Cooling air transfer apparatus for aircraft gas turbine engine e

Fluid sprinkling – spraying – and diffusing – Reaction motor discharge nozzle with jacketed or hollow... – With subsequent mixing in main discharge stream in or...

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60266, B64D 3304

Patent

active

052558495

ABSTRACT:
A cooling air transferring apparatus is provided particularly for transferring cooling air from hollow convergent flaps and seals to hollow divergent flaps and seals respectively in aircraft gas turbine engine variable nozzles. The preferred embodiment includes two semi-circular tubes, the first partially received within the second and both having a common center and radius of curvature so as to slide about the pivot point of the variable nozzle's pivotable convergent and divergent flaps and seals. The preferred embodiment further includes an entrainment opening on the second tube through which part of the first tube is received. The entrainment opening induces cooling air from the nozzle bay into the cooling air transfer tube to help cool the divergent flaps and seals.

REFERENCES:
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patent: 3595023 (1971-07-01), Stockel
patent: 3979065 (1976-09-01), Madden
patent: 4081137 (1978-03-01), Sutton et al.
patent: 4098076 (1978-07-01), Young et al.
patent: 4203286 (1980-05-01), Warburton
patent: 4544098 (1985-10-01), Warburton
patent: 4643356 (1987-02-01), Holler et al.
patent: 4756053 (1988-07-01), Madden et al.

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