Development of Novel Computer Program for Cycle Analysis of Turbojet Engine
Moaz Hussain1, P. Deepak Kumar2, S.R. Arun3, Vismaya4, P. Hari Siva5
1Moaz Hussain*, Department of Aeronautical Engineering, Excel Engineering College, Erode, Tamil Nadu, India.
2P. Deepak Kumar, Department of Aeronautical Engineering, Excel Engineering College, Erode, Tamil Nadu, India.
3S.R. Arun, Department of Aeronautical Engineering, Excel Engineering College, Erode, Tamil Nadu, India.
4Vismaya, Department of Aeronautical Engineering, Excel Engineering College, Erode, Tamil Nadu, India.
5P. Hari Siva, Department of Aeronautical Engineering, Excel Engineering College, Erode, Tamil Nadu, India.
Manuscript received on January 10, 2020. | Revised Manuscript received on January 20, 2020. | Manuscript published on February 10, 2020. | PP: 1872-1878 | Volume-9 Issue-4, February 2020. | Retrieval Number: D1601029420/2020©BEIESP | DOI: 10.35940/ijitee.D1601.029420
Open Access | Ethics and Policies | Cite | Mendeley
© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: A method to simulate the gas turbine cycle and performance is developed. This paper intent to describe a digital computer code to make it useful for other researchers. This program is written in Python language for analyzing the steady-state, parametric cycle performance of turbojet engines. This can be used to analyze one- and two-spool turbojet engines without any modification to the basic program. The influence of initial parameters, component characteristics and flight condition on performance characteristics of gas turbine during operation are shown. The program results are compared and validated with those from an existing GSP (Gas Turbine Simulation Program) software. The major advantage of this new method is that it frees the programmer from having to minimize the number of equations which require iterative solution. As a result, some of the approximations normally used in engine simulations can be eliminated. The outcomes of this analysis form a strong base for further analysis to predict the performance of the gas turbine engine with reasonable accuracy for design and fabrication of gas turbine engines using this performance code.
Keywords: Cycle Analysis, GSP, Python, Thrust, Turbojet Engine.
Scope of the Article: Life Cycle Engineering