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Journal of Thermal Science 2024年第5期33卷 1867-1882页

作者： LIU Tantao GAO Limin LI Ruiyu School of Power and Energy Northwestern Polytechnical UniversityXi'an 710012China School of Aerospace Engineering Xi'an Jiaotong UniversityXi'an 710049China

For complex flows in compressors containing flow separations and adverse pressure gradients,the numerical simulation results based on Reynolds-averaged Navier-Stokes(RANS)models often deviate from experimental measurements more or *** improve the prediction accuracy and reduce the difference between the RANS prediction results and experimental measurements,an experimental data-driven flow field prediction method based on deep learning and l_(1)regularization is proposed and applied to a compressor cascade flow *** inlet boundary conditions and turbulence model parameters are calibrated to obtain the high-fidelity flow *** Saplart-Allmaras and SST turbulence models are used independently for mutual *** contributions of key modified parameters are also analyzed via sensitivity *** results show that the prediction error can be reduced by nearly 70%based on the proposed *** flow fields predicted by the two calibrated turbulence models are almost the same and nearly independent of the turbulence *** corrections of the inlet boundary conditions reduce the error in the first half of the *** turbulence model calibrations fix the overprediction of flow separation on the suction surface near the tail edge.

关键词： experimental data-driven compressor cascade deep learning l_(1)regularization

Numerical Study of Dual Sweeping Jet Actuators for Corner Separation Control in compressor cascade

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Journal of Thermal Science 2021年第1期30卷 201-209页

作者： MENG Qinghe DU Xin CHEN Shaowen WANG Songtao School of Energy Science and Engineering Harbin Institute of TechnologyHarbin 150001China

Unsteady behaviors are important issues in flow control of *** excitation or suction is widely investigated in compressor *** paper presents a discussion on the unsteady flow control realized by dual sweeping jet actuator(SJA)located on the blade suction *** unsteady numerical simulations were utilized to study the effect of applying dual SJAs on controlling the corner *** the numerical results,the following conclusions could be drawn with current compressor cascade.A maximum total pressure loss coefficient reduction of 6.8%was *** analysis of the flow field pointed out that the regulation mechanisms of the corner separation were different with each *** SJA ahead achieved an interruption of the suction side boundary layer development and the rear SJA enhanced the interaction and entrainment between the excitation stream and the secondary ***,the different unsteadiness structures of the flow field frequency spectrum compared with single SJA cases were *** first peak frequency corresponded to the difference of the two SJAs and the rest frequencies could be regulated to a base frequency and its harmonic frequencies.

关键词： sweeping jet actuator compressor cascade active flow control corner separation

Effect of Winglet Geometry Arrangement and Incidence on Tip Clearance Control in a compressor cascade

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Journal of Thermal Science 2014年第4期23卷 381-390页

作者： HAN Shaobing ZHONG Jingjun LU Huawei KAN Xiaoxu YANG Ling Marine Engineering College Dalian Maritime University

An experimental study is conducted to investigate the influences of blade tip winglet on the flow field of a compressor cascade. The tests are performed in a low speed linear cascade with stationary endwall, with three blade tip configurations, including the baseline tip, the suction-side winglet tip and the pressure-side winglet tip. The fiowfield downstream of the cascade is measured using five-hole probe, from which the three-dimensional velocity field, vorticity field and pressure field are obtained. Static pressure measurements are made on the endwall above the blade row using pressure taps embedded in the plywood endwall. All measurements are made at both design and off-design conditions for tip clearance level of about 2 percent of the blade chord. The results revealed the incidence variation significantly affects the secondary flow and the associated loss field downstream of the cascade, where the tip leakage vortex and passage vortex exist as the major contributors on the field. The winglet geometry arrangements can change the trajectory of the tip leakage vortex. The suction-side winglet tip blade provides a lower overall total pressure loss coefficient when compared to the baseline tip blade and pressure-side winglet tip blade at all incidence angles.

关键词： blade tip winglet compressor cascade incidence tip clearance flow

Boundary layer separation control on a highly-loaded,low-solidity compressor cascade

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Journal of Thermal Science 2010年第2期19卷 97-104页

作者： Zhou Yang,Liu Huo-xing,Zou Zheng-ping and Ye Jian National Key Lab.on Aero-Engines,Aero-Engines Simulation Research Center,Beijing Univ.of Aero.& Astro.,Beijing 100083 National Key Lab. on Aero-Engines Aero-Engines Simulation Research Center Beijing Univ. of Aero. & Astro. Beijing China

Separated flow can be effectively controlled through the management of blade boundary layer *** simulations on a highly-loaded,low-solidity compressor cascade indicate that combined blowing and suction flow control technique can significantly improve cascade performance,especially in increasing the cascade loading and static pressure ratio as well as decreasing the loss ***,it is more effective to improve cascade performance by blowing near leading edge on suction surface than suction near trailing *** the locations and flow rates of blowing and suction are major impact factors of this method to cascade *** to the baseline,the static pressure ratio increases by 15% and loss coefficient decreases by 80%,with a blowing fraction of 1.7% and a suction fraction of 1.38% of the inlet mass flow.

