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A turbine blade assembly for a gas turbine includes a spar with raised ribs, a spacer with a plurality of protrusions mounted around the spar, and an outer shell mounted around the spacer. The protruding portions on the spacer surround the raised ribs on the spar. The protruding portions of the spac

A turbine blade assembly for a gas turbine includes a spar with raised ribs, a spacer with a plurality of protrusions mounted around the spar, and an outer shell mounted around the spacer. The protruding portions on the spacer surround the raised ribs on the spar. The protruding portions of the spacer act to space the interior surfaces of the outer shell away from the spar to provide a thermal insulation layer of cooling air.

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1. A blade assembly for a turbine, comprising: a spar having a plurality of raised ribs which extend along exterior sides of the spar;a spacer mounted around the exterior sides of the spar and having a plurality of protruding portions that surround the raised ribs of the spar; andan outer shell moun

1. A blade assembly for a turbine, comprising: a spar having a plurality of raised ribs which extend along exterior sides of the spar;a spacer mounted around the exterior sides of the spar and having a plurality of protruding portions that surround the raised ribs of the spar; andan outer shell mounted around the spacer. 2. The blade assembly of claim 1, further comprising a cap mounted on a top of the spar. 3. The blade assembly of claim 2, wherein an upper edge of the outer shell abuts an underside of the cap. 4. The blade assembly of claim 1, further comprising a base that is configured to be coupled to a rotating shaft of a turbine, wherein the spar is mounted to the base. 5. The blade assembly of claim 4, wherein the base comprises a base cover having an aperture through which the spar extends, and wherein a lower edge of the outer shell is mounted in and extends through the aperture of the base cover. 6. The blade assembly of claim 1, wherein a width of the protruding portions of the spacer is larger than a width of the raised ribs of the spar. 7. The blade assembly of claim 1, wherein the spacer ensures that an inner surface of the outer shell is spaced from an outer surface of the spar. 8. The blade assembly of claim 7, wherein the spacer ensures that an inner surface of the outer shell is spaced from outer ends of the raised ribs of the spar. 9. The blade assembly of claim 1, wherein the spar comprises: at least one cooling air passage that extends along a height of the spar; andat least one effusion cooling passage that extends from the at least one cooling air passage to an effusion cooling hole formed on an exterior side of the spar. 10. The blade assembly of claim 9, wherein a plurality of spacer apertures are formed through the spacer such that cooling air escaping the at least one effusion cooling passage of the spar can pass through the spacer apertures of the spacer to impinge on an inner surface of the outer shell. 11. The blade assembly of claim 10, wherein a plurality of shell apertures are formed through the outer shell, and wherein cooling air delivered to an inner surface of the outer shell can pass through the shell apertures to escape from the blade assembly. 12. The blade assembly of claim 11, wherein the shell apertures are formed along a trailing edge of the outer shell. 13. The blade assembly of claim 1, wherein the raised ribs of the spar extend only along side surfaces of the spar. 14. The blade assembly of claim 1, wherein the spacer comprises multiple sections that are attached together when the spacer is mounted on the spar. 15. The blade assembly of claim 14, wherein the outer shell comprises multiple portions that are attached together when the outer shell is mounted around the spacer. 16. The blade assembly of claim 1, wherein the outer shell comprises multiple portions that are attached together when the outer shell is mounted around the spacer. 17. The blade assembly of claim 16, wherein end edges of the multiple portions of the outer shell are attached together at sides of the blade assembly. 18. A method of assembling a blade assembly for a turbine, comprising: mounting a spacer having a plurality of protruding portions on a spar having a plurality of raised ribs which extend along exterior sides of the spar such that the protruding portions of the spacer surround the raised ribs; andmounting an outer shell around the spacer. 19. The method of claim 18, wherein the step of mounting a spacer on the spar comprises bringing two sections of the spacer together from opposite side of the spar and attaching the two sections together. 20. The method of claim 18, wherein the step of mounting an outer shell around the spacer comprises bringing two sections of the outer shell together from opposite sides of the spar and attaching the two sections together. 21. The blade assembly of claim 2, further comprising a base with a base cover having an aperture through which the spar extends, and wherein the spacer extends along substantially an entire height of the spar extending from the base cover to the cap.