• Document: Turbine Blade Design of a Micro Gas Turbine
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International Journal of Innovations in Engineering and Technology (IJIET) Turbine Blade Design of a Micro Gas Turbine Bhagawat Yedla Vellore Institute of Technlogy, Vellore – 632014, India Sanchit Nawal Vellore Institute of Technlogy, Vellore – 632014, India Shreehari Murali Vellore Institute of Technlogy, Vellore – 632014, India Abstract- The introduction of small drones, missiles and small, made micro gas turbines fairly ubiquitous. The project refers to the design of a micro gas turbine blade. Micro gas turbines are smaller versions of Jet Engines typical used to propel aircrafts of medium to high sizes and capacity. The Blade is theoretically designed and further rendered in Solidworks 2014. CFD analysis has been carried out using ANSYS Fluent and ANSYS ICEM CFX, meshing done by ANSYS Mesh and results shown by CFX Post. Index Terms - Aero Foil, Blade, Camber, Turbine I. INTRODUCTION A turbine is a mechanical shaft energy producing turbomachine. They are divided into two types namely radial inflow turbine and axial flow turbines. Generally axial turbines are used for their efficiency and power to weight ratio. Micro gas turbines are smaller versions of larger jet engines and are typically used to power small scale turbo generators or even in the transmission axles of electric or hybrid vehicles. These turbines, along with heat and power cogeneration components, advancement in electronic supply and stability, can achieve efficiencies of above 80%. II. METHODOLOGY Design Constraints Every turbine is designed with respect to a certain preceding compressor design values or assumption. The blade is hence designed according to these certain initial values. Power demanded by the compressor Pw = 230000 J/kg Blade speed U = 440 m/s Flow Coefficient Φ = 0.7 Reaction ratio R = 0.4 Axial velocity component Cx =307 m/s Inlet stagnation temperature T01 = 1300K Inlet stagnation pressure P01 = 9.8 bar Free vortex design Specific heat ratio γ =1.32 Specific heat constant Cp =1.178 kJ/kg Target efficiency η = 0.95 Volume 7 Issue 3 October 2016 154 ISSN: 2319 - 1058 Volume 6 Issue 4 April 2016 Volume 6 Issue 4 April 2016 International Journal of Innovations in Engineering and Technology (IJIET) Final Calculated Values For Blade Angle Tanα2 =ΔW/U Cx =307 m/s α2 = 59.492° C2 = 606.85 m/s M2 = 0.894 Mach Since α2 = 0° tanβ3 = U/Cx= 1/Φ =1/0.7 β3 =55.00° tanβ2= tanβ3-2R/Φ = 0.28 β2= 15.945° W3 = 307/cos55 =535.238 m/s C2= 307/cos 59.492 =604.73 m/s T2= T01-C2 /2Cp = 1300- 6042/2x1200 =1149.99K M2 = 0.9185 @1150K For Nozzle Area A2 = m/(ρ2CX) P2/P01 =(T2s / T01)/ηn P2 = 584.549 kPa CX =307m/s Since α3=0 P3 =4.3013 bar A =0.02684m2 Mass flow rate=A*ρCx=14.5 kg/m2 Exit Mach number M=C3 / √ (γRT3) =0.4847 α1 =0° α2 =59.492° α3 =0° β2 =15.945 ° β3 =55.09° α2h =67.350 ° α2m =59.492° α2t =51.945° β2h =33.498° β2m =15.945° β2t =-0.4349° β3h =52.108° β3m =55.09° β3t =57.693° Hst1 = 21mm Hst2 =27 mm Hst3 = 32 mm bstator = 25mm brotor =30mm Nstator = 50 Nrotor = 45 blades Mean diameter = 292.86 mm Torque = Power/angular velocity = 230000/ 2034.48 = 113.05 Nm Net tangential force = Torque/Mean Radius = 113.05/ 0.14 = 807.5 N Force on one Blade = Net force/Number of blades = 807.5/50 = 16.15 N Figures Pw Power U Blade speed Φ Flow Coefficient Volume 7 Issue 3 October 2016 155 ISSN: 2319 - 1058 Volume 6 Issue 4 April 2016 Volume 6 Issue 4 April 2016 International Journal of Innovations in Engineering and Technology (IJIET) R Reaction ratio Cx Axial velocity component T01 Inlet stagnation temperature P01 Inlet stagnation pressure γ Specific heat ratio Cp Specific heat constant η Effici

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