Accession Number:

AD0688732

Title:

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

Descriptive Note:

Corporate Author:

FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1969-03-04

Pagination or Media Count:

16.0

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

Subject Categories:

  • Aerodynamics
  • Non-electrical Energy Conversion
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE