Abstract
Different strut-cavity configurations and fuel injection patterns employed in a round supersonic combustor are numerically investigated. A new parameter defined as an ideal nozzle outlet velocity is used to evaluate performances of different strut-cavity configurations and fuel injection patterns. This parameter is a reflection of the contribution of the combustor performance to the engine thrust. The peak of the velocity curve stands for the best performance of the combustor. Then the flowfields are discussed in detail. The flow structures indicate that the injection from the wall behind a strut achieves a great penetration because of the strong upward transport that results from the streamwise vortices behind the strut. Results show that the combustor performance and the flowfields are greatly influenced by the fuel injection patterns. The fuel injections from the strut sides and from the center ring achieve the better performances than that from the wall behind the struts.
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© 2019 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Numerical Study of Combinations of Strut and Cavity in a Round Supersonic Combustor
- Design and Numerical Analysis of a Forepart Rotation Vane for a Variable Nozzle Turbine
- Aerodynamic Efficiency Optimization of the 1st Stage of Transonic High Pressure Turbine through Lean and Sweep Angles
- The Effect of Dilution Air Jets on Aero-Engine Combustor Performance
- Simulation of a High Fidelity Turboshaft Engine-Alternator Model for Turboelectric Propulsion System Design and Applications
- Effects of Non-axisymmetric Casing Grooves Combined with Airflow Injection on Stability Enhancement of an Axial Compressor
- Exhaust System for Radial and Axial-Centrifugal Compressor with Pipe Diffuser
- Advanced Exergy Analysis of a Turbofan Engine (TFE): Splitting Exergy Destruction into Unavoidable/Avoidable and Endogenous/Exogenous
- A Preliminary Design System for Turbine Discs
- Tensile Behavior and Microstructural Evolution of the Polycrystalline Nickel-Based Superalloy Applied in Turbine Disk
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Numerical Study of Combinations of Strut and Cavity in a Round Supersonic Combustor
- Design and Numerical Analysis of a Forepart Rotation Vane for a Variable Nozzle Turbine
- Aerodynamic Efficiency Optimization of the 1st Stage of Transonic High Pressure Turbine through Lean and Sweep Angles
- The Effect of Dilution Air Jets on Aero-Engine Combustor Performance
- Simulation of a High Fidelity Turboshaft Engine-Alternator Model for Turboelectric Propulsion System Design and Applications
- Effects of Non-axisymmetric Casing Grooves Combined with Airflow Injection on Stability Enhancement of an Axial Compressor
- Exhaust System for Radial and Axial-Centrifugal Compressor with Pipe Diffuser
- Advanced Exergy Analysis of a Turbofan Engine (TFE): Splitting Exergy Destruction into Unavoidable/Avoidable and Endogenous/Exogenous
- A Preliminary Design System for Turbine Discs
- Tensile Behavior and Microstructural Evolution of the Polycrystalline Nickel-Based Superalloy Applied in Turbine Disk