Claims
- 1. A combustor apparatus, comprising:a combustor liner support adapted to maintain first and second combustor liners in spaced relation, said combustor liner support having a shroud portion extending into a flowpath defined between first and second flowpath structures maintained in spaced relation by a support member at least partially disposed within said flowpath, said shroud portion being disposed adjacent said support member to shield at least a portion of said support member from fluid flowing through said flowpath.
- 2. The combustor apparatus of claim 1 wherein said shroud portion isolates said at least a portion of said support member from thermal transients.
- 3. The combustor apparatus of claim 1 wherein said shroud portion is disposed about a leading edge of said support member to shield said leading edge from said fluid flowing through said flowpath.
- 4. The combustor apparatus of claim 3 wherein said shroud portion defines a passage extending therethrough, said support member extending through said passage to isolate said support member from said flowpath.
- 5. The combustor apparatus of claim 4 wherein said shroud portion thermally isolates said support member from said fluid flowing through said flowpath.
- 6. The combustor apparatus of claim 1 wherein said shroud portion has an upstream end portion and a downstream end portion, said upstream end portion defining a leading edge tapering outwardly toward said downstream end portion.
- 7. The combustor apparatus of claim 1 wherein said combustor liner support includes a dome portion adapted to support said first and second combustor liners in spaced relation to define a combustion chamber.
- 8. The combustor apparatus of claim 7 wherein said dome portion includes a pair of spaced apart grooves, an upstream end portion of each of said first and second combustor liners being captured within a respective one of said grooves.
- 9. The combustor apparatus of claim 7 wherein said dome portion includes a spraybar guide, said spraybar guide being adapted to maintain a fuel spraybar in a predetermined orientation relative to said dome portion.
- 10. The combustor apparatus of claim 9 wherein said dome portion includes a plurality of fuel delivery openings extending therethrough and positioned in alignment with said fuel spraybar, said fuel spraybar being adapted to spray fuel through said fuel delivery openings and into said combustion chamber.
- 11. The combustor apparatus of claim 7 wherein said dome portion is integrally attached to said shroud portion to form a single piece structure.
- 12. The combustor apparatus of claim 7 wherein said dome portion comprises an annular dome panel, said dome panel supporting said first and second combustor liners in radially spaced relation to define an annular combustion chamber.
- 13. The combustor apparatus of claim 12 wherein a plurality of said shroud portions extend from said dome panel, said plurality of shroud portions shielding a corresponding plurality of said support members from said fluid flowing through said flowpath.
- 14. The combustor apparatus of claim 1 wherein said shroud portion is pinned to at least one of said first and second flowpath structures to allow substantially unrestrained relative displacement between said shroud portion and said at least one of said first and second flowpath structures in at least one direction.
- 15. The combustor apparatus of claim 1 wherein said support member is coupled between said first and second flowpath structures while allowing substantially unrestrained relative displacement between said first and second flowpath structures in at least one direction.
- 16. The combustor apparatus of claim 1 wherein said first and second flowpath structures are annular shaped and are maintained in radially spaced relation by a plurality of said support members to define an annular diffuser flowpath; andwherein said combustor liner support includes a plurality of said shroud portions disposed within said diffuser flowpath and positioned about respective ones of said plurality of support members to substantially isolate said plurality of support members from fluid flowing through said flowpath.
- 17. A gas turbine engine combustor, comprising:inner and outer combustor casings interconnected by a support structure; inner and outer combustor liners disposed between said inner and outer combustor casings; and a combustor liner support having a dome member adapted to maintain said inner and outer combustor liners in spaced relation to define a combustion chamber, said combustor liner support having a load transfer member extending from said dome member, said load transfer member being coupled to at least one of said inner and outer combustor casings and being adapted to cover at least a portion of said support structure.
- 18. The combustor of claim 17 wherein said load transfer member is pinned to said support structure.
- 19. The combustor of claim 17 wherein said support structure is at least partially disposed within a flowpath, said load transfer member shielding said at least a portion of said support structure from fluid flowing through said flowpath.
- 20. The combustor of claim 19 wherein said load transfer member is disposed about a leading edge of said support structure to shield said leading edge from said fluid flowing through said flowpath.
- 21. The combustor of claim 20 wherein said load transfer member defines a passage extending therethrough, said support structure extending through said passage to thermally isolate said support structure from said fluid flowing through said flowpath.
- 22. The combustor of claim 19 further comprising a diffuser having inner and outer flowpath walls maintained in spaced relation by said support structure to define said flowpath.
- 23. The combustor of claim 22 wherein at least one of said inner and outer flowpath walls are pinned to said support structure to allow relative displacement between said inner and outer flowpath walls in at least one direction.
- 24. The combustor of claim 22 wherein said inner combustor casing is integrally formed with said inner flowpath wall to define a single piece structure.
- 25. The combustor of claim 17 wherein said dome member includes a pair of spaced apart grooves, an end portion of each of said inner and outer combustor liners being captured within a respective one of said grooves.
- 26. The combustor of claim 17 wherein said dome member includes a spraybar support having a pair of opposing flanges adapted to support a fuel spraybar, said dome portion including a plurality of fuel delivery openings extending therethrough and positioned in alignment with said fuel spraybar, said fuel spraybar being adapted to spray fuel through said fuel delivery openings and into said combustion chamber.
- 27. A gas turbine engine, comprising:a diffuser section including an inner wall spaced from an outer wall to define an annular flowpath, said inner and outer walls being coupled together by a plurality of struts, said struts being at least partially disposed within said flowpath; and a combustor section including a combustor liner support having an annular dome panel and a plurality of load transfer members extending therefrom, said dome panel being adapted to maintain inner and outer combustor liners in spaced relation to define an annular combustion chamber, each of said load transfer members extending into said flowpath and shielding at least a portion of a respective one of said struts from fluid flowing through said flowpath.
- 28. The gas turbine engine of claim 27 wherein each of said load transfer members is disposed about a leading edge of said respective one of said struts to shield said leading edge from said fluid flowing through said flowpath.
- 29. The gas turbine engine of claim 27 wherein each of said load transfer members surrounds said respective one of said struts to thermally isolate said respective one of said struts from said fluid flowing through said flowpath.
- 30. The gas turbine engine of claim 27 wherein each of said load transfer members is radially pinned to said respective one of said struts to axially couple said combustor liner support to said diffuser section while allowing substantially unrestrained displacement therebetween in a radial direction.
- 31. The gas turbine engine of claim 27 wherein said dome panel includes a pair of spaced apart annular grooves adapted to receive an upstream end portion of each of said inner and outer combustor liners therein.
- 32. The gas turbine engine of claim 27 wherein said plurality of struts are pinned to at least one of said inner and outer walls to axially couple said inner wall to said outer wall while allowing relative displacement therebetween in a radial direction.
- 33. A gas turbine engine, comprising:a diffuser including inner and outer walls spaced apart to define a flowpath and means for transmitting loads between said inner and outer walls, said load transmitting means being at least partially disposed within said flowpath; and means for supporting inner and outer combustor liners in spaced relation to define a combustion chamber, said supporting means including means for substantially isolating said load transmitting means from said flowpath.
Government Interests
This invention was made with U.S. Government support under contract number F33615-97-C-2778 awarded by the United States Air Force, and the U.S. Government may have certain rights in the invention.
US Referenced Citations (12)