Off-Design Analysis of Transonic Bypass Fan Systems Using Streamline Curvature Through-Flow Method
-
Sercan Acarer
und
Ünver Özkol
Abstract
The two-dimensional streamline curvature through-flow modeling of turbomachinery is still a key element for turbomachinery preliminary analysis. Basically, axisymmetric swirling flow field is solved numerically. The effects of blades are imposed as sources of swirl, work input/output and entropy generation. Although the topic is studied vastly in the literature for compressors and turbines, combined modeling of the transonic fan and the downstream splitter of turbofan engine configuration, to the authors’ best knowledge, is limited. In a prior study, the authors presented a new method for bypass fan modeling for inverse design calculations. Moreover, new set of practical empirical correlations are calibrated and validated. This paper is an extension of this study to rapid off-design analysis of transonic by-pass fan systems. The methodology is validated by two test cases: NASA 2-stage fan and GE-NASA bypass fan case. The proposed methodology is a simple extension for streamline curvature method and can be applied to existing compressor methodologies with minimum numerical effort.
Funding statement: The author(s) received no financial support for the research, authorship, and/or publication of this article.
Acknowledgements
Authors would like to thank Tusaş Engine Industries (TEI) for their support for this work.
References
1. Cumpsty NA. Compressor aerodynamics, 5th ed. Florida, USA: Krieger Publishing Company, 2004.Suche in Google Scholar
2. Shahpar S. Optimisation strategies used in turbomachinery design from an industrial perspective. VKI Lecture Series, 2010.Suche in Google Scholar
3. Wu CH. A general theory of three-dimensional flow in subsonic and supersonic turbomachines of axial, radial and mixed-flow types. NACA TN-2604, 1952.10.1115/1.4016114Suche in Google Scholar
4. Smith LH. The radial-equilibrium equations of turbomachinery. J Eng Power 1966;88:1–12.10.1115/1.3678471Suche in Google Scholar
5. Novak RA. Streamline curvature computing procedures for fluid flow problems. Trans ASME J Eng Power 1967;89:478–90.10.1115/1.3616716Suche in Google Scholar
6. Denton J. Throughflow calculations for transonic axial flow turbines. J Eng Power 1978;100:212–8.10.1115/1.3446336Suche in Google Scholar
7. Tiwari P, Stein A, Lin Y. Dual-solution and choked flow treatment in a streamline curvature throughflow solver. Proceedings of ASME Turbo Expo 2011, Vancouver, Canada, 2011.10.1115/GT2011-46545Suche in Google Scholar
8. Marsh H. A digital computer program for the through-flow fluid mechanics in an arbitrary turbomachine using a matrix method. British Aeronautical Research Council Reports and Memoranda R. & M. No. 3509, 1968.Suche in Google Scholar
9. Hirsch C, Warzee G. An integrated quasi-3D finite element calculation program for turbomachinery flows. J Eng Power 1979;101:141–8.10.1115/1.3446435Suche in Google Scholar
10. Petrovic M, Wiedermann A, Banjac M. Development and validation of a new universal through flow method for axial compressors. Proceedings of ASME Turbo Expo 2009, Orlando, USA, 2009.10.1115/GT2009-59938Suche in Google Scholar
11. Spurr A. The prediction of 3D transonic flow in turbomachinery using a combined throughflow and blade-to-blade time marching method. Int J Heat Fluid Flow 1980;2:189–99.10.1016/0142-727X(80)90013-2Suche in Google Scholar
12. Sturmayr A. Evolution of a 3D structured Navier-Stokes solver towards advanced turbomachinery applications. PhD Thesis, University of Vrije, 2004.Suche in Google Scholar
13. Taddei SR, Larocca F, Bertini F. Euler inverse axisymmetric solution for design of axial flow multistage turbomachinery. Proceedings of ASME Turbo Expo 2010, Glasgow, UK, 2010.Suche in Google Scholar
14. Gu F, Anderson M. CFD-based throughflow solver in a turbomachinery design system. Proceedings of ASME Turbo Expo 2007, Montreal, Canada, 2007.10.1115/GT2007-27389Suche in Google Scholar
15. Simon J. Contribution to throughflow modeling for axial-flow turbomachines. PhD Thesis, University of Liege, 2007.Suche in Google Scholar
16. Casey M, Robinson C. A new streamline curvature throughflow method for radial turbomachinery. Proceedings of ASME Turbo Expo 2008, Berlin, Germany, 2008.10.1115/GT2008-50187Suche in Google Scholar
17. Lieblein S, Roudebush WH. Theoretical loss relations for low-speed two dimensional cascade flow. NACA TN 3662, 1956.Suche in Google Scholar
18. Lieblein S. Incidence and deviation-angle correlations for compressor cascades. Trans ASME J Basic Eng 1960;82:575–84.10.1115/1.3662666Suche in Google Scholar
19. Miller G, Lewis G, Jr., Hartmann M. Shock losses in transonic compressor blade rows. J Eng Power 1961;83:235–42.10.1115/1.3673182Suche in Google Scholar
20. Koch C, Smith L. Loss sources and magnitudes in axial-flow compressors. J Eng Power 1976;98:411–24.10.1115/1.3446202Suche in Google Scholar
21. Adkins G, Smith L. Spanwise mixing in axial-flow turbomachines. J Eng Power 1982;104:97–110.10.1115/1.3227271Suche in Google Scholar
