Cooling apparatus for aircraft gas turbine engine exhaust nozzle

Details Cooling apparatus for aircraft gas turbine engine exhaust nozzle Cooling apparatus for aircraft gas turbine engine exhaust nozzle

1991-11-05

1998-02-24

Carone, Michael J.

Fluid sprinkling, spraying, and diffusing

Reaction motor discharge nozzle with jacketed or hollow...

B64D 3304

Patent

active

057204349

ABSTRACT:
The present invention provides coolable exhaust nozzle flap and seal assemblies having liners that are spaced inward and apart from their respective flap and seal cool walls, to form a cooling passage therebetween that converges in the axial downstream flow direction. One embodiment provides single wall multi-hole film cooled nozzle flap and seal liners particularly for use individually or in combination on convergent and divergent hollow flaps and seals for variable exhaust nozzles. Flap and seal coolable assemblies may be unitary structures that are integrally fabricated or formed such as by casting.

REFERENCES:
patent: 3091924 (1963-06-01), Wilder
patent: 3527543 (1970-09-01), Howald
patent: 3623711 (1971-11-01), Thorstenson
patent: 3866417 (1975-02-01), Velegol
patent: 3979065 (1976-09-01), Madden
patent: 4071194 (1978-01-01), Eckert et al.
patent: 4081137 (1978-03-01), Sutton et al.
patent: 4118146 (1978-10-01), Dierberger
patent: 4171093 (1979-10-01), Honeycutt et al.
patent: 4203286 (1980-05-01), Warburton
patent: 4449678 (1984-05-01), Hapke
patent: 4544098 (1985-10-01), Warburton
patent: 4566280 (1986-01-01), Burr
patent: 4637550 (1987-01-01), Nash
patent: 4642993 (1987-02-01), Sweet
patent: 4643356 (1987-02-01), Holler
patent: 4653983 (1987-03-01), Vehr
patent: 4664597 (1987-05-01), Auxier et al.
patent: 4695247 (1987-09-01), Enzaki et al.
patent: 4696431 (1987-09-01), Buxe
patent: 4747542 (1988-05-01), Cires et al.
patent: 4773593 (1988-09-01), Auxier et al.
patent: 4833881 (1989-05-01), Vdoviak et al.
patent: 4878283 (1989-11-01), McLean
patent: 4896510 (1990-01-01), Foltz
patent: 4923371 (1990-05-01), Ben-Amoz
patent: 5000005 (1991-03-01), Kwan et al.
patent: 5181379 (1993-01-01), Wakeman et al.
R.E. Mayle et al, "Multihole Cooling Film Effectiveness and Heat Transfer," Nov. 1975, pp. 534-538.
D.A. Nealy et al, "Alternate Cooling Configuration for Gas Turbine Combustor Systems," May 1985.
Dr. G. J. Sturgess, "Advanced Low-Emissions Catalytic-Combustor Program-Phase I Final Report," Jun. 1981, Report No. NASA-CR-159656, pp. 75-76, 125-128 and 141-142.
Wakeman et al, "Gas Turbine Engine Multi-Hole Film Cooled Combustor Liner and Method of Manufacture," U.S. Patent Application Ser. No. 07/614,418 filed Nov. 15, 1990.

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