The Effect of Dilution Air Jets on Aero-Engine Combustor Performance
-
Yinli Xiao
,
Zhibo Cao
Abstract
In aero-engine combustor, the primary and secondary dilution air jets play a vital role to achieve efficient combustion and provide a satisfactory temperature profile at the combustor exit. In the current research, seven kinds of three-dome combustor sector associated with different dilution holes arrangements are simulated using Flamelet model. The influences of location, number and diameter of dilution air holes on flow field and performance of combustor are analysed in detail. The results demonstrate that the variation of airflow distribution, while keeping the total admission area constant, impact the combustion efficiency and pattern profile considerably, yet has insignificant effect on the total pressure coefficient. The maximum combustion efficiency and minimum pattern factor can be achieved simultaneously with deliberate dilution jet holes arrangement.
Acknowledgements
This work has been funded by the National Natural Science Foundation of China under grant 51576164.
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© 2019 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- 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
Artikel in diesem Heft
- 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
