Home Technology Mass Flow Limitation of Supersonic Blade Rows Due to Leading Edge Blockage
Article
Licensed
Unlicensed Requires Authentication

Mass Flow Limitation of Supersonic Blade Rows Due to Leading Edge Blockage

  • H. Starken, , Ζ. Yongxing, and H. Schreiber,
Published/Copyright: December 1, 1985
Become an author with De Gruyter Brill
Author Information
International Journal of Turbo and Jet Engines
From the journal International Journal of Turbo and Jet Engines Volume 2 Issue 4

Published Online: 1985-12

©2011 by Walter de Gruyter GmbH & Co.

Articles in the same Issue

  1. CONTENTS
  2. Prediciton of Flow in Rotating Disc Systems Using the k-є Turbulence Model
  3. Spray Characteristics of Two Combined Jet Atomizers
  4. Nozzle Design and Integration in an Advanced Supersonic Fighter
  5. Mass Flow Limitation of Supersonic Blade Rows Due to Leading Edge Blockage
  6. Effect of Free Stream Turbulence on Flow Separation
  7. Effect of Aspect Ratio on Energy Loss in Nozzle Blades of Small Power Turbines
  8. A Finite Element Computer Code to Calculate Full 3-D Compressible Potential Flow in Turbomachinery
  9. The Role of the Heat-up Period in Fuel Drop Evaporation
  10. Advanced Concepts in Small Helicopter Engine Air-Cooled Turbine Design
  11. The Influence of Different Geometries for a Vaned Diffuser on the Pressure Distribution in a Centrifugal Compressor
  12. Computer Calculation of Fan Erosion in Coal-fired Power Plants. Part 2: Axial Fans
https://doi.org/10.1515/TJJ.1985.2.4.285

Articles in the same Issue

  1. CONTENTS
  2. Prediciton of Flow in Rotating Disc Systems Using the k-є Turbulence Model
  3. Spray Characteristics of Two Combined Jet Atomizers
  4. Nozzle Design and Integration in an Advanced Supersonic Fighter
  5. Mass Flow Limitation of Supersonic Blade Rows Due to Leading Edge Blockage
  6. Effect of Free Stream Turbulence on Flow Separation
  7. Effect of Aspect Ratio on Energy Loss in Nozzle Blades of Small Power Turbines
  8. A Finite Element Computer Code to Calculate Full 3-D Compressible Potential Flow in Turbomachinery
  9. The Role of the Heat-up Period in Fuel Drop Evaporation
  10. Advanced Concepts in Small Helicopter Engine Air-Cooled Turbine Design
  11. The Influence of Different Geometries for a Vaned Diffuser on the Pressure Distribution in a Centrifugal Compressor
  12. Computer Calculation of Fan Erosion in Coal-fired Power Plants. Part 2: Axial Fans
Sign up now to receive a 20% welcome discount
Institutional Access
How does access work?
Have an idea on how to improve our website?
Please write us.
© 2026 De Gruyter Brill
Downloaded on 19.1.2026 from https://www.degruyterbrill.com/document/doi/10.1515/TJJ.1985.2.4.285/html
Scroll to top button