Ashish VASHISHTHA, Rushikesh KORE, Sasi Kiran PALATEERDHAM, Antonella INGENITO

DOI Number: N/A

Conference number: HiSST-2024-287

With the motivation of operating scramjet in shock induced combustion ramjet (shcramjet) or oblique detonation wave mode, the current study aims to develop strategies for non-premixed oblique detonation wave configuration using numerical simulations. The unsteady two-dimensional Reynolds Averaged Navier-Stokes with reactive multi-species equations are solved using adaptive grid refinement and robust SAGE solver on CONVERGE-CFD platform with detailed chemical kinetics. The sonic hydrogen injection cases (ϕ = 0.5) into incoming air flow at Mach 7 with pressure of 40 kPa and temperature of 300 K are simulated for 2 ms duration. The computational domain consists of finite length wedge (100 mm,
θw = 26◦ as well as hydrogen injection tube upstream of wedge starting point, to obtain non-premixed oblique detonation wave. The unsteady detonation wave patterns are obtained for angle of injection (AOI) 15◦ with injector location at (Dj=) 30 mm from wedge tip. It is found that various flow features, such as jet-shock, shear layer and hot burnt zone near the wedge wall affect the lifted detonation wave starting at the interaction point of shear layer and hot burnt zone. The detonation wave momentarily transition to deflagration flame and re-establish itself as detonation wave multiple times. The angle of injection (AOI) and injector locations are varied to obtain various patterns of unsteady non-premixed
oblique detonation wave and it was found that AOIs below or close to wedge angle lead to formation of unsteady oblique detonation wave, while AOIs higher than the wedge angle lead to formation of stable stretched deflagration flame. Injection location very close to wedge starting point leads to multi-cycle detonation to deflagration transitions and deflagration to detonation transitions. The overall thermal and combustion efficiencies are also compared with equivalent premixed hydrogen-air oblique detonation wave at same wedge angle.

Read the full paper here

In Categories: 1.Events, HiSST 2024, Propulsion Systems and Components
Email
Print
LinkedIn
The paper above was part of  proceedings of a CEAS event and as such the author has signed a publication agreement to have their paper published in the repository. In the case this paper is found somewhere else CEAS always links to the other source.  CEAS takes great care in making the correct content available to the reader. If any mistakes are found  in the listings please contact us directly at papers@aerospacerepository.org and we will correct the listing promptly.  CEAS cannot be held liable either for mistakes in editorial or technical aspects, nor for omissions, nor for the correctness of the content. In particular, CEAS does not guarantee completeness or correctness of information contained in external websites which can be accessed via links from CEAS’s websites. Despite accurate research on the content of such linked external websites, CEAS cannot be held liable for their content. Only the content providers of such external sites are liable for their content. Should you notice any mistake in technical or editorial aspects of the CEAS site, please do not hesitate to inform us.