Combustor panel standoff pin

1. A heat shield panel for use in a gas turbine engine combustor, comprising:

a hot side;

a cold side; and

at least one attachment mechanism, the at least one attachment mechanism having a stud and a central axis extending through the stud and a plurality of standoff pins positioned circumferentially around the stud, the standoff pins having a radial extent with respect to the central axis, a circumferential extent with respect to the central axis that is greater than the radial extent, a radially outer surface having a radially convex shape and a radially inner surface having a radially concave shape with respect to the central axis, each of the standoff pins defining a first circumferential radius of curvature at a first circumferential end and a second circumferential radius of curvature at a second circumferential end.

2. The heat shield panel of claim 1 , wherein the radially outer surface is defined by an outer radius of curvature.

3. The heat shield panel of claim 2 , wherein the radially inner surface is defined by an inner radius of curvature.

4. The heat shield panel of claim 3 , wherein the inner radius of curvature has an inner value with respect to the central axis and the outer radius of curvature has an outer value and the outer value is greater than the inner value.

5. The heat shield panel of claim 4 , wherein the radially outer surface is substantially arcuate in a circumferential direction and straight-sided in an axial direction.

6. The heat shield panel of claim 5 , wherein the radially inner surface is substantially arcuate in the circumferential direction and straight-sided in the axial direction.

7. The heat shield panel of claim 3 , wherein the standoff pins include a contact surface and a transition portion connecting the contact surface to the radially outer surface and the radially inner surface.

8. The heat shield panel of claim 7 , wherein the transition portion includes a transition height and a transition width.

9. The heat shield panel of claim 8 , wherein the transition height and the transition width are substantially constant about an outer periphery of the standoff pins.

10. The heat shield panel of claim 3 , wherein the standoff pins are separated by a standoff spacing in a circumferential direction.

11. The heat shield panel of claim 10 , wherein the standoff pins have an axial height and wherein the standoff spacing has a value greater than the axial height.

12. The heat shield panel of claim 10 , wherein the circumferential extent has a value within a range from about two times the standoff spacing to about three times the standoff spacing.

13. A heat shield liner for use in a gas turbine engine combustor, comprising:

a panel having a hot side and a cold side, and

at least one attachment mechanism connected to the cold side of the panel, the at least one attachment mechanism having a stud and a central axis extending through the stud and a plurality of standoff pins positioned circumferentially around the stud, wherein each of the plurality of standoff pins have a radial extent with respect to the central axis, a circumferential extent with respect to the central axis that is greater than the radial extent, and are separated by a standoff spacing in a circumferential direction, and wherein the circumferential extent of the standoff pins has a value from about two times to about three times the standoff spacing, each of the standoff pins having a radially outer surface having a radially convex shape and a radially inner surface having a radially concave shape with respect to the central axis and defining a first circumferential radius of curvature at a first circumferential end and a second circumferential radius of curvature at a second circumferential end.

14. The heat shield liner of claim 13 , further comprising a shell, wherein the panel is secured to the shell by the at least one attachment mechanism and wherein the plurality of standoff pins include a contact surface abutting the shell.

15. The heat shield liner of claim 14 , wherein the radially outer surface is defined by an outer radius of curvature, the radially inner surface is defined by an inner radius of curvature, the inner radius of curvature has an inner value with respect to the central axis and the outer radius of curvature has an outer value with respect to the central axis and the outer value is greater than the inner value.

16. A heat shield panel for use in a gas turbine engine combustor, comprising:

a hot side;

a cold side; and

at least one attachment mechanism, the at least one attachment mechanism comprising:

a stud having a central axis and

a plurality of standoff pins positioned circumferentially around the stud, the standoff pins having a height,

wherein the plurality of standoff pins each have a radial extent with respect to the central axis and a circumferential extent with respect to the central axis that is greater than the radial extent,

wherein the standoff pins are separated there between by a standoff spacing and the height of the standoff pins is less than the standoff spacing, each of the standoff pins having a radially outer surface having a radially convex shape and a radially inner surface having a radially concave shape with respect to the central axis and defining a first circumferential radius of curvature at a first circumferential end and a second circumferential radius of curvature at a second circumferential end.

17. The heat shield panel of claim 16 , wherein the standoff pins have a radial dimension having a value within a range from about one times the standoff spacing to about two times the standoff spacing.