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11 plate in ?uid communication with said compressor and said nozzle passages, said liner including 1. an annular radially extending portion spaced from said radially extending nozzle portion and de?ning therewith an annular radially extending space, and 2. an annular axially extending portion generally encircling said hub portion and de?ning there with an annular space in ?uid communication with said radially extending space, said axially extending portion projecting axially away from said turbine toward said compressor and into contact wih said hub portion. 2. A gas turbine engine according to claim 1 wherein: E. said engine further includes an annular diffuser platesupportedbysaidhousingandencirclingsaid shaft assembly intermediate said liner and said compressor,saiddiffuserplatehaving I. an annular one piece radially extending diffuser portion having cantilever vanes at least partially 20 de?ningapluralityofradiallyextendingdiffuser passages in ?uid communication with said com bustion chamber and said compressor, and 25 30 35 40 45 50 55 60 65 12 2. an annular axially extending hub-portion, project ing axially away ‘from said compressor toward said turbine in juxtaposition to said shaft assem bly to a location spaced axially from the free end of said nozzle hub portion; and F. said liner further includes 1. another annular radially extending portion spacedfromsaidradiallyextendingdiffuserpor— tion and de?ning therewith an annular radially extendingspace,and, i 2.anotherannularaxiallyextendingportiongener ally encircling said hub portion of said diffuser plate and de?ning therewith an annular space in ?uid communication with said annular radially extending .space between said other radial liner portion and said diffuser portion, said other axi aly extending portion projectingvaxially away .from said compressor toward said turbine and intovcontactwithsaidhubportionofsaiddiffuser plate, said,points of contact between said liner and said hub portions being axially spaced from one another. =|< * * * =0: 4,000,609PDF Image | RADIAL FLOW GAS TURBINE ENGINE WITH ANNULAR COMBUSTOR LINER
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