Large eddy simulation of cryogenic jet under supercritical pressure based on OpenFOAM

Yuhang LI; Baoyuan WU; Yi WANG; Lixin ZHOU

doi:10.13224/j.cnki.jasp.20210244

Chinese

您当前的位置：

首页 >

文章列表页 >

Large eddy simulation of cryogenic jet under supercritical pressure based on OpenFOAM

Rocket Engine | 更新时间：2025-04-07

- Large eddy simulation of cryogenic jet under supercritical pressure based on OpenFOAM
- Journal of Aerospace Power Vol. 37, Issue 5, Pages: 1090-1099(2022)
- 作者机构：
  
  1.中国航天科技集团有限公司西安航天动力研究所液体火箭发动机技术重点实验室，西安 710100
  2.中国航天科技集团有限公司航天推进技术研究院，西安 710100
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210244
  CLC：
- 稿件说明：
移动端阅览
Yuhang LI, Baoyuan WU, Yi WANG, et al. Large eddy simulation of cryogenic jet under supercritical pressure based on OpenFOAM[J]. Journal of Aerospace Power, 2022, 37(5): 1090-1099.
DOI：

Yuhang LI, Baoyuan WU, Yi WANG, et al. Large eddy simulation of cryogenic jet under supercritical pressure based on OpenFOAM[J]. Journal of Aerospace Power, 2022, 37(5): 1090-1099. DOI： 10.13224/j.cnki.jasp.20210244.

摘要

为了深入认识低温射流在超临界压力下的流动特性，将真实流体热物性模型写入开源CFD程序OpenFOAM平台中，开发出了用于模拟超临界压力下流动过程的均相求解器。针对液氮跨临界、超临界射流进行大涡模拟，研究了环境条件变化对于低温射流流动特性的影响。结果表明：采用的真实流体模型能够在广泛的温度与压力范围内准确计算流体的热物理性质，在此基础上开发的均相求解器能够准确描述超临界条件下的低温射流，其流动特性主要表现为稠密液体与环境气体之间的剪切层不稳定以及湍流混合，此类变密度射流在湍流充分发展区域同常密度射流一样具有自相似特性；超临界射流相比于跨临界射流具有更高的混合效率以及更短的液核穿透长度；环境温度升高以及环境压力降低均使得低温射流与周边气体之间的密度梯度增加，对剪切层中不稳定波动的发展起到抑制作用，导致了射流液核长度的增加以及扩张角度的减小。

Abstract

In order to get insights into the flow characteristics of cryogenic jet under supercritical pressure，the real⁃fluid model was implemented into open source CFD code OpenFOAM.The effect of real⁃fluid thermo⁃physical characteristics was introduced into the pressure correction algorithm，contributing to the development of the homogeneous solver for cryogenic flows under supercritical conditions.Transcritical and supercritical jets of LN

were studied using large eddy simulation，including the influence of ambient temperature and pressure.The results indicated that the real⁃fluid model developed can describe thermo⁃physical characteristics accurately within wide temperature and pressure range.The homogeneous solver can correctly reveal the flow structure of cryogenic jet under supercritical conditions，which was characterized by shear layer instability and turbulent mixing.These kinds of variable density jets showed self⁃similarity characteristics in turbulence fully developed region.Compared with transcritical jet，the supercritical jet showed higher turbulent mixing rate and shorter core length.Under higher ambient temperature or lower ambient pressure，the density gradient between cryogenic jet and ambient gas greatly reduced，which restrained the development of instability wave in shear layer，leading to the increase of jet core length and the decrease of jet spreading angle.

关键词

Keywords

references

MAYER W ， SCHIK A . Atomization and breakup of cryogenic propellants under high⁃pressure subcritical and supercritical conditions [J]. Journal of Propulsion and Power ， 1998 ， 14 （ 5 ）: 835 ⁃ 835 .

MAYER W ， SCHIK A ， SCHÄFFLER M ， et al . Injection and mixing processes in high⁃pressure liquid oxygen/gaseous hydrogen rocket combustors [J]. Journal of Propulsion and Power ， 2000 ， 16 （ 5 ）: 823 ⁃ 828 .

MAYER W ， IVANCIC B ， SCHIK A ， et al . Propellant atomization and ignition phenomena in liquid oxygen/gaseous hydrogen rocket combustors [J]. Journal of Propulsion and Power ， 2001 ， 17 （ 4 ）: 794 ⁃ 799 .

MAYER W ， TELAAR J ， BRANAM R ， et al . Raman measurements of cryogenic injection at supercritical pressure [J]. Heat and Mass Transfer ， 2003 ， 39 （ 8 ）: 709 ⁃ 719 .

CHEHROUDI B ， TALLEY D ， COY E . Visual characteristics and initial growth rates of round cryogenic jets at subcritical and supercritical pressures [J]. Physics of Fluids ， 2002 , 14 （ 2 ）: 850 ⁃ 861 .

DAVIS D W ， CHEHROUDI B . Measurements in an acoustically driven coaxial jet under sub⁃，near⁃，and supercritical conditions [J]. Journal of Propulsion and Power ， 2007 , 23 （ 2 ）: 364 ⁃ 374 .

OEFELEIN J C ， YANG V . Modeling high⁃pressure mixing and combustion processes in liquid rocket engines [J]. Journal of Propulsion and Power ， 1998 ， 14 （ 5 ）: 843 ⁃ 857 .

