Research Article | OPEN ACCESS
Computational Analysis of Cooling Effect with Different Flow Injection Angles On Double Chamber Model
Tao Xu, Zheng-Lei Yu and Jun-Lou Li
College of Mechanical Science and Engineering, Jilin University, Changchun 130025, P.R. China
Research Journal of Applied Sciences, Engineering and Technology 2013 4:681-686
Received: September 11, 2012 | Accepted: October 19, 2012 | Published: June 20, 2013
Abstract
In order to explore a better cooling performance of transition piece, a numerical simulation is performed in this study. Advanced gas turbines are designed to operate at increasingly higher inlet temperatures to enhance efficiency and specific power output. This development in the operating temperature is enabled by advances in high-temperature resistant materials and by the development of effective cooling methods that lower the temperature of all surfaces that come in contact with the hot gases. Thus, there is a need for new cooling techniques or enhancing the current techniques available. The current study is a numerical simulation of film cooling in a double chamber model, which could simulate the Transition Piece’s (TP) structure and performance. The adiabatic wall temperature and flow cooling effectiveness for the coolant injection angles (seven orientations, 90°, 75°, 60°, 45°, 30°, 15° and 0o) were investigated numerically. Fluent, a commercial CFD software, is extensively used in the current study for numerical simulations.
Keywords:
Concave surfaces, cooling effectiveness, film cooling,
Competing interests
The authors have no competing interests.
Open Access Policy
This article is distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution, and reproduction in any medium, provided you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons license, and indicate if changes were made.
Copyright
The authors have no competing interests.
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ISSN (Online): 2040-7467
ISSN (Print): 2040-7459 |
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