Fluid-Structure Interaction Study of the Splitter Plate in Turbine-Based Combined-Cycle Inlet System
Publication: Journal of Aerospace Engineering
Volume 30, Issue 4
Abstract
A splitter plate is a key component of the inlet system in turbine-based combined-cycle engines, which divides the whole captured air flow into different engines, namely turbojet and ramjet. The aerodynamic force acting on the thin splitter plate with a single pivot may engender vibration and, in turn, flow-field variations at the start and end of the mode transition phase. A loosely-coupled method was used to simulate the process of fluid-structure interaction. The results showed that the deformation of the splitter plate is, in fact, a process in which the elastic restoring force struggles against the aerodynamic force under the action of damping. At turbojet mode, the splitter plate can attain the maximum displacement of 7.20 mm. The terminal shock was observed to move back and forth in the flowpath. The mass flow rate in turbojet and ramjet flowpaths varied by 5.91 and 44.34%, respectively. At ramjet mode, the inlet fell into the unstart state with a greater displacement of 8.95 mm. The mass flow rate in turbojet and ramjet flowpaths, and slot-coupled cavity varied by 1.69, 23.91, and 51.85%, respectively.
Get full access to this article
View all available purchase options and get full access to this article.
Acknowledgments
We would like to acknowledge the continued support of Natural Science Fund of China (NSFC) under the award number of 50876042 and 90916023.
References
ABAQUS version 6.12-1 [Computer software]. ABAQUS, Providence, RI.
Albertson, C. W., Emami, S., and Trexler, C. A. (2006). “Mach 4 test results of a dual-flowpath, turbine based combined cycle inlet.” Proc., 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conf., AIAA, Atlanta.
Blades, E. L., Luke, E. A., and Ruf, J. (2012). “Fully coupled fluid-structure interaction simulations of rocket engine side loads.” Proc., 48th AIAA/ASME/SAE/ASEE Joint Propuls. Conf. and Exhibit, AIAA, Atlanta.
Chang, X., Ma, R., Zhang, L., He, X., and Li, M. (2015). “Further study on the geometric conservation law for finite volume method on dynamic unstructured mesh.” Comput. Fluids, 120, 98–110.
Clough, J. A., and Lewis, M. J. (2003). “Comparison of turbine-based combined-cycle engine flowpaths.” Proc., 12th AIAA Int. Space Planes and Hypersonic Systems and Technologies Conf., AIAA, Norfolk, VA.
Deng, X., Jiang, Y., Mao, M., Liu, H., Li, S., and Tu, G. (2015). “A family of hybrid cell-edge and cell-node dissipative compact schemes satisfying geometric conservation law.” Comput. Fluids, 116, 29–45.
FLUENT version 14.0 [Computer software]. ANSYS, Canonsburg, PA.
Foster, L. E., Saunders, J. D., Sanders, B. W., and Weir, L. J. (2012). “Highlights from a Mach 4 experimental demonstration of inlet mode transition for turbine-based combined cycle hypersonic propulsion.” Proc., 48th AIAA/ASME/SAE/ASEE Joint Propuls. Conf. and Exhibit, AIAA, Atlanta.
GAMBIT version 2.4.6 [Computer software]. Fluent Europe, Sheffield, U.K.
Garelli, L., Paz, R. R., and Storti, M. A. (2010). “Fluid-structure interaction study of the start-up of a rocket engine nozzle.” Comput. Fluids, 39(7), 1208–1218.
Guo, S., Xu, J., Mo, J., Gu, R., and Pang, L. (2015). “Fluid-structure interaction study of the splitter plate in a TBCC exhaust system during mode transition phase.” Acta Astronaut., 112, 126–139.
Kanda, T., and Kudo, K. (2003). “Conceptual study of a combined-cycle engine for an aerospace plane.” J. Propul. Power, 19(5), 859–867.
