AVIC Aerodynamic Research Institute

Shenyang, China

AVIC Aerodynamic Research Institute

Shenyang, China
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Tang H.N.,Shenyang University of Technology | Yao H.,AVIC Aerodynamic Research Institute | Wang S.J.,Shenyang University of Technology | Meng X.S.,Shenyang University of Technology | And 2 more authors.
IOP Conference Series: Materials Science and Engineering | Year: 2017

The influence of labyrinth seal structure on leakage behaviour in a reciprocating compressor was addressed in this paper. The effects of the main labyrinth seal parameters, such as tooth angle, sealing clearance, and cavity depth, were compared using FLUENT software and iterative calculation results. Simulations of the sealing process with the influence of internal structure size of labyrinth seal performance in different structures were conducted to explore the characteristics of fluid flow. By comparing the simulations of leakage of fluid- structure interaction and experience formula calculations, the results revealed the validity of the fluid-structure interaction analysis method. The CFD analysis method for fluid-structure coupling was adopted to verify the theory of labyrinth seals and for the design of a labyrinth structure.

Zhao Z.,AVIC Aerodynamic Research Institute | Ma X.,AVIC Aerodynamic Research Institute | Du Y.,AVIC Aerodynamic Research Institute
Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica | Year: 2016

A Bump inlet flow control is researched in this paper. Numerical simulation of the inner and outer flow fields of the inlet are focused on its aerodynamic and flow field properties under the condition of supersonic inflow with Mach number of 1.60. Based on this result, flow control devices, which are spoiler for airframe ridge vortex and inlet micro-mass suction/blow or jet control devices, are designed respectively to improve the inlet total pressure recovery and decrease the flow distortion with the inflow Mach number of 1.60 while inlet and engine match point. The performance of control devices are numerically simulated subsequently to provide database for the analysis of each flow control device's performance and its flow control mechanism. The results reveal that the spoiler is of weak performance at negative angles of attack with the inflow Mach number of 1.60; however, the inlet micro-mass suction/blow or jets control method is effective to control inlet total pressure recovery. This study provides certain reference for the engineering development and flow control strategies of Bump inlet used in stealth fighter. © 2016, The Editorial Board of ACTA AERODYNAMICA SINICA. All right reserved.

Zhang P.,Northwestern Polytechnical University | Liu B.,Northwestern Polytechnical University | Wang L.,AVIC Aerodynamic Research Institute | Shi L.,Northwestern Polytechnical University | Mao X.-C.,Northwestern Polytechnical University
Tuijin Jishu/Journal of Propulsion Technology | Year: 2015

In order to further increase the pressure ratio of axial compressor stage, with the method of boundary layer suction, a set of system including S2 through-flow calculation, inviscid inverse design of aspirated airfoil, scheme optimization of boundary layer suction, validation of three-dimension time-averaged flow field calculation was preliminarily established. Research results show that depending on this system, an aspirated compressor which achieves a total pressure ratio of 3.51, an isentropic efficiency of 86.82% and a load factor of more than 0.6 was designed using only 1.7% relative suction mass flow, and validated successfully by three-dimension time-averaged flow field based on the nonlinear harmonic (NLH). As suction basically eliminates wake deficit of upstream rotor, interstage interference is small, and the difference of peak efficiency and total pressure ratio between time-averaged and steady characteristic line is 0.12% and 0.003, respectively. ©, 2015, Editorial Office of Journal of Propulsion Technology. All right reserved.

Zhao Z.-S.,AVIC Aerodynamic Research Institute | Dong J.,AVIC Aerodynamic Research Institute | Guo C.-P.,AVIC Aerodynamic Research Institute
Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica | Year: 2011

The flow field of a dual S inlet with vortex generators is simulated based on numerical vortex generator model. Five parameters which have effect on total pressure recovery and flow field distortion are considered. By using Design-of-Experiment (DOE) theory, twenty-seven vortex generator configurations installed in the inlet are simulated. Based on analysis and optimization of the results, the best vortex generator configuration is presented. The results of this study can provide technical references for optimization design of parameters of dual S passive control devices.

Zhang Y.,Beihang University | Zhang Y.,AVIC Aerodynamic Research Institute | Chen L.,CAS Institute of Chemistry | Shang J.,AVIC Aerodynamic Research Institute | And 6 more authors.
Advanced Materials Research | Year: 2011

As a new optical pressure sensor technique, Pressure Sensitive Paint (PSP) is one of the important techn iques for model surface pressure m easurement in wind tunnel tests. With the help of PSP, it is possible to do pressure measurement on compl icated or special model surface , which is usually difficult to be measured by pressure taps. Since PSP technique being introduced into China from TsAGI (Russia) , AVIC ARI has investigated two-component PSP technique in high-speed wind tunnel in cooperati on with ICCAS China. This report present s the principle of PSP technique, test control system development and the test result comparison s between PSP technique with two-component pressure sensitive paint FOP-2 and classic tap measurement on wing surface of an airplane model. The results showed that the two-component pressure sensitive paint has better performance and can be used for model pressure measurement. © (2011) Trans Tech Publications.

Shi L.,Northwestern Polytechnical University | Liu B.,Northwestern Polytechnical University | Wang L.,AVIC Aerodynamic Research Institute | Wu X.,Northwestern Polytechnical University | Cao Z.,Northwestern Polytechnical University
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2014

Boundary layer suction and blade optimization are employed in the redesign of a dual-stage counter-rotating compressor with numerical simulation. Further experimental research will be carried out according to the numerical results. At near stall point, there is serious flow separation at the tip region of the original outlet guide vane (OGV). Airfoil optimization makes smooth acceleration at the leading edge, and decreases the recirculation zone in the blade passage. Up to 70% spanwise of OGV, total pressure loss coefficient has a 38.4% drop in average. Isentropic efficiency of the compressor is improved by 0.3%. An axisymmetric suction slot located at 66% chordwise of Rotor 2 (R2) tip region with 1 mm width is designed at the shroud case. 1% comparative mass flow at near stall point can optimize the loading level of R2 tip region, bringing a 10% improvement in average on R2 isentropic efficiency in higher spanwise from 65%. These result in a positive effect on the flow condition of the OGV: corner separation is limited to a smaller region, total pressure loss coefficient has a 25% drop in average in the region up to 85% spanwise, and the isentropic efficiency of the compressor is further improved by 0.5%. ©, 2014, AAAS Press of Chinese Society of Aeronautics and Astronautics. All right reserved.

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