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41. 发明申请

US20160305254A1 ROTOR BLADE PLATFORM COOLING PASSAGE 审中-公开
标题翻译：转子叶片平台冷却通道
公开(公告)号：US20160305254A1
公开(公告)日：2016-10-20
申请号：US15100413
申请日：2014-11-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Daniel A. SNYDER , Jeffrey S. BEATTIE
IPC分类号： F01D5/18 , F04D29/58 , F04D29/32
CPC分类号： F01D5/187 , F01D5/186 , F01D11/006 , F04D29/324 , F04D29/582 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform and a platform cooling passage extending inside of the platform. The platform cooling passage includes an inlet disposed through a non-gas path surface of the platform and an outlet disposed through a mate face of the platform.
摘要翻译：根据本公开的示例性方面的转子叶片包括平台，从平台延伸的翼型件和在平台内延伸的平台冷却通道。平台冷却通道包括通过平台的非气体通道表面设置的入口和通过平台的配合面设置的出口。

42. 发明申请

US20160273360A1 COOLING SYSTEM FOR A GAS TURBINE 审中-公开
标题翻译：一种气体涡轮机冷却系统
公开(公告)号：US20160273360A1
公开(公告)日：2016-09-22
申请号：US15074111
申请日：2016-03-18
申请人： Sulzer Turbo Services Venlo B.V.
发明人： Luc GOOREN , Eric VAN DEN HOVEN
IPC分类号： F01D5/08 , F01D5/26 , F01D5/22
CPC分类号： F01D5/081 , F01D5/22 , F01D5/225 , F01D5/26 , F01D11/006 , F05D2220/32 , F05D2240/80 , F05D2240/81 , F05D2260/221 , F05D2260/941 , F05D2260/96
摘要： The invention relates to a cooling system for a gas turbine.The cooling system according the invention comprises an annular array of turbine blades which comprises an undercut (17) formed in a blade platform (11). A substantially cylindrical damper pin (22) is arranged between two turbine blades (10a and 10b). The damper pin (22) comprises a cut-out (23) which is constructed and arranged that at least a portion of a gas flow which generally flows from a blade root portion to a blade profile portion of the turbine blades is directed to the named undercut (17). Since the named gas flow has a lower temperature than the blade platform and especially than the undercut, a cooling of the undercut is performed by the gas flow.
摘要翻译：根据本发明的冷却系统包括涡轮叶片的环形阵列，其包括形成在叶片平台（11）中的底切（17）。在两个涡轮叶片（10a和10b）之间布置有基本上圆柱形的阻尼器销（22）。减震销（22）包括切口（23），该切口（23）被构造和布置成使得通常从叶片根部部分流动到涡轮叶片的叶片轮廓部分的气流的至少一部分被引导到命名底切（17）。由于所命名的气体流动具有比叶片平台更低的温度，特别是比底切部分，所以通过气流进行底切的冷却。

43. 发明申请

US20160265364A1 TURBINE BLADE 审中-公开
标题翻译：涡轮叶片
公开(公告)号：US20160265364A1
公开(公告)日：2016-09-15
申请号：US15030058
申请日：2014-09-22
申请人： SIENENS AKTIENGESELLSCHAFT
发明人： Fathi Ahmad , Christian Menke , Radan Radulovic
IPC分类号： F01D5/18 , F01D9/02 , F01D25/12 , F01D5/30
CPC分类号： F01D5/18 , F01D5/143 , F01D5/187 , F01D5/3007 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2240/81 , F05D2260/22141 , F05D2260/232 , F05D2260/941 , Y02T50/673 , Y02T50/676
摘要： A turbine blade for a gas turbine has a securing region and a platform region that adjoins the securing region and has a platform on which a blade airfoil with a profiled cross-section and with a pressure-side wall and a suction-side wall is arranged, wherein each outer face of the pressure-side wall and/or the suction-side wall transitions into the platform surface via an outer rounded section. The turbine blade also has at least one cavity which is arranged in the blade airfoil and extends into the platform region and in which at least one rib is provided that connects the pressure-side wall to the suction-side wall, the rib extending along a longitudinal direction of the blade airfoil so as to divide the cavity. At least one slot is introduced into the rib in the platform region, the rib passing through the rib and being arranged in the longitudinal direction.
摘要翻译：一种用于燃气轮机的涡轮机叶片具有固定区域和与该固定区域相邻的平台区域，并且具有平台，在该平台上布置具有剖面横截面的叶片翼型以及压力侧壁和吸力侧壁其中，所述压力侧壁和/或所述吸入侧壁的每个外表面经由外部圆形部分转入所述平台表面。涡轮机叶片还具有至少一个空腔，其布置在叶片翼型中并延伸到平台区域中，并且其中设置有至少一个肋，其将压力侧壁连接到吸入侧壁，肋沿着叶片翼型的纵向方向以便分开空腔。至少一个槽被引入平台区域中的肋中，肋通过肋并沿纵向布置。

