Gas turbine diffuser

Power plants – Combustion products used as motive fluid – Combustion products generator

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F02K 148

Patent

active

055928200

ABSTRACT:
A diffuser for a turbojet engine is disclosed in which a plurality of diffuser inlets are arranged in a substantially circular array bounded by inner and outer diffuser walls and by a plurality of partitions extending generally radially from the axis of the annular diffuser. The plurality of diffuser inlets are located so as to receive air or oxidizer from the turbojet engine compressor and the radial partitions may be integrated into the compressor guide vanes. The diffuser has a plurality of sets of diffuser outlets, each set comprising a plurality of diffuser outlets arranged in a circular array about the central axis of the diffuser. The radius of each set of diffuser outlets is different from the radius of each of the other sets of diffuser outlets such that the entirety of diffuser outlets comprise a non-circular array. The diffuser may comprise three different sets of diffuser outlets, a first set directing air or oxidizer onto the baffle such that the air or oxidizer passes through openings in the baffle to feed the fuel injector heads. A second set of diffuser outlets may be curved outward at the outlet end so as to direct a portion of the air or oxidizer into the space defined between the outer combustion chamber wail and the outer casing. A third set of diffuser outlets may be curved inwardly at their downstream ends so as to direct a portion of the air or oxidizer into the space between the inner combustion and the inner casing.

REFERENCES:
patent: 4527386 (1985-07-01), Markowski
patent: 5077967 (1992-01-01), Widener et al.

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