The various incidence, deviation, and loss models used in through-flow analysis methods, such as streamline curvature, are nothing more than statistical curve fits. A closer look at public domain data reveals that these statistical correlations and curve fits are usually based on experimental cascade data that actually display a fairly large scatter, resulting in a relatively high degree of uncertainty. This usually leads to substantial differences between the calculated and actual performances of a given gas turbine engine component. Typically, matching calculated results from a through-flow analysis against experimental data requires the combination of various correlations available in the public domain, through a very tedious, complex, and time consuming “trial and error” process. This particular study supports the view that it might actually be much more time effective to “adopt” a given loss model against experimental data through an iterative, physics-based approach, rather than try to identify the best combination of available correlations. For example, the well-established “Swan’s model” for calculating the blade profile loss factor in subsonic and transonic axial flow compressors depends strongly on approximate correlations for calculating the blade wake momentum thickness, and therefore represents such a case. This study demonstrates this by looking into an iterative approach to blade profile loss model adaptation that can provide a relatively simple and quick, but also physics-based way of “calibrating” profile loss models against available experimental data for subsonic applications. This paper presents in detail all the analysis necessary to support the above concept and discusses Swan’s model in particular as an example. Finally, the paper discusses the performance comparison of a two-dimensional, streamline curvature compressor model against experimental data before and after the adaptation of that particular loss model. This analysis proves the potential of the simulation strategy presented in this paper to “adopt” a given loss model against experimental data through an iterative, physics-based approach.
Skip Nav Destination
e-mail: v.pachidis@cranfield.ac.uk
e-mail: p.pilidis@cranfield.ac.uk
e-mail: templalexis@hafa.gr
e-mail: l.marinai@cranfield.ac.uk
Article navigation
January 2008
Research Papers
An Iterative Method for Blade Profile Loss Model Adaptation Using Streamline Curvature
Vassilios Pachidis,
Vassilios Pachidis
Department of Power and Propulsion, School of Engineering, Gas Turbine Engineering Group,
e-mail: v.pachidis@cranfield.ac.uk
Cranfield University
, Cranfield, Bedfordshire, MK43 0AL, UK
Search for other works by this author on:
Pericles Pilidis,
Pericles Pilidis
Department of Power and Propulsion, School of Engineering, Gas Turbine Engineering Group,
e-mail: p.pilidis@cranfield.ac.uk
Cranfield University
, Cranfield, Bedfordshire, MK43 0AL, UK
Search for other works by this author on:
Ioannis Templalexis,
Ioannis Templalexis
Section of Thermodynamics, Power and Propulsion,
e-mail: templalexis@hafa.gr
Hellenic Air Force Academy
, Dekeleia Air Base, Greece
Search for other works by this author on:
Luca Marinai
Luca Marinai
Department of Power and Propulsion, School of Engineering, Gas Turbine Engineering Group,
e-mail: l.marinai@cranfield.ac.uk
Cranfield University
, Cranfield, Bedfordshire, MK43 0AL, UK
Search for other works by this author on:
Vassilios Pachidis
Department of Power and Propulsion, School of Engineering, Gas Turbine Engineering Group,
Cranfield University
, Cranfield, Bedfordshire, MK43 0AL, UKe-mail: v.pachidis@cranfield.ac.uk
Pericles Pilidis
Department of Power and Propulsion, School of Engineering, Gas Turbine Engineering Group,
Cranfield University
, Cranfield, Bedfordshire, MK43 0AL, UKe-mail: p.pilidis@cranfield.ac.uk
Ioannis Templalexis
Section of Thermodynamics, Power and Propulsion,
Hellenic Air Force Academy
, Dekeleia Air Base, Greecee-mail: templalexis@hafa.gr
Luca Marinai
Department of Power and Propulsion, School of Engineering, Gas Turbine Engineering Group,
Cranfield University
, Cranfield, Bedfordshire, MK43 0AL, UKe-mail: l.marinai@cranfield.ac.uk
J. Eng. Gas Turbines Power. Jan 2008, 130(1): 011702 (8 pages)
Published Online: December 26, 2007
Article history
Received:
April 27, 2007
Revised:
April 30, 2007
Published:
December 26, 2007
Citation
Pachidis, V., Pilidis, P., Templalexis, I., and Marinai, L. (December 26, 2007). "An Iterative Method for Blade Profile Loss Model Adaptation Using Streamline Curvature." ASME. J. Eng. Gas Turbines Power. January 2008; 130(1): 011702. https://doi.org/10.1115/1.2747643
Download citation file:
Get Email Alerts
Cited By
Operation of a Compression Ignition Engine at Idling Load Under Simulated Cold Weather Conditions
J. Eng. Gas Turbines Power (August 2025)
In-Cylinder Imaging and Emissions Measurements of Cold-Start Split Injection Strategies
J. Eng. Gas Turbines Power (August 2025)
Effects of Lattice Orientation Angle on TPMS-Based Transpiration Cooling
J. Eng. Gas Turbines Power (September 2025)
Compressor Development for CO2-Based Pumped Thermal Energy Storage Systems
J. Eng. Gas Turbines Power (September 2025)
Related Articles
Effect of Unsteadiness on the Performance of a Transonic Centrifugal Compressor Stage
J. Turbomach (October,2009)
A Correlation-Based Transition Model Using Local Variables—Part II:
Test Cases and Industrial Applications
J. Turbomach (January,0001)
The Effect of Wake Induced Structures on Compressor Boundary-Layers
J. Turbomach (October,2007)
Compressor Leading Edge Spikes: A New Performance Criterion
J. Turbomach (April,2011)
Related Proceedings Papers
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Boundary Layer Analysis
Centrifugal Compressors: A Strategy for Aerodynamic Design and Analysis
Aerodynamic Performance Analysis
Axial-Flow Compressors