THE INFLUENCE OF NOZZLE ANGLE ON THE EFFICIENCY OF IMPULSE STAGES,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 31, 1968
- Accession Number
- AD0685954
Entities
People
- V. D. Pshenichnyi
Organizations
- National Air and Space Intelligence Center