The invention relates to a method for producing a turbomachine blade from a composite material, having an integrated platform and/or shroud. The method comprises the following steps: the three-dimensional weaving of a flexible fibrous blank as a single part comprising blade vane (220) and root (230) preform portions; the separate production of a blade platform (400) or blade shroud (500) element comprising a stiffened fibrous reinforcement, whereby at least one opening in the shape of the vane profile of the blade to be produced is formed in the platform or shroud element; the mounting of the platform or shroud element, by means of the opening therein, on the flexible fibrous blank, with deformation of the latter, for assembly with the fibrous blank; the forming of the fibrous blank with the assembled platform or shroud element in order to obtain a preform (200) having a shape similar to that of the blade to be produced; the setting of the shape of the preform in a former; and the introduction of a matrix in the preform in order to obtain a blade made from a composite material and having an integrated platform or shroud.

Method for producing a turbomachine blade made from a composite material

An engine has a blade stage (10) and a circumferential array of blade outer air seal segments (66). A support ring (70) carries the blade outer air seal segments (66). The support ring (70) has a low-CTE member (72) and a high-CTE member (90) intervening between the blade outer air seal segments (66) and the low-CTE member (72).

Blade clearance control using high-CTE and low-CTE ring members

A segmented component for use with a gas turbine engine comprises a radially extending gas path portion. The gas path portion is for interacting with gas flow from the gas turbine engine. The component is divided into axially aligned segments comprising a forward segment, an aft segment, and a plurality of middle segments disposed between the forward segment and the aft segment. The middle segments comprise radially elongate ceramic matrix composite material plates. In one embodiment, the gas path portion comprises an airfoil for a turbine blade. In another embodiment, the gas path portion comprises a removable platform for a turbine blade. In another embodiment, the gas path portion comprises an airfoil for a turbine vane.

Segmented ceramic matrix composite turbine airfoil component

A vane assembly (10) for a gas turbine engine is disclosed herein. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil (16) that extends from the inner platform to the outer platform. The ceramic-containing airfoil is manufactured to have radially discontinuous ribs (25) spaced radially apart from one another between the inner platform and the outer platform.

Vane assembly for a gas turbine engine

The invention relates to a blade (12) for a gas turbine, in particular for an aircraft engine, wherein the blade (12) comprises at least one internal and / or external support structure (14) made of a metallic and / or intermetallic material. The invention further relates to a blade cluster (10) having at least one such blade (12) for a gas turbine, to a method for producing such a blade cluster (10) and to a gas turbine.

Blade for a gas turbine

A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a depth-wise coefficient of thermal expansion and a second coefficient of thermal expansion transverse thereto, the depth-wise coefficient of thermal expansion being greater than the second coefficient of thermal expansion.

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Jeffrey R. Schaff

Papers

Ceramic matrix composite turbine engine vane