Requirements
Master's degree in Aerospace Engineering, Mechanical Engineering, Thermal Engineering, or a related discipline. 8-10 years of progressive experience in gas turbine combustion, combustor design, or propulsion system development. Strong technical expertise in combustor fundamentals including swirl, recirculation, fuel atomization, flame stabilization, liner cooling, dilution, and turbine temperature management. Demonstrated experience across the full combustor design lifecycle from concept development through verification and testing. Proven ability to correlate CFD and analytical outputs with rig or engine test data and implement design improvements.
Description
External Job DescriptionJob OverviewThe Senior Combustor Design Engineer is responsible for the design, development, analysis, and validation of combustor systems for advanced micro jet engines. The role focuses on translating engine performance requirements into robust combustor concepts that deliver stable combustion, high thermal efficiency, reliable ignition, low emissions, and long component life within highly constrained small-engine architectures. Due to the compact nature of microjet platforms, the role requires strong expertise in residence time management, flame stability, thermal loading, exit temperature pattern control, and manufacturability.Key ResponsibilitiesDefine combustor design requirements based on engine cycle data, thrust requirements, allowable pressure loss, emissions targets, ignition envelope, and turbine inlet temperature constraints.Translate system-level requirements into combustor architecture, including dome and primary zone design, swirler configuration, fuel injection concept, dilution strategy, and cooling philosophy.Perform preliminary sizing and concept development using first-principles calculations, empirical correlations, and iterative trade-off studies.Develop and refine combustor geometry through concept, preliminary, detailed, and verification phases.Analyse flow field behaviour, mixing efficiency, ignition performance, flame stability, liner heat load, and combustor exit temperature distributionConduct design sensitivity assessments on geometry, airflow split, fuel scheduling, and manufacturing tolerances to improve robustness and reduce technical riskReview and develop detailed combustor hardware including liner, dome, swirler, dilution holes, cooling features, igniter interfaces, and sealing arrangementsSupport CFD studies, rig testing, and full engine testing to validate design assumptions and correlate predictions with measured dataDrive design iterations based on test findings, performance gaps, operability concerns, and durability outcomesWork cross-functionally with performance, aerodynamics, mechanical design, materials, manufacturing, and test teams to ensure seamless engine integrationQualifications & ExperienceMaster's degree in Aerospace Engineering, Mechanical Engineering, Thermal Engineering, or a related discipline.8–10 years of progressive experience in gas turbine combustion, combustor design, or propulsion system development.Strong technical expertise in combustor fundamentals including swirl, recirculation, fuel atomization, flame stabilization, liner cooling, dilution, and turbine temperature management.Demonstrated experience across the full combustor design lifecycle from concept development through verification and testing.Proven ability to correlate CFD and analytical outputs with rig or engine test data and implement design improvements.#Powertech