A quasi-one-dimensional CFD model for multistage turbomachines

Léonard, Olivier; Adam, Olivier

doi:10.1007/s11630-008-0007-z

Request a copy

Article (Scientific journals)

A quasi-one-dimensional CFD model for multistage turbomachines

Léonard, Olivier; Adam, Olivier

2008 • In Journal of Thermal Science, 17 (1), p. 7-20

Peer reviewed

Permalink
https://hdl.handle.net/2268/19953

DOI
10.1007/s11630-008-0007-z

Files (1)Send to Details Statistics Bibliography Similar publications

Files

Full Text

fulltext.pdf

Publisher postprint (42.22 kB)

Request a copy

All documents in ORBi are protected by a user license.

Send to

RIS BibTex APA Chicago Permalink X Linkedin

Details

Keywords :

multistage; compressors; turbines; quasi-one-dimensional; meanline analysis

Abstract :

[en] The objective of this paper is to present a fast and reliable CFD model that is able to simulate stationary and transient operations of multistage compressors and turbines. This analysis tool is based on an adapted version of the Euler equations solved by a time-marching, finite-volume method. The Euler equations have been extended by including source terms expressing the blade-flow interactions. These source terms are determined using the velocity triangles and a row-by-row representation of the blading at mid-span. The losses and deviations undergone by the fluid across each blade row are supplied by correlations. The resulting flow solver is a performance prediction tool based only on the machine geometry, offering the possibility of exploring the entire characteristic map of a multistage compressor or turbine. Its efficiency in terms of CPU time makes it possible to couple it to an optimization algorithm or to a gas turbine performance tool. Different test-cases are presented for which the calculated characteristic maps are compared to experimental ones.

Disciplines :

Mechanical engineering
Aerospace & aeronautics engineering
Space science, astronomy & astrophysics
Physics

Author, co-author :

Léonard, Olivier ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Turbomachines et propulsion aérospatiale

Adam, Olivier

Language :

English

Title :

A quasi-one-dimensional CFD model for multistage turbomachines

Publication date :

March 2008

Journal title :

Journal of Thermal Science

ISSN :

1003-2169

eISSN :

1993-033X

Publisher :

Kexue Chubaneshe/Science Press, China

Volume :

Issue :

Pages :

7-20

Peer reviewed :

Peer reviewed

Available on ORBi :

since 26 August 2009

Statistics

Number of views

105 (9 by ULiège)

Number of downloads

3 (3 by ULiège)