22. Gallimore S. Spanwise mixing in multistage axial flow compressors: part II – throughflow calculations including mixing. J Turbomach 1986;108:10–16.10.1115/1.3262009Suche in Google Scholar
23. Wisler D, Bauer R, Okiishi T. Secondary flow, turbulent diffusion, and mixing in axial-flow compressors. J Turbomach 1987;109:455–69.10.1115/1.3262127Suche in Google Scholar
24. Dunham J. Modelling of spanwise mixing in compressor through-flow computations. Proc Inst Mech Eng 1997;211:243–51.10.1243/0957650971537150Suche in Google Scholar
25. Mönig R, Mildner F, Röper R. Viscous-flow two-dimensional analysis including secondary flow effects. J Turbomach 2001;123:558–67.10.1115/1.1370167Suche in Google Scholar
26. Wennerstrom AJ. Design of highly loaded axial-flow fans or compressors. Vermont, USA: Concepts Eti, 2001.Suche in Google Scholar
27. Boyer KM. An improved streamline curvature approach for off-design analysis of transonic compression systems. PhD Thesis, Virginia Polytechhnic Institute and State University, 2001.10.1115/GT2002-30444Suche in Google Scholar
28. Acarer S, Ozkol U. An extension of the streamline curvature through-flow design method for bypass fans of turbofan engines. Proc IMechE Part G J Aerosp Eng 2017. DOI:10.1177/0954410016636159. (In Press).Suche in Google Scholar
29. Shan P. A mass addition approach to the bypass turbomachine through flow inverse design problem. J Mech Sci Technol 2008;22:1921–5.10.1007/s12206-008-0733-xSuche in Google Scholar
30. Bullock R, Johnsen I. Aerodynamic design of axial flow compressors. NASA SP36, 1965.Suche in Google Scholar
31. Kleppler J. Technique to predict stage-by-stage, pre-stall compressor performance characteristics using a streamline curvature code with loss and deviation correlations. MSc Thesis, University of Tennessee, 1998.Suche in Google Scholar
32. Aungier RH. Axial flow compressors: a strategy for aerodynamic design and analysis. New York, USA: ASME Press, 2003.10.1115/1.801926Suche in Google Scholar
33. Pachidis V. Gas turbine advanced performance simulation. PhD Thesis, Cranfield University, 2006.Suche in Google Scholar
34. Çetin M, Üçer AŞ, Hirsch C, Serovy GK. Application of modified loss and deviation correlations to transonic axial compressors. AGARD R745, 1987.Suche in Google Scholar
35. Creveling H. Axial-flow compressor computer program for calculating off-design performance. NASA CR-72472, 1968.Suche in Google Scholar
36. Urasek D, Gorrell W, Cunnan W. Performance of two-stage fan having low-aspect-ratio first stage rotor blading. NASA TP-1493, 1979.Suche in Google Scholar
37. Sullivan TJ, Younghans JL, Little DR. Single stage, low noise advanced technology fan. Volume 1: aerodynamic design. NASA CR-134801, 1976.Suche in Google Scholar
38. Sullivan T, Silverman I, Little D. Single stage, low noise advanced technology fan. Volume 4: fan aerodynamics. NASA CR-134892, 1977.Suche in Google Scholar
39. Casey M, Gersbach F, Robinson C. An optimization technique for radial compressor impellers. Proceedings of ASME Turbo Expo 2008, Berlin, Germany, 2008.10.1115/GT2008-50561Suche in Google Scholar
40. Zamboni G, Xu L. Fan root aerodynamics for large bypass gas turbine engines: influence on the engine performance and 3D design. Proceedings of ASME Turbo 2009, Florida, USA, 2009.10.1115/GT2009-59498Suche in Google Scholar
© 2019 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Editorial
- Jet-Engines Revised Dictionary for the 6th-Generation-R&D in a New Era
- Original Research Articles
- Off-Design Analysis of Transonic Bypass Fan Systems Using Streamline Curvature Through-Flow Method
- Predicting Lean Blowout and Emissions of Aircraft Engine Combustion Chamber Based on CRN
- Dielectric Barrier Discharge (DBD) Plasma Actuators for Flow Control in Turbine Engines: Simulation of Flight Conditions in the Laboratory by Density Matching
- Application of the Proper Orthogonal Decomposition Method in Analyzing Active Separation Control With Periodic Vibration Wall
- Model Predictive Control and Controller Parameter Optimisation of Combustion Instabilities
- Quasi-One-Dimensional Modeling and Analysis of RBCC Dual-Mode Scramjet Engine
- Investigation on the Performance of Forward Bending Fan
Artikel in diesem Heft
- Frontmatter
- Editorial
- Jet-Engines Revised Dictionary for the 6th-Generation-R&D in a New Era
- Original Research Articles
- Off-Design Analysis of Transonic Bypass Fan Systems Using Streamline Curvature Through-Flow Method
- Predicting Lean Blowout and Emissions of Aircraft Engine Combustion Chamber Based on CRN
- Dielectric Barrier Discharge (DBD) Plasma Actuators for Flow Control in Turbine Engines: Simulation of Flight Conditions in the Laboratory by Density Matching
- Application of the Proper Orthogonal Decomposition Method in Analyzing Active Separation Control With Periodic Vibration Wall
- Model Predictive Control and Controller Parameter Optimisation of Combustion Instabilities
- Quasi-One-Dimensional Modeling and Analysis of RBCC Dual-Mode Scramjet Engine
- Investigation on the Performance of Forward Bending Fan
