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A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced

A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.

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1. A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through said gas turbine engine, said mounting assembly comprising:(a) a pin member extending through each one of a plurality of circumferenti

1. A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through said gas turbine engine, said mounting assembly comprising:(a) a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of said support member for said combustor and into a plurality of partial openings formed in said aft end of said liner, each said pin member including a head portion at one end thereof; and, (b) a device positioned within each said opening in said support member so as to retain said pin members therein; wherein said pin members and said support member are able to slide radially with respect to said liner aft end as said support member experiences thermal growth greater than said liner.2. The liner mounting assembly of claim 1, said support member further comprising a groove portion formed within a sidewall of each opening for receiving a ring-shaped member in a fixed position.3. The liner mounting assembly of claim 2, wherein a diameter of said openings in said support member are enlarged at a portion opposite said liner so as to receive said pin head portion.4. The liner mounting assembly of claim 2, wherein said head portion of said pin members has a diameter greater than an inner diameter of said ring member.5. The liner mounting assembly of claim 1, wherein said openings in said liner aft end are substantially circular.6. The liner mounting assembly of claim 1, wherein said openings in said liner aft end are substantially ovular in shape with a major axis thereof being aligned substantially parallel to said longitudinal centerline axis.7. The liner mounting assembly of claim 6, wherein said pin members and said support member are able to slide axially with respect to said liner aft end as said support member experiences thermal growth greater than said liner.8. The liner mounting assembly of claim 7, wherein said support member is able to move between a first axial position and a second axial position.9. The liner mounting assembly of claim 1, wherein said liner is made of a ceramic matrix composite.10. The liner mounting assembly of claim 1, wherein said support member is made of a metal.11. The liner mounting assembly of claim 1, wherein said support member is able to move between a first radial position and a second radial position.12. The liner mounting assembly of claim 1, wherein said support member is substantially fixed circumferentially with respect to said liner.13. The liner mounting assembly of claim 1, said support member further comprising an annular groove portion formed therein for receiving a band member so as to intersect each opening.14. The liner mounting assembly of claim 1, each said pin member including a threaded partial opening formed therein.15. The liner mounting assembly of claim 1, wherein said liner is an outer liner of said combustor.16. The liner mounting assembly of claim 1, wherein said liner is an inner liner of said combustor.17. A combustor for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising:(a) an outer liner having a forward end and an aft end, said outer liner being made of a ceramic matrix composite material; (b) an outer casing located substantially parallel to said outer liner so as to form an outer passage therebetween, said outer casing being made of a metal; (c) an outer support member associated with said outer casing and located adjacent said outer liner aft end, said outer support member being made of a metal; and, (d) an assembly for mounting said outer liner aft end to said outer support member, said mounting assembly further comprising: (1) a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of said outer support member for said combustor and into a plurality of partial openings formed in said aft end of said outer liner, each said pin member including a head portion at one end thereof; and (2) a device positioned within each said opening in said outer support member so as to retain said pin members therein; wherein said outer support member is movably connected to said outer liner aft end in a radial direction as said outer casing and said outer support member experience thermal growth greater than said outer liner.18. The combustor of claim 17, wherein said outer support member is movably connected to said outer liner aft end in an axial direction as said outer casing and said outer support member experience thermal growth greater than said outer liner.19. A combustor for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising:(a) an outer liner having a forward end and an aft end, said outer liner being made of a ceramic matrix composite material, (b) an outer casing located substantially parallel to said outer liner so as to form an outer passage therebetween, said outer casing being made of a metal; (c) an outer support member associated with said outer casing and located adjacent said outer liner aft end, said outer support member being made of a metal; and, (d) an assembly for mounting said outer liner aft end to said outer support member, said mounting assembly further comprising: (1) a pin member extending through each one of a plurality of circumferentially spaced openings in a first portion of said outer support member for said combustor, a plurality of openings formed in said aft end of said outer liner and into a plurality of partial openings formed in a second portion of said outer support