Combustor assembly for a turbine engine

1. A combustor assembly for a gas turbine engine defining an axial direction, the combustor assembly comprising:

an annular dome including an enclosed surface defining a slot, an inner dome and an outer dome;

a liner at least partially defining a combustion chamber and extending between an aft end and a forward end generally along the axial direction, the forward end of the liner received within the slot of the annular dome;

a heat shield including a first end and a second end, at least one of the first end and the second end also received within the slot of the annular dome; and

a mounting assembly positioned at least partially within the slot of the annular dome, attaching the forward end of the liner and the end of the heat shield to the annular dome, wherein said heat shield extends from said inner dome to said outer dome,

wherein the mounting assembly includes a pin, a first grommet, and a second grommet, wherein the first grommet is positioned in an opening in the forward end of the liner, wherein the second grommet is positioned in an opening in the heat shield, and

wherein the first and second grommets are positioned around the pin.

2. The combustor assembly of claim 1 , wherein the annular dome includes a base plate and a yoke, wherein the base plate and the yoke extend substantially parallel to one another, and wherein the enclosed surface of the dome includes a surface of the base plate and a surface of the yoke such that the slot is defined between the base plate and the yoke.

3. The combustor assembly of claim 2 , wherein the mounting assembly extends through the yoke of the annular dome, the forward end of the liner, at least one of the first end and the second end of the heat shield, and the base plate of the annular dome.

4. The combustor assembly of claim 3 , wherein the mounting assembly includes a bushing, wherein the pin extends through the yoke, the forward end of the liner, the heat shield, and the base plate, and wherein the bushing is positioned around the pin within the slot and pressed between the yoke and the base plate.

5. The combustor assembly of claim 1 , wherein the liner is an outer liner.

6. The combustor assembly of claim 1 , wherein the liner is an inner liner, and wherein first grommet and forward end of the inner liner may move relative to the second grommet and the second end of the heat shield.

7. The combustor assembly of claim 1 , wherein the liner and the heat shield are each comprised of a ceramic matrix composite material, and wherein the annular dome is comprised of a metal material.

8. A gas turbine engine defining an axial direction, the gas turbine engine comprising:

a compressor section;

a turbine section mechanically coupled to the compressor section through a shaft; and

a combustor assembly disposed between the compressor section and the turbine section, the combustor assembly including

an annular dome including an enclosed surface defining a slot, an inner dome and an outer dome;

a liner at least partially defining a combustion chamber and extending between an aft end and a forward end generally along the axial direction, the forward end of the liner received within the slot of the annular dome;

a heat shield including a first end and a second end, at least one of the first end and the second end also received within the slot of the annular dome; and

a mounting assembly positioned at least partially within the slot of the annular dome and attaching the forward end of the liner and the end of the heat shield to the annular dome

wherein said heat shield extends from said inner dome to said outer dome,

wherein said heat shield is attached to both of said inner dome and said outer dome,

wherein the mounting assembly includes a pin, a first grommet, and a second grommet, wherein the first grommet is positioned in an opening in the forward end of the liner, wherein the second grommet is positioned in an opening in the heat shield, and

wherein the first and second grommets are positioned around the pin.

9. The gas turbine engine of claim 8 , wherein the annular dome includes a base plate and a yoke, wherein the base plate and the yoke extend substantially parallel to one another, and wherein the enclosed surface of the dome includes a surface of the base plate and a surface of the yoke such that the slot is defined between the base plate and the yoke.

10. The gas turbine engine of claim 9 , wherein the mounting assembly extends through the yoke of the annular dome, the forward end of the liner, the end of the heat shield, and the base plate of the annular dome.

11. The gas turbine engine of claim 10 , wherein the mounting assembly includes a bushing, wherein the pin extends through the yoke, the forward end of the liner, one of the first end and the second end of the heat shield, and the base plate, and

wherein the bushing is positioned around the pin within the slot and pressed between the yoke and the base plate.

12. The gas turbine engine of claim 8 , wherein the liner is an outer liner.

13. A combustor assembly for a gas turbine engine defining an axial direction, the combustor assembly comprising:

an outer annular dome including an enclosed surface defining a slot;

an outer liner including a forward end received within the slot of the outer annular dome;

an inner annular dome also including an enclosed surface defining a slot;

an inner liner including a forward end received within the slot of the inner annular dome, the inner and outer liners at least partially defining a combustion chamber; and

a heat shield including a first end and a second end, the first end co-mounted with the outer liner to the outer annular dome within the slot of the outer annular dome, and the second end co-mounted with the inner liner to the inner annular dome within the slot of the inner annular dome,

wherein said heat shield extends from said inner annular dome to said outer annular dome,

wherein an inner mounting assembly is positioned at least partially within the slot of the inner annular dome, the inner mounting assembly includes a pin, a first grommet, and a second grommet, wherein the first grommet is positioned in an opening in the forward end of the inner liner, wherein the second grommet is positioned in an opening in the second end of the heat shield, wherein the first and second grommets are positioned around the pin, and

wherein an outer mounting assembly includes a single grommet comprising an outer collar positioned adjacent to an outside surface of the outer liner, a middle collar positioned adjacent to an inside surface of the outer liner and an outside surface of the heat shield, and an inner collar positioned adjacent to an inside surface of the heat shield.

14. The combustor assembly of claim 13 , further comprising:

wherein at least a portion of the outer mounting assembly is positioned within the slot of the outer annular dome, co-mounting the forward end of the outer liner and the first end of the heat shield to the outer annular dome; and

wherein at least a portion of the inner mounting assembly is positioned within the slot of the inner annular dome, co-mounting the forward end of the inner liner and the second end of the heat shield to the inner annular dome, wherein said inner mounting assembly is configured to allow for a relative thermal expansion of the inner liner.