Turbine Performance Increases Through Airfoil Clocking

Daniel J. Dorney,; Om P. Sharma,

doi:10.1515/TJJ.1998.15.2.119

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Turbine Performance Increases Through Airfoil Clocking

Daniel J. Dorney, and Om P. Sharma,

Published/Copyright: June 1, 1998

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From the journal International Journal of Turbo and Jet Engines Volume 15 Issue 2

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MLA
APA
Harvard
Chicago
Vancouver

Dorney,, Daniel J. and Sharma,, Om P.. "Turbine Performance Increases Through Airfoil Clocking" International Journal of Turbo and Jet Engines, vol. 15, no. 2, pp. 119-128. https://doi.org/10.1515/TJJ.1998.15.2.119

Dorney,, D. & Sharma,, O. (). Turbine Performance Increases Through Airfoil Clocking. International Journal of Turbo and Jet Engines, 15(2), 119-128. https://doi.org/10.1515/TJJ.1998.15.2.119

Dorney,, D. and Sharma,, O. () Turbine Performance Increases Through Airfoil Clocking. International Journal of Turbo and Jet Engines, Vol. 15 (Issue 2), pp. 119-128. https://doi.org/10.1515/TJJ.1998.15.2.119

Dorney,, Daniel J. and Sharma,, Om P.. "Turbine Performance Increases Through Airfoil Clocking" International Journal of Turbo and Jet Engines 15, no. 2 (): 119-128. https://doi.org/10.1515/TJJ.1998.15.2.119

Dorney, D, Sharma, O. Turbine Performance Increases Through Airfoil Clocking. International Journal of Turbo and Jet Engines. ;15(2): 119-128. https://doi.org/10.1515/TJJ.1998.15.2.119

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Published Online: 1998-06

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Articles in the same Issue

CONTENTS
Can Thrust Vectoring Save a Doomed Transport Jet?
Jet Deflection Angles in Military, Civil and RPV Thrust Vectoring Aircraft
A Family of Variational Principles for Compressible Rotational Blade-to-Blade Flow Using Semi-Inverse Method
Generalized Variational Principle for Compressible S2-Flow in Mixed-Flow Turbomachinery Using Semi-Inverse Method
Inviscid-Viscous Iterative Solution for Flowfield in Transonic Compressor Rotor
Turbine Performance Increases Through Airfoil Clocking
Ignition Behaviors of Fuel Droplets in a Hot Convective Flowfield
Effect of Dump Gap on Velocity Distribution and Flow Split in a Prototype Reverse-Flow Gas Turbine Combustor

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https://doi.org/10.1515/TJJ.1998.15.2.119

Articles in the same Issue

CONTENTS
Can Thrust Vectoring Save a Doomed Transport Jet?
Jet Deflection Angles in Military, Civil and RPV Thrust Vectoring Aircraft
A Family of Variational Principles for Compressible Rotational Blade-to-Blade Flow Using Semi-Inverse Method
Generalized Variational Principle for Compressible S2-Flow in Mixed-Flow Turbomachinery Using Semi-Inverse Method
Inviscid-Viscous Iterative Solution for Flowfield in Transonic Compressor Rotor
Turbine Performance Increases Through Airfoil Clocking
Ignition Behaviors of Fuel Droplets in a Hot Convective Flowfield
Effect of Dump Gap on Velocity Distribution and Flow Split in a Prototype Reverse-Flow Gas Turbine Combustor