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69 条记录 (耗时 0.014 秒)

    Cooled airfoil
    5.
    发明授权
    Cooled airfoil 失效
    冷却空气

    公开(公告)号：US3644060A

    公开(公告)日：1972-02-22

    申请号：US3644060D

    申请日：1970-06-05

    申请人： BRYAN JOHN K

    发明人： BRYAN JOHN K

    IPC分类号： F01D5/18 ,  F01D5/08

    CPC分类号： F01D5/184

    摘要： A transpiration-cooled turbine vane has a porous wall and an internal strut with a slidable dovetail connection to the wall to reinforce the wall. The dovetails may be directly on the wall or on a fluid distributing plate bonded to the wall. This fluid distributing plate, if present, or the strut provides for metering flow of cooling air to some areas of the wall.

    摘要翻译： 蒸发冷却的涡轮叶片具有多孔壁和内部支柱，其具有与壁的可滑动的燕尾连接以加强壁。 燕尾形可以直接在壁上或结合到墙上的流体分配板上。 该流体分配板（如果有的话）或支柱提供冷却空气流量到壁的某些区域。

    Turbine blade
    6.
    发明授权
    Turbine blade 失效

    公开(公告)号：US3619082A

    公开(公告)日：1971-11-09

    申请号：US3619082D

    申请日：1968-07-05

    申请人： GEN MOTORS CORP

    发明人： MEGINNIS GEORGE B

    IPC分类号： F01D5/18 ,  F01D5/08

    CPC分类号： F01D5/184 ,  Y10T29/49337

    摘要： A turbine rotor blade of laminated porous metal cast into a base includes an inner reinforcing layer which has increasing porosity in the direction spanwise of the blades so that the strength diminishes with load in the spanwise direction and the porosity provides for flow of air to the porous blade wall. Pores or relieved areas in some sections of some layers are elongate and disposed with their long dimension spanwise of the blade for increased strength in this direction, in which stress in the blade is greatest.

    INTEGRATED BRIDGE TURBINE BLADE
    8.
    发明申请
    INTEGRATED BRIDGE TURBINE BLADE 失效
    集成桥式涡轮叶片

    公开(公告)号：US20050008487A1

    公开(公告)日：2005-01-13

    申请号：US10616023

    申请日：2003-07-09

    申请人： Ching-Pang Lee ,  Richard Haubert ,  Harvey Maclin

    发明人： Ching-Pang Lee ,  Richard Haubert ,  Harvey Maclin

    IPC分类号： F01D5/18 ,  F01D5/20 ,  F02C7/18 ,  B63H1/14

    CPC分类号： F01D5/20 ,  F01D5/184 ,  F01D5/186 ,  Y02T50/673 ,  Y02T50/676

    摘要： A turbine blade includes a hollow airfoil integrally joined to a dovetail. The airfoil includes a perforate first bridge defining a flow channel behind the airfoil leading edge. A second bridge is spaced behind the first bridge and extends from a pressure sidewall of the airfoil short of the airfoil trailing edge. A third bridge has opposite ends joined to the pressure sidewall and the second bridge to define with the first bridge a supply channel for the leading edge channel, and defines with the second bridge a louver channel extending aft along the second bridge to its distal end at the pressure sidewall.

    摘要翻译： 涡轮机叶片包括与燕尾形整体连接的中空翼片。 翼型件包括限定在翼型件前缘后面的流动通道的穿孔第一桥。 第二桥隔开在第一桥后面并且从机翼后缘的翼型的压力侧壁延伸出来。 第三桥具有连接到压力侧壁和第二桥的相对端，第一桥与第一桥形成用于前缘通道的供应通道，并且与第二桥一起限定沿着第二桥向后延伸到其远端的百叶窗通道 压力侧壁。

    Perforated two layered sheet for use in film cooling
    10.
    发明授权
    Perforated two layered sheet for use in film cooling 失效
    执行两层薄膜用于电影冷却

    公开(公告)号：US5223320A

    公开(公告)日：1993-06-29

    申请号：US708864

    申请日：1991-05-30

    申请人： John S. Richardson

    发明人： John S. Richardson

    IPC分类号： B32B3/24 ,  F01D5/18 ,  F02K1/82 ,  F23R3/00

    CPC分类号： B32B3/266 ,  F01D5/184 ,  F01D5/186 ,  F02K1/822 ,  F23R3/002 ,  F05D2250/191 ,  F05D2260/202 ,  Y02T50/675 ,  Y10T156/1056 ,  Y10T156/1057 ,  Y10T428/12361 ,  Y10T428/24273 ,  Y10T428/24314 ,  Y10T428/24322 ,  Y10T428/24942 ,  Y10T428/2495

    摘要： A perforated sheet for the promotion of film cooling a gas turbine engine comprises two separate layers of laminate material which are placed in superposed abutting relationship. The first layer has a plurality of apertures of given cross-sectional area therein. The second layer also has a plurality of apertures therein which have larger cross-sectional areas than the corresponding apertures in the first layer. The apertures in the first layer are in fluid communication with the apertures in the second layer to form passageways through the perforated sheet. These passageways permit a cooling flow of fluid to pass through the perforated sheet so it can be discharged as a cooling fluid film along the inner surface of the perforated sheet. The apertures in each layer are independently formed to produce the passageways. The apertures can easily be machined to the desired size, shape, and angle to optimize the cooling film effectiveness for any particular application.

    摘要翻译： 用于促进燃气涡轮发动机的薄膜冷却的穿孔板包括以叠置的邻接关系放置的两层单独的层压材料层。 第一层具有多个给定横截面积的孔。 第二层还具有多个孔，其具有比第一层中的相应孔更大的横截面面积。 第一层中的孔与第二层中的孔流体连通，以形成穿过穿孔片的通道。 这些通道允许流体的冷却流动穿过穿孔板，使得其可以沿着穿孔板的内表面作为冷却流体膜排出。 每个层中的孔独立地形成以产生通道。 孔可以容易地加工到所需的尺寸，形状和角度，以优化任何特定应用的冷却膜效果。