June 12, 2005
June 12, 2005
June 15, 2005
10.448.1 - 10.448.14
Development and Implementation of Interactive/Visual Software for Simple Aircraft Gas Turbine Design Afshin J. Ghajar, Ronald D. Delahoussaye, Vandan V. Nayak School of Mechanical and Aerospace Engineering, Oklahoma State University Stillwater, OK 74078 firstname.lastname@example.org Abstract This paper describes a versatile, user-friendly, and easy to understand software suite that has been developed for analysis and design of a simple turbojet engine. The software has been class room tested for several semesters and it was very well received by the students.
Introduction The school of Mechanical and Aerospace Engineering at Oklahoma State University offers MAE 4243, “Gas Power Systems”, as a required course for the Aerospace Engineering degree and an elective course for the Mechanical Engineering degree. Student use of software to analyze and design gas turbine systems has been an important part of this course since 1988. Use of software has been particularly important in the “design project” phase of the course. The software in use for many years was developed in the DOS environment and lacked many of the ease-of-use features now commonly available in MS Windows style programs. In addition, the source code for the program was not available to allow faculty and students to correct perceived weaknesses in the program. The primary goal of this project was to develop MS Windows based software: Simple Aircraft Gas Turbine Design, that is easy to use, maintain and update, and can be distributed freely.
This software development project contributed in a synergistic way to three different educational missions. It provided a high quality MS level creative component project for the MS student who developed the software. The software is now being used by undergraduates in MAE 4243. The software was written in a modular and expandable way so that it can and has been used for additional research work by MS students.
This paper will describe the components of a Simple Aircraft Gas Turbine, define the thermodynamic cycle implemented in the model, define the key engine performance measures calculated by the model, and describe the calculation of the thermodynamic properties of air for varying altitudes. The capabilities and current limitations of the software will be described. Instructor and student assessments of the contribution of this software to the learning process will be given.
Components of a Simple Aircraft Gas Turbine A simple aircraft gas turbine is nothing but an engine used to convert fuel energy to a more useful form of high speed thrust for a jet aircraft. A typical gas turbine consists of a diffuser, compressor, combustion chamber, turbine and nozzle, as shown schematically in Figure 11. Diffuser: For a turbojet aircraft engine, the airflow entering the compressor must have a low Mach number, in the range of 0.4 to 0.7, to prevent air separation on the compressor blades.
“Proceedings of the 2005 American Society for Engineering Education Annual Conference and Exposition Copyright ©2005, American Society for Engineering Education”
Ghajar, A., & Delahoussaye, R. (2005, June), Development And Implementation Of Interactive / Visual Software For Simple Aircraft Gas Turbine Design Paper presented at 2005 Annual Conference, Portland, Oregon. https://peer.asee.org/15004
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