On the effect of geometry of w-wave trenches on film cooling performance of gas turbine blades

被引:1
|
作者
Bahambari, Alireza Bakhshinejad [1 ]
Kayhani, Mohammad Hassan [1 ]
Norouzi, Mahmood [1 ]
机构
[1] Shahrood Univ Technol, Fac Mech Engn, Shahrood, Iran
关键词
Film cooling; counter-rotating vortices; gas turbine blades; blowing ratio; numerical simulation; HEAT-TRANSFER COEFFICIENT; HOLES; FLOW; DENSITY; JETS; WAKE;
D O I
10.1177/09576509211008277
中图分类号
O414.1 [热力学];
学科分类号
摘要
In the present study, three types of w-wave trenches with different amplitude configurations are compared with transverse trench (TT), and the use of variable radius fillet (VRF) on downstream lips at different blowing ratio is numerically investigated to measure heat transfer coefficient, and cooling effectiveness. The numerical results are obtained by three-dimensional Reynolds average Navier-Stokes equations (RANS) while employing shear stress transport turbulence models, which are validated by comparing with experimental data. The trench width is kept constant in all cases, yet the three different amplitudes and variable fillet radiuses offered a variety of designs in trench film cooling. The results showed that w-wave trenches impressively improved film cooling effectiveness over the transverse trench, and utilizing fillets at downstream lips of the trench caused significant enhancement on both lateral averaged and centerline cooling performance. Due to the w-wave trench configuration, anti-counter-rotating vortices responsible for pushing coolant film toward the near-wall were formed throughout of downstream wall of the trench, and the cooling flow thus had a more uniform structure. The heat transfer coefficient distributions of filleted w-wave trenches are observed to be more uniform than simple w-wave and transverse trench under all blowing ratio conditions. Moreover, enlargement of the fillet radius in Cases 2 and 3 yielded to the growth of centerline coolant flow, which in turn resulted in the improvement of film cooling effectiveness at all blowing ratios.
引用
收藏
页码:1595 / 1618
页数:24
相关论文
共 50 条
  • [41] INVESTIGATING EFFECTIVENESS OF AIR COOLING OF GAS TURBINE BLADES
    LOKAI, VI
    THERMAL ENGINEERING, 1970, 17 (07) : 69 - &
  • [42] The transpiration cooling for blades of high temperatures gas turbine
    Polezhaev, J
    ENERGY CONVERSION AND MANAGEMENT, 1997, 38 (10-13) : 1123 - 1133
  • [43] MODEL TESTS ON COOLING OF GAS TURBINE BLADES.
    Hosenfeld, Hans Georg
    Schwerdtner, Otto Adalbert v.
    Siemens Forschungs- und Entwicklungsberichte/Siemens Research and Development Reports, 1979, 8 (05): : 178 - 282
  • [45] HEAT-TRANSFER MEASUREMENT TECHNIQUES OF FILM-COOLING IN GAS-TURBINE BLADES
    AMMARI, H
    INTERNATIONAL COMMUNICATIONS IN HEAT AND MASS TRANSFER, 1994, 21 (05) : 695 - 706
  • [46] Aerodynamic performance effects of leading-edge geometry in gas-turbine blades
    Hamakhan, I. A.
    Korakianitis, T.
    APPLIED ENERGY, 2010, 87 (05) : 1591 - 1601
  • [47] Enhancement of combined cycle performance using transpiration cooling of gas turbine blades with steam
    Sanjay Kumar
    Onkar Singh
    Journal of Mechanical Science and Technology, 2014, 28 : 2429 - 2437
  • [48] Enhancement of combined cycle performance using transpiration cooling of gas turbine blades with steam
    Kumar, Sanjay
    Singh, Onkar
    JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY, 2014, 28 (06) : 2429 - 2437
  • [49] EFFECT OF INTERNAL CROSSFLOW ON DOUBLE JET FILM COOLING HOLES OF HELIUM TURBINE BLADES
    Sun, Xiao-kai
    Peng, Wei
    Wang, Jie
    Jiang, Pei-xue
    PROCEEDINGS OF THE 25TH INTERNATIONAL CONFERENCE ON NUCLEAR ENGINEERING, 2017, VOL 6, 2017,
  • [50] Effect of film hole geometry and blowing ratio on film cooling performance
    Cao, Nan
    Li, Xue
    Wu, Zeyu
    Luo, Xiang
    APPLIED THERMAL ENGINEERING, 2020, 165