Simultaneous Robust Design and Tolerancing of Compressor Blades
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Author(s)
Dow, Eric A.
Wang, Qiqi
Date Issued
June 2014
Journal
ASME Turbo Expo 2014: Turbine Technical Conference and Exposition Volume 2B: Turbomachinery
Publisher
American Society of Mechanical Engineers
Citation
Dow, Eric A., and Qiqi Wang. “Simultaneous Robust Design and Tolerancing of Compressor Blades.” ASME Turbo Expo 2014: Turbine Technical Conference and Exposition Volume 2B: Turbomachinery (June 16, 2014).
Version
Author's final manuscript
Abstract
The manufacturing processes used to create compressor blades inevitably introduce geometric variability to the blade surface. In addition to increasing the performance variability, it has been observed that introducing geometric variability tends to reduce the mean performance of compressor blades. For example, the mean adiabatic efficiency observed in compressor blades with geometric variability is typically lower than the efficiency in the absence of variability. This “mean-shift” in performance leads to increased operating costs over the life of the compressor blade. These detrimental effects can be reduced by using robust optimization techniques to optimize the blade geometry. The impact of geometric variability can also be reduced by imposing stricter tolerances, thereby directly reducing the allowable level of variability. However, imposing stricter manufacturing tolerances increases the cost of manufacturing. Thus, the blade design and tolerances must be chosen with both performance and manufacturing cost in mind.
This paper presents a computational framework for performing simultaneous robust design and tolerancing of compressor blades subject to manufacturing variability. The manufacturing variability is modelled as a Gaussian random field with non-stationary variance to simulate the effects of spatially varying manufacturing tolerances. The statistical performance of the compressor blade system is evaluated using the Monte Carlo method. A gradient based optimization scheme is used to determine the optimal blade geometry and distribution of manufacturing tolerances.
MIT Department
Massachusetts Institute of Technology. Aerospace Computational Design Laboratory
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
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Creative Commons Attribution-Noncommercial-Share Alike
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DOI of Published Version
https://doi.org/10.1115/GT2014-25795
