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| 1 | Micromanufacturing technologies of compact heat exchangers for hypersonic precooled airbreathing propulsion: A review显示文摘The Hypersonic Precooled Combined Cycle Engine(HPCCE), which introduces precooler into traditional hypersonic engine, is regarded as the most promising propulsion system for realizing a single-stage-to-orbit vehicle. The unique demands lead to the application of the compact heat exchangers, which can realize high thrust-to-weight ratio, sufficient specific impulse and high compression ratio. However, it is challenging to accurately manufacture the compact heat exchanger due to its extremely high heat dissipation capacity, remarkable compactness, superior adaptability and harsh operating condition. This review summarizes the precooling schemes of combined cycle propulsions and describes the demands and key issues in the fabrication of a compact heat exchanger for HPCCE. The investigation focuses on the application of various micromanufacturing methods of heat exchangers constructed from tubes of less than 1 mm in diameter and microchannels of less than 200 micrometers. Various micromanufacturing processes, which include microforming, micromachining, stereolithography, chemical etching, 3 D printing, joining and other advanced microfabricating processes, were reviewed. In addition, the technologies are compared in terms of dimensional tolerance, material compatibility, and process applicability. Furthermore, the boundaries of the micromanufacturing constraints are specified as references for the design of compact heat exchangers. Ultimately, the technological difficulties and development trends are discussed for the fabrication of compact heat exchangers for HPCCE. | Bao MENG Min WAN Rui ZHAO Zhengping ZOU Huoxing LIU | 2021 | Chinese Journal of Aeronautics2021，34，2： | 10 |
| 2 | Numerical investigation of the interaction between upstream cavity purge flow and main flow in low aspect ratio turbine cascade显示文摘In modern gas turbines, rim seal located between the stator-disc and rotor-disc is used to prevent hot-gas ingestion into the inner stage-gap of high pressure turbine. However, the purge flow supplied to the cavity through the rim seal interacts with the main flow, producing additional aerodynamic loss due to the mixing process which plays a significant role in the formation, development and evolution of downstream secondary flow. In this paper, a set of cascade representative of low aspect ratio turbine is selected to numerically investigate the influence of upstream cavity purge flow on the hub secondary flow structure and aerodynamic loss. Cascade with/without upstream cavity and four different purge mass flow rates are all taken into account in this simulation. Then, a deep insight into the loss mechanism of interaction between purge flow and main flow is gained. The results show that the presence of cavity and purge flow has a significant impact on the main flow which not only changes the vortex structure in both the passage and upstream cavity, but also alters the cascade exit flow angle distribution along the spanwise. Moreover, aerodynamic loss in the cascade rises with the increase of purge flow rate while the sealing effect is also enhanced. Therefore, the effect of upstream cavity purge flow must be considered in the process of turbine aerodynamic design. What is more, it is necessary to minimize the purge flow rate in order to reduce aerodynamic loss on the premise of satisfying cooling requirements. | Jia Wei Liu Huoxing | 2013 | Chinese Journal of Aeronautics2013，26，1： | 9 |
| 3 | Computational Study of the Effects of Shroud Geometric Variation on Turbine Performance in a 1.5-Stage High-Loaded Turbine显示文摘Generally speaking,main flow path of gas turbine is assumed to be perfect for standard 3D computation.But in real engine,the turbine annulus geometry is not completely smooth for the presence of the shroud and associated cavity near the end wall.Besides,shroud leakage flow is one of the dominant sources of secondary flow in turbomachinery,which not only causes a deterioration of useful work but also a penalty on turbine efficiency.It has been found that neglect shroud leakage flow makes the computed velocity profiles and loss distribution significantly different to those measured.Even so,the influence of shroud leakage flow is seldom taken into consideration during the routine of turbine design due to insufficient understanding of its impact on end wall flows and turbine performance.In order to evaluate the impact of tip shroud geometry on