Effects of Combustor Exit Profiles on Vane Aerodynamic Loading and Heat Transfer in a High Pressure Turbine

Journal of Turbomachinery - United States
doi 10.1115/1.2950051
Full Text
Abstract

Available in full text

Date
Authors
Publisher

ASME International

Related search

Effects of High Intensity, Large-Scale Freestream Combustor Turbulence on Heat Transfer in Transonic Turbine Blades

2003English

Investigation of Transient Technique for Turbine Vane Heat Transfer Using a Shock Tube

1985English

Flow Analysis of High Pressure Catalytic Combustor for Gas Turbine

1995English

Length Reduction and the Performance Improvement of a High-Pressure Gas Turbine Combustor.

Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B
Condensed Matter PhysicsMechanical Engineering
1989English

The Influence of Film-Cooling on the Aerodynamic Performance of a Turbine Nozzle Guide Vane

1997English

Aerodynamics and Heat Transfer Investigations on a High Reynolds Number Turbine Cascade

1991English

Unsteady Adjoint of Pressure Loss for a Fundamental Transonic Turbine Vane

Journal of Turbomachinery
Mechanical Engineering
2016English

On the Unusual Pressure Rise at Turbine Pump Guide-Vane Entrance

Transactions of the Japan Society of Mechanical Engineers
1960English

Effects of Shocks on the Unsteady Heat Transfer in a Film-Cooled Transonic Turbine Cascade

2001English

Amanote Research

Note-taking for researchers

Follow Amanote

© 2026 Amaplex Software S.P.R.L. All rights reserved.

Privacy PolicyRefund Policy