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Mass Flow Limitation of Supersonic Blade Rows Due to Leading Edge Blockage
-
H. Starken,
Published/Copyright:
December 1, 1985
Published Online: 1985-12
©2011 by Walter de Gruyter GmbH & Co.
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Articles in the same Issue
- CONTENTS
- Prediciton of Flow in Rotating Disc Systems Using the k-є Turbulence Model
- Spray Characteristics of Two Combined Jet Atomizers
- Nozzle Design and Integration in an Advanced Supersonic Fighter
- Mass Flow Limitation of Supersonic Blade Rows Due to Leading Edge Blockage
- Effect of Free Stream Turbulence on Flow Separation
- Effect of Aspect Ratio on Energy Loss in Nozzle Blades of Small Power Turbines
- A Finite Element Computer Code to Calculate Full 3-D Compressible Potential Flow in Turbomachinery
- The Role of the Heat-up Period in Fuel Drop Evaporation
- Advanced Concepts in Small Helicopter Engine Air-Cooled Turbine Design
- The Influence of Different Geometries for a Vaned Diffuser on the Pressure Distribution in a Centrifugal Compressor
- Computer Calculation of Fan Erosion in Coal-fired Power Plants. Part 2: Axial Fans
Articles in the same Issue
- CONTENTS
- Prediciton of Flow in Rotating Disc Systems Using the k-є Turbulence Model
- Spray Characteristics of Two Combined Jet Atomizers
- Nozzle Design and Integration in an Advanced Supersonic Fighter
- Mass Flow Limitation of Supersonic Blade Rows Due to Leading Edge Blockage
- Effect of Free Stream Turbulence on Flow Separation
- Effect of Aspect Ratio on Energy Loss in Nozzle Blades of Small Power Turbines
- A Finite Element Computer Code to Calculate Full 3-D Compressible Potential Flow in Turbomachinery
- The Role of the Heat-up Period in Fuel Drop Evaporation
- Advanced Concepts in Small Helicopter Engine Air-Cooled Turbine Design
- The Influence of Different Geometries for a Vaned Diffuser on the Pressure Distribution in a Centrifugal Compressor
- Computer Calculation of Fan Erosion in Coal-fired Power Plants. Part 2: Axial Fans
