Taguchi Based Regression Analysis of End-Wall Film Cooling in a Gas Turbine Cascade with Single Row of Holes
-
D. Ravi
und
K. M. Parammasivam
Abstract
Numerical investigations were conducted on a turbine cascade, with end-wall cooling by a single row of cylindrical holes, inclined at 30°. The mainstream fluid was hot air and the coolant was CO2 gas. Based on the Reynolds number, the flow was turbulent at the inlet. The film hole row position, its pitch and blowing ratio was varied with five different values. Taguchi approach was used in designing a L25 orthogonal array (OA) for these parameters. The end-wall averaged film cooling effectiveness (
Nomenclature
- Ch
Chord of the blade profile, m
- D
Film hole diameter, m
- H
Blade height, m
- L
Film Hole length, m
- HSV
Horse shoe vortex
- LE
Leading edge of the blade
- M
Blowing ratio
- Ma
Mach number
- P
Blade pitch in the cascade, m; Film hole pitch, m; Pressure, Pa
- PS
Pressure side of the blade
- Re
Reynolds number, refer eq. (1)
- S
Distance along the blade profile from LE to TE
- SS
Suction side of the blade
- T
Temperature of fluid/wall, K
- TE
Trailing edge of the blade
- Greek symbols
- α
Film hole inclination angle, deg.
- γ
Film hole orientation angle, deg.
- ρ
Density, kg/m3
- η
Adiabatic film cooling effectiveness, refer eq. (2)
Uncertainty
- Subscripts
- c
Coolant
- m
Mainstream
- w
Wall
- f
Film
- p
Pitch wise
- Superscripts
- *
Dimensionless value of a parameter, refer eq. (3)
- –
Averaged property being discussed
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©2016 by De Gruyter
Artikel in diesem Heft
- Frontmatter
- Experimental Investigation on the Ignition Delay Time of Plasma-Assisted Ignition
- Effect of Inlet Clearance on the Aerodynamic Performance of a Centrifugal Blower
- Alternative Method to Simulate a Sub-idle Engine Operation in Order to Synthesize Its Control System
- Aerodynamic Design and Numerical Analysis of Supersonic Turbine for Turbo Pump
- A Comparison of Hybrid Approaches for Turbofan Engine Gas Path Fault Diagnosis
- Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm
- Taguchi Based Regression Analysis of End-Wall Film Cooling in a Gas Turbine Cascade with Single Row of Holes
- Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime
Artikel in diesem Heft
- Frontmatter
- Experimental Investigation on the Ignition Delay Time of Plasma-Assisted Ignition
- Effect of Inlet Clearance on the Aerodynamic Performance of a Centrifugal Blower
- Alternative Method to Simulate a Sub-idle Engine Operation in Order to Synthesize Its Control System
- Aerodynamic Design and Numerical Analysis of Supersonic Turbine for Turbo Pump
- A Comparison of Hybrid Approaches for Turbofan Engine Gas Path Fault Diagnosis
- Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm
- Taguchi Based Regression Analysis of End-Wall Film Cooling in a Gas Turbine Cascade with Single Row of Holes
- Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime
