Methods and apparatus for radially compliant component mounting

1. A mounting assembly for a liner of a gas turbine engine combustor, the combustor including a combustion casing, combustor liner positioned within the combustion casing, and a radially outer annular flow sleeve spaced radially outwardly, from the combustor liner, said mounting assembly comprising:

an inner ring surrounding a radially outer surface of the combustor liner, said inner ring comprising a plurality of axially extending fingers;

a radially outer ring coupled to said inner ring through a plurality of spacers that extend radially from a radially outer surface of said inner ring to said outer ring, said radially outer ring comprising a forward edge extending outwardly from said plurality of spacers, and a flange extending radially outwardly from said forward edge, said flange is coupled to the annular flow sleeve and to the combustion casing; and

at least one clamping fastener coupling said plurality of axially extending fingers to the combustor liner, said at least one clamping fastener comprises a bolt head that has a surface contour that is shaped complementary to a contour of the combustor liner radially outer surface.

2. An assembly in accordance with claim 1 wherein the combustion casing includes a forward combustion casing coupled to an aft combustion casing, and a flange extending outwardly from the forward combustion casing, said radially outer ring flange is adapted to be coupled to the combustion casing flange.

3. An assembly in accordance with claim 1 wherein said plurality of axially extending fingers are circumferentially spaced about a forward edge of said inner ring.

4. An assembly in accordance with claim 1 wherein said plurality of axially extending fingers comprise a first material, said inner ring comprises a second material wherein said first material is different than said second material.

5. An assembly in accordance with claim 1 , wherein said plurality of axially extending fingers comprise a first material, said inner ring comprises a second material wherein a coefficient of thermal expansion of the first material is greater than a coefficient of thermal expansion of the second material.

6. An assembly in accordance with claim 1 wherein said fastener comprises a plurality of metals configured to compensate for a difference in thermal growth between the liner and said inner ring such that a clamp force induced by said fastener is maintained at elevated operating temperatures.

7. An assembly in accordance with claim 1 wherein said plurality of axially extending fingers are sized in thickness and length such that axial loads resulting from a differential pressure across the liner are supported and such that said plurality of axially extending fingers deflect radially to accommodate a difference in thermal growth between the liner and said inner ring.

8. An assembly in accordance with claim 1 , wherein a radial outer surface of said radially outer ring and an inner surface of the radially outer annular flow sleeve define a radial clearance gap.

9. An assembly in accordance with claim 1 , wherein said radially outwardly extending flange is configured to couple to a complementary flange face coupled to the radially outer annular flow sleeve.

10. A gas turbine engine comprising:

a compressor;

a turbine coupled in flow communication with said compressor;

a gas turbine casing; and

a plurality of combustors arranged in an annular array about said gas turbine casing, each of said combustors comprising:

an outer casing;

a flow sleeve positioned radially within said outer casing;

a combustor liner positioned radially within said flow sleeve wherein said combustor liner comprises a ceramic matrix composite (CMC); and

a mounting assembly for said combustor liner comprising:

an inner ring surrounding a radially outer surface of said combustor liner, said inner ring comprising a plurality of axially extending fingers;

a radially outer ring coupled to said inner ring through a plurality of spacers that extend radially from a radially outer surface of said inner ring to said outer ring, said radially outer ring comprising a forward edge extending outwardly from said plurality of spacers, and a flange extending radially outwardly from said forward edge, said flange is coupled to said flow sleeve and to said casing; and

at least one clamping fastener coupling said plurality of axially extending fingers to said combustor liner, said at least one clamping fastener comprising a bolt head having a surface contour that is shaped complementary to a contour of said radially outer surface of said combustor liner.

11. A gas turbine engine in accordance with claim 10 , wherein said plurality of axially extending fingers comprise a first material, said inner ring comprises a second material wherein a coefficient of thermal expansion of the first material is greater than a coefficient of thermal expansion of the second material.

12. A gas turbine engine in accordance with claim 10 , wherein said at least one clamping fastener comprises a plurality of metals configured to compensate for a difference in thermal growth between said combustor liner and said inner ring such that a clamp force induced by said at least one clamping fastener is maintained at elevated operating temperatures.

13. A gas turbine engine in accordance with claim 10 , wherein said plurality of axially extending fingers are sized in thickness and length such that axial loads resulting from a differential pressure across said combustor liner are supported and such that said plurality of axially extending fingers deflect radially to accommodate a difference in thermal growth between said combustor liner and said inner ring.

14. A gas turbine engine in accordance with claim 10 , wherein said radially outwardly extending flange is configured to couple to a complementary flange face coupled to said flow sleeve.