Combustor bulkhead heat shield

1. A gas turbine engine comprising:

a compressor section;

a combustor in fluid communication with the compressor section;

a turbine section in fluid communication with the combustor;

said combustor further comprising a combustor region defined by at least one bulkhead panel and at least one combustor wall, and at least one heat shield panel interior to said combustor region, wherein said at least one heat shield panel is maintained between said at least one bulkhead panel and said at least one combustor wall via an interference fit at a radially outward edge of the at least one heat shield panel.

2. A gas turbine engine comprising:

a compressor section;

a combustor in fluid communication with the compressor section;

a turbine section in fluid communication with the combustor;

said combustor further comprising a combustor region defined by at least one bulkhead panel and at least one combustor wall, and at least one heat shield panel interior to said combustor region, wherein said at least one heat shield panel is maintained between said at least one bulkhead panel and said at least one combustor wall via an interference fit; and

wherein said at least one heat shield panel comprises a plurality of axially aligned through holes, and wherein said combustor comprises a plurality of swirlers protruding into said plurality of axially aligned through holes.

3. A gas turbine engine comprising:

a compressor section;

a combustor in fluid communication with the compressor section;

a turbine section in fluid communication with the combustor;

said combustor further comprising a combustor region defined by at least one bulkhead panel and at least one combustor wall, and at least one heat shield panel interior to said combustor region, wherein said at least one heat shield panel is maintained between said at least one bulkhead panel and said at least one combustor wall via an interference fit; and

wherein said combustor further comprises a plurality of outer liner panels and a plurality of inner liner panels, and wherein at least one panel of said plurality of outer liner panels and said plurality of inner liner panels comprises a portion curved toward a center of the combustor region.

4. The gas turbine engine of claim 3 , wherein said at least one heat shield panel comprises at least one layer of a ceramic matrix composite (CMC) material and at least one layer of a high heat tolerance machinable temperature material.

5. The gas turbine engine of claim 4 , wherein said high heat tolerance machinable material comprises silicon.

6. The gas turbine engine of claim 3 , wherein said at least one combustor wall further comprises an outer diameter combustor shell and an inner diameter combustor shell, wherein at least one of said outer diameter combustor shell and said inner diameter combustor shell includes a protrusion into said combustor and wherein an edge of said at least one heat shield panel is axially positioned between said protrusion and said at least one bulkhead panel relative to an axis defined by said gas turbine engine.

7. The gas turbine engine of claim 6 , wherein each of said outer diameter combustor shell and said inner diameter combustor shell includes a protrusion into said combustor and wherein an inner diameter edge of said at least one heat shield panel is axially positioned between said protrusion on said inner diameter combustor shell and said at least one bulkhead panel, and wherein a portion of said at least one heat shield panel is axially positioned between said protrusion on said outer diameter combustor shell and said at least one bulkhead panel.

8. The gas turbine engine of claim 6 , wherein said interference fit is an interference fit between said protrusion, said at least one bulkhead panel and one of an inner diameter edge and an outer diameter edge of said at least one heat shield panel.

9. The gas turbine engine of claim 3 , wherein said at least one heat shield panel has a primary axial thickness and a secondary axial thickness, where said secondary axial thickness is positioned proximate to one of an inner diameter and an outer diameter.

10. The gas turbine engine of claim 3 , wherein said portion is an interference fit protection feature and is a portion of a liner closest to the at least one heat shield panel.

11. A heat shield for a combustor comprising:

a ring shaped body including a central opening defining a radially inner edge of the ring shaped body, the ring shaped body comprising a ceramic material,

a plurality of through holes distributed circumferentially about the ring shaped body;

an interference fit shaped portion on at least one of said radially inner edge and a radially outward edge of the heat shield; and

wherein said interference fit shaped portion is a rounded bulb shape and wherein said rounded bulb shape has a diameter larger than a thickness of said ring shaped body along an axis defined by the ring shaped body.

12. The heat shield of claim 11 , further comprising a high heat tolerance machinable material layer applied to all sides of said heat shield.

13. The heat shield of claim 12 , wherein said high heat tolerance machinable layer comprises silicon.

14. The heat shield of claim 11 , further comprising an interference fit shaped portion on both said radially inner edge and a radially outer edge of the ring shaped body.

15. The heat shield of claim 11 , wherein said interference fit shaped portion has a first thickness along an axis defined by the ring shaped body, the ring shaped body has a second thickness along the axis defined by the ring shaped body, and the first thickness is larger than the second thickness.

16. The heat shield of claim 11 , wherein an edge of said ring shaped body extends into the interference fit shaped portion.

17. The heat shield of claim 11 , wherein the ring shaped body comprises a ceramic matrix composite (CMC) material.