초록 ▼

Hot spots in the first stage turbine nozzles of small and medium sized engines are eliminated by spinning the nozzle assembly which consists of an annular hub circumscribed by a nozzle diaphragm having an inner and outer shroud ring between which are a multiplicity of symmetrically positioned vanes

Hot spots in the first stage turbine nozzles of small and medium sized engines are eliminated by spinning the nozzle assembly which consists of an annular hub circumscribed by a nozzle diaphragm having an inner and outer shroud ring between which are a multiplicity of symmetrically positioned vanes of airfoil design. Power to turn the nozzle assembly is obtained by connecting it to a rotary-type, vaned diffuser stage which lies in radial alignment with the impeller of the engine compressor. The rotary diffuser and nozzle combination is configured to turn at 50-1,000 rpm enabling the combined assembly to be mounted on unlubricated ceramic bearings.

대표청구항 ▼

In a gas turbine engine having an integrally connected rotary diffuser and first stage turbine nozzle assembly useful with a centrifugal compressor of the type having a shaft-driven radial-flow impeller for delivering compressible gas, said diffuser-nozzle assembly comprising: a rotary diffuser stag

In a gas turbine engine having an integrally connected rotary diffuser and first stage turbine nozzle assembly useful with a centrifugal compressor of the type having a shaft-driven radial-flow impeller for delivering compressible gas, said diffuser-nozzle assembly comprising: a rotary diffuser stage having a pair of annular axially spaced front and rear sidewalls, each of said sidewalls having an inner and an outer circumference, said inner circumference closely surrounding the periphery of said impeller, said diffuser stage further having a plurality of symmetrically arranged wedge-shaped vanes mounted between said spaced sidewalls, the annular space between said sidewalls and said vanes defining flow passages for receiving gas radially discharged from said impeller, said diffuser stage being mounted for rotation substantially about the axis of the engine; and a first stage turbine nozzle consisting of an annular hub circumscribed by a nozzle diaphragm having an inner and outer shroud ring between which there are a multiplicity of symmetrically positioned vanes of airfoil design, the hub region of the turbine nozzle being integrally connected with said rear sidewall of said diffuser, said first stage turbine nozzle being mounted for rotation with said diffuser.