Abstract

The improvement in ultra compact thermal power creation is constrained by the unavailability of fluid machinery sufficient for supersonic flow circumstances. Conservative turbine designs exhibit unacceptable performances related to large aerodynamic losses and a narrow operation range. This paper provides for the first time in the open literature the design procedure, and subsequent analysis of the turbine performance of a turbine satisfactory for supersonic axial pulsating flows, as those encountered in pioneering combustors. The design comes up to consider the most adverse condition, a steady inlet axial Mach number equal to 3.5. The possible turbine families were classified by the velocity triangles and discussed. An elementary issue in supersonic passages is to ensure the normal shock at the start of the engine is swallowed through the turbine passages, namely the turbine passage is started. To ensure self starting capability the turning is restricted to lower values than in the conventional subsonic turbines. The design procedure was based on the method of characteristics, converting the inlet uniform flow into a vortex flow field, such that the adequate deflection is inflicted to the supersonic flow. The presentation of the supersonic passage was first assessed and then compared to conservative designs. The present design procedure and analysis of unconventional supersonic turbines provides strategy for the plan and optimization of efficient elevated supersonic passages, fit to future tightly packed fluid machinery. Nadupuru Bhaskara Rao | Rajesh CVS | Uppada Komali "Design and Analysis of Revolutionary Elevated Supersonic Axial Turbines" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-2 | Issue-6 , October 2018, URL: http://www.ijtsrd.com/papers/ijtsrd18481.pdf

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