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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. Source

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. Source

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. Source

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. Source

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