Article
Mechanics
Prasanth P. Nair, Abhilash Suryan, Vinod Narayanan
Summary: Combustion at supersonic speeds is crucial for improving performance. The research discovers that the divergence angle of the passive strut has an impact on the mixing efficiency and acoustic behavior. Unstable combustion occurs when the divergence angle is too high, while pressure loss decreases with a smaller divergence angle.
Article
Engineering, Aerospace
Singeetham Pranaykumar, Dinesh Mengu, Akshay Prakash
Summary: An innovative air-throttling injection mechanism is proposed and investigated in this study, aiming to improve the combustion efficiency and mixing efficiency in scramjets. The mechanism shows promising results in terms of flame stabilization, combustion efficiency, and shorter ignition length even at higher Mach numbers.
AEROSPACE SCIENCE AND TECHNOLOGY
(2023)
Article
Chemistry, Physical
Rocky Simon Pinto, T. Sree Renganathan, S. M. D. Hamid Ansari, T. M. Muruganandam
Summary: The experimental study investigates the influence of stagnation temperature on hysteresis in flame stabilization in a hydrogen-fueled supersonic combustor. The results show that the variation in stagnation temperature significantly affects the hysteresis between different flame stabilization modes.
INTERNATIONAL JOURNAL OF HYDROGEN ENERGY
(2023)
Article
Energy & Fuels
Junjie Miao, Yuxin Fan, Weiqiu Wu, Shilong Zhao
Summary: The novel air-assistant design proposed for cavity-strut based combustor can widen the ignitable space for ignition, extend the flammable Mach number, and decrease the lean ignition and blowout fuel/air ratio. The introduction of air-assistant method regulates the flame structure, enhances flame stability, and increases the temperature rise of combustor within the full range of operating fuel/air ratio.
Article
Engineering, Aerospace
Huimin Tian, Junlong Zhang, Hongchao Qiu, Wen Bao, Songjing Li
Summary: This study achieved stable supersonic combustion in a scramjet combustor fueled by liquid kerosene with the help of an O2-pilot strut. The effect of different mass flow rate of oxygen on cold flow and combustion characteristics was investigated, and the results showed that adjusting the mass flow rate of oxygen improved the combustion zone around the ignitor. However, excessive or insufficient oxygen resulted in delayed ignition or increased flame lift distance.
Article
Engineering, Aerospace
Xin Li, Yu Pan, Chaoyang Liu, Xiao Liu
Summary: To avoid the thermal choking problem in scramjet, a wall-expansion scheme is usually adopted, but it poses challenges to flame holding. This paper uses large eddy simulation to study the effect of expansion angle change on the flameout limit in the strut-based supersonic combustor. The numerical results show the establishment of the recirculation zone and the role of reflected shock waves in enhancing combustion.
AEROSPACE SCIENCE AND TECHNOLOGY
(2023)
Article
Thermodynamics
Fuxu Quan, Juntao Chang, Chen Kong, Chengkun Lv, Guangwei Wu
Summary: This study investigates the fuel injection strategy and the effect of supplemental oxygen on the mixing performance in a scramjet combustor through large eddy simulations. The results show that injecting fuel from the upstream nozzle enhances mixing efficiency compared to the downstream nozzle. Additionally, supplementing oxygen at the trailing edge of the strut significantly improves turbulence and enhances fuel and oxidizer mixing.
APPLIED THERMAL ENGINEERING
(2024)
Article
Engineering, Aerospace
A. A. Dhankarghare, T. Jayachandran, T. M. Muruganandam
Summary: This study combines a strut and a cavity into a strut cavity and compares it with a wall cavity using numerical simulations at different Mach numbers and aspect ratios. The results show that the wall cavity is more prone to oscillations compared to the strut cavity. The generation process of waves inside the cavity is revisited, where both the unstable shear layer and vortex shedding contribute to the wave generation in supersonic flows.
