|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||415/143 ; 415/146 ; 415/147 ; 415/211|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 22 인용 특허 : 3|
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...
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 o...