In English

Conceptual Modelling of Civil and Military Aero-Engines

Subramanyam Natarajan
Göteborg : Chalmers tekniska högskola, 2013. Examensarbete - Institutionen för tillämpad mekanik, Chalmers tekniska högskola, ISSN 1652-9901; 2013:14, 2013.
[Examensarbete på avancerad nivå]

Statistical research has been performed on available turbofan engine congurations up to 1995 and documented by Grieb. A mathematical model is developed as a part of this thesis work to utilize the research data into predicting the parameters for 2015 and 2020 engines. This the- sis work mainly focuses on modelling the polytropic eciencies of the various components that constitute a 3-spool turbofan engine: fan, in- termediate pressure compressor, high pressure compressor, high pressure turbine, intermediate pressure turbine and the low pressure turbine. An optimizer code is developed in the C programming language as a second part of this project to feed the modelled values as input to the gas turbine analysis software EVA. It then varies the design parameters like inlet mass ow, velocity ratio, pressure ratios and turbine inlet temper- ature continuously between two arbitrary xed points. The specic fuel consumption at mid-cruise conditions is read from the output of EVA. Installed SFC is then calculated by taking nacelle inputs from Weico (a program to calculate engine dimensions) to get the minimal value. Design parameters at this value of installed SFC are returned into the input of EVA. Successive iterations are performed to get a global minimum value of installed SFC.



Publikationen registrerades 2018-09-06. Den ändrades senast 2018-09-20

CPL ID: 255827

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