Study of Transitional Flow Through a Low-Pressure Turbine Cascade by Application of Higher-Order Compact-Difference Scheme to Large-Eddy Simulation

2006 ◽  
Author(s):  
Shirdish Poondru ◽  
Urmila Ghia ◽  
Karman Ghia
Keyword(s):  
Large Eddy Simulation ◽  
Difference Scheme ◽  
Transitional Flow ◽  
Turbine Cascade ◽  
Compact Difference Scheme ◽  
Low Pressure Turbine ◽  
Compact Difference ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Flow Through

Large-Eddy Simulation of Transitional Flow Through a Low-Pressure Turbine Cascade

2006 ◽  
Author(s):  
Shirdish Poondru ◽  
Urmila Ghia ◽  
Karman Ghia
Keyword(s):  
Large Eddy Simulation ◽  
Air Force ◽  
Time Integration ◽  
Low Pressure ◽  
Transitional Flow ◽  
Low Pressure Turbine ◽  
Compact Difference ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Flow Through

Subsonic, transitional flow through a low-pressure turbine (LPT) cascade is investigated using high-order compact difference scheme in conjunction with large-eddy simulation (LES). Three-dimensional simulations are performed at chord inlet Reynolds numbers (Re) of 25,000 and 50,000. The inlet Mach number is approximately 0.06. An MPI-based higher-order accurate, Chimera version of the FDL3DI flow solver developed by the Air Force Research Laboratory at Wright Patterson Air Force base, is extended for the present turbomachinery application. The implicit solver is based on an approximate factored time-integration method of Beam and Warming. Fourth-order compact-difference formulations are used for discretizing spatial derivatives in conjunction with sixth-order non-dispersive filtering. Solutions are obtained both with and without a sub-grid scale (SGS) model. A dual topology, 16-block, structured grid generated using GridPro is utilized for all simulations. The flow features are examined, and the results for both LES approaches are compared to each other, and with experimental data.

Large Eddy Simulation of a Low Pressure Turbine Cascade

2003 ◽  
Author(s):  
Yoshinori Ooba ◽  
Hidekazu Kodama ◽  
Chuichi Arakawa ◽  
Yuichi Matsuo ◽  
Hitoshi Fujiwara ◽  
...  
Keyword(s):  
Large Eddy Simulation ◽  
Low Pressure ◽  
Turbine Cascade ◽  
Low Pressure Turbine ◽  
Eddy Simulation ◽  
Large Eddy

Large Eddy Simulation of Secondary Flows in an Ultra-High Lift Low Pressure Turbine Cascade at Various Inlet Incidences

2020 ◽  
Vol 37 (2) ◽  
pp. 195-207
Author(s):  
Site Hu ◽  
Chao Zhou ◽  
Shiyi Chen
Keyword(s):  
Large Eddy Simulation ◽  
Engine Performance ◽  
Low Pressure ◽  
Secondary Flows ◽  
Turbine Cascade ◽  
High Lift ◽  
Blade Loading ◽  
Low Pressure Turbine ◽  
Eddy Simulation ◽  
Large Eddy

AbstractIncreasing the blade loading of a low pressure turbine blade decreases the number of blades, thus improving the aero-engine performance in terms of the weight and manufacture cost. Many studies focused on the blade-to-blade flow field of ultra-high lift low pressure turbines. The secondary flows of ultra-high lift low pressure turbines received much less attention. This paper investigates the secondary flows in an ultra-high lift low pressure turbine cascade T106C by large eddy simulation at a Reynolds number of 100,000. Both time-averaged and instantaneous flow fields of this ultra-high lift low pressure turbine are presented. To understand the effects of the inlet angle, five incidences of ‒10°, ‒5°, 0, +5° and +10° are investigated. The case at the design incidence is analyzed first. Detailed data is used to illustrate the how the fluids in boundary layers develops into secondary flows. Then, the cases with different inlet incidences are discussed. The aerodynamic performances are compared. The effect of blade loading on the vortex structures is investigated. The horseshoe vortex, passage vortex and the suction side corner vortex are very sensitive to the loading of the front part of the blade.

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