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A Reduced Model for Prediction of Thermal and Rotational Effects on Turbine Tip ClearanceThis paper describes a dynamic model that was developed to predict changes in turbine tip clearance the radial distance between the end of a turbine blade and the abradable tip seal. The clearance is estimated by using a first principles approach to model the thermal and mechanical effects of engine operating conditions on the turbine sub-components. These effects are summed to determine the resulting clearance. The model is demonstrated via a ground idle to maximum power transient and a lapse-rate takeoff transient. Results show the model demonstrates the expected pinch point behavior. The paper concludes by identifying knowledge gaps and suggesting additional research to improve the model.
Document ID
Document Type
Technical Memorandum (TM)
Kypuros, Javier A.
(Texas Univ. Edinburg, TX, United States)
Melcher, Kevin J.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
September 8, 2013
Publication Date
March 1, 2003
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:212226
Funding Number(s)
OTHER: 22-708-87-06
Distribution Limits
Work of the US Gov. Public Use Permitted.
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