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1. 发明申请

US20180283182A1 TURBINE COMPONENT WITH SHAPED COOLING PINS 审中-公开
公开(公告)号：US20180283182A1
公开(公告)日：2018-10-04
申请号：US15475597
申请日：2017-03-31
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Benjamin Dosland Kamrath , Jason Smoke , Daniel C. Crites
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/18 , F05D2220/323 , F05D2240/30 , F05D2250/18 , F05D2250/60 , F05D2260/20 , F05D2260/2212 , F05D2260/22141 , F05D2260/607 , Y02T50/676
摘要： A turbine component with shaped cooling pins is provided. The turbine component includes at least one cooling circuit defined within the turbine component, the at least one cooling circuit in fluid communication with a source of a cooling fluid. The turbine component includes at least one shaped cooling pin disposed in the at least one cooling circuit. The at least one shaped cooling pin has a first end and a second end extending along an axis. The first end has a first curved surface defined by a minor diameter and the second end has a second curved surface defined by a major diameter. The first curved surface is upstream in the cooling fluid and the minor diameter is less than the major diameter.

2. 发明申请

US20170342904A1 SPLIT-ZONE FLOW METERING T-TUBE 审中-公开
公开(公告)号：US20170342904A1
公开(公告)日：2017-11-30
申请号：US15134653
申请日：2016-04-21
申请人： One Financial Plaza
发明人： Jorge I. Farah , Kalpendu J. Parekh , Constantine Baltas
IPC分类号： F02C7/18 , F02C3/045
CPC分类号： F02C7/18 , F01D5/08 , F01D5/18 , F01D9/065 , F01D25/28 , F02C3/045 , F02C6/08 , F02C7/12 , F02C7/20 , F05D2250/18 , Y02T50/675
摘要： A gas turbine engine according to an example of the present disclosure includes a fan situated at an inlet of a bypass passage. The fan has a fan diameter, Dfan. A low pressure turbine section is configured to drive the fan and a first compressor section. The low pressure turbine section has a greater number of stages than the first compressor section. The low pressure turbine section has a maximum rotor diameter, Dturb. A ratio of the maximum rotor diameter Dturb divided by the fan diameter Dfan is less than 0.6.

3. 发明授权

US09771827B2 Damping device for being situated between a housing wall and a casing ring of a housing of a thermal gas turbine 有权
公开(公告)号：US09771827B2
公开(公告)日：2017-09-26
申请号：US14337960
申请日：2014-07-22
申请人： MTU Aero Engines AG
发明人： Rudolf Stanka , Thomas Hess , Karl Maar , Karl-Heinz Dusel
IPC分类号： F01D25/04 , B28B1/00 , F02C7/24 , F01D25/14 , F01D11/18 , F01D11/12
CPC分类号： F01D25/04 , B28B1/001 , F01D11/127 , F01D11/18 , F01D25/145 , F02C7/24 , F05D2230/20 , F05D2230/22 , F05D2240/11 , F05D2250/11 , F05D2250/12 , F05D2250/13 , F05D2250/18 , F05D2260/941 , F05D2300/501 , F05D2300/514 , Y02T50/672 , Y02T50/675
摘要： A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring is provided. The casing ring includes an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the gas turbine. The damping device includes at least sectionally a porous damping structure. A method for manufacturing this type of damping device as well as to a thermal gas turbine, in particular an aircraft engine, in which this type of damping device is situated in a housing of the gas turbine between a housing wall and a casing ring are also provided.

4. 发明申请

US20170175560A1 TURBINE ABRADABLE LAYER WITH AIRFLOW DIRECTING PIXELATED SURFACE FEATURE PATTERNS 审中-公开
公开(公告)号：US20170175560A1
公开(公告)日：2017-06-22
申请号：US15128578
申请日：2015-02-18
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Gary B. MERRILL , Marco Claudio Pio BRUNELLI , Jonathan E. SHIPPER Jr. , David G. SANSOM , Cora SCHILLIG , Dimitrios ZOIS , Neil HITCHMAN
IPC分类号： F01D11/12 , F01D5/28
CPC分类号： F01D11/122 , C23C4/04 , C23C4/12 , F01D5/18 , F01D5/187 , F01D5/288 , F01D9/02 , F01D9/041 , F01D11/08 , F01D25/12 , F05D2220/31 , F05D2220/32 , F05D2230/311 , F05D2230/312 , F05D2230/90 , F05D2240/11 , F05D2250/00 , F05D2250/141 , F05D2250/18 , F05D2250/181 , F05D2250/182 , F05D2250/185 , F05D2250/23 , F05D2250/28 , F05D2250/294 , F05D2260/202 , F05D2260/231 , F05D2260/941 , F05D2300/10 , F05D2300/21 , F05D2300/5023 , F05D2300/516 , F05D2300/611
摘要： A turbine abradable component includes a support surface and a thermally sprayed ceramic/metallic abradable substrate coupled to the support surface for orientation proximal a rotating turbine blade tip circumferential swept path. An elongated pixelated major planform pattern (PMPP) of a plurality of discontinuous micro surface features (MSF) project from the substrate surface. The PMPP repeats radially along the swept path in the blade tip rotational direction, for selectively directing airflow between the blade tip and the substrate surface. Each MSF is defined by a pair of first opposed lateral walls defining a width, length and height that occupy a volume envelope of 1-12 cubic millimeters. The PMPP arrays of MSFs provide airflow control of hot gasses in the gap between the abradable surface and the blade tip with smaller potential rubbing surface area than solid projecting ribs with similar planform profiles.

