IDDES Investigation of Rotor Blade Tip Vortices in Hovering State with Tip Slots

Author:

Shi Wenbo1,Zhang Heng2,Li Yuanxiang3

Affiliation:

1. School of Defense Science and Technology, Xi’an Technological University, Xi’an 710021, China

2. School of Aerospace Engineering, Tsinghua University, Beijing 100084, China

3. School of Mechanical Engineering, Xi’an Jiaotong University, Xi’an 710049, China

Abstract

The slots on a blade tip can effectively suppress the tip vortices by diffusing the core structure of a vortex and thus mitigate the adverse impacts of vortex interactions. In this paper, the effect of a slotted tip on vortex diffusion in the hovering state is investigated numerically by implementing the IDDES method using the fifth-order WENO scheme. The resulting wake flow field show that the number of secondary turbulent structures of so-called vortex worms near the slotted tip reduces significantly, indicating the weakening of vortex core rotation. It was found that the slotted tip reduced the peak value of velocity profiles in the vicinity of the vortex core by about 50%. The numerical result is close to the experimental conclusion. Correspondingly, the diameter of the vortex core is approximately doubled at each wake age relative to the baseline blade because the local flow passing through the slots will disintegrate the stable structure of the core region during the early stages of tip vortex generation. This promotes the turbulence mixture, resulting in the reduction in the vorticity value and rotating effect near the vortex core. Based on the overall results, the study of the slot parameters demonstrated that reducing the slot number or diameter will weaken the diffusing effect, causing a decrease in the flow rate.

Funder

Scientific Research Fund of Young Teachers from Xi’an Technological University

Publisher

MDPI AG

Subject

Aerospace Engineering

Reference27 articles.

1. Modern helicopter aerodynamics;Conlisk;Annu. Rev. Fluid Mech.,1997

2. Modern helicopter rotor aerodynamics;Conlisk;Prog. Aerosp. Sci.,2001

3. Rotor blade–vortex interaction noise;Yung;Prog. Aerosp. Sci.,2000

4. A review of helicopter rotor blade tip shapes;Brocklehurst;Prog. Aerosp. Sci.,2013

5. Active rotor control for helicopters: Individual blade control and swashplateless rotor designs;Kessler;CEAS Aeronaut. J.,2011

同舟云学术

1.学者识别学者识别

2.学术分析学术分析

3.人才评估人才评估

"同舟云学术"是以全球学者为主线,采集、加工和组织学术论文而形成的新型学术文献查询和分析系统,可以对全球学者进行文献检索和人才价值评估。用户可以通过关注某些学科领域的顶尖人物而持续追踪该领域的学科进展和研究前沿。经过近期的数据扩容,当前同舟云学术共收录了国内外主流学术期刊6万余种,收集的期刊论文及会议论文总量共计约1.5亿篇,并以每天添加12000余篇中外论文的速度递增。我们也可以为用户提供个性化、定制化的学者数据。欢迎来电咨询!咨询电话:010-8811{复制后删除}0370

www.globalauthorid.com

TOP

Copyright © 2019-2024 北京同舟云网络信息技术有限公司
京公网安备11010802033243号  京ICP备18003416号-3