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A gas turbine combustor includes a substantially cylindrical combustor liner located substantially concentrically within a flow sleeve, the combustor liner composed through a ceramic matrix composite material, a forward end of the combustor liner provided with a plurality of circumferentially arrang

A gas turbine combustor includes a substantially cylindrical combustor liner located substantially concentrically within a flow sleeve, the combustor liner composed through a ceramic matrix composite material, a forward end of the combustor liner provided with a plurality of circumferentially arranged bolt holes. An inner metal ring is located about an outside surface of the forward end of the combustor liner, the inner metal ring provided with a second plurality of circumferentially spaced bolt holes, with a plurality of bolts extending through the first and second pluralities of bolt holes and secured by self-locking nuts. An outer metal ring is spaced radially outwardly of the inner metal ring, with a plurality of circumferentially spaced struts extending between the inner and outer rings.

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What is claimed is: 1. A gas turbine combustor comprising a substantially cylindrical combustor liner located substantially concentrically within a flow sleeve, said combustor liner composed of a ceramic matrix composite material, a forward end of said combustor liner provided with a first pluralit

What is claimed is: 1. A gas turbine combustor comprising a substantially cylindrical combustor liner located substantially concentrically within a flow sleeve, said combustor liner composed of a ceramic matrix composite material, a forward end of said combustor liner provided with a first plurality of circumferentially arranged bolt holes; an inner metal ring located about an outside surface of said forward end of said combustor liner, said inner metal ring provided with a second plurality of circumferentially spaced bolt holes; and a plurality of bolts extending through said first and second pluralities of bolt holes to thereby secure one end of said inner metal ring to said combustor liner; and wherein said inner metal ring comprises a solid annular portion and a plurality of axially extending, circumferentially spaced spring fingers, said second plurality of circumferentially spaced bolt holes located in respective ones of said spring fingers. 2. The gas turbine combustor of claim 1 wherein a self-locking nut is threadably secured to each bolt and engaged in a countersunk flat formed in a radially outer surface of a respective spring finger. 3. The gas turbine combustor of claim 2 and further comprising a first plurality of resilient metal seals engaged with a radially inner surface of said combustor liner, at said forward end of said liner. 4. The gas turbine combustor of claim 3 and further comprising a second plurality of resilient metal seals engaged with said radially inner surface of said combustor liner, at an aft end of said liner. 5. The gas turbine combustor of claim 1 wherein said second plurality of bolt holes of said inner metal ring are each formed with a slab-sided counter bore adapted to receive a slab-sided shank portion of said bolts. 6. The gas turbine combustor of claim 1 and further comprising an outer metal ring spaced radially outward of said inner metal ring, with a plurality of circumferentially spaced struts extending between said inner and outer rings. 7. The gas turbine combustor of claim 6 wherein said circumferentially spaced struts are provided in pairs, each pair connected by a curved segment fixed to said outer metal ring. 8. A gas turbine combustor comprising a substantially cylindrical combustor liner located substantially concentrically within a flow sleeve, said combustor liner composed of a ceramic matrix composite material, a forward end of said combustor liner provided with a first plurality of circumferentially arranged bolt holes; an inner metal ring located about an outside surface of said forward end of said combustor liner, said inner metal ring having a solid annular portion and a plurality of axially extending, circumferentially spaced spring fingers, with a second plurality of circumferentially spaced slab-sided bolt holes located in respective ends of said spring fingers; and a plurality of bolts extending through said first and second pluralities of bolt holes to thereby secure said inner metal ring to said combustor liner; wherein a self-locking nut is threadably secured to each bolt and engaged with a radially outer surface of a respective spring finger; and wherein said slab-sided bolt holes are each adapted to receive a slab-sided shank portion of a respective one of said bolts. 9. The gas turbine combustor of claim 8 and further comprising an outer metal ring spaced radially outward of said inner metal ring, with a plurality of circumferentially spaced, radial struts extending between said inner and outer rings. 10. The gas turbine combustor of claim 9 wherein said circumferentially spaced struts are provided in pairs, each pair connected by a curved segment fixed to said outer metal ring. 11. The gas turbine combustor of claim 10 wherein said segments are welded to said outer ring and said struts are welded to said inner ring. 12. The gas turbine combustor of claim 8 wherein each of said bolts has an integral washer face with a cylindrically curved face. 13. The gas turbine combustor of claim 12 wherein said cylindrically curved face substantially matches a curvature of said combustor liner and wherein said slab-sided counter bore and said slab-sided shank are oriented to align said curved face with the curvature of said combustor liner. 14. The gas turbine combustor of claim 9 wherein a ratio of number of spring fingers to number of radial struts is 2 to 1. 15. The gas turbine combustor of claim 9 wherein said outer metal ring is sized and shaped such that radial and axial gaps are established between said liner and said flow sleeve, thus permitting limited radial and axial float of said liner relative to said flow sleeve. 16. A gas turbine combustor comprising a substantially cylindrical combustor liner located substantially concentrically within a flow sleeve, said combustor liner composed of a ceramic matrix composite material, a forward end of said combustor liner provided with a first plurality of circumferentially arranged bolt holes; an inner metal ring located about an outside surface of said forward end of said combustor liner, said inner metal ring provided with a second plurality of circumferentially spaced bolt holes; and a plurality of bolts extending through said first and second pluralities of bolt holes to thereby secure one end of said inner metal ring to said combustor liner, an opposite end of said inner metal ring provided with a plurality of radially extending struts connecting said opposite end of said inner metal ring to a radially outer metal ring located in proximity to said flow sleeve such that a limited degree of radial and axial float is permitted between said combustor liner and said flow sleeve. 17. The gas turbine combustor of claim 16 wherein said inner metal ring comprises a solid annular portion and a plurality of axially extending, circumferentially spaced spring fingers, said second plurality of circumferentially spaced bolt holes located in respective ones of said spring fingers. 18. The gas turbine combustor of claim 17 wherein a self-locking nut is threadably secured to each bolt and engaged in a countersunk flat formed in a radially outer surface of a respective spring finger.