5. 发明申请

US20160363132A1 VEHICLE COOLING FAN WITH AERODYNAMIC STATOR STRUTS 审中-公开
标题翻译：车辆冷却风扇与气动定子条
公开(公告)号：US20160363132A1
公开(公告)日：2016-12-15
申请号：US15120868
申请日：2015-03-12
申请人： MAGNA POWERTRAIN BAD HOMBURG GmbH
发明人： Brian Havel
IPC分类号： F04D29/54 , F04D25/06 , F04D25/08
CPC分类号： F04D29/544 , F04D25/06 , F04D25/08 , F05D2240/121 , F05D2240/122 , F05D2250/18 , F05D2250/183 , F05D2250/75 , F05D2300/43
摘要： An axial cooling fan for a vehicle includes an electrically powered motor operable to rotate fan blades to move air to cool a component or accessory of the vehicle. A stator is at the motor and has a plurality of struts that fixedly support the motor at the vehicle. The struts of the stator include leading edge surfaces that generally face air that is flowing towards the struts and past the struts and stator, such as when the motor is powered to rotate the fan blades. The leading edge surfaces of the struts comprise an aerodynamic design or pattern or structure established thereat, such as a toothed pattern or structure at the leading edge surfaces of the struts.
摘要翻译：用于车辆的轴向冷却风扇包括电动马达，其可操作以旋转风扇叶片以移动空气以冷却车辆的部件或附件。定子位于电动机上，并且具有多个固定支撑电动机在车辆上的支柱。定子的支柱包括前缘表面，其通常面向朝着支柱流动并经过支柱和定子的空气，例如当电动机被供电以旋转风扇叶片时。支柱的前缘表面包括在其上建立的空气动力学设计或图案或结构，例如在支柱的前缘表面处的齿形图案或结构。

6. 发明授权

US09243654B2 Panel attachment system 有权
标题翻译：面板附件系统
公开(公告)号：US09243654B2
公开(公告)日：2016-01-26
申请号：US14337524
申请日：2014-07-22
申请人： ROLLS-ROYCE PLC
发明人： Paul Robert Hayton
IPC分类号： E04B1/38 , F16B5/00 , F01D25/28 , F02K1/04 , F02K1/80 , F02K1/82 , F02C7/20
CPC分类号： F16B5/00 , F01D25/28 , F02C7/20 , F02K1/04 , F02K1/80 , F02K1/82 , F05D2230/54 , F05D2250/18 , F05D2300/5021 , Y10T403/32951
摘要： A panel attachment device for removably connecting a panel to a casing comprises a first bracket, a second bracket, and a link. The link has a first end and an opposite second end, with the first end being removably connected to the first bracket and the second end being removably connected to the second bracket. Each of the first end and second ends is located by, and rotatable relative to, the first bracket and second bracket respectively to thereby constrain the panel relative to the casing.
摘要翻译：用于将面板可拆卸地连接到壳体的面板附接装置包括第一支架，第二支架和连杆。连杆具有第一端和相对的第二端，第一端可移除地连接到第一支架，而第二端可移除地连接到第二支架。第一端部和第二端部中的每一个分别位于第一支架和第二支架上并相对于第一支架和第二支架可转动，从而相对于壳体约束板。

7. 发明申请

US20150233295A1 SPLIT-ZONE FLOW METERING T-TUBE 有权
标题翻译：分区流量计T型管
公开(公告)号：US20150233295A1
公开(公告)日：2015-08-20
申请号：US14429167
申请日：2013-03-01
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Jorge I. Farah , Kalpendu J. Parekh
IPC分类号： F02C7/18 , F02C3/045
CPC分类号： F02C7/18 , F01D5/08 , F01D5/18 , F01D9/065 , F01D25/28 , F02C3/045 , F02C6/08 , F02C7/12 , F02C7/20 , F05D2250/18 , Y02T50/675
摘要： A gas turbine engine includes a core engine that has a compressor section, a combustor section and a turbine section. A thermal management system is configured to receive a cooling stream. The thermal management system includes a metering device that is located near an outer diameter of the core engine. The metering device is configured to divide the cooling stream into multiple segregated passages. The metering device can be configured to divide the cooling stream between a first passage and a second passage that is concentric with the first passage.
摘要翻译：燃气涡轮发动机包括具有压缩机部分，燃烧器部分和涡轮部分的核心发动机。热管理系统被配置为接收冷却流。热管理系统包括位于核心发动机外径附近的计量装置。计量装置构造成将冷却流分成多个分离的通道。计量装置可以被配置为在第一通道和与第一通道同心的第二通道之间划分冷却流。

