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EXPERIMENTAL AND NUMERICAL INVESTIGATION OF A CIRCUMFERENTIAL GROOVE CASING TREATMENT IN A LOW SPEED AXIAL RESEARCH COMPRESSOR AT DIFFERENT TIP CLEARANCES

[+] Author and Article Information
Matthias Rolfes

Technische Universität Dresden, Institute of Fluid Mechanics, Chair of Turbomachinery and Flight Propulsion, 01062 Dresden, Germany
Matthias.Rolfes@tu-dresden.de

Martin Lange

Technische Universität Dresden, Institute of Fluid Mechanics, Chair of Turbomachinery and Flight Propulsion, 01062 Dresden, Germany
martin.lange@tu-dresden.de

Konrad Vogeler

Technische Universität Dresden, Institute of Fluid Mechanics, Chair of Turbomachinery and Flight Propulsion, 01062 Dresden, Germany
konrad.vogeler@tu-dresden.de

Ronald Mailach

Technische Universität Dresden, Institute of Fluid Mechanics, Chair of Turbomachinery and Flight Propulsion, 01062 Dresden, Germany
ronald.mailach@tu-dresden.de

1Corresponding author.

ASME doi:10.1115/1.4037822 History: Received August 21, 2017; Revised August 29, 2017

Abstract

The demand of increasing pressure ratios for modern high pressure compressors leads to decreasing blade heights in the last stages. As tip clearances cannot be reduced to any amount, the tip clearance ratios of the last stages can reach values notably higher than current norms. This can be intensified by a compressor running in transient operations. The ability of circumferential casing grooves in the rotor casing to improve the compressor's operating range has been in the focus of research for many years. Their simplicity is one reason for their continuing popularity nowadays. In a previous paper, three different circumferential groove CTs were investigated in a single stage environment in the LSRC at TUDresden. One groove was able to notably improve the operating range and the efficiency of the compressor at very large rotor tip clearances (5% chord). In this paper, tests with this particular groove type in a 3 stage environment in the LSRC are presented. Two different rotor tip clearance sizes of 1.2% and 5% of chord were investigated. At the small tip clearance, the grooves are almost neutral. If the compressor runs with large tip clearances, 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 tip clearance sizes will be discussed.

Copyright (c) 2017 by ASME
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