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Research Papers

Stability Enhancement of a Multistage Compressor by Air Injection

[+] Author and Article Information
Sven-Jürgen Hiller

 MTU Aero Engines, Dachauer Straße 665, 80995 Munich, Germanysven-juergen.hiller@mtu.de

Roland Matzgeller

 MTU Aero Engines, Dachauer Straße 665, 80995 Munich, Germanyroland.matzgeller@mtu.de

Wolfgang Horn

 MTU Aero Engines, Dachauer Straße 665, 80995 Munich, Germanywolfgang.horn@mtu.de

J. Turbomach 133(3), 031009 (Nov 12, 2010) (7 pages) doi:10.1115/1.4001228 History: Received August 11, 2009; Revised September 14, 2009; Published November 12, 2010; Online November 12, 2010

Cold and hot air injection upstream of the first rotor tip of a multistage compressor was tested experimentally. The compressor operating range was extended toward lower mass flow by more than 60% indicating a better throttling capability when air injection was activated. A strong dependency of the stability enhancement on the injected mass flow and injection velocity was found. Both increasing injection mass flow rate and increasing injection velocity led to a considerable extension of the throttling line. Comparable enhancements were achieved when reducing the number of nozzles and hence the injection mass flow. It was also found that injection of hot air, at temperatures comparable to air that bled off at a following stage, had no penalty on the stability enhancement. Investigation of the influence of air injection on radial work distribution showed that only small amounts of injected air were sufficient to lead to a significant radial work redistribution. This in turn changed the operating point of the first stage, leading to axial rematching and thus changed the whole operational behavior of the compressor.

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Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 1

Schematic diagram of the injection configuration

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Figure 2

Manifold with piping

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Figure 3

CFD simulation of the injection nozzle

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Figure 4

Compressor characteristics at 82% speed for different injection flow rates

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Figure 5

Change of inlet mass flow due to air injection at different speeds.

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Figure 6

Increase in stable operating range

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Figure 7

Characteristics of the first stage

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Figure 8

Radial profiles of total temperature and total pressure at the stator leading edges of the first stage

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Figure 9

Radial total pressure traverses compared with stator leading edge instrumentation

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