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1. (WO2019046022) COMPOSANT CMC HYBRIDE AYANT DES CARÉNAGES INTÉGRÉS ET MODULAIRES
Note: Texte fondé sur des processus automatiques de reconnaissance optique de caractères. Seule la version PDF a une valeur juridique

What is claimed is:

1. A gas turbine engine component (25) comprising:

an outer metallic shroud substructure (11) forming part of an outer shroud

(12) ;

an inner metallic shroud substructure (13) forming part of an inner shroud (14); a metallic core airfoil structure (9) extending between the outer metallic shroud substructure (13) and the inner metallic shroud substructure (13), wherein the metallic core airfoil structure (9) forms part of an airfoil (9);

a first CMC structure (20) covering the metallic core airfoil structure (9) and the outer metallic shroud substructure (11), wherein the first CMC structure (20) forms part of the outer shroud (12) and the airfoil (9); and

a second CMC structure (21) covering the inner metallic shroud substructure

(13) , wherein the second CMC structure (21) forms part of the inner shroud (14).

2. The gas turbine engine component (25) of claim 1, wherein the metallic core airfoil structure (9) is fixedly attached to the outer metallic shroud substructure (11) and the inner metallic shroud substructure (13).

3. The gas turbine engine component (25) of claim 1, wherein the first CMC structure (20) is fixedly attached to the outer metallic shroud substructure (11).

4. The gas turbine engine component (25) of claim 1, wherein the second CMC structure (21) is fixedly attached to the inner metallic shroud substructure (13).

5. The gas turbine engine component (25) of claim 1, wherein the airfoil (9) can accommodate thermal expansion within the inner shroud (14).

6. The gas turbine engine component (25) of claim 1, wherein the airfoil (9) further comprises fillets (23) formed from the first CMC structure (20).

7. The gas turbine engine component (25) of claim 1 , wherein the first CMC structure (20) is formed with a plurality of plies (30, 31, 32), wherein a first set (31) of the plurality of plies extends along the length of airfoil (9) into the outer shroud (12), thereby transferring loads into the outer metallic shroud substructure (11).

8. The gas turbine engine component (25) of claim 7, wherein the plurality of plies (30, 31, 32) further comprises a second set (31) of the plurality of plies which extends along the length of the airfoil (9) and forms part of the outer shroud (12).

9. The gas turbine engine component (25) of claim 7, wherein the plurality of plies (30, 31, 32) further comprises a third set of the plurality of plies which extends into the outer shroud (12) and forms part of the outer shroud (12).