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- W2563804481 abstract "The research paper is a design study to reduce multiple stages of High Pressure Turbine (HPT) to maintain the same thrust - to - weight ratio of gas turbines. This current approach of gas turbine design is to reduce cost and weight of the component. The preliminary design for the turbomachinery features three different gas turbines such as AL-2LF-3, GT - 26, and SK30 - GT. The research survey used to fulfill this task is an Advance Mathematical Modeling Principles; based on the Inlet Annulus Design Analysis, Prediction of Turbine Efficiency using Smith's Efficiency Correlation Chart, Design Analysis for the Outlet Annulus and a design study for Turbine Free Vortex. The ability to determine this aerodynamic geometry of the HPT stage(s) of gas turbine is the peak of the research. Nevertheless, study results revealed that a single stage HPT deriving a corresponding compressor can produce the same and needed aerodynamic performance of the gas turbine. Thus, all conditions required in the design of HPT stage were met having turbine stage efficiency within the range of 1.0 < (ΔH/U 2 ) < 2.5 and 0.5 < (Va/U) < 0.8; fulfilling Smith's Efficiency Prediction Law. A corresponding Mach number for the three engines of study are 0.51, 0.46 and 0.52 respectively. This is a clear indication to prevent the choking condition of the compressible flow at the minimum area along the duck of the gas turbine." @default.
- W2563804481 created "2017-01-06" @default.
- W2563804481 creator A5051445047 @default.
- W2563804481 date "2014-01-01" @default.
- W2563804481 modified "2023-09-26" @default.
- W2563804481 title "Design Study for Single Stage High Pressure Turbine of Gas Turbine Engines" @default.
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- W2563804481 hasPublicationYear "2014" @default.
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