Mounting for gas turbine powerplant

Aeronautics and astronautics – Aircraft power plants – Mounting

Patent

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Details

60226R, 248554, F02C 720, B64D 2720

Patent

active

043266827

ABSTRACT:
A gas turbine powerplant has an inner casing (4A) containing a gas turbine engine, an outer casing (5) surrounding the inner casing, a fan driven by the engine and driving air through an annular duct defined between the casings. The powerplant is connected to an aircraft fuselage (1) by a front mounting (9,9A,9B,9C) and by a rear mounting (8,10,17,18). The front and rear mountings react lateral forces on the powerplant. The powerplant includes a thrust reverser (11) situated rearwards of the rear mounting and supported by a ring (18) lying in the annulus of the outer casing and forming part of the rear mounting. At each side of the powerplant there is provided a tie (14,15) which connects the inner casing at a joint (6,16A) adjacent the front mounting to the ring of the rear mounting. The ties therefore lie oblique to the main engine axis. The ties react the forward and reverse thrusts of the powerplant.

REFERENCES:
patent: 2539960 (1951-01-01), Marchant et al.
patent: 2720370 (1955-10-01), Hasbouak
patent: 3352114 (1967-11-01), L'Wilde et al.
patent: 3675418 (1972-07-01), Lenkeit et al.
patent: 3856239 (1974-12-01), Leibach
patent: 4044973 (1977-08-01), Moorehead
patent: 4185798 (1980-01-01), Dickenson

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