| Issue |
MATEC Web Conf.
Volume 189, 2018
2018 2nd International Conference on Material Engineering and Advanced Manufacturing Technology (MEAMT 2018)
|
|
|---|---|---|
| Article Number | 02003 | |
| Number of page(s) | 7 | |
| Section | Material Simulation | |
| DOI | https://doi.org/10.1051/matecconf/201818902003 | |
| Published online | 10 August 2018 | |
Gas turbine power calculation method of turboshaft based on simulation and performance model
1
Aviation Foundation College, Naval Aviation University, Yantai Shandong 264001, China
2
Unit 91911, Sanya Hainan 572000, China
3
Institute of Aviation Equipment, Naval Academy of Armament, Shanghai 200436, China
*
Corresponding author : wuheng89810@163.com
Gas turbine power of turboshaft engine cannot be measured, a total of five typical steady state point test data from the ground slow state to the maximum state were selected according to the factory acceptance test drive of a certain type of carrier-based helicopter turboshaft engine. Combustion chamber three-dimensional simulation model was established to carry on simulation analysis of different typical steady state combustion process. The simulated combustion chamber exit section parameters are input into the established gas turbine isentropic adiabatic aerodynamic calculation model to obtain the gas turbine power and outlet temperature. Select five typical steady state points of five sets of turboshaft engines on the same type to repeat the above calculation process, and compare the calculated value of gas turbine outlet temperature with the acceptance test values, it is found that the error values are all within 5%, and the effectiveness and accuracy of the gas turbine power calculation method are verified.
© The Authors, published by EDP Sciences, 2018
This is an Open Access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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