ROTATING EFFECT ON TRANSONIC SQUEALER TIP COOLING PERFORMANCE

被引：0
|
作者：
Zhu, D. [1 ]
Lu, S. [2 ]
Ma, H. [1 ]
Zhang, Q. [3 ]
Teng, J. [2 ]
机构：
[1] Univ Michigan Shanghai Jiao Tong Univ Joint Inst, Shanghai, Peoples R China
[2] Shanghai Jiao Tong Univ, Sch Aeronaut & Astronaut, Shanghai, Peoples R China
[3] City Univ London, London, England
来源：
PROCEEDINGS OF THE ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2017, VOL 5A | 2017年
基金：
美国国家科学基金会;
关键词：
LEADING-EDGE REGION; GAS-TURBINE BLADE; ROWS;
D O I：
暂无
中图分类号：
O414.1 [热力学];
学科分类号：
摘要：
The aerothermal behavior of turbine blade tip has been studied for decades, mostly using stationary linear cascade. The blade rotation effect still remains unclear to the tip research community. This paper investigates two squealer tip cooling configurations with the effect of relative casing movement. The numerical method was validated against thermal measurement obtained in a transonic wind tunnel. Further analysis is presented for cases with relative casing motion. Dramatic changes in aerodynamics and heat transfer were observed, mostly due to the strong interactions between the over tip leakage flow and the coolant injection. The need to consider the rotating effect into future experimental validation is highlighted.
引用
收藏
页数：10
相关论文
共 50 条
  • [21] Numerical analysis of the aerodynamic performance & heat transfer of a transonic turbine with a partial squealer tip
    Kim, Jae Hoon
    Lee, Seung Yeob
    Chung, Jin Taek
    APPLIED THERMAL ENGINEERING, 2019, 152 : 878 - 889
  • [22] Influence of incidence angle and squealer tip cutback on the aerothermal performance of a transonic turbine blade
    Jiang, Shoumin
    Jiang, Hongmei
    Tao, Zhi
    Lu, Shaopeng
    Yan, Yifei
    Song, Liming
    INTERNATIONAL COMMUNICATIONS IN HEAT AND MASS TRANSFER, 2024, 155
  • [23] Uncertainty quantification of aerothermal performance of squealer tip with film cooling structure
    Huang, Ming
    Zhang, Kaiyuan
    Li, Zhigang
    Li, Jun
    Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica, 2024, 45 (19):
  • [24] Impact of Cooling Injection on the Transonic Over-Tip Leakage Flow and Squealer Aerothermal Design Optimization
    Wang, Z.
    Zhang, Q.
    Liu, Y.
    He, L.
    JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME, 2015, 137 (06):
  • [25] IMPACT OF COOLING INJECTION ON TRANSONIC OVER-TIP LEAKAGE FLOW AND SQUEALER AEROTHERMAL DESIGN OPTIMIZATION
    Wang, Z.
    Zhang, Q.
    Liu, Y.
    He, L.
    PROCEEDINGS OF THE ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2014, VOL 5B, 2014,
  • [26] INVESTIGATIONS OF HEAT TRANSFER AND FILM COOLING EFFECT ON A WORN SQUEALER TIP
    Ye, Mingliang
    Yan, Xin
    PROCEEDINGS OF THE ASME TURBO EXPO: TURBOMACHINERY TECHNICAL CONFERENCE AND EXPOSITION, VOL 7B, PT I, 2020,
  • [27] SQUEALER TIP HEAT TRANSFER WITH FILM COOLING
    Acharya, Sumanta
    Kramer, Gregory
    Moreaux, Louis
    Nakamata, Chiyuki
    PROCEEDINGS OF THE ASME TURBO EXPO 2010, VOL 4, PTS A AND B, 2010, : 1869 - 1877
  • [28] Study on Aerodynamic and Cooling Performance of Turbine Blade Squealer Tip with Film Cooling Pulsation Characteristics Considered
    Xu C.
    Li Z.
    Li J.
    Hsi-An Chiao Tung Ta Hsueh/Journal of Xi'an Jiaotong University, 2022, 56 (05): : 127 - 140
  • [29] Effect of film hole location on film-cooling effectiveness of squealer tip
    Cheng, Fengna
    Chang, Haiping
    Zhang, Jingyang
    Tian, Xingjiang
    Du, Zhineng
    Hangkong Dongli Xuebao/Journal of Aerospace Power, 2017, 32 (08): : 1844 - 1852
  • [30] Effect of squealer tip geometry on rotor blade aerodynamic performance
    Gao, Jie
    Zheng, Qun
    Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica, 2013, 34 (02): : 218 - 226
12345