44. 发明申请

US20160245093A1 OUTER DIAMETER PLATFORM COOLING HOLE SYSTEM AND ASSEMBLY 有权
标题翻译：外径平台冷却孔系统和组件
公开(公告)号：US20160245093A1
公开(公告)日：2016-08-25
申请号：US14627915
申请日：2015-02-20
申请人： United Technologies Corporation
发明人： Russell Deibel , Matthew S. Gleiner
IPC分类号： F01D5/18 , F02C7/18 , F02C3/04
CPC分类号： F02C7/18 , F01D5/186 , F01D9/041 , F05D2240/81 , F05D2260/202 , Y02T50/676
摘要： An airfoil component is described herein. The airfoil component may include an OD platform comprising a gaspath face and a non-gaspath face coupled together via a plurality of cooling holes. The airfoil component may include an airfoil extending in from the outer diameter platform. The plurality of cooling holes comprises a plurality of groups of cooling holes disposed in the outer diameter platform proximate a suction side of the airfoil and a pressure side of the airfoil.
摘要翻译：这里描述了翼型件。机翼部件可以包括OD平台，该平台包括经由多个冷却孔连接在一起的气路面和非气道面。机翼部件可以包括从外径平台延伸的翼型件。多个冷却孔包括多个组的冷却孔，其设置在靠近翼型的吸力侧的外径平台和翼型的压力侧。

45. 发明授权

US09416971B2 Multiple diffusing cooling hole 有权
标题翻译：多个扩散冷却孔
公开(公告)号：US09416971B2
公开(公告)日：2016-08-16
申请号：US13544098
申请日：2012-07-09
申请人： JinQuan Xu
发明人： JinQuan Xu
IPC分类号： F01D5/18 , F23R3/06 , F01D9/06
CPC分类号： F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R3/06 , F23R2900/03042 , Y02T50/676
摘要： 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, a first diffusing section extending downstream from the metering section, and a second diffusing section extending downstream from the first diffusing section to the outlet. The second diffusing section includes first and second lobes, each lobe diverging longitudinally and laterally relative to the metering section, and a trailing edge.
摘要翻译：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该壁的冷却孔。所述冷却孔包括位于所述第一壁表面处的入口，位于所述第二壁表面处的出口，在所述入口的下游延伸的计量部分，从所述计量部分下游延伸的第一扩散部分和从所述计量部分的下游延伸的第二扩散部分第一个扩散段到出口。第二扩散部分包括第一和第二凸角，每个凸起相对于计量部分纵向和横向发散，以及后缘。

46. 发明申请

US20160201473A1 TURBINE BLADE HAVING FILM COOLING HOLE ARRANGEMENT 审中-公开
标题翻译：涡轮叶片有薄膜冷却孔安排
公开(公告)号：US20160201473A1
公开(公告)日：2016-07-14
申请号：US14929692
申请日：2015-11-02
申请人： United Technologies Corporation
发明人： Brandon W. Spangler , Laurie L. Burstynski
IPC分类号： F01D5/18 , F02C7/18 , F02C3/04
CPC分类号： F01D5/186 , F02C3/04 , F02C7/18 , F05D2220/3212 , F05D2240/81 , F05D2250/74 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides. An airfoil extends radially outwardly from the platform to a free tip end. The airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides. A root extends radially inwardly from the platform. The platform and the airfoil include film cooling holes arranged in substantial conformance with the Cartesian coordinates set forth in Table 1 herein. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm).
摘要翻译：涡轮叶片包括具有由两个平台周向侧连接的平台前缘和后缘的平台。机翼从平台径向向外延伸到自由尖端。翼型件包括通过相对的压力和吸力侧连接的翼型件前缘和后缘。根从平台向内径向延伸。平台和翼型件包括基本上符合本文表1所示的笛卡尔坐标的薄膜冷却孔。相对于零坐标，笛卡尔坐标由轴向坐标，圆周坐标和径向坐标提供，并且冷却孔相对于0.200英寸（5.0mm）的指定坐标具有径向表面公差。

47. 发明授权

US09376918B2 Aerofoil cooling arrangement 有权
标题翻译：机翼冷却装置
公开(公告)号：US09376918B2
公开(公告)日：2016-06-28
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。

