叶片源项模型的研究回顾与进展

doi:10.7527/S1000-6893.2024.31178

Abstract

Abstract:

With the enhancement of the coupling depth between the distributed propulsion system and the aircraft in terms of structure and aerodynamics， the blade source term model that balances calculation accuracy and efficiency plays an increasingly important role in the analysis and optimization of the internal and external flow coupling of the distributed layout. This paper systematically reviews the basic logic， implementation path and application results of the existing blade source term models for compressors， fans， propellers， etc.， and provides support for the selection of blade source term models in the process of internal and external flow coupling analysis of distributed propulsion systems. Firstly， the applications and development of the descriptive and iterative body force methods based on the actuator disk model are reviewed and summarized. The Hough-Ordway model and its improvement ideas are discussed. The potential flow-viscous flow coupling and the iterative calculation strategy based on Blade Element Momentum Theory （BEMT） coupling are analyzed. Secondly， the applications and development of the analysis mode and the extraction mode body force model based on the Marble body force model are sorted out. The Gong model， the Hall model， and the improved Gong-Thollet model and Hall-Thollet model based on the analysis mode are discussed. Subsequently， the body force models of Turbine Engine Analysis Compressor Code （TEACC）， Kiwada and Chima， which directly extract the blade source terms from the flow field data by using the streamline curvature method and the Reynolds-Averaged Navier-Stokes （RANS） equation calculation results， are discussed. Finally， the collected blade source term models are compared and analyzed， and specific suggestions for the applications of blade source term models in numerical analysis of rotating turbomachinery are given， which provides a reference for the integrated analysis of internal and external flow for balancing calculation accuracy and efficiency.

Key words: distributed propulsion, turbomachinery, blade source term model, actuator disk, body force

CLC Number:

V231.1

Fang ZHOU, Qingyong WANG, Yuqi QIN, Botao ZHANG, Yangang WANG. Review and progress of research on blade source term model[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(10): 31178.

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转速/（r∙min^-1）		1 500	2 000	2 500
相对误差/%	JAVAFOIL	49	47	44
	XROTOR	6	3	6
	XFOIL	-1	-6	-7

建模方法	推力/N	功率/kW	效率
RANS高保真	1 390	164.4	0.863
未进行叶尖损失修正的RANS/BEMT	1 748 （+25.7%）	199.1 （+21.1%）	0.896 （+3.8%）
RANS/BEMT 结合Glauert 叶尖损失修正	1 574 （+13.3%）	184.3 （+12.1%）	0.872 （+1.8%）
RANS/BEMT结合Glauert + Shen叶尖损失修正	1 514 （+9.0%）	176.8 （+7.5%）	0.874 （+1.27%）

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Review and progress of research on blade source term model

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