基于体积力模型边界层吸入式风扇数值模拟

中国民航大学学报 ›› 2025, Vol. 43 ›› Issue (5): 73-81.

基于体积力模型边界层吸入式风扇数值模拟

中国民航大学 a. 科技创新研究院； b.中欧航空工程师学院，天津 300300

收稿日期:2024-03-12 修回日期:2024-06-10 出版日期:2025-11-17 发布日期:2025-11-17
作者简介:杨晓军（1980— ），男，辽宁朝阳人，教授，博士，研究方向为航空发动机气动传热
基金资助:
国家重点研发计划项目（2022YFB4301000）

The numerical simulation of boundary layer ingestion fan based on body force

model

a. Research Institute of Science and Technology Innovation; b. Sino-European Institute of Aviation Engineering,

CAUC, Tianjin 300300, China

Received:2024-03-12 Revised:2024-06-10 Online:2025-11-17 Published:2025-11-17

摘要/Abstract

摘要：

边界层吸入（BLI，boundary layer ingestion）式风扇进口存在复杂的畸变流场，现有研究大多局限于传统的三

维模拟方式，计算耗时长。本文以 DGEN380 风扇转子为研究对象，设计了一款与之匹配的 S 型进气道以吸

入来流边界层，并采用基于体积力模型（BFM，body force modelling）的计算方法，计算结果的参数变化趋势

与非定常计算结果吻合良好，风扇入口的旋流角及无量纲总压值的周向均值与非定常结果偏差在 6%以内，

计算时间为非定常方法的 1/50。基于此模型探究了 15%、30%、60% 进口高度下 3 种不同厚度 BLI 对于风扇

转子进出口流场的影响。结果表明：针对风扇转子入口，在不同叶高处总压畸变及旋流畸变程度随着 BLI 厚

度的增加均有所增加，且旋流分布呈现对涡形式，在经过风扇转子通道叶片作用之后，对涡逐渐转化为单向

涡，风扇转子出口气流落后角减小，BLI 区风扇功系数值较均匀流工况有所提升。

关键词:

边界层吸入, 体积力模型, S 型进气道, 旋流畸变, 总压畸变

Abstract:

There is a complex distorted flow field at the inlet of boundary layer ingestion (BLI) fan, but most of the existing

research are limited to traditional three-dimensional simulation methods, which are time-consuming. This article

takes the DGEN380 fan rotor as the research object and designs an S-shaped inlet that matches it to ingest incoming boundary layer, and a calculation method based on the body force model (BFM) is adopted. The trend of

parameter changes in the calculation results is well consistent with the unsteady calculation results. The circumferential average values of the swirl angle and dimensionless total pressure at the fan inlet deviate from the unsteady

results within 6%, and the calculation time is 1/50 of that of the unsteady method. Based on this model, the influence of three different thicknesses of BLI at inlet heights of 15%, 30%, and 60% on the flow field at the inlet and

outlet of the fan rotor is explored. The results show that, for the fan rotor inlet, the degree of total pressure distortion and swirl distortion increases with the BLI thickness increasing at different blade heights, and the swirl distribution presents a paired vortex form. After passing through the fan rotor passage blades, the paired vortexes

gradually transform into a unidirectional vortex, and the backward angle of the airflow at the fan rotor outlet decreases. The power coefficient value of BLI fan has been improved compared to the uniform flow condition.

Key words:

boundary layer ingestion, body force model, S-shaped inlet, swirl distortion, total pressure distortion

中图分类号:

V231.3

杨晓军 a , 余思颖 b , 孔庆国 b.

基于体积力模型边界层吸入式风扇数值模拟

[J]. 中国民航大学学报, 2025, 43(5): 73-81.

YANG Xiaojuna , YU Siyingb , KONG Qingguob.

The numerical simulation of boundary layer ingestion fan based on body force

model

[J]. Journal of Civil Aviation University of China, 2025, 43(5): 73-81.

