| 摘要 |
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.
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