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A mounting arrangement (10) for a multivane segment (12) of ceramic matrix composite (CMC) composition positioned between outer and inner metallic rings (14, 16). Selected ones of the vanes (18a) of the multivane segment surround internal struts (24) joining the outer and inner rings. Spring members

A mounting arrangement (10) for a multivane segment (12) of ceramic matrix composite (CMC) composition positioned between outer and inner metallic rings (14, 16). Selected ones of the vanes (18a) of the multivane segment surround internal struts (24) joining the outer and inner rings. Spring members (26, 28) accommodate differential thermal growth between the multivane segment and the outer and inner rings, and a compliant material (30) seals against gas leakage around the segments.

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The invention claimed is: 1. A vane mounting arrangement for a gas turbine engine comprising: a plurality of multivane segments collectively defining a vane stage, each segment comprising a plurality of vanes extending between an inner shroud and an outer shroud, each segment comprising a ceramic m

The invention claimed is: 1. A vane mounting arrangement for a gas turbine engine comprising: a plurality of multivane segments collectively defining a vane stage, each segment comprising a plurality of vanes extending between an inner shroud and an outer shroud, each segment comprising a ceramic matrix composite material; an inner ring comprising a metallic material; an outer ring comprising a metallic material; a plurality of struts connected between the inner ring and the outer ring and extending through respective selected ones of the vanes; and a plurality of biasing members disposed between the segments and the respective inner ring and outer ring for preloading the segments into position between the rings and for accommodating differential thermal expansion there between. 2. The vane mounting arrangement of claim 1, further comprising compliant material disposed between the segments and at least one of the inner ring and the outer ring for accommodating relative movement between the segments and the respective ring while restricting gas passage there between. 3. The vane mounting arrangement of claim 1, further comprising: the struts comprising a center passageway; and a means for conveying a cooling fluid into the center passageway. 4. The vane mounting arrangement of claim 3, wherein the struts each comprise at least one aperture along a radial length of the respective vane for exhausting the cooling fluid. 5. The vane mounting arrangement of claim 1, wherein each strut comprises an airfoil shape. 6. The vane mounting arrangement of claim 1, further comprising: at least one of the outer shroud and the inner shroud comprising a radially extending portion extending proximate an opposed surface of a respective at least one of the outer ring and the inner ring; and a seal disposed between the radially extending portion and respective opposed surface. 7. The vane mounting arrangement of claim 6, wherein the seal comprises a rope seal. 8. The vane mounting arrangement of claim 1, wherein the biasing members comprise one of an undulating wave spring, a coil spring and a Belleville spring. 9. The vane mounting arrangement of claim 1, wherein each segment comprises a sectioned vane at each opposed end, with adjoining sectioned vanes of abutting segments defining a respective complete vane. 10. The vane mounting arrangement of claim 1, wherein vanes receiving a strut comprise a shape different than vanes not receiving a strut. 11. A gas turbine engine comprising the vane mounting arrangement of claim 1. 12. A vane mounting arrangement for a gas turbine engine comprising: a ceramic matrix composite vane stage comprising a plurality of multivane segments positioned in an abutting end-to-end arrangement; a metallic support structure for supporting the plurality of multivane segments in the abutting end-to-end arrangement within a gas turbine engine, the metallic support structure further comprising: a radially outer support for resisting movement of the vane stage in a radially outward direction; a radially inner support for resisting movement of the vane stage in a radially inward direction; a plurality of radially extending members arranged between the radially outer support and the radially inner support, each radially extending member disposed within a respective selected vane of the vane stage for relative radial movement there between, wherein fewer vanes are selected than are present; and a first spring biasing member disposed between the vane stage and the radially outer support and a second spring biasing member disposed between the vane stage and the radially inner support; the first and second spring biasing members cooperating to position the vane stage at a radial position between the radially outer support and the radially inner support responsive to a differential thermal growth condition existing between the ceramic matrix composite vane stage and the metallic support structure. 13. The vane mounting arrangement of claim 12, further comprising a sealing member disposed between the vane stage and at least one of the radially outer support and the radially inner support for blocking a gas flow there between. 14. The vane mounting arrangement of claim 12, further comprising a cooling gas passage formed in at least one of the radially outer support and the radially inner support in fluid communication with a passageway formed in each radially extending member. 15. The vane mounting arrangement of claim 12, wherein a portion of at least one of the radially extending members is in contact with its respective vane for resisting relative rotation there between. 16. The vane mounting arrangement of claim 12. wherein vanes receiving a radially extending member comprise a shape different than vanes not receiving a radially extending member. 17. A gas turbine engine comprising the vane mounting arrangement of claim 12. 18. A mounting arrangement comprising: a ceramic nozzle structure comprising a plurality of arcuate-shaped vane segments; a plurality of radially oriented struts connecting between an inner metallic support structure and an outer metallic support structure, wherein the struts support the plurality of vane segments in an abutting end-to-end arrangement within a gas turbine engine, each of the struts passing through a portion of a respective vane segment for resisting rotation of the ceramic nozzle structure while allowing radial movement of the vane segments relative to the inner and outer metallic support structures; and biasing members for positioning the ceramic structure at a relative position between the inner and outer metallic support structures responsive to a temperature condition causing differential thermal growth between the ceramic structure and the inner and outer metallic support structures. 19. The mounting arrangement of claim 18, further comprising: each segment comprising a plurality of airfoils; and each strut comprising an airfoil shape disposed within a respective one of the plurality of segment airfoils. 20. A gas turbine engine comprising the mounting arrangement of claim 18.