F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
60/175
F02C 6/20 (2006.01) F23R 3/00 (2006.01) F23R 3/60 (2006.01)
Patent
CA 1114623
GAS TURBINE ENGINE COMBUSTOR MOUNTING Abstract of the Disclosure A gas turbine engine combustor assembly of annular configuration has outer and inner walls made up of a plurality of axially extending multi-layered porous metal panels joined together at butt joints therebetween and each outer and inner wall including a transition panel of porous metal defining a combustor assembly outlet supported by a combustor mount assembly including a stiffener ring having a side undercut thereon fit over a transition panel end face; and wherein an annular weld joins the ring to the end face to transmit exhaust heat from the end face to the stiffener ring for dissipation from the combustor; a combustor pilot member is located in axially spaced, surrounding relationship to the end face and connector means support the stiffener ring in free floating rela- tionship with the pilot member to compensate for both radial and axial thermal expansion of the transition panel; and said connector means includes a radial gap for main- taining a controlled flow of coolant from outside of the transition panel into cooling relationship with the stiffener ring and said weld to further cool the end face against excessive heat build-up therein during flow of hot gas exhaust through said outlet.
312501
Sweeney Ralph B.
Verdouw Albert J.
General Motors Corporation
Gowling Lafleur Henderson Llp
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