Mounting a ceramic component to a non-ceramic component in a gas turbine engine

1. A combustor with a centerline, comprising:

a support structure; and

a heat shield extending circumferentially about and axially along the centerline, the heat shield comprising ceramic material, and the heat shield mounted to the support structure by an interlocking joint connection;

the interlocking joint connection comprising a projection and a groove, the projection configured with the support structure and including a plurality of fingers arranged along and projecting into the groove, and the groove formed in the heat shield;

wherein the groove is formed within the heat shield radially between a groove first side surface and a groove second side surface;

wherein the plurality of fingers include a first finger configured with a first portion and a second portion;

wherein the first portion radially engages the groove first side surface and is spaced from the groove second side surface; and

wherein the second portion radially engages the groove second side surface and is spaced from the groove first side surface.

2. The combustor of claim 1 , wherein

the first portion is biased radially the against groove first side surface; and

the second portion is biased radially the against groove second side surface.

3. The combustor of claim 1 , wherein the first portion overlaps the second portion.

4. The combustor of claim 1 , wherein

a groove end surface extends radially between the groove first side surface and the groove second side surface; and

the second portion is between the first portion and the groove end surface.

5. The combustor of claim 1 , wherein the first finger is further configured with a third portion that radially engages the groove first side surface or the groove second side surface.

6. The combustor of claim 1 , wherein the combustor is configured to direct cooling air to a portion of the projection within the groove.

7. The combustor of claim 1 , wherein the projection comprises metal.

8. The combustor of claim 1 , further comprising:

a heat shield mount including the projection;

the heat shield mount configured as a monolithic full hoop body.

9. The combustor of claim 1 , further comprising:

a heat shield mount including the projection and a mount base;

the projection projecting axially out from the mount base and into the groove.

10. The combustor of claim 9 , further comprising:

a combustor bulkhead; and

a combustor hood;

the combustor hood, the combustor bulkhead, the heat shield mount and the support structure arranged together in a stack and connected together by a fastener that projects radially through the stack.

11. The combustor of claim 1 , further comprising:

a heat shield mount including the projection and a mount base;

the heat shield mount configured with a mount groove extending radially between the projection and the mount base; and

the support structure and the heat shield projecting axially into the mount groove.

12. The combustor of claim 11 , wherein the heat shield mount is attached to the support structure by a fastener extending radially through a slot formed in the mount base.

13. The combustor of claim 1 , wherein

the heat shield extends axially along the centerline between an upstream end and a downstream end; and

the interlocking joint connection is located at the upstream end or the downstream end.

14. The combustor of claim 1 , further comprising a locating feature configured to circumferentially and/or axially locate the heat shield relative to the support structure, the locating feature comprising a tubular body that forms a quench aperture.

15. An assembly for a gas turbine engine, comprising:

a support structure; and

a turbine engine component extending circumferentially about and axially along a centerline, the turbine engine component comprising ceramic matrix composite material, and the turbine engine component mounted to the support structure by a connection;

the connection comprising a plurality of protrusions and a groove, the plurality of protrusions arranged circumferentially about the centerline and extending axially into the groove, and the groove formed within the turbine engine component at an axial end of the turbine engine component;

wherein the groove is formed within the turbine engine component radially between a groove first side surface and a groove second side surface;

wherein a first of the plurality of protrusions contacts and is biased radially against the groove first side surface; and

wherein a second of the plurality of protrusions contacts and is biased radially against the groove second side surface.

16. An assembly for a gas turbine engine, comprising:

a support structure; and

a turbine engine component extending circumferentially about and axially along a centerline, the turbine engine component comprising ceramic matrix composite material and configured with a groove, an inner groove side surface and an outer groove side surface, and the turbine engine component mounted to the support structure by a connection;

the connection comprising the groove and a projection; and

the projection configured with the support structure and projecting axially along the centerline into the groove;

wherein a first portion of the projection is engaged with the inner groove side surface and disengaged from the outer groove side surface; and

wherein a second portion of the projection is engaged with the outer groove side surface and disengaged from the inner groove side surface.

17. The assembly of claim 16 , wherein the first portion of the projection is axially aligned with the second portion of the projection along the centerline.

18. The assembly of claim 16 , wherein the first portion of the projection is circumferentially aligned with the second portion of the projection about the centerline.