Solidity in compressors is defined as the ratio of the aerodynamic chord over the peripheral distance between two adjacent blades, the pitch. This parameter is simply the inverse of the pitch-to-chord ratio generally used in turbines. Solidity must be selected at the earliest design phase, i.e. at the level of the meridional design and represents a crucial step in the whole design process. Most of the existing studies on this topic rely on low-speed compressor cascade correlations from Carter or Lieblein. The aim of this work is to update those correlations for state-of-the-art controlled diffusion blades, and extend their application to high Mach number flow regimes more typical of modern compressors. Another objective is also to improve the physical understanding of the solidity effect on compressor performance and stability. A numerical investigation has been performed using the commercial software FINE/Turbo. Two different blade profiles were selected and investigated in the compressible flow regime as an extension to the low-speed data on which the correlations are based. The first cascade uses a standard double circular arc profile, extensively referenced in the literature, while the second configuration uses a state-of-the-art CDB, representative of low pressure compressor stator mid-span profile. Both profiles have been designed with the same inlet and outlet metal angles and the same maximum thickness but the camber and thickness distributions, the stagger angle and the leading edge geometry of the CDB have been optimized. The determination of minimum loss, optimum incidence and deviation is addressed and compared with existing correlations for both configurations and various Mach numbers that have been selected in order to match typical booster stall and choke operating conditions. The emphasis is set on the minimum loss performance at mid-span. The impact of the solidity on the operating range and the stability of the cascade are also studied.
Skip Nav Destination
ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
June 16–20, 2014
Düsseldorf, Germany
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-4560-8
PROCEEDINGS PAPER
Numerical Investigation of the Solidity Effect on Linear Compressor Cascades
J. Sans,
J. Sans
von Karman Institute for Fluid Dynamics, Rhode-Saint-Genèse, Belgium
Search for other works by this author on:
M. Resmini,
M. Resmini
von Karman Institute for Fluid Dynamics, Rhode-Saint-Genèse, Belgium
Search for other works by this author on:
J.-F. Brouckaert,
J.-F. Brouckaert
von Karman Institute for Fluid Dynamics, Rhode-Saint-Genèse, Belgium
Search for other works by this author on:
S. Hiernaux
S. Hiernaux
Techspace Aero, Milmort, Belgium
Search for other works by this author on:
J. Sans
von Karman Institute for Fluid Dynamics, Rhode-Saint-Genèse, Belgium
M. Resmini
von Karman Institute for Fluid Dynamics, Rhode-Saint-Genèse, Belgium
J.-F. Brouckaert
von Karman Institute for Fluid Dynamics, Rhode-Saint-Genèse, Belgium
S. Hiernaux
Techspace Aero, Milmort, Belgium
Paper No:
GT2014-25532, V02AT37A013; 15 pages
Published Online:
September 18, 2014
Citation
Sans, J, Resmini, M, Brouckaert, J, & Hiernaux, S. "Numerical Investigation of the Solidity Effect on Linear Compressor Cascades." Proceedings of the ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. Volume 2A: Turbomachinery. Düsseldorf, Germany. June 16–20, 2014. V02AT37A013. ASME. https://doi.org/10.1115/GT2014-25532
Download citation file:
95
Views
Related Proceedings Papers
Related Articles
Experimental Investigation of the Effects of a Moving Shock Wave on Compressor Stator Flow
J. Turbomach (January,2007)
Design of Industrial Axial Compressor Blade Sections for Optimal Range and Performance
J. Turbomach (April,2004)
Related Chapters
Other Components and Variations
Axial-Flow Compressors
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential