Accession Number : AD0685954

Title :   THE INFLUENCE OF NOZZLE ANGLE ON THE EFFICIENCY OF IMPULSE STAGES,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Pshenichnyi,V. D.

Report Date : 31 OCT 1968

Pagination or Media Count : 16

Abstract : This work is a continuation of a previous investigation with the difference that it deals with wider nozzle exit angles and greater heights-up to the limit of applicability of nontwisted blading, given a fixed nozzle-blade root diameter. Flow around nozzle blade cascades with such exit angles was investigated by methods described in the aforementioned investigation. It is established that for an isolated turbine stage of the impulse type there exists an optimal exit angle, which amounts to 8-10 deg. for a nozzle cascade with flat frontal walls; for an intermediate stage with total utilization of exit energy the efficiency is near-optimal over a broad range of angles of from 8 to 14 deg., which makes it possible to assure a broad spectrum of capacities by merely altering the blading angle. (Author)

Descriptors :   (*GAS TURBINES, *GAS TURBINE NOZZLES), (*NOZZLE INSERTS, NOZZLE GAS FLOW), EFFICIENCY, KINETIC ENERGY, OPTIMIZATION, VORTICES, FRICTION, USSR

Subject Categories : Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE