Thermodynamic analysis of flow field at the end of combustor simulator-Reference-Cited by-同舟云学术

Thermodynamic analysis of flow field at the end of combustor simulator

Published:2013-06 Issue: Volume:61 Page:389-396
ISSN:0017-9310
Container-title:International Journal of Heat and Mass Transfer
language:en
Short-container-title:International Journal of Heat and Mass Transfer

Author:

Kianpour Ehsan,Sidik Nor Azwadi Che,Bozorg Mohsen Agha Seyyed Mirza

Publisher

Elsevier BV

Subject

Fluid Flow and Transfer Processes,Mechanical Engineering,Condensed Matter Physics

Reference23 articles.

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3. A method for correlating the influence of external cross flow on the discharge coefficients of film cooling holes;Rowbury;J. Turbomach.,2001

4. The interior heat transfer characteristics of gas turbine blade due to sparse film cooling holes;Zhang;Heat Transfer J. – Asian Res.,2005

5. R.T. Herbert, Innovative cooling configurations for low emission gas turbine combustors, Master theses, Louisiana State University, Louisiana, 2004.

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1. Multi-axis low-cycle creep/fatigue life prediction of high-pressure turbine blades based on a new critical plane damage parameter;Engineering Failure Analysis;2019-12

2. Effusion cooling characteristics of a model combustor liner at non-reacting/reacting flow conditions;Applied Thermal Engineering;2017-02

3. Film-Cooling Techniques at the End of Combustor and Inlet of Turbine in a Gas Turbine Engine: A Review;Applied Mechanics and Materials;2014-06

4. The Effect of Blowing Ratio on Film Cooling Effectiveness Using Cylindrical and Row Trenched Cooling Holes with Alignment Angle of 90 Degrees;Mathematical Problems in Engineering;2014

5. A comparison of cylindrical and row trenched cooling holes with alignment angle of 0 degree near the combustor endwall;IOP Conference Series: Materials Science and Engineering;2013-12-16