Two-Dimensional Supersonic Thrust Vectoring Using Staggered Ramps

Significance 

Significant technological innovations have been made in jet engines to achieve outstanding thermal efficiency with increased thrust, enabling aircraft to go greater distances. Researchers have also continued to explore the potential to vector the produced thrust (thrust vector control) to better manipulate the direction of the thrust from its engine in order to control the attitude or exit angular velocity making aircraft more maneuverable. Therefore, they have proposed a number of vector control mechanisms, which are either mechanical or fluidic.

Fluidic vector control mechanisms such as shock vector control, counter-flow, and co-flow have been investigated. All the three methods adopt a secondary flow, but shock vector control adopts a secondary injected flow to generate an oblique shockwave. All the investigations centering on the three methods have reported flow deflections within 30°.

Mechanical thrust control mechanisms, for example, small external and rotatable nozzles, external flaps, and swiveling the nozzle’s diverging section, have been implemented in military jet engines. Depending on the arrangement, these mechanisms can vector an engine’s thrust up to 90°. Some mechanical thrust vector control designs implement a flap system, while others adopt asymmetrically sized flaps for thrust vectoring in the pitch direction.

Carlos Montes and Professor Roger Davis at the University of California Davis explored the vectoring performance of a unique mechanical mechanism implementing a ramp at the nozzle throat along one wall and another at the exit of the opposite wall. They designed the nozzle for air-breathing engines using piecewise quartic splines, isentropic relationships, and published engine data. Their research work is published in the Journal of Engineering for Gas Turbines and Power.

The proposed mechanism used two staggered, adjustable ramps. By comparing the findings of a baseline inviscid numerical simulation without ramps with analytical data, the authors were able to verify the nozzle design. They later evaluated 9 ramp setups under steady-state turbulent viscous conditions implementing two sets of parameters that corresponded to inlet conditions with and without an after burner.

The use of both internal and external ramps reported excellent thrust vector control performance when compared to the performance of purely fluidic thrust vector control mechanisms. Significant flow deflections as high as 21° were realized when the ramp length used was less than the nozzle’s length.

The authors found that the thrust vectoring of the proposed nozzle arrangement increased with increasing angle and ramp length. When the largest ramp angle was used, a maximum flow deflection of about 30° was recorded. While the results recorded fell below the values of other mechanical thrust vector control designs, it was projected that larger ramp angles would have resulted to greater flow deflection angles.

For a given ramp configuration, the mean flow deflection angle would be obtained by numerically integrating the flow angle distribution at the second ramp’s exit plane and weighting the value with the corresponding exit area. The authors recorded an excellent thrust vectoring performance with non-after-burner conditions. At moderate to high angles and ramp lengths, the flow solution residuals modulated suggesting the presence of an unsteady flow.

The thrust vectoring data obtained by Carlos Montes and Roger Davis through the steady-state simulation are promising in the performance potential of the provisionally patented thrust vector control mechanism.

Two-Dimensional Supersonic Thrust Vectoring Using Staggered Ramps. Advances in Engineering

Figure legend: Mach number contour plot for one of our ramp configurations (40 deg, 3.5-in long), but with streamlines added to provide some insight on the recirculating flow downstream of the throat ramp. Additionally, the streamlines in the core flow at the exit provide a visualization of average flow deflection angle (-24.5 deg as reported for this configuration).

 

About the author

Carlos Montes graduated from the University of California, Davis in 2014 with a B.S. degree in Mechanical and Aerospace Engineering. In 2016, he graduated from UC Davis with an M.S. degree in Aerospace Engineering, focusing on thermo-fluids and computational fluid dynamics. At the beginning of 2017, Carlos started working at Lockheed Martin Space Systems Company as an aeronautical engineer. He is currently heavily involved in CFD modeling of several 2D and 3D problems under the Navy’s Fleet Ballistic Missile program. His current career achievements include one publication and a patent.

About the author

Roger Davis graduated from the Ohio State University in 1975 with B.S. and M.S. degrees in Aeronautical and Astronautical Engineering and from the University of Connecticut in 1981 with a PhD in Mechanical Engineering specializing in Computational Fluid Dynamics. From 1975 to 1981 he worked at Pratt & Whitney in East Hartford, Connecticut on developing and improving computational and design system techniques and performing linear cascade experiments. Dr. Davis transferred to the United Technologies Research Center in 1983 where he developed various viscous computational schemes. He was a Senior Consulting Professor at Stanford University from 1999 until 2003 working on a Department of Energy contract in the Accelerated Strategic Computing Initiative (ASCI) program.

Dr. Davis transferred to the University of California, Davis in 2002 as a Professor in the Mechanical and Aerospace Engineering Department where he taught courses in Fluid Mechanics, Heat Transfer, Propulsion, Advanced Turbomachinery and Parallel Computing as well as performs research on gas-turbine simulation and design technology. Prof. Davis is the author or co-author of over 110 internal and external publications including over 50 refereed journal articles.

He served as an associate editor of the ASME Journal of Turbomachinery for ten years and on the editorial board of the International Journal of Aerospace Engineering for 8 years. He is the recipient of 6 best paper and achievement awards and one patent.

Reference

Carlos F. Montes and Roger L. Davis. Two-Dimensional Supersonic Thrust Vectoring Using Staggered Ramps. Journal of Engineering for Gas Turbines and Power August 2017, Vol. 139 / 082605-1.

 

Go To Journal of Engineering for Gas Turbines and Power 

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