More statistics

Scopus citations^®

Scopus citations^®
without self-citations

OpenCitations

Bibliography

Sellers J.F., Daniele C.J., 1975: DYNGEN-A Program for Calculating Steady-State and Transient Performance of Turbojet and Turbofan Engines, NASA Technical Note TN-D-7901.
Reddy K.C., Nayani S.N., 1985: Compressor and Turbine Models-Numerical Stability and Other Aspects, AEDC Report TR-85-5.
Garrard G.D., 1995: ATEC: The Aerodynamic Turbine Engine Code for the Analysis of Transient and Dynamic Gas Turbine Engine System Operations, Ph.D. Thesis, University of Tennessee, USA.
O'Brien W.F., 1992: Dynamic Simulation of Compressor and Gas Turbine Performance, AGARD LS-183, pp. 5.1-5.28.
Davis M.W.Jr, 1987: A Post-Stall Compression System Modeling Technique, NASA Technical Report AD-A177610.
Bloch G.S., O'Brien W.F., 1992: A Wide-Range Axial-Flow Compressor Stage Compressor Model, ASME Paper 92-GT-58.
Schobeiri M.T., Attia M., Lippke C., 1994: GETRAN: A Generic, Modularly Structured Computer Code for Simulation of Dynamic Behaviour of Aero-and Power Generation Gas Turbine Engines, ASME Journal of Engineering for Power, Vol 116, pp. 483-494.
Day I.J., Freeman C., 1993: The Unstable Behaviour of Low and High Speed Compressors, ASME Paper 93-GT-26
Vavra M.H., 1960: Aero-Thermodynamics and Flow in Turbomachines, John Wiley and Sons, New-York.
Lieblein S., 1965: Experimental Flow in Two-Dimensional Cascades, NASA SP-36, pp. 183-226.
Creveling H.F., Carmody R.H., 1968: Axial Flow Compressor Computer Program for Calculating Off-Design Performance (Program IV), NASA Contract Report CR-72427.
Çetin M., Üçer A.Ş., Hirsch Ch., Serovy G.K., 1987: Application of Modified Loss Correlations to Transonic Axial Compressors, AGARD Report 745.
Cahill J.E., 1997: Identification and Evaluation of Loss and Deviation Models for Use in Transonic Compressor Stage Performance Prediction, M.Sc. Thesis, Virginia Polytechnic Institute and State University, USA.
Koch C.C., Smith L.H.Jr, 1976: Loss Sources and Magnitudes in Axial-Flow Compressors, ASME Journal of Engineering for Power, july 1976, pp. 411-424.
Horlock J.H., 1958: Axial Flow Compressors, Butterworths Scientific Publications, London, UK.
Cumpsty N.A., 1989: Compressor Aerodynamics, Longman Scientific & Technical, Harlow, UK.
Aungier R.H., 2003: Axial-Flow Compressors-A Strategy for Aerodynamic Design and Analysis, ASME Press, New York, USA.
Roberts W.B., Serovy G.K., Sandercock D.M., 1986: Modeling the 3D Flow Effects on Deviation Angle for Axial Compressor Middle Stages, ASME Journal of Engineering for Gas Turbines and Power, vol. 108, pp. 131-137.
Ainley D.G., Mathieson G.C.R., 1951: A Method for Performance Estimation of Axial-Flow Turbines, ARC R&M 2974.
Ainley D.G., Mathieson G.C.R., 1951: An Examination of the Flow and Pressure Losses in Blade Rows of Axial-Flow Turbines, ARC R&M 2891.
Dunham J., Came P.M., 1970: Improvements to the Ainley-Mathieson Method of Turbine Performance Prediction, ASME Journal of Engineering for Power, July 1970.
Kacker S.C., Okapuu U., 1982: Mean line Prediction Method for Axial Flow Turbine Efficiency, ASME Journal of Engineering for Power vol. 104/1, pp 111-119.
Zhu J., Sjolander S.A., 2005: Improved Profile Loss and Deviation Correlations for Axial-Turbine Blade Rows, Proceedings of ASME Turbo Expo 2005, paper GT2005-69077.
Benner M.W., Sjolander S.A., Moustapha S.H., 1997: Influence of Leading-Edge Geometry on Profile Losses in Turbines at Off-Design Incidence: Experimental Results and an Improved Correlation, ASME Journal of Turbomachinery, vol. 119, pp 193-200.
Benner M.W., Sjolander S.A., Moustapha S.H., 2005: An Empirical Prediction Method for Secondary Losses in Turbines: Part I - A New Loss Breakdown Scheme and Penetration Depth Correlation, Proceedings of ASME Turbo Expo 2005, paper GT2005-68637.
Benner M.W., Sjolander S.A., Moustapha S.H., 2005: An Empirical Prediction Method for Secondary Losses in Turbines: Part II - A New Secondary Loss Correlation, Proceedings of ASME Turbo Expo 2005, paper GT2005-68639.
Dunham J., 1970: A Review of Cascade Data on Secondary Losses in Turbines, Journal of Mechanical Engineering Science, vol. 12/1, pp 48-59.
Stratford, B.S., 1967: The Use of Boundary Layer Techniques to Calculate the Blockage from the Annulus Boundary Layers in a Compressor, ASME Paper 67-WA/GT-7.
Craig H.R.M., Cox H.J.A, 1970: Performance Estimation of Axial Flow Turbines, Proceedings of the Institution of Mechanical Engineers 1970-71, vol. 185 32/71, pp 407-424.
Wei N., 2000: Significance of Loss Models in Aerother-modynamic Simulation for Axial Turbines, PhD Thesis, Royal Institute of Technology (KTH), Sweden.
Hirsch Ch., 1988: Numerical Computation of Internal and External Flows - Volume 1: Fundamentals of Numerical Discretization, John Wiley & Sons, Chichester, UK.
Jennions I.K., Stow P., 1985: A Quasi Three Dimensional Turbomachinery Blade Design System: Part 1-Throughflow Analysis, ASME Journal of Engineering for Gas Turbines and Power, vol. 107, pp. 301-307.
Barth T.J., 1993: Recent Developments in High Order K-Exact Reconstruction on Unstructured Meshes, AIAA Paper 93-0668.
Horlock J.H., Perkins H.J., 1974: Annulus Wall Boundary Layers in Turbomachines, AGARD Lecture Series AG-185.
Burdsall E.A., Canal E.Jr, Lyons K.A., 1979: Core Compressor Exit Stage Study-I. Aerodynamic and Mechanical Design, NASA Contract Report CR-159714.
Behlke R.F., Burdsall E.A., Canal E.Jr, Korn N.D., 1980: Core Compressor Exit Stage Study - II. Final Report, NASA Contract Report CR-159812.
Timko L.P., 1984: Energy Efficient Engine High Pressure Turbine Component Test Performance Report, NASA Contract Report 168289.
Rodriguez C.G., 1997: One-Dimensional, Finite-Rate Model for Gas-Turbine Combustors, Ph.D. Thesis, Virginia Polytechnic Institute and State University, USA.
Hartsel J.E., 1972: Prediction of Effects of Mass-Transfer Cooling on the Blade Row Efficiency of Turbine Airfoils, AIAA Paper 72-11.
Ito S., Eckert E.R.G., Goldstein R.J., 1980: Aerodynamic Loss in a Gas Turbine Stage with Film Cooling, ASME Journal of Engineering for Power, vol. 102, pp 964-970.
Aungier R.H., 2000: Centrifugal Compressors: a Strategy for Aerodynamic Design and Analysis, ASME Press, New York.
von Backström T.W., 2006: A Unified Correlation for Slip Factors in Centrifugal Impellers, ASME Journal of Turbomachinery, vol. 128, pp 1-10.