Investigation on effect of injector orifice diameter on injector atomization and combustion characteristics of pulse detonation combustor
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Wang Ding-Ding
,
Zheng Long-Xi
,
Tan Wen-Hao
Abstract
To reduce the fuel consumption rate of the pulse detonation combustor (PDC), an experimental study was carried out to study the influence of the injector aperture on the atomization particle size of the pneumatic atomization injector and its combustion characteristics of the PDC. The test used gasoline\air as the fuel and oxidant, tested the atomization particle size and obtained the detonation characteristics of PDC. The research results show that the atomization particle size of the injector under the three apertures decreases with the increase of the mixed air volume and increases with the increase of the fuel flow rate. The injector atomization effect is better when the aperture is 1.4 mm, the atomization particle size range is 71.8–119.8 μm. PDC using different injectors can achieve stable operation in the range of 5–20 Hz. Under the same working conditions, the smaller the injector aperture, the higher the average detonation pressure of the PDC.
Acknowledgments
The author conveys thanks to Professor Zheng Longxi for his strong support for this research and Professor Lu Jie for his guidance on article writing.
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Research ethics: The local Institutional Review Board deemed the study exempt from review.
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Author contributions: The authors have accepted responsibility for the entire content of this manuscript and approved its submission. The main research work of this article was completed by Dr. Wang Dingding and Dr. Tan Wenhao. Professor Zheng Longxi provided experimental equipment and venues for the study; Professor Lu Jie corrected the writing of the article; Engineer Li Qing provided technical support for the installation of experimental equipment.
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Competing interests: No potential competing interests was reported by the authors.
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Research funding: None declared.
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Data availability: The raw data can be obtained on request from the corresponding author.
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© 2024 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Experimental and numerical investigations on controlled parameter selection methods for kerosene-fueled scramjet
- Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization
- Parametric analysis of thermal cycle of a short take-off and vertical landing engine
- Conjugate heat transfer analysis on double-wall cooling configuration including jets impingement and film holes with conformal pins
- Research on the design method of mode transition control law for Ma6 external parallel TBCC engine
- A new schedule method for compact propulsion system model
- Numerical investigation on mixing of heated confined swirling coaxial jets with blockage
- Finite element based dynamic analysis of a porous exponentially graded shaft system subjected to thermal gradients
- Numerical study on aerodynamic performance of an intake duct affected by ground effect
- Influence of metal magnesium addition on detonation initiation in shock wave focusing Pulse Detonation Engine
- Probabilistic analysis of solid oxide fuel-cell integrated with gas turbine
- Improving thermal performance of turbine blade with combination of circular and oblong fins in a wedge channel: a numerical investigation
- Investigation on effect of injector orifice diameter on injector atomization and combustion characteristics of pulse detonation combustor
- Research on cascade control method for turboshaft engine with variable rotor speed
- The overall film cooling performance of crescent holes
- Air tab location effect on supersonic jet mixing
- Design and analysis of air intake of subsonic cruise vehicle with experimental validation
- Research on an optimization design method for a TBCC propulsion scheme
- Performance analysis of a gas turbine engine via intercooling and regeneration- Part 2
- Effects of bleed pressure on shock-wave/boundary-layer interactions in a transonic compressor stator with suction holes
- Effect of asymmetric leading edge on transition of suction side
Artikel in diesem Heft
- Frontmatter
- Experimental and numerical investigations on controlled parameter selection methods for kerosene-fueled scramjet
- Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization
- Parametric analysis of thermal cycle of a short take-off and vertical landing engine
- Conjugate heat transfer analysis on double-wall cooling configuration including jets impingement and film holes with conformal pins
- Research on the design method of mode transition control law for Ma6 external parallel TBCC engine
- A new schedule method for compact propulsion system model
- Numerical investigation on mixing of heated confined swirling coaxial jets with blockage
- Finite element based dynamic analysis of a porous exponentially graded shaft system subjected to thermal gradients
- Numerical study on aerodynamic performance of an intake duct affected by ground effect
- Influence of metal magnesium addition on detonation initiation in shock wave focusing Pulse Detonation Engine
- Probabilistic analysis of solid oxide fuel-cell integrated with gas turbine
- Improving thermal performance of turbine blade with combination of circular and oblong fins in a wedge channel: a numerical investigation
- Investigation on effect of injector orifice diameter on injector atomization and combustion characteristics of pulse detonation combustor
- Research on cascade control method for turboshaft engine with variable rotor speed
- The overall film cooling performance of crescent holes
- Air tab location effect on supersonic jet mixing
- Design and analysis of air intake of subsonic cruise vehicle with experimental validation
- Research on an optimization design method for a TBCC propulsion scheme
- Performance analysis of a gas turbine engine via intercooling and regeneration- Part 2
- Effects of bleed pressure on shock-wave/boundary-layer interactions in a transonic compressor stator with suction holes
- Effect of asymmetric leading edge on transition of suction side
