Research Work
Research Work
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Trapped Vortex Combustor
The energy sector is a major contributor to global greenhouse emissions, with a share of approximately 36 % across advanced economies. In comparison, the remaining 64 % are emitted from other sectors such as industry, mobility, and residential. For the last few decades, reducing carbon emissions in energy has been a challenge.
Of the conventional fossil-fuel generation technologies, gas turbines are the cleanest option. Instead of coal power plants, the use of natural gas-fired open-cycle gas turbines reduces specific carbon emissions by 25% to 50%. With the increase in population, the demand for energy resources will also increase. This will increase the load on the energy sector; if we continue to use hydrocarbon-based fuel, the carbon footprint will also increase.
In the long term, replacing natural gas fuel with hydrogen is a viable means of enabling carbon-neutral power plant operation. Additionally, blending natural gas and hydrogen can substantially lower carbon emissions. A trapped Vortex Combustor cavity is proposed as a viable combustion device. An extensive study has been done for Trapped Vortex Combustor for high combustion efficiency.
Liquid Jet in a Supersonic Cross Flow
The thin pylon has been found to be one of the most promising hypermixers, offering enhanced mixing of fuel with minimum pressure loss. In this study, the effect of pylon height and the angled injection on the liquid jet breakup and its effect on atomization in a free stream of Mach 1.71 has been studied experimentally. Acetone is used as the liquid medium to characterize the liquid jet injection in supersonic flow. Acetone is injected into the flow in the transverse direction behind the pylon at different mass flow rates for 3 different pylon geometries and 3 angled injection cases. The height of the pylon is varied (17.32 mm, 10 mm, 6 mm) and the injection angle is such that it impinges against the pylon wall at three different angles of 30°, 45°and 60°while maintaining the other geometrical features to be the same. The study included Schlieren imaging to find the effect of liquid injection and pylon on the compressible flow field, and Shadowgraphy visualization was employed to evaluate the jet disintegration and atomization; Mie Scattering visualization techniques were used for evaluating the lateral spread of liquid jet spray. Mathematical techniques such as temporal variance, POD, and DMD are used to analyze the temporal behavior of the jet spread. It is observed that the pylon height not only increases the penetration height but also has a significant effect on the jet breakup and atomization. The shear layer also plays a major role in jet atomization and penetration height. Angled injection cases were observed to perform better than transverse injections in terms of penetration height and jet spread.
Minimum Energy Launch Opportunity for Mars Orbiter Missions
An interplanetary mission is proposed to be launched by an Indian launch vehicle within the next decade. The research involves mission trajectory design. The work on trajectory design carried out is divided into three stages. In the first stage, it is required to find the launch opportunities, this has been achieved by minimizing the V∞ requirement using the patched conic technique. Four launch opportunities are studied for the mission: 2022 AD, 2024 AD, 2026 AD, and 2028 AD. In the second stage, orbital constraints were imposed on the mission due to the geographic location of the Indian Launch sites and the optimal trajectory of the launch vehicle. The launch opportunity is decided based on the minimum V∞ after imposing the optimum inclination constraints of 19.5◦ and 45◦and the optimum argument of Perigee achieved by the launch vehicle. In the third stage, a feasibility study is carried out with respect to the Indian launch vehicle in the context of the payload mass of the CubeSat constellation. The velocity impulse for the Trans-planetary injection, during the approach phase as well as the orbit reduction maneuvers, is obtained based on the constrained minimum V∞ and subsequently converted in terms of propellant mass requirements.
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