8. 发明授权

US08782896B2 Method for the manufacture of an ejector nozzle tube 有权
标题翻译：用于制造喷射器喷嘴管的方法
公开(公告)号：US08782896B2
公开(公告)日：2014-07-22
申请号：US12566803
申请日：2009-09-25
申请人： Predrag Todorovic
发明人： Predrag Todorovic
IPC分类号： B05B15/00 , F02K1/36 , F01D25/12 , B64D33/10 , F01D25/18 , B21D51/06 , B21D53/06 , B21D51/10
CPC分类号： F02K1/36 , B21D51/06 , B21D51/10 , B21D53/06 , B64D33/10 , F01D25/12 , F01D25/18 , F05D2250/18 , F05D2250/181 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2260/20 , F05D2260/601 , Y02T50/675 , Y10T29/49366 , Y10T29/49401 , Y10T29/49428 , Y10T29/49432
摘要： A method for manufacturing an ejector nozzle tube, includes forming an essentially rectangular plate-type blank 1 to have an undulating configuration on two opposite edge areas 2, 3, subsequently bending the blank around an axis 4, which is arranged centrically and parallel to the edge areas 2, 3, with the edge areas 2, 3 being superposed and subsequently joining the edge areas by point connections 6, providing for the formation of ejector nozzles 5 between the point connections.
摘要翻译：一种喷射器喷嘴管的制造方法，包括在两个相对的边缘区域2,3上形成基本上矩形的板状坯料1以具有起伏构型，随后将坯料围绕轴线4弯曲，所述轴线4中心并平行于边缘区域2,3，其中边缘区域2,3重叠并且随后通过点连接6连接边缘区域，从而在点连接之间形成喷射器喷嘴5。

9. 发明申请

US20120201653A1 GAS TURBINE ENGINE AND COOLED FLOWPATH COMPONENT THEREFOR 审中-公开
标题翻译：燃气涡轮发动机和冷却流量组件
公开(公告)号：US20120201653A1
公开(公告)日：2012-08-09
申请号：US13337103
申请日：2011-12-24
申请人： Corina Moga , Jerry Layne , Jeffrey F. Rhodes
发明人： Corina Moga , Jerry Layne , Jeffrey F. Rhodes
IPC分类号： F01D9/02 , F01D25/12
CPC分类号： F01D5/147 , F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/126 , F05D2240/304 , F05D2250/18 , F05D2260/202 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： One embodiment of the present invention is a unique gas turbine engine. Another embodiment of the present invention is a unique cooled gas turbine engine flowpath component. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and cooled gas turbine engine flowpath components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
摘要翻译：本发明的一个实施例是独特的燃气涡轮发动机。本发明的另一个实施例是独特的冷却燃气涡轮发动机流路组件。其他实施例包括用于燃气涡轮发动机和冷却燃气涡轮发动机流路部件的装置，系统，装置，硬件，方法和组合。本申请的其它实施例，形式，特征，方面，益处和优点将从本文提供的描述和附图中变得显而易见。

10. 发明申请

US20100221117A1 METHOD OF MANUFACTURING A BLADE 有权
公开(公告)号：US20100221117A1
公开(公告)日：2010-09-02
申请号：US12699507
申请日：2010-02-03
申请人： Phillip BRENNAND , Richard M. JONES
发明人： Phillip BRENNAND , Richard M. JONES
IPC分类号： F01D5/14 , B21D21/00 , B21D31/02
CPC分类号： B23K20/18 , B21D26/059 , B21D53/78 , B23K20/023 , B23K2101/001 , F01D5/147 , F05D2230/236 , F05D2230/31 , F05D2250/18 , Y02T50/672 , Y02T50/673
摘要： A method of manufacturing a blade (20) for a turbomachine by superplastic forming and diffusion bonding a first layer (18), a second layer (16) and a membrane (2), the membrane (2) being disposed between the first and second layers (18, 16), the method comprising: applying a stop-off material in a first predetermined pattern between the first layer (18) and the membrane (2) so as to prevent a diffusion bond from forming between the first layer and the membrane across said first predetermined pattern; wherein the first pattern is applied such that it defines one or more first strips (12) and one or more first dots (15), the first strips and first dots being void of the stop-off material, and wherein the first strips are arranged in a span-wise direction, and the first dots are located between the first strips and the blade tip edge, the first dots (15) being offset from a longitudinal axis of the first strips (12) in a chord-wise direction; and applying the stop-off material in a second predetermined pattern between the second layer (16) and the membrane (2) so as to prevent a diffusion bond from forming between the second layer and the membrane across said second predetermined pattern; wherein the second pattern is applied such that it defines one or more second strips (10) and one or more second dots (14), the second strips and second dots being void of the stop-off material, and wherein the second strips are arranged in a span-wise direction and the second dots are located between the second strips and the blade tip edge, the second dots (14) being offset from a longitudinal axis of the second strips (10) in a chord-wise direction; wherein the first and second predetermined patterns are applied such that the second strips (10) are spaced apart from the first strips (12) and the first dots (15) are spaced apart from the second dots (14) on opposite sides of the membrane (2).

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