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Rotating Turbine Rig, Heat Transfer, Film Cooling

Rotating Turbine Rig, Heat Transfer, Film Cooling. Facility: A new two-loop turbine specially designed for Film cooling/heat tarassfer measurement under rotating condition. Instrumentation used: Pressure Sensitive paints (PSP) for film cooling effectiveness measurement

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Rotating Turbine Rig, Heat Transfer, Film Cooling

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  1. Rotating Turbine Rig, Heat Transfer, Film Cooling • Facility: A new two-loop turbine specially designed for • Film cooling/heat tarassfer measurement under rotating condition. • Instrumentation used: • Pressure Sensitive paints (PSP) for film cooling effectiveness measurement • Temperature sensitive paints (TSP) for heat transfer measurement TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  2. Rotating Turbine Rig, Aero-Performance Research Capability Following figures give you an idea about the rotating turbine Aero-performance research capability The turbine facility is designed to address aerodynamics, heat transfer and performance issues under rotating condition. The facility with its components is shown below schematically. TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  3. Turbine Rotor Specially Designed for Heat Transfer and Film Cooling Rotor has two loops: an Internal cooling loop for purge flow through an inclined circumferential slot and an external loop for platform film cooling/heat transfer Experiments. . TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  4. Coolant Injection Through Gap • Cross sectional view of the slot ahead of the 1st stage rotor • Coolant enters the plenum through the hollow shaft and exits the slot at 25º to the horizontal. TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  5. Coolant Injection Film Cooling Holes on Hub Platform Rotor ROTOR STATOR Passage Vortex GAP u Stator Coolant injection from discrete Holes Turbine 1st Stage Rotor platform and Flow Schematics Downstream Film Cooling Holes Injection TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  6. Using Pressure Sensitive Paints (PSP) for Film Cooling EffectivenessMeasurement • Block diagram of the experimental facility TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  7. PSP - Calibration Calibration for Temp. range = 22.2oC to 60.1oC Fig. 6 Calibration Curve for PSP PC Camera Strobe light Green light to excite PSP Thermocouple Vacuum Pump Red light emitted from PSP PSP coated test sample Vacuum Chamber Heater for Temperature Control TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  8. Boundary Condition and Sample Results Turbine Stage Operating Conditions • 1st Rotor • Inlet Velocity = 35.8 m/s • Inlet Mach Number = 0.1 • Inlet Temperature = 46°C • Exit Velocity = 107 m/s • Exit Mach Number = 0.3 • Exit Temperature = 43°C • Re = 2.0*105 (axial chord length and exit velocity) • Inlet Total – to – Exit Pressure Ratio = 1.4 • Angular Velocity = 2400 rpm , 2550 rpm, 3000 rpm • Stator-Rotor Ejection: Cooling Flow ~ 0.5% to 2% of Mainstream • Platform Film Cooling: Blowing Ratio (M=rcVc/r∞V∞) ~ 0.5 to 2 • Density Ratio (DR=rc/r∞) = 1 (N2 Injection) TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  9. Results PS PS PS SS SS SS M=1.25 M=0.75 M=1.00 PS PS PS SS SS SS M=2.00 M=1.75 M=1.50 MeasuredFilm Cooling Effectiveness on the Rotating Platform using PSP – Downstream Discrete Hole Injection M=ρcVc/ ρ∞V∞ ; MFR=(msc/ ms) Pitchwise Averaged Film Cooling Effectiveness at 2400rpm – Effect of Blowing ratio 2400 rpm TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  10. Results PS PS PS SS SS SS M=1.25 M=0.75 M=1.00 PS PS PS SS SS SS M=2.00 M=1.75 M=1.50 MeasuredFilm Cooling Effectiveness on the Rotating (Reference Point) Platform using PSP – Downstream Discrete Hole Injection M=ρcVc/ ρ∞V∞ ; MFR=(msc/ ms) Pitchwise Averaged Film Cooling Effectiveness at 2550rpm – Effect of Blowing ratio 2550 rpm TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  11. Results PS PS PS SS SS SS M=1.25 M=0.75 M=1.00 PS PS PS SS SS SS M=2.00 M=1.75 M=1.50 MeasuredFilm Cooling Effectiveness on the Rotating Platform using PSP – Downstream Discrete Hole Injection M=ρcVc/ ρ∞V∞ ; MFR=(msc/ ms) Pitchwise Averaged Film Cooling Effectiveness at 3000rpm – Effect of Blowing ratio 3000 rpm

  12. Results Pitchwise AveragedFilm Cooling Effectiveness on the Rotating Platform using PSP – Downstream Film Cooling Hole Injection M=ρcVc/ ρ∞V∞ ; MFR=(msc/ ms) Pitchwise Averaged Film Cooling Effectiveness– Effect of Rotor Speed

  13. Results MeasuredFilm Cooling Effectiveness on the Rotating Platform using PSP – Upstream Stator- Rotor Injection Through Circumferential Slot Only 3000 rpm 2550 rpm 2400 rpm TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  14. Combination of Slot and Hole Injections Rotor Passage Vortex GAP ROTOR u STATOR Stator Coolant injection from discrete holes Coolant injection through Stator-Rotor Seal Turbine 1st Stage Rotor platform and Flow Schematics for Combined Upstream Stator- Rotor Gap Injection and Downstream Film Cooling Holes Injection TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  15. Results PS SS MFR=1.00% M=1.25 MeasuredFilm Cooling Effectiveness on the Rotating Platform using PSP – Combined Upstream Stator- Rotor Gap Injection and Downstream Film Cooling Hole Injection 2400 rpm M=ρcVc/ ρ∞V∞ ; MFR=(msc/ ms) PS PS SS SS MFR=1.00% M=0.75 MFR=1.00% M=1.00 Pitchwise Averaged Film Cooling Effectiveness at 2400rpm – Effect of Blowing ratio TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

  16. Results MeasuredFilm Cooling Effectiveness on the Rotating Platform using PSP – Combined Upstream Stator- Rotor Gap Injection and Downstream Film Cooling Hole Injection 3000 rpm M=ρcVc/ ρ∞V∞ ; MFR=(msc/ ms) PS PS SS SS MFR=1.00% M=0.75 MFR=1.00% M=1.00 PS SS MFR=1.00% M=1.25 Pitchwise Averaged Film Cooling Effectiveness at 3000rpm – Effect of Blowing ratio TPFL: The Turbomachinery Performance and Flow Research Laboratory Texas A&M University M. T. Schobeiri

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