stream of cooling fluid to the aft airfoil cooling passage. The airfoil also defines at least one aft cooling exit for discharging the aft stream of cooling fluid from the aft airflow cooling passage to the peripheral plenum. The tip shroud defines at least one peripheral plenum vent for discharging the aft stream of cooling fluid.
摘要翻译：冷却的涡轮叶片包括用于将叶片固定到转子的根部，沿着径向轴线从根部延伸的翼型件，以及设置在翼型件的径向向外端部处的尖端护罩。尖端护罩从翼型件在圆周方向上延伸，并且在其本身内限定出一个内部集气室和一个周边通风室。翼型件限定了靠近翼型件的后缘部分的径向延伸穿过翼型件的后翼型件冷却通道。翼型件还限定了一个后部冷却入口，用于向后翼型冷却通道提供冷却流体的后部流。翼型件还限定至少一个后冷却出口，用于将后流冷却流体从尾气流冷却通道排出到周边通风室。尖端罩限定了至少一个周边通风口，用于排出冷却流体的后部流。

65. 发明申请

US20150121885A1 Gas Turbine Combustor 审中-公开
标题翻译：燃气轮机燃烧器
公开(公告)号：US20150121885A1
公开(公告)日：2015-05-07
申请号：US14531253
申请日：2014-11-03
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Osami YOKOTA , Masataka HIDAKA , Shohei NUMATA , Tetsuma TATSUMI
IPC分类号： F23R3/06 , F23R3/00
CPC分类号： F23R3/06 , F05D2260/202 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F23R3/002 , F23R3/005 , F23R3/54 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03045
摘要： There is provided a gas turbine combustor that achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural intensity.A gas turbine combustor structure includes a plurality of circularity recesses 20 formed on a side of an annular passage 11 on a partial area of a combustion liner 8 that requires cooling. The circularity recesses 20 each have a rectangular surface 25 forming a convex at a right angle with respect to a flowing direction of combustion air 2. The circularity recesses 20 is a rectangular triangle having an oblique surface 26 facing upstream of the flowing direction of the combustion air 2.
摘要翻译：提供了一种燃气轮机燃烧器，其通过在冷却特性和结构强度上的改进来实现提高的产品可靠性和减小的压力损失增加。燃气轮机燃烧器结构包括形成在需要冷却的燃烧衬套8的局部区域上的环形通道11的侧面上的多个圆形凹部20。圆形凹部20各自具有相对于燃烧用空气2的流动方向成直角的矩形的表面25.圆形凹部20是具有朝向燃烧流动方向的上游侧的倾斜面26的矩形三角形空气2。

66. 发明授权

US08920123B2 Turbine blade with integrated serpentine and axial tip cooling circuits 有权
标题翻译：涡轮叶片具有集成的蛇形和轴向尖端冷却回路
公开(公告)号：US08920123B2
公开(公告)日：2014-12-30
申请号：US13714518
申请日：2012-12-14
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： F01D5/18 , F01D5/20
CPC分类号： F01D5/187 , F01D5/186 , F01D5/20 , F05D2240/307 , F05D2250/185 , F05D2250/75 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/2214
摘要： An air cooled turbine blade including leading and trailing edges, and pressure and suction side walls extending between the leading and trailing edges. Leading and trailing edge cooling circuits extend spanwise adjacent to the leading and trailing edges, respectively. A forward flow mid-section serpentine cooling circuit extends spanwise and is located between the leading and trailing edge cooling circuits. An axial tip cooling circuit extends in the chordal direction and is located between a tip cap of the blade and the serpentine cooling circuit at an outer end of the serpentine cooling circuit. The axial tip cooling circuit has a forward end receiving cooling air from a final channel of the serpentine cooling circuit and discharges the cooling air adjacent to the trailing edge.
摘要翻译：包括前缘和后缘的空气冷却涡轮叶片，以及在前缘和后缘之间延伸的压力和吸力侧壁。前缘和后缘冷却回路分别沿着前缘和后缘分别延伸。向前流动的中段蛇形冷却回路沿横向延伸并且位于前缘和后缘冷却回路之间。轴向尖端冷却回路在弦向延伸，位于蛇形冷却回路的外端处，位于叶片的顶盖和蛇形冷却回路之间。轴向尖端冷却回路具有从蛇形冷却回路的最终通道接收冷却空气的前端，并排出与后缘相邻的冷却空气。

67. 发明授权

US08915087B2 Methods and systems for transferring heat from a transition nozzle 有权
标题翻译：从过渡喷嘴传热的方法和系统
公开(公告)号：US08915087B2
公开(公告)日：2014-12-23
申请号：US13164908
申请日：2011-06-21
申请人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
发明人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
IPC分类号： F02C1/00 , F01D9/02 , F23R3/00
CPC分类号： F01D9/023 , F05D2260/2214 , F23R3/002 , F23R3/005 , F23R2900/03045 , Y10T29/49229
摘要： Methods and systems are provided for transferring heat from a transition nozzle. The transition nozzle includes a transition portion, a nozzle portion integrally formed with the transition portion, and at least one surface feature configured to transfer heat away from the transition portion and/or the nozzle portion. The transition portion is oriented to channel the combustion gases towards the nozzle portion.
摘要翻译：提供了用于从转换喷嘴传热的方法和系统。过渡喷嘴包括过渡部分，与过渡部分一体形成的喷嘴部分，以及被配置为将热量从过渡部分和/或喷嘴部分传递的至少一个表面特征。过渡部分被定向成将燃烧气体引向喷嘴部分。