turbine performance,a 3D computational investigation for 1.5-stage turbine with shrouded blades was performed in this paper.The following geometry parameters were varied respectively:-Inlet cavity length and exit cavity length,-Shroud overhang upstream of the rotor leading edge and downstream of the trailing edge,-Shroud radial tip clearance,The aim of this paper is to isolate the influence of shroud and cavity geometry modifications on turbine aerodynamic performance and to obtain clear trends of efficiency changes caused by different tip shroud geometry.Moreover,interaction between leakage flow and mainstream for different shroud configuration is also highlighted in order to penetrate into the physical mechanisms producing them.Due to the limitations of the model selected in this paper,the aim of research is not to put forward the design rules of turbine shroud.However,the results obtained from this work will be useful to the integrated design and optimization of turbine with shrouded blades. | Wei Jia Huoxing Liu | 2013 | Journal of Thermal Science2013，22，5： | 4 |
| 4 | Effect of Applied Stresses on the Microstructure and Dissolution Behavior of Plasma Sprayed Wollastonite Coatings显示文摘Wollastonite coatings were deposited on the U-shape titanium alloy coupons by atmospheric plasma spraying.The effect of applied stresses on the microstructure and dissolution behavior of wollastonite coatings was investigated.The microstructure and composition of coatings were examined by scanning electron microscope(SEM)and electron diffraction spectroscopy(EDS).In addition,the dissolution behavior of coatings was evaluated by immersion in simulated body fluid(SBF).More apatite is observed on the surface of coatings under a tensile stress and a stress-free condition after immersion in the SBF solution,whereas almost no apatite can be found for the coatings under a compressive stress.The dissolution rate of coatings characterized by the pH changes and the ion concentration of Ca,Si and P in the SBF solution is lower under the compressive stress than those under a tensile stress or a stress-free condition.It can be concluded from the experimental results that the compressive stress inhibits the dissolution of wollastonite coatings and the formation of apatite,whereas a tensile stress enhances the two processes. | Wang Weize Liang Jiachun Xuan Fuzhen Hong Huoxing | 2012 | 稀有金属材料与工程2012，41，S1： | 2 |
| 5 | A novel approach to Finafloxacin hydrochloride (BAY35-3377)显示文摘 | Jian Hong Zonghua Zhang Huoxing Lei Haiying Cheng Yufang Hu Wanliang Yang Yinglin Liang Debasis Das Shu-Hui Chen Ge Li | 2009 | Tetrahedron Letters2009，，21： | 1 |
| 6 | Application of SPIV in turbomachinery 显示文摘 | LIU Baojie YU Xianjun LIU Huoxing | 2006 | Experiments in Fluids2006，40，4： | 1 |
| 7 | Aerodynamics Design of Two-stage Vane-less Counter-rotating Turbinec显示文摘It is one of the most efficient ways to greatly improve aero-engines' performance by utilizing vaneless counterrotating turbine(VCRT) technology.To supply sufficient power,VCRT turns to be high Mach number,large flow angle at high-pressure turbine(HPT) rotor exit,and low blade camber angle,which increase difficulties to turbine design.As the axial velocity ratio of HPT rotor is much larger than the conventional ones,the optimal selection of VCRT velocity triangles based on theoretical analysis is developed,and how the efficiency varied by HPT stator/rotor exit flow angle is also figured out.The key points to design a high efficient practicable VCRT are to select velocity triangles that are characterized by low flow coefficient,high outlet flow angle and large axial velocity ratio of HPT rotor.Meanwhile,performance comparison between convergent blade and convergent-divergent blade shows the latter is more appropriate for VCRT. | Yang Zhou Huoxing Liu Wei Li Jun Zeng | 2011 | Journal of Thermal Science2011，20，5： | 1 |
| 8 | Numerical investigation of the effect of rim seal on turbine aerodynamic design parameters and end wall flows in low aspect ratio turbine 显示文摘 | Wei Jia Huoxing l iu | 2013 | Computers2013，2013，5： | 1 |
| 9 | Experimental Investigation on Dynamic Properties of Rubberized Concrete显示文摘 | Zheng L Sharon HuoX and Yuan Y | 2008 | Construction and Building Materials2008，22，5： | 1 |
| 10 | Relationship between HPV16/18 E6 and 53,21WAF1,MDM2,Ki67 and cyclin D1 expression in esophageal squamous cell carcinoma:comparative study by using tissue microarray technology显示文摘 | Qi zL HuoX XuXj | 2006 | Exp Oncol2006，28，3： | 1 |
| 11 | A novel approach tofinafloxacin hydrochloride显示文摘 | Jian H Zonghua Z Huoxing L | 2009 | Tetrahedron Letters2009，50，21： | 1 |