Lin, T. J., Guan, Z. Q., Chang, J. H., and Lo, S. H. (2014). “Vertex-ball spring smoothing: an efficient method for unstructured dynamic hybrid meshes.” Comput. Struct., 136(7), 24–33.
Liu, J., Yuan, H., and Guo, R. (2015). “Unsteady flow characteristic analysis of turbine based combined cycle (TBCC) inlet mode transition.” Propul. Power Res., 4(3), 141–149.
Marshall, A. W., Gupta, A. K., Lewis, M. J., and Lavelle, T. (2004). “Critical issues in TBCC modeling.” Proc., 40th AIAA/ASME/SAE/ASEE Joint Propuls. Conf. and Exhibit, AIAA, Fort Lauderdale, FL.
MpCCI version 4.2.1 [Computer software]. Fraunhofer Institute for Algorithms and Scientific Computing SCIA, Sankt Augustin, Germany.
Sanders, B. W., and Weir, L. J. (2008). “Aerodynamic design of a dual-flow Mach 7 hypersonic inlet system for a turbine-based combined-cycle hypersonic propulsion system.”.
Saunders, J. D., Slater, J. W., Dippold, V., Lee, J., Sanders, B. W., and Weir, L. J. (2008). “Inlet mode transition screening test for a turbine-based combined-cycle propulsion system.” Jannaf.
Slater, J. W., and Saunders, J. D. (2009). “CFD simulation of hypersonic TBCC inlet mode transition.” Proc., 16th AIAA/DLR/DGLR Int. Space Planes and Hypersonic Systems and Technologies Conf., AIAA, Orlando, FL.
Snyder, D., Koutsavdis, E., and Anttonen, J. (2003). “Transonic store separation using unstructured CFD with dynamic meshing.” Proc., 33rd AIAA Fluid Dynamics Conf. and Exhibit, AIAA, Orlando, FL.
Starkey, R. (2015). “Hypersonic vehicle telemetry blackout analysis.” J. Spacecraft Rocket, 52(2), 426–438.
Stickan, B., Dillinger, J., and Schewe, G. (2014). “Computational aeroelastic investigation of a transonic limit-cycle-oscillation experiment at a transport aircraft wing model.” J. Fluids Struct., 49(8), 223–241.
Storti, M. A., Nigro, N. M., Paz, R. R., and Dalcin, L. D. (2009). “Strong coupling strategy for fluid-structure interaction problems in supersonic regime via fixed point iteration.” J. Sound Vibr., 320(4–5), 859–877.
Tabiei, A., and Sockalingam, S. (2012). “Multiphysics coupled fluid/thermal/structural simulation for hypersonic reentry vehicles.” J. Aerosp. Eng., 273–281.
Wang, C., Tian, X., Yan, L., Xue, L., and Cheng, K. (2014). “Preliminary integrated design of hypersonic vehicle configurations including inward-turning inlets.” J. Aerosp. Eng., .
Xiang, X. H., Liu, Y., and Qian, Z. (2015). “Aerodynamic design and numerical simulation of over-under turbine-based combined-cycle (TBCC) inlet mode transition.” Procedia Eng., 99, 129–136.
Zhao, X., Bayyuk, S., and Zhang, S. J. (2013). “Aeroelastic response of rocket nozzles to asymmetric thrust loading.” Comput. Fluids, 76(10), 128–148.
Zhao, X., Zhu, Y. F., and Zhang, S. J. (2012). “Transonic wing flutter predictions by a loosely-coupled method.” Comput. Fluids, 58(58), 45–62.
Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 30 • Issue 4 • July 2017
Copyright
©2017 American Society of Civil Engineers.
History
Received: Jun 15, 2016
Accepted: Oct 13, 2016
Published online: Feb 2, 2017
Published in print: Jul 1, 2017
Discussion open until: Jul 2, 2017
Authors
Metrics & Citations
Metrics
Citations
Download citation
If you have the appropriate software installed, you can download article citation data to the citation manager of your choice. Simply select your manager software from the list below and click Download.