GAS TURBINE ENGINE COMPONENT WITH SEPARATION RIB FOR COOLING PASSAGES
    4.
    发明申请
    GAS TURBINE ENGINE COMPONENT WITH SEPARATION RIB FOR COOLING PASSAGES 审中-公开
    具有用于冷却通道的分离RIB的气体涡轮发动机部件

    公开(公告)号:US20160326909A1

    公开(公告)日:2016-11-10

    申请号:US15111517

    申请日:2015-01-21

    摘要: A gas turbine engine component comprises a body extending between two ends and having at least two cooling passages. The body has a first wall and second wall. At least two cooling passages include a first passage that is closer to the first wall than is a second of the passages at upstream locations along a flow path. The second passage has upstream locations that are closer to the second wall than are upstream portions of the first passage. The first and second passages cross along a length of the flow path such that downstream portions of the second passage are closer to the first wall than are downstream portions of the first passage, and downstream portions of the first passage are closer to the second wall than are downstream portions of the second passage.

    摘要翻译: 燃气涡轮发动机部件包括在两端之间延伸并且具有至少两个冷却通道的主体。 身体有第一个墙壁和第二个墙壁。 至少两个冷却通道包括比沿着流动路径的上游位置处的第二通道更靠近第一壁的第一通道。 第二通道具有比第一通道的上游部分更靠近第二壁的上游位置。 所述第一通道和所述第二通道沿所述流动路径的长度交叉,使得所述第二通道的下游部分比所述第一通道的下游部分更靠近所述第一壁,并且所述第一通道的下游部分比所述第一通道的下游部分更靠近所述第二壁 是第二通道的下游部分。

    PEDESTALS WITH HEAT TRANSFER AUGMENTER
    5.
    发明申请
    PEDESTALS WITH HEAT TRANSFER AUGMENTER 审中-公开
    带有传热装置的底盘

    公开(公告)号:US20160230664A1

    公开(公告)日:2016-08-11

    申请号:US15023010

    申请日:2014-10-16

    IPC分类号: F02C7/18 F01D25/12

    摘要: A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.

    摘要翻译: 燃气涡轮发动机部件包括第一侧壁和与第一侧壁间隔开的第二侧壁。 在第一和第二侧壁之间形成至少一个内部冷却通道。 至少一个基座定位在至少一个冷却通道内,并且具有从连接到第一侧壁的第一端延伸到连接到第二侧壁的第二端的主体。 主体包括至少一个突起。

    BORESCOPE ASSEMBLY AND METHOD OF INSTALLING BORESCOPE PLUGS
    6.
    发明申请
    BORESCOPE ASSEMBLY AND METHOD OF INSTALLING BORESCOPE PLUGS 有权
    BORESCOPE组装和安装BORESCOPE PLUGS的方法

    公开(公告)号:US20150040581A1

    公开(公告)日:2015-02-12

    申请号:US13961257

    申请日:2013-08-07

    IPC分类号: F01D21/00 F02C7/00 F01D25/00

    摘要: A borescope assembly includes a first borescope plug comprising a first perimeter geometry portion. Also included is a second borescope plug comprising a second perimeter geometry portion distinct from the first perimeter geometry portion. Further included is a first borescope hole comprising a first hole geometry portion corresponding to the first perimeter geometry portion of the first borescope plug. Yet further included is a second borescope hole comprising a second hole geometry portion corresponding to the second perimeter geometry portion of the second borescope plug.

    摘要翻译: 管状窥镜组件包括第一内窥镜插头,其包括第一周边几何部分。 还包括第二内窥镜插塞,其包括与第一周边几何部分不同的第二周边几何部分。 还包括第一管孔孔,其包括对应于第一管孔塞的第一周边几何部分的第一孔几何部分。 还包括第二孔眼孔,其包括对应于第二内窥镜插头的第二周边几何形状部分的第二孔几何部分。

    TURBINE BUCKET WITH NOTCHED SQUEALER TIP
    7.
    发明申请
    TURBINE BUCKET WITH NOTCHED SQUEALER TIP 有权
    涡轮马桶,带有凹槽的推杆

    公开(公告)号:US20140030102A1

    公开(公告)日:2014-01-30

    申请号:US13558685

    申请日:2012-07-26

    IPC分类号: F04D29/38

    摘要: A turbine bucket having an airfoil is disclosed. The airfoil may include a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the airfoil may include a tip. The tip may include a tip floor and a tip wall extending outwardly from the tip floor. The tip wall may include an inner surface defining an inner perimeter of the tip wall. Moreover, a plurality of notches may be defined by the inner surface around at least a portion of the inner perimeter.

