MIT-World Peace University (MIT-WPU) is a top educational institute located in Pune, India. It is recognized within&nbsp;UGC under Government of Maharashtra Act No. XXXV 2017.&nbsp;

It is part of the MIT group of institutions (established in 1983) which covers 10+ campuses across India and has more than 50,000+ students enrolled across various disciplines at a given point of time. The institute houses 15 schools ranging from Engineering &amp; Technology, Design, Pharmacy, Commerce, Governance among others. It offers undergraduate, postgraduate and PhD programs among different disciplines.&nbsp;

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MIT World Peace University

World University root node

School of Mechanical Engineering

Engineering and Technology

Advances in Transdisciplinary Engineering

Investigation of Effect of Geometry on the Linear Behavior of Helical Compression Spring for Valve Applications

As the importance of hose reels is known in applications such as fire and safety systems, agricultural equipment, underwater diving equipment and oil industries, it is also worth observing the need of hose reels for applications involving the suction (negative) pressures. Some of the applications of negative pressures or vacuum include sewage and drainage cleaning systems, coal industries, cement industries and many more. So, it becomes of utmost importance to develop equipment that increase the convenience using vacuum for various applications. One such equipment for increasing the convenience for applications involving vacuum would be a hose reel. It is proposed to develop a hose reel that is acclimated to high vacuum pressures. The effect of different parameters associated with the seal materials and their effect on sealing performance using FEA tool will also be studied. © 2022 Wolters Kluwer Medknow Publications. All rights reserved.

Journal of Pharmaceutical Negative Results

Development of a Hose Reel (Swivel Joint) Suitable for High Suction Pressures

The use of conventional fiber (Glass/Carbon) reinforced polymer composites is not enough for many applications in modern world and hence hybrid polymer composites are required which can overcome the specific needs of various applications. In this study, farm-wastes are used to manufacture a hybrid composite which made it a cleaner material along with cost efficient one as well. Basalt reinforced sheep wool, paddy straw and bagasse based hybrid polymer composites with laminate structure were prepared using compression molding. Basalt fiber mats were kept on both sides of the mold and sheep wool content was varied in each composite sample. The composites then tested for their tensile, impact and thermal properties. The study on basalt-paddy straw-sheep wool and basalt-bagasse-sheep wool hybrid composites clearly brought out the effective use of waste material for producing value added product with improved properties. Varying of sheep wool also had optimum effect on these composites. Just 10% of sheep wool in these hybrid composites leads to more than 1.5 times improvement in tensile strength, 5 times increase in modulus, 3 times increase of elongation, and 2 times increase of charpy impact value at 20% sheep wool concentration. The thermal stability is also improved by 8–10 degrees as degradation temperature is increased. The sheep wool is more effective in basalt-paddy straw hybrid composite than the bagasse hybrid one. © 2022 The Authors

School of Polymer Engineering

Cleaner Materials

Tensile, impact and thermal properties of farm-waste based hybrid basalt polymer composites

Recently few countries have tested the scramjet engine for aerospace application. The challenge was to achieve complete combustion atsupersonic flow and to generate the required thrust for given inlet flow conditions. Research is still going on so as to attain the necessary mixing andefficient combustion inside a scramjet combustor. Performance parameter like total pressure loss across the scramjet combustor is one of the crucialparameters and has to be minimized. Factors such as equivalence ratio, inlet flow conditions affect the combustion process and hence the useful thrust.Also, the fuel injection configuration plays a vital role in mixing and thus on the performance of a scramjet combustor. Over the recent years numericalsimulation has been acknowledged as a promising tool for investigation of Scramjet flow. In this work, the investigation of effect of injector configuration hasbeen carried out using a commercial CFD tool. Validation of initial numerical results is done with existing experimental results in the available literature.Modified configurations were obtained by varying number of injection holes for same equivalence ratio. These cases were simulated to observe the rightbargain between combustion efficiency and total pressure loss. Conclusions are based on performance parameters like total pressure loss, combustionefficiency, top wall static pressure etc. Mass fraction contour plots of species are obtained to comment further on mixing and combustion performance.

International Journal Of Scientific & Technology Research

Numerical Investigation of Effect of Fuel Jet Configuration on Scramjet Combustor Performance

Constant area section length downstream to the fuel injection point is a crucial dimension of scramjet duct geometry. It has a major contribution in creating the maximum effective pressure inside the combustor that is required for propulsion. The length is limited by the thermal choking phenomenon, which occurs when heat is added in a flow through constant area duct. As per theory, to avoid thermal choking the constant area section length depends upon the inlet conditions and the rate of heat addition. The complexity related to mixing and combustion process inside the supersonic stream makes it difficult to predict the rate of heat addition and in turn the length. Recent efforts of simulating the reacting flow inside scramjet combustors are encouraging and can be useful in this regard. The presented work attempts to use simulation results of scramjet combustion for predicting the constant area section length for a typical scramjet combustor. Though the technique appears to be simple, in general it can be applied in the design of combustor ducts where thermal chocking needs to be avoided. A typical scramjet combustor geometry with isolator, constant area section, and diverging section with an intrusive fuel injection scheme from the available experimental work is modeled for simulation. Reacting simulations are done and validated with the available experimental results. The inlet conditions being those corresponding to a Mach 6 scramjet flight. One-dimensional analysis of frictionless flow through constant area ducts is used to calculate maximum possible enthalpy addition in the flow. For the given injector configuration and equivalence ratio of 0.34, the limiting length of constant area section to avoid thermal choking was obtained as 59 mm. The value of this limiting length obtained from simulation is verified. Comments are made about the method.