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Title: Gas turbine transient performance modeling for engine flight path cycle analysis
Author: Janikovic, Jan
ISNI:       0000 0004 2735 2372
Awarding Body: Cranfield University
Current Institution: Cranfield University
Date of Award: 2010
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The growth in competitiveness in airline industry has called for more advanced tool to estimate the operating costs. Engine maintenance costs are an important decisionmaking element during airline fleet selection judgment. Long term observation in aerospace led to the development of engine maintenance costs calculators based on empirical correlation. But the possibilities of empirical model application for future engines without prior operational data are limited. A physics-based tool to estimate the life of the engine components and predict the shop visit rate requires the variations of thermodynamic parameters over the flight path. High fidelity engine models are simulated using an engine performance program. A test program designated for design, off-design and transient performance simulation for simple turbojet layout gas turbine engine has been programmed and tested. The knowledge gained from program coding was used to generate more robust transient performance code implemented to Turbomatch. Two transient methods have been tested: The rapid transient performance method and the thermodynamic matching method. The tests showed greater robustness and stability of the second method, which has been finally adopted for the program. For industrial engine configuration and for future novel engine cycles the heat-exchanger dynamic response model was implemented and tested. Created tool was demonstrated on short-haul study of engine flight path analysis. Together with the aircraft model, the tool produced variations of parameters needed for the lifing algorithm.
Supervisor: Pilidis, Pericles; Singh, R. Sponsor: Not available
Qualification Name: Thesis (Ph.D.) Qualification Level: Doctoral
EThOS ID:  DOI: Not available