FIELD: engines and pumps.
SUBSTANCE: proposed device comprises circular element. Nozzle guide vanes are arranged radially between circular outer and inner sites, spaced apart to constrict gaseous combustion product passage in turbine. Vanes are spaced apart to constrict critical section to make it minimum section. Circular element features coefficient of expansion less than that of guide vanes sites. Circular element is secured on outer site to stay in two positions: first position corresponding to site no-expansion state wherein it provides for continuous gas-air flow profile, and second position corresponding to site expansion state wherein it extends into gas-air flow to reduced its section. Another invention of the set relates to turbine nozzle guide vanes comprising above described device.
EFFECT: higher reliability, simple assembly and servicing.
9 cl, 5 dwg
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