涡轮动叶气膜冷却结构的凹槽状叶顶气热性能不确定性量化

doi:10.7527/S1000-6893.2024.29979

Abstract

Abstract:

This study proposes an efficient gas turbine blade aerothermal performance uncertainty system based on the genetic algorithm acceleration strategy， and develops a method for uncertainty data analysis of the blade tip aerothermal properties. The proposed system and method are utilized for the quantitative study of the uncertainty in the aerothermal performance of a squealer tip with film cooling structure， taking into account the operating condition fluctuation and geometrical parameter deviation. The results show that coolant jet injection will enhance the unsteady tendency of the downstream flow field of the first-stage rotor blades. In the actual operation of the gas turbine， the film cooling effectiveness in the region predicted at the design stage to be adequately covered by the coolant jet will be much lower than the value obtained from the deterministic calculations. Under the impact of the uncertainty inputs， the film cooling effectiveness of the squealer tip meets the Normal distribution. The mean value is reduced by 20.06% compared with the design value， and the probability of 10% deviation from the design value is as high as 81.84%. The result of sensitivity analysis shows that the main parameter affecting the fluctuation of the total downstream pressure loss coefficient is the tip clearance deviation， with the variance index as high as 87.21%. The total inlet temperature fluctuation is the key parameter affecting the uncertainty of the film cooling effectiveness， with the variance index of 84.01%.

Key words: turbine blade, squealer tip, film cooling, uncertainty quantification, sensitivity analysis

CLC Number:

V231

Ming HUANG, Kaiyuan ZHANG, Zhigang LI, Jun LI. Uncertainty quantification of aerothermal performance of squealer tip with film cooling structure[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(19): 629979.

Figures/Tables 23

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参数	数值
叶顶间隙S/mm	1.97
弦长C_ax/mm	86.1
肩壁宽度w/mm	2.29
凹槽深度D/mm	5.08

位置	边界条件	数值
进口	进口总压P/kPa	344.74
	进口湍流度Tu/%	5.0
	进口总温T/K	709
	进口气流角A/（°）	0.0
	雷诺数	2.86×10⁵
	马赫数	0.352
出口	静压P_out/kPa	141.44
出口	马赫数	0.761
壁面	壁面温度/K	496.3
壁面	旋转速度/（r·min^-1）	8 450.0
冷却气流	入口总温T_c/K	295
冷却气流	质量流量m_c/（kg·s^-1）	3.75×10^-5

网格数/10⁶	h/（W∙m^-2∙K^-1）	m/（g∙s^-1）	凹槽节点数	叶顶间隙节点数
3.5	592.15	4.24	40	30
4.6	602.87	4.18	48	35
7.4	613.54	3.93	70	60
9.8	616.94	3.93	80	75

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Uncertainty quantification of aerothermal performance of squealer tip with film cooling structure

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