A Simple Method for Geometry Definition of Radial Compressors

V. Zurita-Ugalde,; J.C. Gomez-Mancilla,; F. Garcia-Cristiano,

doi:10.1515/TJJ.2001.18.1.31

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A Simple Method for Geometry Definition of Radial Compressors

V. Zurita-Ugalde, , J.C. Gomez-Mancilla, und F. Garcia-Cristiano,

Veröffentlicht/Copyright: 1. März 2001

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Aus der Zeitschrift International Journal of Turbo and Jet Engines Band 18 Heft 1

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MLA
APA
Harvard
Chicago
Vancouver

Zurita-Ugalde,, V., Gomez-Mancilla,, J.C. and Garcia-Cristiano,, F.. "A Simple Method for Geometry Definition of Radial Compressors" International Journal of Turbo and Jet Engines, vol. 18, no. 1, 2001, pp. 31-36. https://doi.org/10.1515/TJJ.2001.18.1.31

Zurita-Ugalde,, V., Gomez-Mancilla,, J. & Garcia-Cristiano,, F. (2001). A Simple Method for Geometry Definition of Radial Compressors. International Journal of Turbo and Jet Engines, 18(1), 31-36. https://doi.org/10.1515/TJJ.2001.18.1.31

Zurita-Ugalde,, V., Gomez-Mancilla,, J. and Garcia-Cristiano,, F. (2001) A Simple Method for Geometry Definition of Radial Compressors. International Journal of Turbo and Jet Engines, Vol. 18 (Issue 1), pp. 31-36. https://doi.org/10.1515/TJJ.2001.18.1.31

Zurita-Ugalde,, V., Gomez-Mancilla,, J.C. and Garcia-Cristiano,, F.. "A Simple Method for Geometry Definition of Radial Compressors" International Journal of Turbo and Jet Engines 18, no. 1 (2001): 31-36. https://doi.org/10.1515/TJJ.2001.18.1.31

Zurita-Ugalde, V, Gomez-Mancilla, J, Garcia-Cristiano, F. A Simple Method for Geometry Definition of Radial Compressors. International Journal of Turbo and Jet Engines. 2001;18(1): 31-36. https://doi.org/10.1515/TJJ.2001.18.1.31

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Published Online: 2001-03

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Artikel in diesem Heft

CONTENTS
The Effects of Blade Count on Boundary Layer Development in a Low-Pressure Turbine
Effects of Hot Streak Shape on Rotor Heating in a High-Subsonic Single-Stage Turbine
A Simple Method for Geometry Definition of Radial Compressors
Advanced Aerothermodynamics Associated with Clean Technologies for Upgrading Gas Turbines in Simple and Combined-Cycle Power Stations
Thrust Vectoring Flight Control To Maximize Future Jet Transport Flight Safety
Simultaneous Prediction of External Flow-Field and Temperature in Internally Cooled 3-D Turbine Blade Material
A Simple Mobile Anechoic Chamber For Experiments in Jet Acoustics
The Influence of Fuel Droplet Characteristics on Chemical Mechanisms in a Premixed Laminar Spray Flame

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https://doi.org/10.1515/TJJ.2001.18.1.31

Artikel in diesem Heft

CONTENTS
The Effects of Blade Count on Boundary Layer Development in a Low-Pressure Turbine
Effects of Hot Streak Shape on Rotor Heating in a High-Subsonic Single-Stage Turbine
A Simple Method for Geometry Definition of Radial Compressors
Advanced Aerothermodynamics Associated with Clean Technologies for Upgrading Gas Turbines in Simple and Combined-Cycle Power Stations
Thrust Vectoring Flight Control To Maximize Future Jet Transport Flight Safety
Simultaneous Prediction of External Flow-Field and Temperature in Internally Cooled 3-D Turbine Blade Material
A Simple Mobile Anechoic Chamber For Experiments in Jet Acoustics
The Influence of Fuel Droplet Characteristics on Chemical Mechanisms in a Premixed Laminar Spray Flame