Final Design Geometry Selection
- 1. Final Design Geometry Using Inward Flow Radial Turbine Theory
- 2. Final Design Geometry • Once the vane profile was chosen we had to choose the number of vanes, angle and arrangement for the optimum performance • Using turbine theory for radial turbochargers we could account for: o Shock Effects o Throat Area o Number of Vanes o Vane Angle o Gas Angle o Incidence Angle
- 3. Final Design Geometry • To chose the final design we calculated gas angles for different quantities of vanes, this resulted in 18 vanes in the final design when comparing to the original design 60 62 64 66 68 70 72 74 76 78 80 3.5 4.5 5.5 6.5 7.5 8.5 9.5 FinalFlowAngle(α4) Height of the Vane channel due to different Rack Positions (mm) Gas Angle at Rotor Inlet for Different Rack Positions Holset HY40-V NACA 0008, 14 Vanes NACA 0008 15 Vanes NACA 0008 16 Vanes NACA 0008 17 Vanes NACA 0008 18 Vanes
- 4. Final Design Geometry • These 18 vanes then had the positions altered and we again calculated the gas angles to match the original conditions • This resulted in a 1mm position shift away from the rotor 60 62 64 66 68 70 72 74 76 78 80 3.5 4.5 5.5 6.5 7.5 8.5 9.5 FinalFlowAngle(α4) Height of the Vane channel due to different Rack Positions (mm) Gas Angle at Rotor Inlet for Different Rack Positions Holset HY40-V 18 Vanes -1 mm 18 Vanes, +2mm 18 Vanes + 1mm 18 Vanes - 2mm 18 Vanes (Holset Position)
- 5. Final Design Geometry • Our final design had 18 vanes, set an additional 1mm distance from the rotor (compared to the HY40V). The superior aerodynamic performance of our vanes would lead to greater overall performance.