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A refined design method for precoolers with consideration of multi-parameter variations based on low-dimensional analysis

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Chinese Journal of Aeronautics 2022年第3期35卷 329-344页

作者： Hui LI zhengping zou Yumin LIU National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics School of Energy&Power Engineering Beihang University Beijing 100083China Advanced Jet Propulsion Creativity Center AEACBeijing 101304China Research Institute of Aero-Engine Beihang University Beijing 100083China International School Beihang University Beijing 100083China

The precooler is a distinctive component of precooled air-breathing engines but constitutes a challenge to conventional thermal design *** latter are based upon assumptions that often reveal to be limited for precooler *** this paper,a refined design method considering the variations of fluid thermophysical properties,flow area and thermal parameters distortion,was proposed to remediate their ***,the precooler was discretized into a fixed number of sub-microtubes based on a new discretization ***,in-house one-dimensional(1D)and two-dimensional(2D)segmented models were established for rapid thermal design and precooler rating with non-uniform airflow,*** heat transfer experimental studies of supercritical hydrocarbon fuel were performed to verify the Jackson correlation for precooler design and the in-house models were validated against the reported data from open *** this basis,the proposed method was employed for the design analysis of hydrocarbon fuel precoolers for precooled-Turbine Based Combined Cycle(TBCC)*** results show that the local performance of precoolers is intrinsically impacted by the aforementioned three *** the case study,the local heat transfer performance is drastically affected by coolant flow *** the circumferential temperature distortion of airflow is weakened by heat *** consideration of additional parameter variations,this novel method improves design accuracy and shortens the design time.

关键词： Compact heat exchangers Heat exchanger design Low-dimensional segmented model Non-uniform inflow Precooled engine Thermophysical properties variation

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Nonlinear uncertainty impact of geometric variations on aerodynamic performance of low-pressure turbine blades with ultra-high loading under extreme operational conditions

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Chinese Journal of Aeronautics 2024年第5期37卷 281-300页

作者： Xiaojing WANG zhengping zou Chao FU Pengcheng DU School of Energy and Power Engineering Beihang UniversityBeijing 100191China National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics Beihang UniversityBeijing 100191China Research Institute of Aero-Engine Beihang UniversityBeijing 100191China

Uncertainty impact of random geometric variations on the aerodynamic performance of low-pressure turbine blades is considerable,which is further amplified by the current ultra-high-lift design trend for weight ***,this uncertainty impact on ultra-highly loaded blades under extreme operational conditions near the margins with potential large-scale open separation is focused on in this *** is demonstrated that this impact is significant,unfavourable,and nonlinear,which is clearly severer under extreme *** addition to the overall attenuation and notable scattering of specific performance,the operational margins with open separation are also notably scattered with great risk of significant *** scattering and nonlinearity are dominated by the variations in leading-edge *** thinning of leading edge triggers local transition,enhancing downstream friction and reducing resistance to open separation,which is further exacerbated by operational ***,the opposite thickening yields less benefit,implying *** unfavourable impact highlights the need for robust aerodynamic design,where both a safer operational condition and a more robust blade are indispensable,i.e.,a compromise among performance,weight,and *** the necessary limitation of loading levels,a mid-loaded design is recommended to reduce adverse pressure gradients in both the leading edge and rear region of the suction side,which helps to decrease the susceptibility of the transition and open separation to random *** improvements can also be achieved by appropriately thickening the leading edge.

关键词： Ultra-highly loaded turbine blade Geometric variations Uncertainty analysis Operational margins Robust aerodynamic design Nonlinearity

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Uncertainty analysis of measured geometric variations in turbine blades and impact on aerodynamic performance

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Chinese Journal of Aeronautics 2023年第6期36卷 140-160页

作者： Xiaojing WANG Pengcheng DU Lichao YAO zhengping zou Fei ZENG School of Energy and Power Engineering Beihang UniversityBejing 100191China National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics Beihang UniversityBejing 100191China Research Institute of Aero-Engine Beihang UniversityBeijing 100191China AECC Hunan Aviation Powerplant Research Institute Zhuzhou 412002China

Inevitable geometric variations significantly affect the performance of turbines or even that of entire engines;thus,it is necessary to determine their actual characteristics and accurately estimate their impact on *** this study,based on 1781 measured profiles of a typical turbine blade,the statistical characteristics of the geometric variations and the uncertainty impact are analyzed,and some commonly used uncertainty modelling methods based on Principal-Component Analysis(PCA)are *** geometric variations are found to be evident,asymmetric,and non-uniform,and the non-normality of the random distributions is *** performance is notably affected,which is manifested as an overall offset,a notable scattering,and significant deterioration in several extreme ***,it is demonstrated that the PCA reconstruction model is effective in characterizing major uncertainty characteristics of the geometric variations and their impact on the performance with almost the first 10 PCA *** on a reasonable profile error and mean geometric deviation,the Gaussian assumption and stochasticprocess-based model are also found to be effective in predicting the mean values and standard deviations of the performance ***,they fail to predict the probability of some extreme cases with high ***,a Chi-square-based correction model is proposed to compensate for this *** present work can provide a useful reference for uncertainty analysis of the impact of geometric variations,and the corresponding uncertainty design of turbine blades.