48. 发明申请

US20160177758A1 ANGLED RAIL HOLES 有权
标题翻译：防护眼镜
公开(公告)号：US20160177758A1
公开(公告)日：2016-06-23
申请号：US14656446
申请日：2015-03-12
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： CAREY CLUM , JONATHAN PERRY SANDOVAL
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , F01D5/081 , F02C7/18 , F05D2240/81 , F23R3/06 , Y02T50/672 , Y02T50/675
摘要： A gas turbine engine combustor configured to cool a first vane platform by directing airflow through an aft combustor rail is disclosed. In various embodiments, a gas turbine engine combustor may comprise an aft combustor rail connected between an outer wall of an outer liner and an aft heat shield panel, and a plurality of holes in the aft combustor rail. The aft combustor rail may be positioned near an outer vane platform of a first vane stage of a turbine. Further, the plurality of holes may be designed to focus pass-through airflow onto the outer vane platform. In various embodiments, each hole of the plurality of holes may be angled between 20°-90° relative to the aft combustor rail. Additionally, the plurality of holes may be angled to converge the airflow to a focused area, such as a leading edge vane airfoil of the first vane stage.
摘要翻译：公开了一种燃气涡轮发动机燃烧器，其构造成通过引导气流通过尾部燃烧器轨道来冷却第一叶片平台。在各种实施例中，燃气涡轮发动机燃烧器可以包括连接在外衬套的外壁和后隔热板之间的后燃烧器轨道，以及后燃烧器轨道中的多个孔。后燃烧器轨道可以位于涡轮机的第一叶片级的外叶片平台附近。此外，多个孔可以设计成将通过气流聚焦到外叶片平台上。在各种实施例中，多个孔的每个孔可以相对于后燃烧器轨道在20°-90°之间成角度。另外，多个孔可以成角度以将气流会聚到聚焦区域，例如第一叶片台的前缘叶片翼型件。

49. 发明申请

US20160177754A1 BONDED FAN PLATFORM 有权
标题翻译：绑定风扇平台
公开(公告)号：US20160177754A1
公开(公告)日：2016-06-23
申请号：US14862390
申请日：2015-09-23
申请人： United Technologies Corporation
发明人： Thomas J. Robertson
IPC分类号： F01D5/30 , F01D5/12
CPC分类号： F01D5/3069 , F01D5/12 , F01D5/147 , F01D5/282 , F01D5/3053 , F01D11/005 , F01D11/008 , F02K3/06 , F04D29/023 , F04D29/324 , F05D2220/36 , F05D2240/80 , F05D2240/81 , F05D2260/30 , F05D2260/36 , F05D2300/603 , Y02T50/676
摘要： A fan is provided. The fan may comprise a fan blade and a blade platform coupled to the fan blade. The blade platform may be a thermoplastic. A fan blade platform is also provided. The fan blade platform may comprise a first platform half comprising a slot at a first end of the first platform half and a first receiving member at a second end of the first platform half opposite the first end of the first platform half. A second platform half may comprise a hook. The second platform half may also include a second receiving member at a second end of the second platform half opposite the first end of the second platform half with the hook configured to interface with the slot. A pin may be configured to pass through the first receiving member and the second receiving member.
摘要翻译：提供风扇。风扇可以包括风扇叶片和联接到风扇叶片的叶片平台。刀片平台可以是热塑性的。还提供风扇叶片平台。风扇叶片平台可以包括第一平台半部，其包括在第一平台半部的第一端处的狭槽和在第一平台的与第一平台半部的第一端相对的第二端的第一接收构件。第二平台半部可以包括钩子。第二平台半部还可以包括在第二平台的与第二平台半部的第一端相对的第二端处的第二接收构件，其中钩被配置为与狭槽接合。销可以被配置成穿过第一接收构件和第二接收构件。

50. 发明申请

US20160130951A1 COOLING FOR TURBINE BLADE PLATFORM-AEROFOIL JOINTS 审中-公开
标题翻译：用于涡轮叶片平台-AEROFOIL接头的冷却
公开(公告)号：US20160130951A1
公开(公告)日：2016-05-12
申请号：US14934932
申请日：2015-11-06
申请人： ALSTOM Technology Ltd.
发明人： Marc HENZE , Joerg KRÜCKELS , Laura BOGDANIC
IPC分类号： F01D5/18 , F01D11/00 , F01D5/14
CPC分类号： F01D5/187 , F01D5/147 , F01D5/18 , F01D5/188 , F01D11/005 , F05D2220/32 , F05D2240/127 , F05D2240/30 , F05D2240/55 , F05D2240/81 , F05D2260/2212
摘要： The invention concerns a turbine blade for a gas turbine having a platform part and an aerofoil part. The platform part includes a platform surface arranged to be attached to a corresponding aerofoil surface of the aerofoil part. The turbine blade further includes a cooling duct for cooling the platform and aerofoil surfaces, the cooling duct having at least one cavity in the platform surface and at least one cavity in the corresponding aerofoil surface, and the platform and aerofoil surface cavities are aligned such that when the platform surface and the aerofoil surface are touching, the cooling duct remains open. This provides a reliable cooling of both the platform and aerofoil surfaces.
摘要翻译：本发明涉及一种具有平台部分和机翼部分的燃气轮机的涡轮机叶片。平台部分包括平台表面，该平台表面布置成附接到机翼部件的对应的机翼表面。涡轮机叶片还包括用于冷却平台和机翼表面的冷却管道，冷却管道具有平台表面中的至少一个空腔和相应机翼表面中的至少一个空腔，并且平台和翼面表面腔体对齐，使得当平台表面和机翼表面接触时，冷却管保持打开。这为平台和机翼表面提供了可靠的冷却。

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