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CFD Analysis of Mixing Characteristics of Several Fuel Injectors at Hypervelocity Flow ConditionsCFD analysis is presented of the mixing characteristics and performance of three fuel injectors at hypervelocity flow conditions. The calculations were carried out using the VULCAN-CFD solver and Reynolds-Averaged Simulations (RAS). The high Mach number flow conditions match those proposed for the planned experiments conducted as a part of the Enhanced Injection and Mixing Project (EIMP) at the NASA Langley Research Center. The EIMP aims to investigate scramjet fuel injection and mixing physics, improve the understanding of underlying physical processes, and develop enhancement strategies and functional relationships relevant to flight Mach numbers greater than eight. Because of the high Mach number flow considered, the injectors consist of a fuel placement device, a strut; and a fluidic vortical mixer, a ramp. These devices accomplish the necessary task of distributing and mixing fuel into the supersonic cross-flow albeit via different strategies. Both of these devices were previously studied at lower flight Mach numbers where they exhibited promising performance in terms of mixing efficiency and total pressure recovery. For comparison, a flush-wall injector is also included. This type of injector generally represents the simplest method of introducing fuel into a scramjet combustor, however, at high flight Mach number conditions, the dynamic pressure needed to induce sufficient fuel penetration may be difficult to achieve along with other requirements such as achieving desired levels of fuel-to-air mixing at the required equivalence ratio. The three injectors represent the baseline configurations planned for the experiments. The current work discusses the mixing flow field behavior and differences among the three fuel injectors, mixing performance as described by the mixing efficiency and the total pressure recovery, and performance considerations based on the thrust potential.
Document ID
20160010332
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Drozda, Tomasz G. (NASA Langley Research Center Hampton, VA, United States)
Drummond, J. Philip (NASA Langley Research Center Hampton, VA, United States)
Baurle, Robert A. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2016
Publication Date
July 25, 2016
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NF1676L-23413
Meeting Information
Meeting: AIAA Propulsion and Energy Forum and Exposition
Location: Salt Lake, UT
Country: United States
Start Date: July 25, 2016
End Date: July 27, 2016
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 147016.02.07.05.03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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