AEROSPACE SCIENCE AND TECHNOLOGY
(2022)
Article
Mechanics
A. A. Dhankarghare, T. Jayachandran, T. M. Muruganandam
Summary: A study was conducted on flow dynamics in strut cavity and wall cavity at different freestream Mach numbers using numerical simulations. The results showed that oscillations occurred in both cavities for low supersonic Mach numbers and decreased for high values, with the strut cavity responding better to the change in Mach number. The study explored wave propagation and interactions inside the cavities, discussed secondary recirculation, revisited the process of wave generation, provided insights into vortex propagation along the cavity length, and described and compared mass exchange between the cavities and freestream.
Article
Mechanics
Hongchao Qiu, Guowei Luan, Guangjun Feng, Junlong Zhang, Wen Bao
Summary: This study investigates the effect of fuel injection methods on flame oscillation characteristics in an annular combustor. Experimental results show that the flame exhibits different oscillation modes and frequencies under different injection conditions, which are related to pressure gradients and combustion modes. Increasing the spacing between injection struts can alleviate flashback issues.
Article
Nanoscience & Nanotechnology
Fuxu Quan, Juntao Chang, Chen Kong, Guangwei Wu, Dayi Wang
Summary: The flow field structure and mixing characteristics of a supersonic combustor are studied using large eddy simulation. The combustor is equipped with fuel injection holes and oxygen injection holes to enhance mixing. The mixing performance of the combustor is evaluated based on the fuel and oxidant mixing efficiency, and the differences in mixing characteristics with and without oxygen supplementation are compared.
Article
Engineering, Aerospace
Jieli Wei, Huanyu Zhu, Zhixiang Zhu, Xiaomin He, Zhuyin Ren
Summary: Flame characteristics in an evaporating-flame holder can be modulated by supersonic shear, but flame stabilization is not affected by the presence of shear flow. The development of the flame is influenced by the recirculation zone and outer shear layer behind the flame holder.
AEROSPACE SCIENCE AND TECHNOLOGY
(2021)
Article
Energy & Fuels
Zehua Zhang, Abouelmagd Abdelsamie, Cheng Chi, Dominique Thevenin, Kai H. Luo
Summary: This study numerically investigated the flame anchoring of a hydrogen-rich jet injecting perpendicularly into hot vitiated crossflow. The flame was found to be anchored around the jet exit and downstream only on the windward side. Diffusion flame was dominant, though some premixed or partially premixed regions were found on the leeward side due to turbulent mixing.
Article
Thermodynamics
Wonsik Song, Francisco E. Hernandez Perez, Efstathios-Al. Tingas, Hong G. Im
Summary: The statistical analysis of turbulent hydrogen-air premixed flames at various Karlovitz numbers reveals that the global turbulent flame speed is mostly determined by the integral length scale, with flame surface area enhancement playing a key role. Probability density function analysis of displacement speed shows that the highest probability of local flame speed coincides with one-dimensional unstretched flame speed.
COMBUSTION AND FLAME
(2021)
Article
Thermodynamics
Longjuan Ji, Jinhua Wang, Weijie Zhang, Runze Mao, Guangya Hu, Zuohua Huang
Summary: This study experimentally investigated the blow-off and flame macrostructure transition behavior of unconfined and confined premixed CH4/air flames. The results showed that the combustor confinement could significantly broaden the blow-off limits. The influence of confinement ratio (CR) on flame stabilization was revealed by analyzing flame structures and flow fields. The transition from stable to unstable was extended by increasing the CR in the confined combustor.
EXPERIMENTAL THERMAL AND FLUID SCIENCE
(2022)
Article
Engineering, Aerospace
Youyin Wang, Wen Shi, Xuan Wang, Junlong Zhang, Jin Gao, Jingfeng Tang, Juntao Chang, Wen Bao
Summary: This study investigates a 20-degree deflection angle wave-elimination variable geometry combustor, demonstrating through numerical simulations and experimental tests its superior performance in a wide range of operating speeds, especially at high Mach numbers. The wave-elimination design improves the total pressure recovery coefficient of the combustor under different conditions, showing significant advantages for improving the performance of variable-geometry combustors in future hypersonic aircrafts.
