The completion of the mathematical model by parameter identification for simulating a turbofan engine

The purpose of this paper is to set up a method to determine the missing engine design parameters (turbine inlet temperature T3T, airflow rate) which significantly influence the jet engines thrust. The authors have introduced a new non-linear equation connecting the fan specific work with the temper...

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Bibliographic Details
Published in:INCAS bulletin 2015-09, Vol.7 (3), p.25-37
Main Authors: Andrei, Irina Carmen, Pricop, Mihai Victor, Niculescu, Mihai Leonida, Cernat, Andreea
Format: Article
Language:English
Subjects:
Airflow
engine parameters
Gas turbine engines
Mathematical analysis
Mathematical models
Nonlinearity
numerical simulation
off-design regimes
operating maps
Pressure ratio
Thrust
turbofan
Turbofans
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Summary:The purpose of this paper is to set up a method to determine the missing engine design parameters (turbine inlet temperature T3T, airflow rate) which significantly influence the jet engines thrust. The authors have introduced a new non-linear equation connecting the fan specific work with the temperature T3T, customized for turbofan. The method of chords, since it converges unconditionally, has been used for solving the non-linear equation of variable temperature T3T. An alternate method, based for the same relation between fan specific work and T3T, has been presented in purpose to determine airflow rate and fan pressure ratio. Two mixed flows turbofans have been considered as study cases. For case #1 it was determined a value comparable to the Turbomeca Larzac turbofan series 04-C6 and 04-C20 which power the AlphaJet machines (series A - Luftwaffe, series E - Dassault Dornier). For the F100-PW229 turbofan, as case #2, being given T3T, then have been determined the airflow rate, fan pressure ratio and fan specific work. After completing the mathematical model with the missing parameters, the performances of the engines at off-design regimes and the operational envelopes revealing i.e. the variations of thrust, specific thrust and fuel specific consumption with altitude and Mach number have been calculated.
ISSN:2066-8201
2247-4528
DOI:10.13111/2066-8201.2015.7.3.3