Gas turbine engines
AssigneeROLLS-ROYCE plc
InventorsDavid H. Taylor, Arthur B. Griffin, David W. Tuson
Life of this patent
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Abstract
A gas turbine engine component support assembly (30) comprises a pair of ring members (64) and (74) defining a slot in which a cranked flange (28) extending from the inner surfaces of an array of combustion chamber discharge nozzles (22) is located. One part (28B) of the cranked flange has projections (28C) which engage with radial slots (76) formed in one of the ring members (74) to provide cross-key location of the discharge nozzles. The support assembly (30) is located adjacent the radially inner platform of an array of nozzle guide vanes (20), and also provides support and location for the vanes.
Claims8
An axial flow gas turbine engine including a plurality of combustion chamber discharge nozzle means and an array of nozzle guide vanes each located downstream of a said discharge nozzle means, each said nozzle means having a downstream end, each said nozzle guide vane having an inner platform with an upstream portion extending towards the downstream end of said discharge nozzle means, the discharge nozzle means being cross-key located and supported by a support assembly positioned adjacent said upstream portion of the inner platform of said nozzle guide vane, said support assembly comprising a ring member defining an axially extending annular slot, each discharge nozzle means having flange means located in the annular slot, each flange means having angularly spaced radial projections located in complementary apertures provided in the said ring member.
An axial flow gas turbine engine including combustion chamber discharge nozzle means and an array of nozzle guide vanes located downstream of said discharge nozzle means, the nozzle guide vanes having inner platforms with upstream portions extending towards the downstream end of the discharge nozzle means, the discharge nozzle means being cross-key located and supported by a support assembly positioned adjacent the upstream portions of the inner platforms of the nozzle guide vanes, the support assembly comprising a ring member defining an axially extending annular slot, the discharge nozzle means having flange means located in the annular slot, the flange means having angularly spaced radial projections located in complementary apertures provided in said ring member.
Dependencies are inferred from the claim text.