Jet engine having combustion chamber within compressor

Details Jet engine having combustion chamber within compressor Jet engine having combustion chamber within compressor

1977-01-25

1978-09-05

Garrett, Robert E.

Power plants

Reaction motor

Air passage bypasses combustion chamber

60269, 60 3935, 415 80, F02K 302

Patent

active

041109759

ABSTRACT:
A jet engine, comprising a long, tube-shaped casing open at both ends, a shaft supported centrally in the casing, a compressor and gas turbine rigidly connected to the shaft, and a combustion chamber with fuel supply located between the compressor and turbine. The engine is equipped with two coaxial compressors with radial blades. The compressors are separated by a backwardly-diverging, conical partition, by a radial turbine disposed immediately back of the compressor in connection with the back end of the conical partition. A rear wall is disposed in back of the turbine. The combustion chamber is bound by said wall, said conical partition and the turbine blades.

REFERENCES:
patent: 2448972 (1948-09-01), Gizara
patent: 3005311 (1961-10-01), Ross
patent: 3121414 (1964-02-01), Peterson
patent: 3287904 (1966-11-01), Warren et al.

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