member oriented substantially parallel to said outer support member first portion; and, (2) a device positioned within each said opening in said outer support member so as to retain said pin members therein; wherein said outer support member is movably connected to said outer liner aft end in a radial direction as said outer casing and said outer support member experience thermal growth greater than said outer liner.20. A combustor for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising:(a) an inner liner having a forward end and an aft end, said inner liner being made of a ceramic matrix composite material; (b) an inner support cone located substantially parallel to said inner liner so as to form an inner passage therebetween, said inner support come being made of a metal; and, (c) an assembly for mounting said inner liner aft end to said inner support cone, said mounting assembly further comprising: (1) a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of said inner support cone for said combustor and into a plurality of partial openings formed in said aft end of said inner liner, each said pin member including a head portion at one end thereof; and, (2) a device positioned within each said openings in said inner support cone so as to retain said pin members therein; wherein said inner support cone is movably connected to said inner liner aft mad in a radial direction as said inner support cone experiences thermal growth greater than said inner liner.21. The combustor of claim 20, wherein said inner support cone is movably connected to said inner liner aft end in an axial direction as said inner support cone experiences thermal growth greater than said inner liner.22. A combustor for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising:(a) an inner liner having a forward end and an aft end, said inner liner being made of a ceramic matrix composite material; (b) an inner support cone located substantially parallel to said inner liner so as to form an inner passage therebetween, said inner support cone being made of a metal; and, (c) an assembly for mounting said inner liner aft end to said inner support cone, said mounting assembly further comprising: (1) a pin member extending through each one of a plurality of circumferentially spaced openings in a first portion of said inner support cone for said combustor, a plurality of openings formed in said aft end of said inner liner and into a plurality of partial openings formed in a second portion of said inner support cone oriented substantially parallel to said inner support cone first portion; and, (2) a device positioned within each said opening in said inner support cone so as to retain said pin members therein; wherein said inner support cone is movably connected to said inner liner aft end in a radial direction as said inner support cone experiences thermal growth greater than said inner liner.23. A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through said gas turbine engine, said mounting assembly comprising:(a) a pin member extending through each one of a plurality of circumferentially spaced openings in a first portion of said support member for said combustor, a plurality of openings formed in said aft end of said liner and into a plurality of partial openings formed in a second portion of said support member oriented substantially parallel to said support member first portion, each said pin member including ahead portion at one end thereof; and, (b) a device positioned within each said opening in said support member first portion so as to retain said pin members therein; wherein said pin members and said support member are able to slide radially with respect to said liner aft end as said support member experiences thermal growth greater than said liner.24. The liner mounting assembly of claim 23, said support member first portion further comprising a groove portion formed within a sidewall of each opening for receiving said device in a fixed position.25. The liner mounting assembly of claim 23, said support member further comprising a third portion connecting said first and second portions, wherein a gap for receiving said liner aft end is defined between said first and second support member portions.26. The liner mounting assembly of claim 23, wherein said openings in said liner aft end are substantially circular.27. The liner mounting assembly of claim 23, wherein said openings in said liner aft end are substantially ovular an shape with a major axis thereof being aligned substantially parallel to said longitudinal axis.28. The liner mounting assembly of claim 27, wherein said pin members and said support member are able to slide axially with respect to said liner aft end as said support member experiences thermal growth greater than said liner.29. The liner mounting assembly of claim 28, wherein said support member is able to move between a first axial position and a second axial position.30. The liner mounting assembly of claim 23, wherein said liner is made of a ceramic matrix composite.31. The liner mounting assembly of claim 23, wherein said support member is made of a metal.32. The liner mounting assembly of claim 23, each said pin member including a threaded partial opening formed therein.33. The liner mounting assembly of claim 23, wherein said support member is able to move between a first radial position and a second radial position.34. The liner mounting assembly of claim 23, wherein said support member is substantially fixed circumferentially with respect to said liner.35. The liner mounting assembly of claim 23, wherein said liner is an outer liner of said combustor.36. The liner mounting assembly of claims 23, wherein said liner is an inner liner of said combustor.