초록 ▼

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 diffuse

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.

대표청구항 ▼

A diffuser for a turbojet engine having an oxidizer compressor located upstream of a generally annular combustion chamber assembly with inner and outer casings extending about a longitudinal axis, inner and outer walls spaced from the inner and outer casings bounding the combustion chamber, an upstr

A diffuser for a turbojet engine having an oxidizer compressor located upstream of a generally annular combustion chamber assembly with inner and outer casings extending about a longitudinal axis, inner and outer walls spaced from the inner and outer casings bounding the combustion chamber, an upstream end wall connecting the inner and outer walls, a baffle extending between the inner and outer walls and spaced from the upstream end wall, the baffle defining a plurality of openings, and a plurality of fuel injectors extending through the baffle and the upstream end wall, the diffuser located between the compressor and the combustion chamber assembly and comprising: a) a plurality of diffuser inlets bounded by inner and outer diffuser walls extending about the longitudinal axis and a plurality of partitions extending substantially radially with respect to the longitudinal axis and interconnecting the inner and outer diffuser walls such that the diffuser inlets are arranged in a substantially circular array and are located so as to receive oxidizer from the compressor; and, b) a plurality of sets of diffuser outlets, each set comprising a plurality of diffuser outlets arranged in a substantially circular array about the longitudinal axis wherein the radius of each set of diffuser outlets is different from the radius of the other sets of diffuser outlets such that the entirety of diffuser outlets comprises a non-circular array about the longitudinal axis whereby the diffusion outlets are displaced in a circumferential direction around the longitudinal axis such that no two diffuser outlets lie on a common radial line extending from the longitudinal axis.