| 摘要 |
Fabricating a refractory component for a gas turbine engine, such as a turbine shroud ring segment, by arranging refractory fiber tows ( 24 ) in a flaired tubular geometry ( 20 ) comprising a stem portion ( 21 ) and a funnel-shaped portion ( 22 ); impregnating the refractory fibers ( 24 ) with a ceramic matrix to form a flaired tube ( 20 ) of ceramic composite matrix material; at least partially filling the funnel-shaped portion ( 22 ) with a ceramic core ( 30 ) extending beyond the end of the funnel-shaped portion to provide a working gas containment surface ( 31 ); curing the flaired tube ( 20 ) and the ceramic core ( 30 ) together; cutting the funnel-shaped portion ( 22 ) to provide rectangular edges ( 27 ); and providing an attachment mechanism ( 34, 36, 38, 40 ) on the stem portion ( 21 ) for attaching the component to a surrounding support structure. Additional tows ( 24 ) may be introduced at intermediate stages to maintain a desired fabric density.
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