关键词： Aerodynamic performance Measured geometric variations Principal-component analysis Turbine blade Uncertainty analysis

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Micromanufacturing technologies of compact heat exchangers for hypersonic precooled airbreathing propulsion: A review

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Chinese Journal of Aeronautics 2021年第2期34卷 79-103页

作者： Bao MENG Min WAN Rui ZHAO zhengping zou Huoxing LIU School of Mechanical Engineering and Automation Beihang UniversityBeijing 100191China School of Energy and Power Engineering Beihang UniversityBeijing 100191China

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.

关键词： Compact heat exchangers Hypersonic precooled engine Microchannels Micromanufacturing Microtube

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Effects of Squealer Geometry of Turbine Blade Tip on the Tip-Leakage Flow and Loss

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Journal of Thermal Science 2021年第4期30卷 1376-1387页

作者： ZENG Fei ZHANG Weihao WANG Yufan CAO Xia zou zhengping National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics School of Energy&Power EngineeringBeihang UniversityBeijing 100191China Research Institute of Aero-Engine Beihang UniversityBeijing 100191China

The effective control of the tip-leakage flow and loss is of great significance to improve the aerodynamic performance of the *** this paper,the evolution mechanism of tip-leakage flow in a transonic high pressure turbine with a squealer tip is investigated with numerical simulation *** impacts of squealer geometric,such as the inclined pressure side rim and squealer rim width,on the vortex structure in the gap and tip-leakage loss are *** results show that the scraping vortex inside the cavity plays the role of aero-labyrinth seal,and forms interlocking sealing labyrinth structure with the rims on both sides,which has an effective sealing effect on the tip-leakage *** inclined pressure side squealer rim inhibits the development of the pressure side squealer corner vortex,which is beneficial to expand the influence range of the scraping vortex and enhance the sealing effect on the tip-leakage *** increase of the suction side squealer rim width reduces the effective flow area at the gap exit,which is conducive to reduction of the tip-leakage flow rate and tip-leakage ***,the increase of the pressure side squealer rim width strengthens the pressure side squealer corner vortex and limits the development space of the scraping vortex,causing the adverse effects on the control of tip-leakage flow.

关键词： turbine squealer tip tip-leakage flow squealer width tip-leakage loss

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Conjugate heat transfer investigations of turbine vane based on transition models

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Chinese Journal of Aeronautics 2013年第4期26卷 890-897页

作者： Zhang Hongjun zou zhengping Li Yu Ye Jian Song Songhe National Key Laboratory of Science and Technology on Aero-Engines School of Energy and Power Engineering Beihang University Science College National University of Defence and Technology

The accurate simulation of boundary layer transition process plays a very important role in the prediction of turbine blade temperature field. Based on the Abu-Ghannam and Shaw （AGS） and c-Re h transition models, a 3D conjugate heat transfer solver is developed, where the fluid domain is discretized by multi-block structured grids, and the solid domain is discretized by unstructured grids. At the unmatched fluid/solid interface, the shape function interpolation method is adopted to ensure the conservation of the interfacial heat flux. Then the shear stress transport （SST） model, SST ＆ AGS model and SST ＆ c-Re h model are used to investigate the flow and heat transfer characteristics of Mark II turbine vane. The results indicate that compared with the full turbulence model （SST model）, the transition models could improve the prediction accuracy of temperature and heat transfer coefficient at the laminar zone near the blade leading edge. Compared with the AGS transition model, the c-Re h model could predict the transition onset location induced by shock/boundary layer interaction more accurately, and the prediction accuracy of temperature field could be greatly improved.

关键词： AGS and c-Re h transition models Conjugate heat transfer Flow and heat transfer char- acteristics Temperature prediction accuracy Transition flow

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A novel multi-fidelity coupled simulation method for flow systems

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Chinese Journal of Aeronautics 2013年第4期26卷 868-875页

作者： Wang Peng Zheng Yun zou zhengping Qi Lei Zhou Zhixiang National Key Laboratory of Science & Technology on Aero-Engine Aero-thermodynamics School of Energy and Power Engineering Beihang University Aeroengine Numerical Simulation Research Center School of Energy and Power Engineering Beihang University Chinese Aviation Powerplant Research Institute

For the numerical simulation of flow systems with various complex components, the traditional one-dimensional （1D） network method has its comparative advantage in time consuming and the CFD method has its absolute advantage in the detailed flow capturing. The proper coupling of the advantages of different dimensional methods can strike balance well between time cost and accuracy and then significantly decrease the whole design cycle for the flow systems in modern machines. A novel multi-fidelity coupled simulation method with numerical zooming is developed for flow systems. This method focuses on the integration of one-, two-and three-dimensional codes for various components. Coupled iterative process for the different dimensional simulation cycles of sub-systems is performed until the concerned flow variables of the whole system achieve convergence. Numerical zooming is employed to update boundary data of components with different dimen-sionalities. Based on this method, a highly automatic, multi-discipline computing environment with integrated zooming is developed. The numerical results of Y-Junction and the air system of a jet engine are presented to verify the solution method. They indicate that this type of multi-fidelity simulationmethod can greatly improve the prediction capability for the flow systems.