AEROSPACE SCIENCE AND TECHNOLOGY
(2021)
Article
Engineering, Aerospace
Jingying Zuo, Dingyuan Wei, Silong Zhang, Jiang Qin, Wen Bao, Naigang Cui
Summary: Film cooling is an effective method for achieving thermal protection and reducing skin friction in scramjet combustors. Combustion of the coolant film has double effects on film cooling performance and reduces skin friction. Additionally, shock waves generated after ignition of hydrocarbon fuel significantly influence skin friction distribution.
AEROSPACE SCIENCE AND TECHNOLOGY
(2021)
Article
Mechanics
Nan Li, Juntao Chang, Kejing Xu, Daren Yu, Wen Bao
Summary: The study investigated the unstable behavior of a shock train system in a back pressured duct with incident shocks. It found that as the shock train enters the SWBLI region, divergent vibration emerges, leading to instability. An analysis based on the feedback mechanism identified a criterion for this instability.
JOURNAL OF FLUID MECHANICS
(2021)
Article
Engineering, Aerospace
Hongchao Qiu, Junlong Zhang, Jin Gao, Juntao Chang, Wen Bao
Summary: An experimental study was conducted on a strut/wall combined fuel injection scheme in a flush-wall scramjet combustor fueled with liquid kerosene. Results showed that increasing fuel equivalence ratio enhances core flame and leads to the formation of wall flame, while optimizing the position of wall fuel injectors can improve combustion efficiency.
AEROSPACE SCIENCE AND TECHNOLOGY
(2021)
Article
Thermodynamics
Youyin Wang, Wenxin Hou, Junlong Zhang, Jingfeng Tang, Juntao Chang, Wen Bao
Summary: This paper analyzes the pressure rise mechanism of the dual mode scramjet engine and the characteristic of the isolator maximum pressure rise. The operating range and performance of the scramjet under the pressure rise limit are investigated using a constant cross-sectional area combustor. The study suggests a variable divergent section to balance pressure under different freestream Mach numbers and equivalence ratios.
Article
Engineering, Aerospace
Jingying Zuo, Silong Zhang, Jiang Qin, Wen Bao, Naigang Cui, Oskar J. Haidn
Summary: This paper numerically investigates the interaction between oblique shock waves and hydrocarbon fueled supersonic film cooling with combustion using Reynolds-averaged Navier-Stokes equations. It is found that the shock wave reflects on the flame and induces small-momentum region on the wall, leading to an increase in reflected shock wave intensity. Additionally, the interaction between shock waves and combustion reduces the beneficial cooling performance and increases the skin friction reduction region.
AEROSPACE SCIENCE AND TECHNOLOGY
(2021)
Article
Engineering, Aerospace
Wanqian Xu, Junlong Zhang, Chenguang Zhong, Juntao Chang, Wen Bao
Summary: An algorithm for noncontact portable temperature measurement sensors for scramjet combustion chambers has been developed, comparing the inversion capabilities of OH radical emission spectra using multilayer perceptron and convolutional neural networks. Noise levels in the measurements were considered, with the convolutional neural network showing promising results with added random Gaussian noise.
Article
Thermodynamics
Hongchao Qiu, Junlong Zhang, Guangjun Feng, Juntao Chang, Wen Bao
Summary: This study presents the design of an axisymmetric variable geometry scramjet combustor equipped with a strut flame holder. Numerical calculations and experiments were conducted to investigate the performance of the combustor. The results demonstrate that the designed combustor can operate effectively in a wide range of flight Mach numbers, with good performance at high Mach numbers.