SCHMITT T ， SELLE L ， RUIZ A ， et al . Large⁃eddy simulation of supercritical⁃pressure round jets [J]. AIAA Journal ， 2010 ， 48 （ 9 ）: 2133 ⁃ 2144 .

ZONG N ， YANG V . Cryogenic fluid jets and mixing layers in transcritical and supercritical environments [J]. Combustion Science and Technology ， 2006 ， 179 （ 1 ）: 193 ⁃ 227 .

ZONG N ， YANG V . Cryogenic fluid dynamics of pressure swirl injectors at supercritical conditions [J]. Physics of Fluids ， 2008 ， 20 （ 5 ）: 056103.1 ⁃ 056103.15

WANG X ， WANG Y ， YANG V . Three⁃dimensional flow dynamics and mixing in a gas⁃centered liquid⁃swirl coaxial injector at supercritical pressure [J]. Physics of Fluids ， 2019 ， 31 （ 6 ）: 065109.1 ⁃ 065109.14

HAKIM L ， RUIZ A ， SCHMITT T ， et al . Large eddy simulations of multiple transcritical coaxial flames submitted to a high⁃frequency transverse acoustic modulation [J]. Proceedings of the Combustion Institute ， 2015 , 35 : 1461 ⁃ 1468 .

SCHMITT T ， MERY Y ， BOILEAU M ， et al . Large eddy simulation of oxygen/methane flames under transcritical conditions [J]. Proceedings of the Combustion Institute ， 2011 , 33 : 1383 ⁃ 1390 .

URBANO A ， SELLE L ， STAFFELBACH G ， et al . Exploration of combustion instability triggering using large eddy simulation of a multiple injector liquid rocket engine [J]. Combustion and Flame ， 2016 ， 169 : 129 ⁃ 140 .

MA P C ， BANUTI D ， IHME M ， et al . Numerical framework for transcritical real⁃fluid reacting flow simulations using the flamelet progress variable approach [R]. AIAA⁃2017⁃0143 , 2017 .

HUO H ， WANG X ， YANG V . A general study of counterflow diffusion flames at subcritical and supercritical conditions:Oxygen/hydrogen mixtures [J]. Combustion and Flame ， 2014 ， 161 （ 12 ）: 3040 ⁃ 3050 .

WANG X ， ZHANG L ， LI Y ， et al . Supercritical combustion of gas⁃centered liquid⁃swirl coaxial injectors for staged⁃combustion engines [J]. Combustion and Flame ， 2018 ， 197 : 204 ‑ 214 .

ZONG N . Modeling and simulation of cryogenic fluid injection and mixing dynamics under supercritical conditions [D]. State College,US ： The Pennsylvania State University ， 2005 .

TERASHIMA H ， KAWAI S ， YAMANISHI N . High⁃resolution numerical method for supercritical flows with large density variations [J]. AIAA Journal ， 2011 , 49 （ 12 ）: 2658 ⁃ 2672 .

TERASHIMA H ， KOSHI M . Approach for simulating gas‑liquid‑like flows under supercritical pressures using a high⁃order central differencing scheme [J]. Journal of Computational Physics ， 2012 ， 231 （ 20 ）: 6907 ⁃ 6923 .

LACAZE G ， SCHMITT T ， RUIZ A ， et al . Comparison of energy⁃，pressure⁃ and enthalpy⁃based approaches for modeling supercritical flows [J]. Computers and Fluids ， 2019 ， 181 : 35 ⁃ 56 .

POLING B E ， PRAUSNITZ J M ， O'CONNELL J P . 气液物性估算手册 [M].赵红玲，王凤坤，陈圣坤，译. 北京 : 化学工业出版社， 2006 .

POPE S B . Turbulent flows [M]. Cambridge,UK : Cambridge University Express ， 2000 .

HO CM ， HUERRE P . Perturbed free shear layers [J]. Annual Review of Fluid Mechanics ， 1984 ， 16 （ 1 ）: 365 ⁃ 422 .

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Analysis of n⁃dodecane spray jet by proper orthogonal decomposition

Large eddy simulation on the staggered tube bundle of the compact precooler

Study on opposed mixing flow in circumferential intake

引用格式：王庆宇,刘琪麟,赖焕新.高亚声速喷流近场的流-声关联［J］.航空动力学报,2020,35(12):2532-2542.WANG Qingyu,LIU Qilin,LAI Huanxin.Flow-acoustics correlations in near-fields of high subsonic jet［J］.Journal of Aerospace Power,2020,35(12):2532-2542.Flow-acoustics correlations in near-fields of high subsonic jet

Large eddy simulation of low swirl premixed flame stabilization mechanism

Related Author

Wenjin QIN

Lihui XU

Dengbiao LU

Hao LIU

CHEN Yiming

LI Zepeng

ZHANG Junqiang

ZOU Zhengping

Related Institution

Beijing Aerospace Institute for Metrology and Measurement Technology， China Academy of Launch Vehicle Technology， China Aerospace Science and Technology Corporation

School of Mechanical Engineering， University of Shanghai for Science and Technology

Research Institute of Aero-engine,Beijing University of Aeronautics and Astronautics

National Key Laboratory of Science and Technology on Aero-Engine,Aero-thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics

School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