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).
References
1. Haglind F. Variable geometry gas turbines for improving the part-load performance of marine combined cycles – gas turbine performance. Energy 2010;35:562–570.10.1016/j.energy.2009.10.026Search in Google Scholar
2. Haglind F. Variable geometry gas turbines for improving the part-load performance of marine combined cycles – combined cycle performance. Appl Thermal Eng 2011;31:467–476.10.1016/j.applthermaleng.2010.09.029Search in Google Scholar
3. Chen S. The experimental research and numerical simulation of variable geometry linear turbine cascade, Master thesis, 2010.Search in Google Scholar
4. Yue GQ, Yin SQ, Zheng Q. Numerical simulation of flow fields of variable geometry turbine with spherical endwalls or nonuniform clearance. ASME paper, paper GT2009-59737, 2009.10.1115/GT2009-59737Search in Google Scholar
5. Srithar R, Ricardo MB. Variable geometry mixed flow turbine for turbochargers: an experimental study. Int J Fluid Machinery Syst 2008;1:155–168.10.5293/IJFMS.2008.1.1.155Search in Google Scholar
6. Galinto J, Tiseira A, Faiardo P, Garcia-Cuevas LM. Development and validation of a radial variable geometry turbine model for transient pulsating flow applications. Energy Convers Manage 2014;85:190–203.10.1016/j.enconman.2014.05.072Search in Google Scholar
7. Chen S, Qiu C, Song HF. Numerical simulation on variable geometry linear turbine cascades by CFD. Gas Turbine Technol 2010;24:32–36.Search in Google Scholar
8. Qiu C, Song HF. Loss research of variable geometry turbine. Gas Turbine Technol 2007;20:39–42.Search in Google Scholar
9. Rains DA. Tip clearance flows in axial flow compressors and pumps. Ph.D. thesis.10.21236/AD0037339Search in Google Scholar
10. Moore J, Moore JG, Herny GS, Chaudhry U. Flow and heat transfer in turbine tip gaps. J Turbomachinery 1989;111:301–309.10.1115/1.3262269Search in Google Scholar
11. Ameri AA, Steinthorsson E, Rigby DL. Effect of squealer tip on rotor heat transfer and efficiency. J Turbomachinery 1998;120:753–759.10.1115/1.2841786Search in Google Scholar
12. Azad GM, Han JC, Bunker RS. Effect of squealer geometry arrangement on a gas turbine blade tip heat transfer. ASME J Heat Transfer 2002;124:452–459.10.1115/1.1471523Search in Google Scholar
13. Prakash C, Lee CP, Cherry DG. Analysis of some improved blade tip concepts. J Turbomachinery 2006;128:639–642.10.1115/1.2220050Search in Google Scholar
14. Camci C, Dey D, Kavurmacioglu L. Tip leakage flows near partial squealer rims in an axial flow turbine stage. ASME paper GT2003-38979, 2003.10.1115/GT2003-38979Search in Google Scholar
15. Acharya S, Yang H, Prakash C. Numerical study of flow and heat transfer on a blade tip with different leakage reduction strategies. ASME paper GT2003-38617, 2003.10.1115/GT2003-38617Search in Google Scholar
16. AEA Technology, ANSYS CFX User Documentation 2010.Search in Google Scholar
17. Yamamoto A. Endwall flow/loss mechanisms in a linear turbine cascade with blade tip clearance. J Turbomachinery 1989;111:264–275.10.1115/1.3262265Search in Google Scholar
© 2019 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- 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
Articles in the same Issue
- 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
