Combustion Design Senior Engineer

Job Overview:

The Gas Turbine Combustor Engineer is responsible for the design, analysis, development, and support of combustor systems for micro jet engines. The role requires the incumbent to gather and interpret customer requirements and contextualise the performance criteria in conjunction with the engine performance analysis team. It is expected that the combustor designer will use the appropriate tools for the given stage of the design process, for instance, comprehensive 1-D and correlation-based modelling for the introductory sizing phases and eventually exploit high-fidelity CFD analysis to model the complex combustion processes.

The role of the designer focuses on achieving stable combustion, high efficiency, low emissions, reliable ignition, and long life within the constraints of very small engine architectures, where combustor residence time, temperature patterns, and manufacturability are especially challenging. The designer must communicate across a wide range of functions, such as system engineering, mechanical design, materials engineering, and advanced additive manufacturing, for instance.

In summary, the goal of the combustor designer is to assess requirements, demonstrate innovation in the application of the tools, maintain a pragmatic product-centric outlook, and finally deliver a fit-for-purpose design.

• Define combustor requirements from engine cycle conditions, including thrust class, allowable pressure loss, operability range, emissions intent, and turbine inlet temperature constraints.
• Translate system requirements into a combustor concept by selecting the overall architecture, primary zone arrangement, fuel injection approach, dilution strategy, and cooling philosophy.
• Carry out preliminary sizing and concept development using first-principles methods, empirical correlations, and iterative trade studies to establish feasible geometry and performance.
• Analyse flow field, mixing, ignition, flame stability, liner heat load, and exit temperature distribution to refine the design through successive development stages.
• Evaluate design sensitivities to geometry, fuel scheduling, airflow split, and manufacturing tolerance to improve robustness and reduce risk early in the process.
• Develop and review detailed combustor hardware, including dome, swirler, liner, dilution holes, cooling features, igniter location, and sealing interfaces.
• Support CFD, rig testing, and engine testing to validate assumptions, correlate analytical predictions with measured data, and update the design accordingly.
• Iterate the combustor design through concept, preliminary, detailed, and verification phases until performance, durability, and operability targets are met.
• Work closely with performance, aerodynamics, mechanical design, materials, manufacturing, and test teams to ensure the combustor design integrates cleanly into the full engine system.
• Document design rationale, trade-offs, test findings, and verification evidence to support technical reviews and development gates.

• Masters’s degree in Aerospace Engineering, Mechanical Engineering, Thermal Engineering, or a closely related discipline.
• 8–10 years of progressively responsible experience in gas turbine combustion, combustor design, or propulsion system development.
• Strong academic and practical background in gas turbine combustor fundamentals, including fuel injection, swirl and recirculation, flame stabilisation, liner cooling, dilution, and turbine inlet temperature management.
• Demonstrated experience in the full combustor design process: concept development, preliminary sizing, detailed design, and verification through analysis and test.
• Proven ability to correlate analytical and CFD results…