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 thermo-mechanical finite element models. The model calculates symmetric rotor tip clearance changes in the turbo-machinery 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 air flows 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 thermo-mechanical 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.
Modeling and Validation of the Thermal Effects on Gas Turbine Transients
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Nielsen, AE, Moll, CW, & Staudacher, S. "Modeling and Validation of the Thermal Effects on Gas Turbine Transients." Proceedings of the ASME Turbo Expo 2004: Power for Land, Sea, and Air. Volume 3: Turbo Expo 2004. Vienna, Austria. June 14–17, 2004. pp. 363-374. ASME. https://doi.org/10.1115/GT2004-53344
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