    摘要翻译: 公开了一种具有翼型的涡轮机桶。 翼型件可以包括在前缘和后缘之间延伸的压力侧和吸力侧。 此外,翼型件可以包括尖端。 尖端可以包括尖端地板​​和从尖端底板向外延伸的尖端壁。 尖端壁可以包括限定尖端壁的内周边的内表面。 此外,多个凹口可以由围绕内周边的至少一部分的内表面限定。

    Composite vane mounting
    8.
    发明授权
    Composite vane mounting 有权
    复合叶片安装

    公开(公告)号:US08550776B2

    公开(公告)日:2013-10-08

    申请号:US12845261

    申请日:2010-07-28

    IPC分类号: F01D9/04

    摘要: A vane includes a composite airfoil having chordwise spaced apart forward and aft dovetail feet at or near leading and trailing edges of the airfoil. Each foot includes a shank connecting a dovetail root to an airfoil base and each root is slidably received in a dovetail slot in an inner vane mount. The dovetail slot has a triangular slot cross section and a flat slot bottom and flat slot pressure and suction side crush faces corresponding to pressure and suction sides of the airfoil. The dovetail root having a triangular root cross section and a flat root bottom and flat dovetail root pressure and suction side crush faces. A biasing means urges the root bottom of the dovetail roots away from the slot bottom and presses and preloads the dovetail root pressure and suction side crush faces against the slot pressure and suction side slot crush faces.

    摘要翻译: 叶片包括在翼型件的前缘和后缘处或其附近具有弦向间隔开的前后燕尾脚的复合翼型件。 每个脚包括将燕尾根连接到翼型基部的柄,并且每个根部可滑动地容纳在内叶片安装件中的燕尾槽中。 燕尾槽具有三角形槽横截面和平坦的槽底部以及对应于翼型的压力和吸力侧的平坦的槽压力和吸力侧的挤压面。 燕尾根具有三角形根部横截面和平底根部,扁平的燕尾根压力和吸力侧面。 偏压装置促使燕尾根的根部底部远离槽底,并将燕尾根压力和吸力侧挤压面按压并预加载在槽压力和吸力侧槽挤压面上。

    Sealing System Between a Shroud Segment and a Rotor Blade Tip and Manufacturing Method for Such a Segment
    9.
    发明申请
    Sealing System Between a Shroud Segment and a Rotor Blade Tip and Manufacturing Method for Such a Segment 审中-公开
    护罩段和转子叶片之间的密封系统及其制造方法

    公开(公告)号:US20110171010A1

    公开(公告)日:2011-07-14

    申请号:US13001800

    申请日:2009-07-02

    IPC分类号: F01D11/08 B23P11/00

    摘要: An arrangement including a turbine blade is provided. The turbine blade includes at least a root, an airfoil and a tip which is mounted to a rotor by means of the root. The rotor extends along a machine axis. The arrangement also includes a circumferential casing segment which includes a surface. The surface faces tips of the blades, wherein the surface is structured. A method to produce a casing segment is also provided. In order to increase efficiency without limiting the operational range of the turbine, the surface is provided at least partially with an at least partially ceramic coating. The method includes machining a first structure into the surface and providing the surface with a ceramic coating.

    摘要翻译: 提供了一种包括涡轮叶片的装置。 涡轮叶片至少包括根部,翼型件和通过根部安装到转子的尖端。 转子沿机床轴线延伸。 该布置还包括包括表面的圆周壳体段。 表面面对刀片的尖端,其中表面被构造。 还提供了一种生产套管段的方法。 为了在不限制涡轮机的操作范围的情况下提高效率,表面至少部分地具有至少部分陶瓷的涂层。 该方法包括将第一结构加工到表面中并为表面提供陶瓷涂层。

    Method and device for reducing engine noise
    10.
    发明授权
    Method and device for reducing engine noise 有权
    减少发动机噪音的方法和装置

    公开(公告)号:US07240493B2

    公开(公告)日:2007-07-10

    申请号:US10999449

    申请日:2004-11-30

    申请人: John M. Seiner

    发明人: John M. Seiner

    IPC分类号: F02K1/34

    摘要: A method and device to reduce the noise produced by jet aircraft engines and/or other supersonic nozzles involves the use of corrugated engine seals (30) for the secondary internal divergent flaps (14) of the nozzle (10). Such corrugated seals (30) serve not only to eliminate shock-generated noise, but also generate a counter-rotating vorticity to force low speed mixing of surrounding ambient air with the high-speed jet exhaust. Lower exhaust velocities, combined with reduced levels of the turbulent Reynolds shear stress, lead to reduction of turbulence-generated noise, including Mach wave emission.

    摘要翻译: 用于减少由喷气式飞行器发动机和/或其它超音速喷嘴产生的噪声的方法和装置涉及使用用于喷嘴(10)的次级内部发散翼片(14)的波纹发动机密封件(30)。 这种波纹密封件(30)不仅用于消除冲击产生的噪声,而且还产生反向旋转的涡流,以迫使周围环境空气与高速喷射式排气的低速混合。 较低的排气速度,结合湍流雷诺剪切应力水平的降低,导致湍流产生的噪声减少,包括马赫波发射。