关键词： combined blowing and suction flow control compressor cascade boundary layer separated flow

Reduced order model for unsteady aerodynamic performance of compressor cascade based on recursive RBF

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Chinese Journal of Aeronautics 2021年第4期34卷 341-351页

作者： Jiawei HU Hanru LIU Yan'gang WANG Weixiong CHEN Yan MA School of Power and Energy Northwestern Polytechnical UniversityXi'an 710072China Yangtze River Delta Research Institute Northwestern Polytechnical UniversityTaicang 215400China

Based on Recursive Radial Basis Function(RRBF)neural network,the Reduced Order Model(ROM)of compressor cascade was established to meet the urgent demand of highly efficient prediction of unsteady aerodynamics performance of *** novel ROM called ASA-RRBF model based on Adaptive Simulated Annealing(ASA)algorithm was developed to enhance the generalization ability of the unsteady *** ROM was verified by predicting the unsteady aerodynamics performance of a highly-loaded compressor *** results show that the RRBF model has higher accuracy in identification of the dimensionless total pressure and dimensionless static pressure of compressor cascade under nonlinear and unsteady conditions,and the model behaves higher stability and computational ***,for the strong nonlinear characteristics of aerodynamic parameters,the RRBF model presents lower ***,the RRBF model predicts with a large error in the identification of aerodynamic parameters under linear and unsteady *** ASA-RRBF,by introducing a small-amplitude and highfrequency sinusoidal signal as validation sample,the width of the basis function of the RRBF model is optimized to improve the generalization ability of the ROM under linear unsteady ***,this model improves the predicting accuracy of dimensionless static pressure which has strong nonlinear *** ASA-RRBF model has higher prediction accuracy than RRBF model without significantly increasing the total time *** novel model can predict the linear hysteresis of dimensionless static pressure happened in the harmonic condition,but it cannot accurately predict the beat frequency of dimensionless total pressure.

关键词： compressor cascade Neural network Recursive radial basis function Reduced order model Unsteady flow

Influences of a Kind of Groove-blade on the Flow Field in a compressor cascade

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Journal of Thermal Science 2006年第3期15卷 193-199页

作者： Hongwei MA Wuying YAN Qiao TIAN School of Jet Propulsion Beijing University of Aeronautics and Astronautics Beijing 100083 ChinaNational Key Laboratory on Aero-Engines Beijing 100083 China

This paper presents an experimental investigation of effects of a kind of streamwise-grooved blades on the flowfield in a compressor *** flow field downstream the cascade and the boundary layer on the suctionsurface were measured using a mini 5-hole pressure probe at different incidence *** flow field in thegroove cascade was compared with that in the smooth *** measurement results indicate that:(1)thegroove surface can restrain the development of the boundary layer on the suction surface;(2)the grooves canrestrain the radial migration of the low-energy fluids in the boundary layer on the suction surface;(3)the grooveblades can reduce total pressure loss and flow blockage in the cascade at the incidence angles of 0°,5°and 8°;(4)the maximum benefit of 8.6% loss reduction was obtained at the incidence angle of 5° while negative benefit of-3.0% loss reduction occurred at the incidence angle of-5°.

关键词： groove blade compressor cascade secondary flow flow loss boundary layer

Effects of Airfoil-probe Tubes on the Flow Field of a compressor cascade

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Journal of Thermal Science 2017年第4期26卷 321-330页

作者： MA Hongwei JIN Chao ZHAO Lianpeng MA Rong National Key Laboratory of Science and Technology on Aero-Engines Collaborative Innovation Center of Advanced Aero-EngineSchool of Energy&Power EngineeringBeihang UniversityBeijing100191China

To explore the effects of airfoil-probe tubes and its installment position on the flow field of the compressor cas- cade, and find out the mechanism that how the airfoil-probes affect the aerodynamic characteristics of the com- pressor cascade, this paper performed both numerical and experimcntal works on the same compressor cascade. The experiment mainly focused on the cases of low Mach number （Ma = 0.1）, and cases with different Mach numbers （0.1, 0.3, 0.7） and different incidence angles （-5, 0, 5） are investigated by the numerical method. The case without the airfoil-probe tube was referenced as the baseline, and other three cases with the airfoil-probe tubes installed in different chordwise positions O0%, 50%, 70% of the chord length） were studied. The diameter of the airfoil-probe tube is 3ram, which is configured as 300% amplification of some particular airfoil-probe ac- cording to the geometrical similarity principle. The results show that the airfoil-probe tubes have a negative in- fluenc~ on the flow capacity of the cascade at all investigation points. The separations and the large scale stream- wise vortices that induced by the airfoil-probe tube on the pressure side cause most the losses at the high Mach number. The influence of the airfoil-probe tube on the flow field in the vicinity of the pressure side surface is lo- cal separation at the low Mach number. The airfoil-probe tubes also have a clearly effect on the leakage flow. It decreases the mass flow of the leakage flow and weakens the intensity of the leakage vortex, but enlarges the in- fluence area. The total pressure loss of the case that the tube is installed at the half chordwise position is generally lower than other cases especially at the high Mach number, it can even decrease the losses compared with the ba- sic case.

