TY - CONF
T1 - High-fidelity simulation of combustion processes in liquid rocket engines
AU - Wang, Xingjian
AU - Yang, Vigor
N1 - Funding Information:
This work was sponsored partly by the Air Force Office of Scientific Research under Grant No. FA 9550-10-1-0179, and partly by the William R. T. Oakes Endowment of the Georgia Institute of Technology. The authors gratefully acknowledge support and advice given by Dr. Mitat A. Birkan.
Funding Information:
Figure 5: Global view of snapshots of the temperature field for three different recess lengths. 4. Conclusion A unified theoretical and numerical framework is implemented to study the combustion processes of oxygen and kerosene in liquid rocket engines at supercritical conditions. Large eddy simulation is used to achieve the turbulence closure. Turbulence/chemistry interaction is modeled by a laminar flamelet approach. The flamelet library was established based upon the solutions of counterflow diffusion flames of a three-component surrogate model of kerosene with a skeleton chemical mechanism. Two representative injectors, bi-swirl and jet-swirl types typically used in contemporary liquid rocket engines, are examined at different injection temperatures and ambient pressures. The flow and flame characteristics are captured for both cases. The recess region is found to be critical for efficient and stable combustion process. Further analyses are underway to study the detailed flame structures and the dynamic responses of the flame field. 5. Acknowledgement This work was sponsored partly by the Air Force Office of Scientific Research under Grant No. FA 9550-10-1-0179, and partly by the William R. T. Oakes Endowment of the Georgia Institute of Technology. The authors gratefully acknowledge support and advice given by Dr. Mitat A. Birkan. 6. References [1] W. Mayer, A. Schik, M. Sch-aring, ffler, H. Tamura, Injection and mixing processes in high-pressure liquid oxygen/gaseous hydrogen rocket combustors, J Propul Power 16 (2000) 823-828. [2] V.G. Bazarov, V. Yang, Liquid-propellant rocket engine injector dynamics, J Propul Power 14 (1998) 797-806. [3] K. Ahn, H.-S. Choi, Combustion dynamics of swirl coaxial injectors in fuel-rich combustion, J. Propul. Power 28 (2012) 1359-1367. [4] V. Yang, Modeling of supercritical vaporization, mixing, and combustion processes in liquid-fueled propulsion systems, P Combust Inst 28 (2000) 925-942. [5] W. Mayer, H. Tamura, Propellant injection in a liquid oxygen/gaseous hydrogen rocket engine, J Propul Power 12 (1996) 1137-1147.
Publisher Copyright:
© 2017 Eastern States Section of the Combustion Institute. All rights reserved.
PY - 2017
Y1 - 2017
N2 - The combustion characteristics of oxygen and kerosene in liquid rocket engines are investigated using large eddy simulation. These engines operate at pressure levels higher than the critical pressures of propellants, i.e., supercritical conditions. A theoretical and numerical framework along with real-fluid thermodynamic and transport properties is implemented. The turbulence/chemistry interaction is treated using a laminar flamelet approach. The resultant scheme provides high-fidelity information of flame fields that are extremely challenging to capture in experiments. Two types of swirl-related injectors are considered, bi-swirl and jet-swirl. Oxygen and kerosene are both tangentially introduced into the injector for the former, while oxygen is axially injected and kerosene is tangentially introduced for the latter. The flow and flame structures are presented. The flame anchors at the injector post in the recess region for both cases, and is further stabilized by the recirculation zone immediately downstream of the injector. The kerosene film flows along the injector surface because of the swirl-induced centrifugal force, and provides effective thermal protection to the surface against the heat flux in the flame zone. The dynamic responses of the combustion filed is currently underway to explore the stability characteristics.
AB - The combustion characteristics of oxygen and kerosene in liquid rocket engines are investigated using large eddy simulation. These engines operate at pressure levels higher than the critical pressures of propellants, i.e., supercritical conditions. A theoretical and numerical framework along with real-fluid thermodynamic and transport properties is implemented. The turbulence/chemistry interaction is treated using a laminar flamelet approach. The resultant scheme provides high-fidelity information of flame fields that are extremely challenging to capture in experiments. Two types of swirl-related injectors are considered, bi-swirl and jet-swirl. Oxygen and kerosene are both tangentially introduced into the injector for the former, while oxygen is axially injected and kerosene is tangentially introduced for the latter. The flow and flame structures are presented. The flame anchors at the injector post in the recess region for both cases, and is further stabilized by the recirculation zone immediately downstream of the injector. The kerosene film flows along the injector surface because of the swirl-induced centrifugal force, and provides effective thermal protection to the surface against the heat flux in the flame zone. The dynamic responses of the combustion filed is currently underway to explore the stability characteristics.
UR - http://www.scopus.com/inward/record.url?scp=85049074678&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85049074678&partnerID=8YFLogxK
M3 - Paper
AN - SCOPUS:85049074678
T2 - 10th U.S. National Combustion Meeting
Y2 - 23 April 2017 through 26 April 2017
ER -