关键词： Complex flow system Coupling Jet engine Multi-fidelity Zooming

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An experimental method for squealer tip flow field considering relative casing motion

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Chinese Journal of Aeronautics 2020年第7期33卷 1942-1952页

作者： Fei ZENG Jinlin DU Lin HUANG Liming XUAN Qiang ZHAO zhengping zou National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics School of Energy&Power EngineeringBeihang UniversityBeijing 100083China Collaborative Innovation Center for Advanced Aero-Engine School of Energy&Power EngineeringBeihang UniversityBeijing 100083China

Squealer tip is widely used in turbines to reduce tip leakage *** typical turbine environment,the squealer tip leakage flow is affected by multiple factors such as the relative casing motion and the wide range of variable incidence *** development of experimental methods which can accurately model the real turbine environment and influencing factors is of great significance to study the squealer tip leakage flow *** the present paper,a low-speed turbine cascade test facility which can model the relative casing motion and wide range of variable incidence angles(-25°to 55°)is *** on the similarity criteria,a high-low speed similarity transformation method of the turbine cascade is established by considering the thickness of the turbine blade.A combined testing method of Particle Image Velocimetry(PIV)and local pressure measurement is proposed to obtain the complex flow structures within the tip *** results show that the experimental method can successfully model the relative casing motion and the wide range of variable incidence *** low-speed cascade obtained by the similarity transformation can model the high-speed flow *** measurement technique developed can obtain the complex flow field and successfully capture the scraping vortex within the squealer tip.

关键词： Blade tip/casing gap measurement Particle Image Velocimetry(PIV) Relative casing motion Similarity transformation Turbine Wide range of variable incidence angles

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Insights into thermodynamic performance of a hypersonic precooled air-breathing engine with a complicated multi-branch closed cycle

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Chinese Journal of Aeronautics 2024年第8期37卷 106-123页

作者： Yifan WANG zhengping zou Pengcheng DU Lichao YAO Huoxing LIU Yusen XU Research Institute of Aero-Engine Beihang UniversityBeijing 102206China National Key Laboratory of Science and Technology on Aero-Engine and Aero-Thermodynamics Beihang UniversityBeijing 102206China

An advanced precooled airbreathing engine with a closed Brayton cycle is a promising solution for high-speed propulsion,of which the Synergetic Air Breathing Rocket Engine(SABRE)is a representative *** performance of the latest SABRE-4 cycle was analyzed in this ***,a relatively complete engine performance model that considers the characteristics of turbomachinery and heat exchangers was ***,Sobol’global sensitivity analysis of key performance parameters was carried out to identify the most influential design *** specific impulses under different target specific thrusts were obtained by particle swarm optimization,of which the thermodynamic parameters corresponding to a specific thrust of 1.12 kN·s·kg^(-1)and a specific impulse of 3163 s were chosen as the design *** different control laws were analyzed in contrast,and the charge control method had the strongest ability of thrust regulation as well as maintaining a favorable specific impulse ***,working characteristics under the charge control and over a typical flight envelope were calculated,in which the average value of the maximum specific impulse was as high as 5315 *** study would help to deepen the understanding of SABRE-4 thermodynamic characteristics and other precooled airbreathing engine cycles with similar layouts.

关键词： Hypersonic Precooled airbreathing engine Thermodynamic cycle Control law Working characteristics

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Impact of Stagger Angle Nonuniformity on Turbine Aerodynamic Performance

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Journal of Thermal Science 2010年第5期19卷 465-472页

作者： Weihao Zhang zhengping zou Shangneng Pan Huoxing Liu Huoxing Liu Wei Li National Key Laboratory of Science and Technology on Aero-Engines School of Jet Propulsion Beihang University Beijing 100191 China Aeroengine Numerical Simulation Research Center B eihang University Beijing 100191 China Chinese Aviation Powerplant Research Institute Zhuzhou 412002 China

The assembling error may lead to variation in stagger angles,which would affect the aerodynamic performance of the *** 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 *** 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 *** these consequences caused by nonuniformity mentioned above enhance the unsteadiness of the flow,finally,the aerodynamic performance changes *** also shows that,compared with steady simulation,the unsteady numerical simulation is necessary in this investigation.

关键词： assembling error stagger angle nonuniformity turbine aerodynamic performance

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