A Methodology for Robust Design of Impingement Cooled HSCT Combustion Liners

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AIAA-97-0288.pdf (122.83 KB)
Author(s)
Roth, Bryce Alexander
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Daniel Guggenheim School of Aerospace Engineering
The Daniel Guggenheim School of Aeronautics was established in 1931, with a name change in 1962 to the School of Aerospace Engineering
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http://hdl.handle.net/1853/6366
Abstract
This paper describes the use of a robust design simulation methodology for the determination of an optimum lean, premixed, prevaporized combustor liner cooling configuration for a High Speed Civil Transport. The objective of design robustness as developed at the Georgia Institute of Technology is to find settings for design parameters which will not only maximize performance, but also minimize the influence of uncertainty on performance. This robust design simulation methodology is formulated here as a very general approach that lends itself to any design problem where uncertainty exists. This general methodology is applied to the design of a combustor liner in order to quantify the effect of cycle parameter and heat transfer coefficient uncertainties on combustor liner metal temperature variance. The results show that for the parameter ranges of interest, impingement hole spacing and thermal barrier coating thickness have the greatest effect on metal temperature variance and are used to find a robust liner configuration.
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1997-01
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125778 bytes
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