The demand of increasing pressure ratios for modern high pressure compressors leads to decreasing blade heights in the last stages. As tip clearances (TC) cannot be reduced to any amount and minimum values might be necessary for safety reasons, the TC ratios of the last stages can reach values notably higher than current norms. This can be intensified by a compressor running in transient operations where thermal differences can lead to further growing clearances. For decades, the detrimental effects of large clearances on an axial compressor's operating range and efficiency are known and investigated. The ability of circumferential casing grooves in the rotor casing to improve the compressor's operating range has also been in the focus of research for many years. Their simplicity and ease of installation are one reason for their continuing popularity nowadays, where advanced methods to increase the operating range of an axial compressor are known. In the authors' previous paper, three different circumferential groove casing treatments were investigated in a single-stage environment in the low-speed axial research compressor at TU Dresden. One of these grooves was able to notably improve the operating range and the efficiency of the single stage compressor at very large rotor TC (5% of chord length). In this paper, the results of tests with this particular groove type in a three stage environment in the low-speed axial research compressor are presented. Two different rotor TC sizes of 1.2% and 5% of tip chord length were investigated. At the small TC, the grooves are almost neutral. Only small reductions in total pressure ratio and efficiency compared to the solid wall can be observed. If the compressor runs with large TC, it notably benefits from the casing grooves. Both, total pressure and efficiency can be improved by the grooves in a similar extent as in single stage tests. Five-hole probe measurements and unsteady wall pressure measurements show the influence of the groove on the flow field. With the help of numerical investigations, the different behavior of the grooves at the two TC sizes will be discussed.
Skip Nav Destination
Article navigation
December 2017
Research-Article
Experimental and Numerical Investigation of a Circumferential Groove Casing Treatment in a Low-Speed Axial Research Compressor at Different Tip Clearances
Matthias Rolfes,
Matthias Rolfes
Chair of Turbomachinery and Flight Propulsion,
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
e-mail: Matthias.Rolfes@tu-dresden.de
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
e-mail: Matthias.Rolfes@tu-dresden.de
Search for other works by this author on:
Martin Lange,
Martin Lange
Chair of Turbomachinery and Flight Propulsion,
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Search for other works by this author on:
Konrad Vogeler,
Konrad Vogeler
Chair of Turbomachinery and Flight Propulsion,
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Search for other works by this author on:
Ronald Mailach
Ronald Mailach
Chair of Turbomachinery and Flight Propulsion,
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Search for other works by this author on:
Matthias Rolfes
Chair of Turbomachinery and Flight Propulsion,
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
e-mail: Matthias.Rolfes@tu-dresden.de
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
e-mail: Matthias.Rolfes@tu-dresden.de
Martin Lange
Chair of Turbomachinery and Flight Propulsion,
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Konrad Vogeler
Chair of Turbomachinery and Flight Propulsion,
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Ronald Mailach
Chair of Turbomachinery and Flight Propulsion,
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Institute of Fluid Mechanics,
Technische Universität Dresden,
Dresden 01062, Germany
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 21, 2017; final manuscript received August 29, 2017; published online October 3, 2017. Editor: Kenneth Hall.
J. Turbomach. Dec 2017, 139(12): 121009 (10 pages)
Published Online: October 3, 2017
Article history
Received:
August 21, 2017
Revised:
August 29, 2017
Citation
Rolfes, M., Lange, M., Vogeler, K., and Mailach, R. (October 3, 2017). "Experimental and Numerical Investigation of a Circumferential Groove Casing Treatment in a Low-Speed Axial Research Compressor at Different Tip Clearances." ASME. J. Turbomach. December 2017; 139(12): 121009. https://doi.org/10.1115/1.4037822
Download citation file:
Get Email Alerts
Related Articles
Effects of Double-Leakage Tip Clearance Flow on the Performance of a Compressor Stage With a Large Rotor Tip Gap
J. Turbomach (June,2017)
High Resolution RANS Nonlinear Harmonic Study of Stage 67 Tip Injection Physics
J. Turbomach (May,2015)
Loss and Deviation in Windmilling Fans
J. Turbomach (October,2016)
Effects of Tip Gap Size on the Aerodynamic Performance of a Cavity-Winglet Tip in a Turbine Cascade
J. Turbomach (October,2017)
Related Proceedings Papers
Related Chapters
Aerodynamic Performance Analysis
Axial-Flow Compressors
Other Components and Variations
Axial-Flow Compressors
Pulsation and Vibration Analysis of Compression and Pumping Systems
Pipeline Pumping and Compression Systems: A Practical Approach, Second Edition