SUPERSONIC REACTION PROFILE FOR THE ROTOR BLADE OF THE LAST STEP OF A POWERFUL TURBINE,

Abstract

In turbine blades 780--1050 mm long, it is established that the Mach number at the exit of the turbine blades increases at a higher rate than the increase in the inlet angle. Therefore, the inverse curvature of the profile center line can be realized only near the peripheral section. At the blade cross-section with the transition from a concave to a convex surface, the concave blade should have an oblique section. The experimental study indicates that the plane surface profile can be used in steam turbine blades to provide a transition to an inverse concavity. Losses of profiles constructed by this method are 3.5 percent. (Author)

Document Details

Document Type
Technical Report
Publication Date
Mar 04, 1969
Accession Number
AD0688732

Entities

People

  • G. A. Sokolovskii
  • O. N. Slabchenko

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Curvature
  • Energy Generators
  • Energy Systems
  • Generators
  • Geometry
  • Mach Number
  • Mechanical Equipment
  • Rotor Blades (Turbomachinery)
  • Steam Turbine Blades
  • Steam Turbines
  • Transitions
  • Turbine Blades
  • Turbines
  • Turbomachinery

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Operations Research

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow