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23 条记录 (耗时 0.017 秒)

    Use of biased fabric to improve properties of SiC/SiC ceramic composites for turbine engine components
    22.
    发明授权
    Use of biased fabric to improve properties of SiC/SiC ceramic composites for turbine engine components 有权
    使用偏置织物来改善涡轮发动机部件的SiC / SiC陶瓷复合材料的性能

    公开(公告)号：US07306826B2

    公开(公告)日：2007-12-11

    申请号：US10784734

    申请日：2004-02-23

    申请人： Suresh Subramanian ,  James Dale Steibel ,  Douglas Melton Carper ,  Brian Keith Flandermeyer

    发明人： Suresh Subramanian ,  James Dale Steibel ,  Douglas Melton Carper ,  Brian Keith Flandermeyer

    IPC分类号： C23C16/00

    CPC分类号： F01D5/282 ,  F01D5/284 ,  F05C2203/0839 ,  F05D2300/2261 ,  F05D2300/6012 ,  Y02T50/67 ,  Y02T50/672 ,  Y10T428/30

    摘要： A method for making a ceramic matrix composite turbine engine component, wherein the method includes providing a plurality of biased ceramic plies, wherein each biased ply comprises ceramic fiber tows, the tows being woven in a first warp direction and a second weft direction, the second weft direction lying at a preselected angular orientation with respect to the first warp direction, wherein a greater number of tows are woven in the first warp direction than in the second weft direction. The plurality of biased plies are laid up in a preselected arrangement to form the component, and a preselected number of the plurality of biased plies are oriented such that the orientation of the first warp direction of the plies lie about in the direction of maximum tensile stress during normal engine operation. A coating is applied to the plurality of biased plies. The coated component preform is then densified.

    摘要翻译： 一种制造陶瓷基体复合涡轮发动机部件的方法，其中所述方法包括提供多个偏置的陶瓷层，其中每个偏置层包括陶瓷纤维丝束，所述丝束以第一经向和第二纬向织造，所述第二纬纱 纬纱方向相对于第一经向方向位于预选角度方向，其中在第一经向方向上比在第二纬向方向上编织更多数量的丝束。 多个偏置层被放置成预选布置以形成部件，并且预选数量的多个偏置层被定向成使得层的第一经向方向的取向围绕最大拉伸应力的方向 在正常发动机运行期间。 将涂层施加到多个偏压层。 然后将涂覆的部件预制件致密化。

    Method of forming cooling holes in a ceramic matrix composite turbine components
    23.
    发明授权
    Method of forming cooling holes in a ceramic matrix composite turbine components 有权
    在陶瓷基复合涡轮机部件中形成冷却孔的方法

    公开(公告)号：US06441341B1

    公开(公告)日：2002-08-27

    申请号：US09595866

    申请日：2000-06-16

    申请人： James Dale Steibel ,  Wayne Garcia Edmondson ,  Wilbur Douglas Scheidt

    发明人： James Dale Steibel ,  Wayne Garcia Edmondson ,  Wilbur Douglas Scheidt

    IPC分类号： B23K2618

    CPC分类号： B23K26/1476 ,  B23K26/1436 ,  B23K26/1462 ,  B23K26/384 ,  B23K26/389 ,  B23K26/40 ,  B23K2101/35 ,  B23K2103/16 ,  B23K2103/30 ,  B23K2103/50 ,  B23K2103/52 ,  F01D5/186 ,  F01D5/284 ,  F05D2200/261 ,  F05D2230/13 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/676 ,  Y10T428/249928

    摘要： A method for producing apertures in hot section components of gas turbine engines made from ceramic matrix composites that have at least one oxidizable component. The method involves forming the apertures using a laser beam controlled by parameters that ablate the ceramic matrix composite in the path of the beam, while simultaneously heating the matrix material, SiC or SiN, to a sufficient temperature to oxidize it to form a silica. Sufficient heat is supplied by the beam to melt the silica to cause it to flow. The melted silica is quickly solidified as recast silica along the walls of the newly created aperture before it has an opportunity to flow and form undesirable geometries. The wall of the aperture is formed of recast silica that is a smooth surface and that forms an oxidation barrier to inhibit any further oxidation of the underlying composite as it is exposed to the high temperatures and oxidative, corrosive atmosphere of an operating gas turbine.

    摘要翻译： 一种用于在具有至少一种可氧化组分的陶瓷基复合材料制成的燃气涡轮发动机的热段部件中产生孔的方法。 该方法包括通过使用在梁的路径中烧蚀陶瓷基体复合材料的参数控制的激光束，同时将基体材料SiC或SiN加热至足以使其氧化形成二氧化硅的激光束。 通过梁供应足够的热量来熔化二氧化硅以使其流动。 熔融的二氧化硅在其具有流动和形成不期望的几何形状的机会之前，沿着新生成的孔的壁快速固化为重铸硅石。 孔的壁由重新形成的二氧化硅形成，其是光滑的表面，并且形成氧化屏障，以在暴露于工作燃气轮机的高温和氧化，腐蚀性气氛的情况下抑制下面的复合材料的任何进一步的氧化。