کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
806423 | 905331 | 2011 | 11 صفحه PDF | دانلود رایگان |
The operability limits of a supersonic combustion engine for an air-breathing hypersonic vehicle are characterized using numerical simulations and an uncertainty quantification methodology. The time-dependent compressible flow equations with heat release are solved in a simplified configuration. Verification, calibration and validation are carried out to assess the ability of the model to reproduce the flow/thermal interactions that occur when the engine unstarts due to thermal choking. quantification of margins and uncertainty (QMU) is used to determine the safe operation region for a range of fuel flow rates and combustor geometries.
► In this work we introduce a method to study the operability limits of hypersonic scramjet engines.
► The method is based on a calibrated heat release model.
► It accounts explicitly for uncertainties due to flight conditions and model correlations.
► We examine changes due to the combustor geometry and fuel injection.
Journal: Reliability Engineering & System Safety - Volume 96, Issue 9, September 2011, Pages 1150–1160