A methodology for robust design of impingement cooled HSCT combustor liners

Dimitri Mavris, Bryce Roth, Dimitri Mavris, Bryce Roth
1997 35th Aerospace Sciences Meeting and Exhibit   unpublished
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
more » ... ogy 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.
doi:10.2514/6.1997-288 fatcat:c5bmwyitmneudiclypnvszhgli