| 12 | Epi- genetic changes mediated by microRNA miR29 activate cyclooxygenase 2 and lambda-1 interferon production during viral infection显示文摘 | FangJ Hao Q LiuL LiY WuJ HuoX ZhuY | 2012 | J Virol2012，86，2： | 1 |
| 13 | Impact of Stagger Angle Nonuniformity on Turbine Aerodynamic Performance显示文摘The assembling error may lead to variation in stagger angles,which would affect the aerodynamic performance of the turbine.To investigate this underlying effect,two parallel numerical experiments on two turbines with the same profile,but uniform and nonuniform vane stagger angle respectively,were conducted in both steady and unsteady methods.The results indicate that certain changes in the detailed flow field of the turbine occur when the stagger angles are nonuniform,further,the blade loading distribution of the vane and rotor become markedly different from that in uniform vane stagger angle situation.Then these consequences caused by nonuniformity mentioned above enhance the unsteadiness of the flow,finally,the aerodynamic performance changes dramatically.It also shows that,compared with steady simulation,the unsteady numerical simulation is necessary in this investigation. | Weihao Zhang Zhengping Zou Shangneng Pan Huoxing Liu Huoxing Liu Wei Li | 2010 | Journal of Thermal Science2010，19，5： | 0 |
| 14 | Investigation of pressure wave behaviors in the rotational speed effects on a pressure-exchange wave rotor显示文摘A wave rotor is suitable for compact and efficient pressure-exchange between gas flows.This work measured the circumferential pressure distribution of the rotor/stator interfaces and utilized a CFD method to simulate the unsteady pressure waves.The experimental and CFD results showed some slopes in the circumferential pressure distributions,and the slopes indicated the traces of specific unsteady pressure waves.Such traces varied regularly if the rotational speed varied within a range from-11%to+11%off the baseline value,but they were seriously disturbed if the rotational speed varied by-45%from the baseline value.It verified that a pressure wave in a wave rotor tended to keep its pressure ratio and propagation velocity unchanged if the rotational speed varied by a small extent,and that the pressure wave could not keep its propagation patterns if the rotational speed varied by a large extent.Because of the pressure wave behaviors,the wave rotor demonstrated specific regulations of the rotational speed effects on its operational states. | Shining CHAN Huoxing LIU Hang SONG Fengchao LI Chongwen JIANG Zhenxun GAO | 2022 | Chinese Journal of Aeronautics2022，35，5： | 0 |
| 15 | Numerical Investigation of the Interaction between Mainstream and Tip Shroud Leakage Flow in a 2-Stage Low Pressure Turbine显示文摘The pressing demand for future advanced gas turbine requires to identify the losses in a turbine and to understand the physical mechanisms producing them. In low pressure turbines with shrouded blades, a large portion of these losses is generated by tip shroud leakage flow and associated interaction. For this reason, shroud leakage losses are generally grouped into the losses of leakage flow itself and the losses caused by the interaction between leakage flow and mainstream. In order to evaluate the influence of shroud leakage flow and related losses on turbine performance, computational investigations for a 2-stage low pressure turbine is presented and discussed in this paper. Three dimensional steady multistage calculations using mixing plane approach were performed including detailed tip shroud geometry. Results showed that turbines with shrouded blades have an obvious advantage over unshrouded ones in terms of aerodynamic performance. A loss mechanism breakdown analysis demonstrated that the leakage loss is the main contributor in the first stage while mixing loss dominates in the second stage. Due to the blade-to-blade pressure gradient, both inlet and exit cavity present non-uniform leakage injection and extraction. The flow in the exit cavity is filled with cavity vortex, leakage jet attached to the cavity wall and recirculation zone induced by main flow ingestion. Furthermore, radial gap and exit cavity size of tip shroud have a major effect on the yaw angle near the tip region in the main flow. Therefore, a full calculation of shroud leakage flow is necessary in turbine performance analysis and the shroud geometric features need to be considered during turbine design process. | JIA Wei LIU Huoxing | 2014 | Journal of Thermal Science2014，23，3： | 0 |
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