Secondary effects, such as heat transfer from fluid to engine structure and the resulting changes in tip and seal clearances affect component performance and stability. A tip clearance model to be used in transient synthesis codes has been developed. The tip clearance model is derived as a state space structure. The model parameters have been identified from thermomechanical finite element models. The model calculates symmetric rotor tip clearance changes in the turbomachinery and symmetric seal clearance changes in the secondary air system for engine transients within the entire flight envelope. The resulting changes in efficiency, capacity, and cooling airflows are fed into the performance program. Corrections for tip clearance changes on the component characteristics are derived from rig tests. The effect of seal clearance changes on the secondary air system is derived using sophisticated air system models. The clearance model is validated against FE thermomechanical models. The modeling method of modifying the component characteristics is verified comparing engine simulation and test data, which show good agreement. Based on a representative transient maneuver typical transient overshoots in fuel flow and turbine gas temperature and changes in component stability margins can be shown. With the use of this model in the performance synthesis the transient engine performance can be predicted more accurate than currently in the engine development program.

Therkorn, D., 1992, “Fortschrittliches Leistungs-Berechnungsverfahren fu¨r luftatmende Turbotriebwerke,” Doctor thesis, University of Stuttgart.
Khalid, S. J., and Hearne, R. E., 1980, “Enhancing Dynamic Model Fidelity for Improved Prediction of Turbofan Engine Transient Performance,” AIAA 80-1083.
Fiola, R., 1993, “Berechnung des Instationa¨ren Betriebsverhaltens unter Besonderer Beru¨cksichtigung von Sekunda¨reffekten,” Doctor thesis, Technical University of Munich.
Riegler, C., 1999, “Correlations to Include Heat Transfer in Gas Turbine Performance Calculations,” Aerospace Science and Technology, No. 5, pp. 281–292.
Frank, R., Rist, D., and Kappler, G., 1993, “On-line U¨berwachung der Ermu¨dungslebensdauer von Rotierenden Flugtriebwerkskomponenten,” DGLR Jahresbuch No. 93-03-048.
Peters, P., Breisig, V., Giboni, A., Lerner, C., and Pfost, H., 2000, “The Influence of the Clearance of Shrouded Rotor Blade on the Development of the Flowfield and Losses in the Subsequent Stator,” ASME GT-478.
Staudacher, S., 1995, “Untersuchungen zum sekunda¨ren Luftsystem von Luftstrahltriebwerken,” Doctor thesis, Technical University of Munich.
Staudacher, S., Berns, W., and Ye, Haiwen, “Modeling Multistage Compressors by Several Split Compressors,” Institute for Aircraft Propulsion, University of Stuttgart, ALSTOM, Switzerland, AIAA 2003-1019.
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