关键词： airfoil-probe compressor cascade installment position 5-hole probe

Experimental Study of Effects of One Kind of Tangentially Non-uniform Tip Clearance on the Flow Field at an Exit of a compressor cascade Passage

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Journal of Thermal Science 2010年第1期19卷 7-13页

作者： Hongwei MA Jinghui ZHANG Jun ZHANG School of Jet Propulsion Beihang University Beijing 100191 China National Key Laboratory of Science and Technology on Aero-Engines Beijing 100191 China

This paper presents an experimental investigation of effects of one kind of tangentially non-uniform tip clearance on the flow field at an exit of a compressor cascade *** tests were performed in a low-speed large-scale cascade with the uniform tip clearance and the non-uniform *** three-dimensional flow field was measured at the exit at three incidence angles of 0°,5°,and 8° using a mini five-hole pressure *** measurement results show that the non-uniform tip clearance can moderate the leakage flow and blow down more low-energy fluids at the tip corner and decrease the accumulation of low-energy fluids which cause the flow blockage in the blade *** the meantime,the non-uniform clearance can weaken the tangential migration of the low-energy fluids in the endwall boundary layer and reduce the secondary loss and the flow blockage in the tip region.

关键词： compressor cascade clearance leakage flow secondary flow vortex

Effect of tip geometry and tip clearance on aerodynamic performance of a linear compressor cascade

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Chinese Journal of Aeronautics 2013年第3期26卷 583-593页

作者： Zhong Jingjun Han Shaobing Lu Huawei Kan Xiaoxu Marine Engineering College Dalian Maritime University

The tip leakage flow between a blade and a casing wall has a strong impact on compressor pressure rise capability, efficiency, and stability. Consequently, there is a strong motivation to look for means to minimize its impact on performance. This paper presents the potential of passive tip leakage flow control to increase the aerodynamic performance of highly loaded compressor blades. Experimental investigations on a linear compressor cascade equipped with blade winglets mounted to the blade tips have been carried out. Results for a variation of the tip clearance and the winglet geometry are presented. Current results indicate that the use of proper tip winglets in a compressor cascade can positively affect the local aerodynamic field by weakening the tip leakage vortex. Results also show that the suction-side winglets are aerodynamically superior to the pressure-side or combined winglets. The suction-side winglets are capable of reducing the exit total pressure loss associated with the tip leakage flow and the passage secondary flow to a significant degree.

关键词： compressor cascade Experimental investigation Tip clearance Tip geometry Tip leakage vortex

Application of shear-sensitive liquid crystal coating to visualization of transition and reattachment in compressor cascade

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Chinese Journal of Aeronautics 2018年第11期31卷 2073-2079页

作者： Ruiyu LI Limin GAO Shuai ZHANG Yongzeng LI Tianyu GAO School of Power and Energy Northwestern Polytechnical UniversityXi'an 710072China Collaborative Innovation Center of Advanced Aero-Engine Beijing 100191China Aero-Engine Flight Test Chinese Flight Test EstablishmentXi'an 710089China

The present paper aims at introducing Shear-Sensitive Liquid Crystal Coating(SSLCC)technology into compressor cascade measurement for the first time and serves as a basis for better understanding of the influence from the boundary layers. Optical path layout, which is the most significant difficulty in internal flow field measurement, will be solved in this paper by selfdesigned image acquisition device. Massive experiments with different Mach number and incidence are conducted at a continuous subsonic cascade wind tunnel to capture the boundary layer phenomenon. Image processing methods, such as Three-Dimensional(3-D) reconstruction and Hue conversion, are used to improve the accuracy for transition position detection. The analysis of the color-images indicates that complex flow phenomena including transition, flow separation,and reattachment are captured successfully, and the effect of Mach number and incidence on the boundary layer flow is also discussed. The results show that: the Mach number has a significant effect on transition position; the incidence has little effect on transition position, but it has a great impact on the transition distance and leading-edge separation; influenced by the end-walls, the reattachment occurs in advance under positive angle of attack conditions.

关键词： compressor cascade Flow visualization Leading edge separation Shear-sensitive liquid crystal coating Transition