Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
-
Yuting Jiang
,
Hongfei Lin
Abstract
The part-load performance of gas turbine is of great importance due to the consideration of running time spent at part power, and Variable Geometry Turbine (VGT) is an important way to meet the requirements. Effect of variable geometry guide-vane with cylindrical endwalls on part-load turbine stage performance is quantified by detailed analysis of aerodynamic characteristics. The turbine stage characteristics of corrected mass flow, corrected output power and efficiency are presented to investigate the VGT performance under the condition of four off-design rotating angles. In addition, the flow field, the loss distribution and the leakage flow are analyzed for different rotating angles. Results show that both the corrected mass flow and the corrected output power increase as the vane throat area is increased, the total leakage area and the shroud area are increased with the increase of rotating angle, whereas the hub leakage area is decreased, and the total pressure loss and the entropy change of variable geometry vane are both increased with the decrease of vane throat area.
Copyright Reminder
None declared.
Nomenclature
- Gin
Inlet mass flow rate [kg/s]
- n
Rotational speed [rpm]
- N
Output power [kW]
- pt1
Inlet total pressure [pa]
- R
The radius of gyration [m]
- s
Static entropy [J/kg·K]
- Tt1
Inlet total temperature [K]
- x
x direction
- y
y direction
- z
z direction
- α
The rotation angle [deg]
- β
The angle for position 2 [deg]
- γ
The angle for position 1 [deg]
Acknowledgements
The authors wish to thank the support of National Natural Science Foundation of China (No. 51741901), Natural Science Foundation of Heilongjiang Province of China (No. QC2017047) and Fundamental Research Funds for the Central Universities (No. HEUCFJ170303).
References
1. Yue GQ, Lin HF, Jiang YT, Dong P. Effect of tip configurations on aerodynamic performance of variable geometry linear turbine cascade. Int J Turbo Jet-Engines. 2017.10.1515/tjj-2017-0001Search in Google Scholar
2. Yue GQ, Yin SQ, Zheng Q. Numerical simulation of flow fields of variable geometry turbine with spherical endwalls or nonuniform clearance. ASME paper, paper No. GT2009-59737, 2009.10.1115/GT2009-59737Search in Google Scholar
3. Haglind F. Variable geometry gas turbines for improving the part-load performance of marine combined cycles – gas turbine performance. Energy. 2010;35:562–70.10.1016/j.energy.2009.10.026Search in Google Scholar
4. Haglind F. Variable geometry gas turbines for improving the part-load performance of marine combined cycles – combined cycle performance. Appl Thermal Eng. 2011;31:467–76.10.1016/j.applthermaleng.2010.09.029Search in Google Scholar
5. Chen S, 2010. The experimental research and numerical simulation of variable geometry linear turbine cascade. Master thesis.Search in Google Scholar
6. Srithar R, Ricardo MB. Variable geometry mixed flow turbine for turbochargers: an experimental study. Int J Fluid Machinery Syst. 2008;1:155–68.10.5293/IJFMS.2008.1.1.155Search in Google Scholar
7. 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
8. Vlaskos I, Christensen HH, Codan E, Bulaty T. Turbocharging of gas engines with variable geometry ABB turbochargers. 1st Dessau Gas Engine Conference, 10-11 June 1999, Dessau, Germany, 1999:145–60.Search in Google Scholar
9. Vlaskos I, Seiler M, Schulz J. ABB TPL65 turbocharger with variable turbine geometry for medium-speed diesel engines. 7th ImechE Conference on Turbochargers and Turbocharging, London UK, 2002:75–87.10.1115/ICEF2002-524Search in Google Scholar
10. Baets J, Bernard O, Gamp T, Zehnder M. Design and performance of ABB turbocharger TPS57 with variable turbine geometry. 6th International Conference on Turbocharging and Turbochargers, Institution of Mechanical Engineers, London UK, 1998:315–25.Search in Google Scholar
11. Ishino M, Bessho A. Mixed-flow variable nozzle turbine. R&D Rev Toyota CRDL. 2000;35:1–25.Search in Google Scholar
12. 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
13. Qiu C, Song HF. Loss research of variable geometry turbine. Gas Turbine Technol. 2007;20:39–42.Search in Google Scholar
14. Lakshminarayana B, Tallman J. Methods for desensitizing tip clearance effects in turbines. ASME GT2001-0486, 2001.Search in Google Scholar
15. Ainley DG, Mathieson GC. A method of performance estimation for axial flow turbines. British ARC, R&M 2974, 1951.Search in Google Scholar
16. Dunham J, Came PM. Improvement to the Ainley/Mathieson method of turbine performance prediction. ASME J Eng Power. 1970;92:252–56.10.1115/1.3445349Search in Google Scholar
17. Craig HR, Cox HJ. Performance estimation of axial flow turbines. ARCHIVE Proc Inst Mech Eng. 1971;185:407–24.10.1243/PIME_PROC_1970_185_048_02Search in Google Scholar
18. Denton JD. Throughflow calculations for transonic axial flow turbines. ASME J Eng Power. 1978;100:212–18.10.1115/1.3446336Search in Google Scholar
19. Jesus GS, Barbosa JR, Ramsden KW, “A comparison of loss models using different radial distribution of loss in an axial turbine streamline curvature program”, ASME paper, paper No. GT2007-27641, 2007.10.1115/GT2007-27641Search in Google Scholar
20. Takagi T. Investigation of the aerodynamic performance of a transonic axial-flow turbine with variable nozzle. Bull JSME. 1985;28:2332–40.10.1299/jsme1958.28.2332Search in Google Scholar
21. AEA Technology, ANSYS CFX User Documentation, 2010.Search in Google Scholar
© 2018 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
Articles in the same Issue
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
