Effect of Tip Configurations on Aerodynamic Performance of Variable Geometry Linear Turbine Cascade
-
Guoqiang Yue
,
Qun Zheng
Abstract
The variable geometry turbine (VGT) has been widely used in different fields due to its higher efficiency and lower fuel consumption at part-load. However, the flow field in a VGT is characterized by the leakage flow through the radial clearance of rotational vane compared with a general fixed vane turbine. Numerical simulations are conducted on a linear turbine cascade to reduce the leakage flow based on passive control method. The aerodynamic performances and flow fields are compared for four kinds of tip configuration firstly. Then, the effect of variable geometry on the linear turbine cascade aerodynamic performance is investigated for five installation angles ranging from –5 to 5 deg. In addition, the development patterns and trends of the tip leakage vortex and the passage vortex are analyzed. The results show that the squealer tip and the rotating axis have a significant impact on suppressing leakage flow. The leakage flow rate has a tendency to decrease, and the total pressure coefficient is gradually increased when installation angle ranges from –5 to 5 deg. The interactions between tip leakage vortex and passage vortex leads to the different trends on leakage flow at various installation angles and axial sections.
Funding statement: The authors wish to thank the support of Fundamental Research Funds for the Central Universities (No: HEUCF160305).
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© 2019 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Design of a Compact Crossover Diffuser for Micro Gas Turbines Using a Mean-Line Code
- Parametric Modeling and Dynamic Characteristics Analysis of a Power Turbine Rotor System
- Operation Study of Miniature Air-blast Atomizer under Very Low Liquid Pressures
- Investigation on the Time Error of Detonation Acoustic in Process of Formation and Propagation
- Experimental Investigation of Pressure Fluctuations on Inner Wall of a Centrifugal Pump
- Numerical Analysis of Exhaust Emission from an Aero Gas Turbine Combustor under Fuel-Rich Condition
- Film Cooling Mechanism of Combined Hole and Saw-tooth Slot
- A Multi-Regulator Linear Matrix Inequalities Approach for Aircraft Engine Limit Management
- Direct Numerical Simulation of Turbine Cascade Flow with Heat Transfer
- Effect of Tip Configurations on Aerodynamic Performance of Variable Geometry Linear Turbine Cascade
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Design of a Compact Crossover Diffuser for Micro Gas Turbines Using a Mean-Line Code
- Parametric Modeling and Dynamic Characteristics Analysis of a Power Turbine Rotor System
- Operation Study of Miniature Air-blast Atomizer under Very Low Liquid Pressures
- Investigation on the Time Error of Detonation Acoustic in Process of Formation and Propagation
- Experimental Investigation of Pressure Fluctuations on Inner Wall of a Centrifugal Pump
- Numerical Analysis of Exhaust Emission from an Aero Gas Turbine Combustor under Fuel-Rich Condition
- Film Cooling Mechanism of Combined Hole and Saw-tooth Slot
- A Multi-Regulator Linear Matrix Inequalities Approach for Aircraft Engine Limit Management
- Direct Numerical Simulation of Turbine Cascade Flow with Heat Transfer
- Effect of Tip Configurations on Aerodynamic Performance of Variable Geometry Linear Turbine Cascade
