Gas turbine engine

Details Gas turbine engine Gas turbine engine

1987-10-29

1988-08-23

Stout, Donald E.

Power plants

Reaction motor

Interrelated reaction motors

60 39162, 60268, F02K 3072

Patent

active

047651350

ABSTRACT:
A gas turbine engine for an aircraft comprises a gas generator which includes a compressor stage, a combustion chamber, and a turbine for driving the compressor, and through which the air and combustion gases flow from the rear towards the front in relation to the direction of travel of the aircraft before undergoing a reversal of direction to feed two contra-rotating power turbines which directly drive two contra-rotating airscrew or fan stages located near the front of the engine in the same longitudinal region as the power turbines. The gas generator is supplied by an air intake consisting of a plurality of ducts disposed around the outer casing of the engine, and the gases exiting from the power turbines are exhausted through a plurality of ducts positioned between the inlet ducts.

REFERENCES:
patent: 2428330 (1947-09-01), Heppner
patent: 2430399 (1947-11-01), Heppner
patent: 2454738 (1948-11-01), Hawthorne
patent: 2504181 (1950-04-01), Constant
patent: 2519130 (1950-08-01), Griffith
patent: 2546420 (1951-03-01), Barr
patent: 2704434 (1955-03-01), Schmitt
patent: 3131536 (1964-05-01), Snell
patent: 3253406 (1966-05-01), Grieb
patent: 3818695 (1974-06-01), Rylewski
Aviation Week & Space Tech., "CFM56-5 Thrust Reverser for A320 Undergoes Tests", 10-20-86, p. 68.

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