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    Conbustor having a ceramic matrix composite liner
    4.
    发明授权
    Conbustor having a ceramic matrix composite liner 有权
    具有陶瓷基体复合衬套的聚变器

    公开(公告)号：US06397603B1

    公开(公告)日：2002-06-04

    申请号：US09567557

    申请日：2000-05-05

    申请人： Wayne Garcia Edmondson ,  James Dale Steibel ,  Harold Ray Hansel

    发明人： Wayne Garcia Edmondson ,  James Dale Steibel ,  Harold Ray Hansel

    IPC分类号： F23R360

    CPC分类号： F23R3/007 ,  F05B2230/606 ,  F23D2212/103 ,  F23R3/60

    摘要： A combustor having liners made from ceramic matrix composite materials (CMC's) that are capable of withstanding higher temperatures than metallic liners. The ceramic matrix composite liners are used in conjunction with mating components that are manufactured from superalloy materials. To permit the use of a combustor having liners made from CMC materials in conjunction with metallic materials used for the mating forward cowls, and aft seals with attached seal retainer over the broad range of temperatures of a combustor, the combustor is designed to allow for the differential thermal expansion of the differing materials at their interfaces in a manner that does not introduce stresses into the liner as a result of thermal expansion and also balances the flow of cooling air as a result of the thermal expansion.

    摘要翻译： 具有由陶瓷基质复合材料（CMC）制成的衬垫的燃烧器能够承受比金属衬里更高的温度。 陶瓷基复合衬套与由超级合金材料制成的配合部件结合使用。 为了允许使用具有由CMC材料制成的衬垫与用于配合前罩的金属材料的燃烧器以及在燃烧器的宽范围的温度下具有附接的密封保持器的尾部密封件，燃烧器被设计成允许 不同材料在其界面处的不均匀热膨胀以不会由于热膨胀而将应力引入衬垫并且还由于热膨胀而平衡冷却空气的流动的方式。

    Use of biased fabric to improve properties of SiC/SiC ceramic composites for turbine engine components
    7.
    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：US07579094B2

    公开(公告)日：2009-08-25

    申请号：US11424722

    申请日：2006-06-16

    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： B32B9/00

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

    摘要： The present invention is a ceramic matrix composite turbine engine component, wherein the component has a direction of maximum tensile stress during normal engine operation. The component comprises 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, and wherein a number of tows in the second weft direction allows the biased plies to maintain their structural integrity when handled. 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 preselected number of biased 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 coating is selected from the group consisting of BN, SiC, and combinations thereof. A ceramic matrix material lies in interstitial regions between the tows of each biased ply and the interstitial region between the biased plies.

    摘要翻译： 本发明是一种陶瓷基体复合涡轮发动机部件，其中该部件在正常发动机运转期间具有最大拉伸应力的方向。 所述组件包括多个偏置的陶瓷层，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，所述第二纬向相对于所述第一翘曲位于预选角度取向 方向，其中在第一经向方向上比在第二纬向上编织更多数量的丝束，并且其中在第二纬向方向上的多个丝束允许偏置层在处理时保持其结构完整性。 多个偏置层叠被布置成预选的布置以形成部件，并且多个偏置层的预选数量被定向成使得预选数量的偏置层片的第一经向方向的取向位于方向 在正常发动机运行期间最大拉伸应力。 将涂层施加到多个偏压层。 涂层选自BN，SiC及其组合。 陶瓷基质材料位于每个偏置层的丝束之间的间隙区域和偏置层之间的间隙区域之间。