Experimental and numerical investigation on total pressure distortion generated by a rectangular movable flat baffle

被引:4
作者
Tu, Baofeng [1 ]
Xuan, Bin [1 ]
Li, Chuanpeng [1 ]
Zhang, Xinyu [1 ]
Hu, Jun [1 ]
机构
[1] Nanjing Univ Aeronaut & Astronaut, Coll Energy & Power Engn, 29 Yudao St, Nanjing 210016, Peoples R China
关键词
Total pressure distortion; flat baffle; APU; DES; experiment;
D O I
10.1177/1687814021994397
中图分类号
O414.1 [热力学];
学科分类号
摘要
A distortion generator equipped with a motor-activated movable flat baffle was installed just upstream of a rectangular plenum entrance to investigate the effects of inlet total pressure distortion on the stability and performance of an auxiliary power unit (APU). Experiments and numerical simulations on a direct connect scale inlet model of the APU were carried out to obtain a quantitative relationship between the insertion depth of the flat baffle in the flow stream and the total pressure distortion intensity and region. In the experiments, the blocking coefficient and total pressure distortion coefficient were controlled by adjusting the insertion depth of the flat baffle and the mass flow. In the simulations, detailed flow field was analyzed based on the detached-eddy simulation (DES) method. The results show that the pressure distribution of the distorted flow on the aerodynamic interface plane (AIP) can be divided into a high-pressure region, a transition region, and a low-pressure region. The area affected by the distorted flow was larger than the inserting area of the flat baffle. That area was more related to the relative blocking coefficient, and less affected by the mass flow. The total pressure distortion coefficient had a linear relationship with the mass flow rate and is positively correlated with the relative blocking coefficient. As the relative blocking coefficient increased to a certain value, an exponential growth in the total pressure distortion coefficient occurred, and consequently, the flow field distortion was intensified. In the flow field, a pair of corner vortices were formed at the corner between the flat baffle and the bottom wall of the inlet pipe, and a large separation zone was formed behind the flat baffle and exhibits certain unsteady characteristics.
引用
收藏
页数:11
相关论文
共 22 条
  • [1] Beale D., 2002, 22 AIAA AER MEAS TEC
  • [2] Bion J., 1984, 20 JOIN PROP C CINC
  • [3] Cousins W.T., 2004, P ASME TURBO EXPO 20, V2, P305
  • [4] An argument for enhancement of the current inlet distortion ground test practice for aircraft gas turbine engines
    Davis, M
    Hale, A
    Beale, D
    [J]. JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 2002, 124 (02): : 235 - 241
  • [5] Gu W., 2006, GAS TURBINE EXP RES, V19, P54
  • [6] Detached-Eddy Simulation of Rotating Stall Inception for a Full-Annulus Transonic Rotor
    Im, Hongsik
    Chen, Xiang-Ying
    Zha, Gecheng
    [J]. JOURNAL OF PROPULSION AND POWER, 2012, 28 (04) : 782 - 798
  • [7] Effects of inlet flow distortion on the performance of aircraft gas turbines
    Kurzke, Joachim
    [J]. JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME, 2008, 130 (04):
  • [8] Lee K., 2010, 27 AIAA AER MEAS TEC, P1
  • [9] Li Liang, 2009, Journal of Aerospace Power, V24, P925
  • [10] DDES Analysis of the Wake Vortex Related Unsteadiness and Losses in the Environment of a High-Pressure Turbine Stage
    Lin, Dun
    Su, Xinrong
    Yuan, Xin
    [J]. JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 2018, 140 (04):