Combustor apparatus for a gas turbine engine
AssigneeAllison Advanced Development Company
InventorsEdward C. Rice, Spencer D. Pack
Life of this patent
Estimating the term…
Abstract
A combustor apparatus for a gas turbine engine includes a combustor liner support having an annular dome panel and a plurality of load transfer members extending axially therefrom. The dome panel maintains inner and outer combustor liners in spaced relation to define a combustion chamber. The load transfer members extend into a diffuser flowpath defined by inner and outer flowpath structures which are interconnected by a plurality of struts. Each of the load transfer members surrounds at least a portion of a corresponding strut to shield the strut from fluid flowing through the diffuser flowpath.
Claims33
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.
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.
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.
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.
Dependencies are inferred from the claim text.