68. 发明申请

US20140234073A1 CASING COOLING DUCT 有权
标题翻译：铸造冷却塔
公开(公告)号：US20140234073A1
公开(公告)日：2014-08-21
申请号：US14113954
申请日：2012-04-11
申请人： Kevin Moreton , Kevin Scott
发明人： Kevin Moreton , Kevin Scott
IPC分类号： F01D25/14 , F01D25/26
CPC分类号： F01D25/14 , F01D9/00 , F01D25/26 , F02C7/18 , F05D2250/323 , F05D2260/205 , F05D2260/221 , F05D2260/2214 , Y02T50/676
摘要： A turbine includes an inner casing to which at least a stator vane of a turbine section is mountable, and an outer casing arranged around the inner casing in such a way that an outer cooling channel is formed between the inner casing and the outer casing. The outer cooling channel includes a fluid inlet through which a cooling fluid is injectable from an outer volume of the turbine into the outer cooling channel. The cooling channel includes a fluid outlet such that the cooling fluid is exhausted into an inner volume of the turbine. The fluid inlet is located with respect to the fluid outlet such that the cooling fluid inside the outer cooling channel includes a flow direction which has a component that is orientated in opposite direction with respect to a main flow direction of a working fluid of the turbine.
摘要翻译：涡轮机包括内壳体，涡轮机部分的至少一个定子叶片可安装在该内壳体上，外壳体以这样的方式设置，使得在内壳体和外壳体之间形成外部冷却通道。外部冷却通道包括流体入口，冷却流体可以通过该入口从涡轮机的外部容积注入外部冷却通道。冷却通道包括流体出口，使得冷却流体被排放到涡轮机的内部容积中。流体入口相对于流体出口定位，使得外部冷却通道内的冷却流体包括具有相对于涡轮机的工作流体的主流动方向相反方向定向的部件的流动方向。

69. 发明申请

US20140064967A1 AEROFOIL COOLING ARRANGEMENT 有权
标题翻译： AEROFOIL冷却布置
公开(公告)号：US20140064967A1
公开(公告)日：2014-03-06
申请号：US13682109
申请日：2012-11-20
申请人： ROLLS-ROYCE PLC
发明人： Adrian Lewis HARDING
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/186 , F05D2240/81 , F05D2260/201 , F05D2260/204 , F05D2260/2214 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： An aerofoil typically for a blade or vane for a gas turbine engine comprises a pressure wall, a suction wall and a web that extends therebetween. One of the walls comprises an inner leaf and an outer leaf which defines a cavity, the other wall defines a first outlet, the aerofoil defines at least one first passage extending from the cavity through the web and to the outlet. Coolant in the cavity on one side wall of the aerofoil is thereby routed across the web to be used to cool the other wall by convention and formation of a coolant film.
摘要翻译：通常用于燃气涡轮发动机的叶片或叶片的机翼包括压力壁，吸力壁和在其间延伸的腹板。其中一个壁包括限定空腔的内叶和外叶，另一个壁限定第一出口，翼面限定了至少一个从空腔延伸通过腹板和出口的第一通道。因此，机翼的一个侧壁上的空腔中的冷却液被布线穿过网，用于通过惯例冷却另一壁并形成冷却剂膜。

70. 发明申请

US20140010639A1 GAS TURBINE ENGINE OIL TANK WITH INTEGRATED PACKAGING CONFIGURATION 有权
标题翻译：具有集成包装配置的气体涡轮发动机油箱
公开(公告)号：US20140010639A1
公开(公告)日：2014-01-09
申请号：US13541935
申请日：2012-07-05
申请人： Nathan Snape , Gabriel L. Suciu , Simon Pickford
发明人： Nathan Snape , Gabriel L. Suciu , Simon Pickford
IPC分类号： F01D25/12 , F01D1/02 , F01D25/18
CPC分类号： F01D25/18 , B64D29/08 , B64D33/00 , F01D25/12 , F01M5/002 , F02C7/06 , F02C7/14 , F02C7/32 , F05D2260/2214 , F16N19/00 , Y02T50/675
摘要： A gas turbine engine includes a fan case radially outwardly of a core compartment. A compressor section is located within an engine core compartment and includes a front mount flange and an aft mount flange. An oil tank is mounted to at least one of the fan case or the front and aft mount flanges. The oil tank has a cooling structure integrated into an outer surface such that the oil tank is subjected to cooling air flow from a plurality of air sources.
摘要翻译：燃气涡轮发动机包括在核心隔室的径向外侧的风扇壳体。压缩机部分位于发动机核心舱内，并且包括前安装法兰和后安装法兰。油箱安装到风扇壳体或前后安装法兰中的至少一个上。油箱具有集成到外表面中的冷却结构，使得油箱经受来自多个空气源的冷却空气流。

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