参考文献 20

[1]	OKONKWO P, SMITH H. Review of evolving trends in blended wing
	body aircraft design[J]. Progress in Aerospace Sciences, 2016, 82: 1-23.
[2]	KIM H, LIOU M S. Flow simulation and optimal shape design of N3-X
	hybrid wing body configuration using a body force method[J]. Aerospace
	Science and Technology, 2017, 71: 661-674.
[3]	SMITH L H. Wake ingestion propulsion benefit[J]. Journal of Propulsion and Power, 1993, 9(1): 74-82.
[4]	LIEBECK R H. Design of the blended wing body subsonic transport[J].
	Journal of Aircraft, 2004, 41(1): 10-25.
[5]	HARDIN L W, COUSINS W T, WOLTER J D, et al. Data analysis techniques for fan performance in highly-distorted flows from boundary layer ingesting inlets[C]//2018 AIAA Aerospace Sciences Meeting, January 8 -12, 2018, Kissimmee, Florida. Reston, Virginia: AIAA, 2018:1888.
[6]	HARDIN L, TILLMAN G, SHARMA O, et al. Aircraft system study of
	boundary layer ingesting propulsion[C]//48th AIAA/ASME/SAE/ASEE
	Joint Propulsion Conference & Exhibit, July 30-August 01, 2012, Atlanta, Georgia. Reston, Virginia: AIAA, 2012: 3993.
[7]	HATHAWAY M D, DEL ROSARIO R, MADAVAN N. NASA fixed wing
	project propulsion research and technology development activities to reduce specific energy consumption [C]//49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, July 14-17, 2013, San Jose, CA. Reston,
	Virginia: AIAA, 2013: 3605.
[8]	KAWAI R T, FRIEDMAN D M, SERRANO L. Blended wing body (BWB)
	boundary layer ingestion (BLI) inlet configuration and system studies[R].Washington DC: NASA Technical Reports Server, 2006.
[9]	SIERADZKI A, KWIATKOWSKI T, TURNER M G, et al. Numerical
	modeling and design challenges of boundary layer ingesting fans [J].
	Journal of Turbomachinery, 2022, 144(11): 111012.
[10]	达兴亚, 范召林, 熊能, 等. 分布式边界层吸入推进系统的建模与分析[J]. 航空学报, 2018, 39(7): 113-121.
[11]	KIM H, LIOU M S. Shape design optimization of embedded engine inlets for N2B hybrid wing-body configuration[J]. Aerospace Science and Technology, 2013, 30(1): 128-149.
[12]	邓文剑, 王占学, 周莉, 等. 附面层吸入式进气道内流动损失特性[J]. 航空动力学报, 2023, 38(3): 698-708.
[13]	BERRIER B, MOREHOUSE M. Evaluation of flush-mounted, S-duct inlets with large amounts of boundary layer ingestion[R]. Washington DC: NASA Technica Reports Server, 2003.
[14]	宁乐. BLI 进气道流动特性的地面模拟方法和初步实验研究[D].南京: 南京航空航天大学, 2016.
[15]	魏巍, 任思源, 达兴亚. 边界层吸入对方转圆进气道、风扇耦合影响[J]. 航空动力学报, 2020, 35(9): 1943-1953.
[16]	CHIMA R V. A three-dimensional unsteady CFD model of compressor stability[C]// ASME Turbo Expo 2006: Power for Land, Sea， and Air,May 8-11, 2006, Barcelona, Spain, 2008: 1157-1168.
[17]	安玉戈, 刘火星. 压气机进气畸变数值模拟技术研究[J]. 航空学报,2012, 33(9): 1624-1632.
[18]	史磊, 杨光, 林文俊. 前缘侵蚀对风扇转子叶片气动特性的影响机理[J]. 航空学报, 2019, 40(10): 123007.
[19]	BERRIER B, CARTER M B, ALLAN B. High Reynolds number investigation of a flush -mounted, S -duct inlet with large amounts of boundary layer ingestion[R]. Washington DC: NASA Technical Reports Server, 2005.
[20]	FELDER J, BROWN G, DAEKIM H, et al. Turboelectric distributed
	propulsion in a hybrid wing body aircraft[C]//International Symposium
	of Air Breathing Engine. Gorthenburg, Sweden: AIAA, 2011, 2: 1340-1360.