Stand-off device for double-skin combustor liner
A combustor for a gas turbine engine comprises a combustor chamber defined at least partially by an outer combustor skin and an inner combustor skin. A plurality of stand-off devices have a body including a first end and a second end, the second end of the body retained in an opening in the outer combustor skin, the first end spaced apart from the second end and abutting the inner combustor skin to space the inner combustor skin apart from the outer combustor skin.
1. A combustor for a gas turbine engine comprising:
a combustor chamber defined at least partially by an outer combustor skin being metallic and by an inner combustor skin made of a ceramic matrix composite (CMC), a coating against the inner combustor skin; and
a plurality of stand-off devices, each standoff-device of the plurality of stand-off devices having a body including a first end and a second end, the second end of the body retained in an opening in the outer combustor skin, the first end spaced apart from the second end and abutting the coating disposed between the first end of the body and the inner combustor skin, to space the inner combustor skin apart from the outer combustor skin, the first end being displaceable relative to the inner combustor skin.
2. The combustor according to claim 1 , wherein the body has enlarged portions on opposite sides of the opening.
3. The combustor according to claim 2 , wherein the body has an elongated pin shape having a long axis coinciding with an axis of the opening in the outer combustor skin.
4. The combustor according to claim 1 , wherein the stand-off devices are circumferentially and axially distributed along the combustor chamber.
5. The combustor according to claim 1 , further comprising a biasing assembly biasing the body against the inner combustor skin.
6. The combustor according to claim 5 , wherein the body has a stop portion at the second end to bound movement of the body when biased.
7. The combustor according to claim 5 , wherein the biasing assembly includes a spring.
8. The combustor according to claim 7 , wherein the biasing assembly includes a cap secured to an outer surface of the outer combustor skin and accommodating the spring therein.
9. The combustor according to claim 1 , wherein the coating is secured to the inner combustor skin.
10. The combustor according to claim 1 , wherein the coating is resilient and configured to provide damping by elastic deformation of the coating.
11. A combination comprising a stand-off device and a double-skin combustor liner having an outer combustor skin and an inner combustor skin, the stand-off device comprising a body having a first end and a second end, the body configured to be retained by the outer combustor skin and to pass through an opening in the outer combustor skin for the first end to hold the inner combustor skin spaced apart from the outer combustor skin, the first end configured to contact a coating applied against the inner combustor skin, the first end being displaceable relative to the inner combustor skin, the second end of the body accessible from an outer surface of the outer combustor skin.
12. The combination according to claim 11 , wherein the body has enlarged portions configured to be on opposite sides of the opening.
13. The combination according to claim 12 , wherein the body is a rivet.
14. The combination according to claim 11 , wherein the first end has a flat contact surface configured to contact the inner combustor skin.
15. The combination according to claim 11 , further comprising a biasing assembly configured to bias the body against the inner combustor skin.
16. The combination according to claim 15 , wherein the body has a stop portion at the second end to bound movement of the body when biased.
17. The combination according to claim 15 , wherein the biasing assembly includes a spring.
18. The combination according to claim 17 , wherein the biasing assembly includes a cap configured to be secured to the outer surface of the outer combustor skin and accommodating the spring therein.
19. A combustor for a gas turbine engine, comprising:
a combustor chamber defined at least by an outer combustor skin being metallic and by an inner combustor skin made of a ceramic matrix composite (CMC); and
a plurality of stand-off devices, each standoff-device of the plurality of stand-off devices having a body including a first end and a second end, the second end of the body retained in an opening in the outer combustor skin, the first end spaced apart from the second end and abutting the inner combustor skin to space inner combustor skin apart from the outer combustor skin, the first end being displaceable relative to the inner combustor skin, the body having an outer portion abutted against an outer surface of the outer combustor skin and an inner portion abutted against an inner surface of the outer combustor skin, the outer portion having an outer portion diameter and the inner portion having an inner portion diameter, the outer portion diameter and the inner portion diameter being greater than a diameter of the opening in the outer combustor skin.
20. The combustor according to claim 19 , comprising a coating against the inner combustor skin, the coating disposed between the first end of the body and the inner combustor skin.