COMBUSTION SCIENCE AND TECHNOLOGY
(2023)
Article
Thermodynamics
Jianfei Wei, Silong Zhang, Jingjia Xue, Xingyu Zhou, Jiang Qin, Wen Bao
Summary: Film cooling using gaseous hydrocarbon fuel is an effective method to meet the requirements of thermal protection and friction reduction in hydrocarbon-fueled scramjet engines. The characteristics of the hydrocarbon film cooling and friction reduction are influenced by the wall thermal state through chemical reactions. Numerical investigations show that wall cooling heat flux has a positive effect on film cooling performance but a negative effect on friction reduction performance. The endothermic chemistry in the hydrocarbon film can enhance cooling comparable to regenerative cooling, but the wall shear stress is less sensitive to the wall thermal state.
APPLIED THERMAL ENGINEERING
(2022)
Review
Engineering, Aerospace
Yunfei Li, Juntao Chang, Chen Kong, Wen Bao
Summary: This article provides an overview of the development and applications of machine learning in the field of fluid mechanics. Machine learning offers a wide range of analysis methods for understanding flow mechanisms and for practical applications. Machine learning algorithms can enhance flow information and perform tasks automatically.
CHINESE JOURNAL OF AERONAUTICS
(2022)
Article
Thermodynamics
Xin Pan, Yuefei Xiong, Cong Wang, Jiang Qin, Silong Zhang, Wen Bao
Summary: Precooling is crucial for hydrocarbon-fueled TBCC engines to expand the flight Mach number and improve specific impulse. The low-temperature endothermic fuel precooling scheme shows great potential in enhancing heat sink and overall performance.
Article
Thermodynamics
Xin Pan, Jiang Qin, Silong Zhang, Wen Bao
Summary: Precooling technology with a low-temperature endothermic fuel is a potential solution for the reduction of specific impulse in hydrocarbon-fueled turbojet engines. Methanol cracking reaction can enhance the cooling effect but may decrease the compactness of the precooler with an increase in the longitudinal pitch-to-diameter ratio. Decreasing the transverse pitch-to-diameter ratio can increase the cooling effect but will result in significant pressure loss.
CASE STUDIES IN THERMAL ENGINEERING
(2022)
Review
Engineering, Aerospace
Chengkun Lv, Juntao Chang, Wen Bao, Daren Yu
Summary: The paper provides a summary report on recent research progress in the control of airbreathing aero-engines, covering different control problems and methods, as well as issues related to hypersonic flight and turbine-based combined cycle engines. It serves as a useful reference for researchers working in this field.
PROPULSION AND POWER RESEARCH
(2022)
Article
Engineering, Aerospace
Junlong Zhang, Libo Lin, Zhaohui Yao, Wen Bao
Summary: In this paper, the unstart boundary of the strut-equipped variable geometry combustor was experimentally verified at Mach 2 condition. The study focuses on the requirements of fuel equivalent ratio and combustor expansion ratio for the working boundary of the supersonic combustor. Through simulation analyses and static regulations, the optimization of flow field structure and successful ignition were achieved. Experimental investigations were then conducted to adapt the fuel equivalent ratio and expansion ratio for performance enhancement, leading to qualitative and quantitative conclusions about the starting boundary and performance distribution pattern of the combustor.
Article
Thermodynamics
Kunlin Cheng, Jiang Qin, Duo Zhang, Wen Bao, Wuxing Jing
Summary: The closed-Brayton-cycle (CBC) power generation system is a potential high-power electricity generation scheme for hypersonic vehicles, but it is limited by finite cold source onboard. This study proposes a combined power generation system based on supercritical carbon dioxide closed-Brayton-cycle and multi-stage thermoelectric generator (TEG) to extend the available temperature range of the cold source and increase electric power output.
Article
Engineering, Aerospace
Andre F. P. Ribeiro, Carlos Ferreira, Damiano Casalino
Summary: This study compares a filament-based free wake panel method to experimental and validated numerical data in order to simulate propeller slipstreams and their interaction with aircraft components. The results show that the free wake panel method is able to successfully capture the slipstream deformation and shearing, making it a useful tool for propeller-wing interaction in preliminary aircraft design.
AEROSPACE SCIENCE AND TECHNOLOGY
(2024)