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Effects of tip injection on the performance of a multi-stage high-pressure compressor

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Abstract

Within the European research project NEWAC (New Aero Engine Core Concepts), a multi-stage high-pressure compressor equipped with a tip injection system upstream of the first rotor was tested in three different configurations at MTU Aero Engines. One aim of the test campaign was to investigate the effects of tip injection on the compressor performance. This paper gives an overview of the influences of tip injection on the characteristics of the first three stages. Following an outline of the motivation for tip injection, it is assessed to what extent the surge behavior of the tested compressor is affected by tip injection. The assessment is made by evaluating the surge line extension due to tip injection. If the injection system is applied in an engine, re-matching of its turbo components will occur. Due to this fact, the focus is placed on evaluating the benefits afforded by the use of the injection system in an aircraft engine. The test results are integrated in an existing engine model for a next generation geared turbofan engine and off-design simulations are performed. In this way, changes in surge margin due to tip injection are evaluated. In addition to mere tip injection tests, measurement data of test cases is analyzed, in which mass flow recirculation was simulated. The evaluation of these tests is discussed analogously to the test cases of tip injection. It is found that tip injection prevents the generation of stall cells almost completely. The analyses also show that the stage matching of the multi-stage compressor is changed by tip injection at the front stage. According to the synthesis calculations carried out, recirculation increased the surge margin at part speed by up to about 35% relative to the reference compressor without tip injection.

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Abbreviations

HPC:

High-pressure compressor

HPT:

High-pressure turbine

LPC:

Low-pressure compressor

LPT:

Low-pressure turbine

NEWAC:

New Aero Engine Core Concepts

γ:

Ratio of specific heat

φ:

Flow coefficient

ψ:

Pressure rise coefficient

Δht :

Total enthalpy increase

ΔSM:

Changes in surge margin

cax :

Axial flow velocity

cp :

Specific heat capacity

f:

Correction factor

m:

Absolute mass flow rate

N:

Aerodynamic speed

OLE:

Operating line extension

pt :

Total pressure

SLE:

Surge line extension

SM:

Surge margin

SME:

Surge margin extension

Tt :

Total temperature

u:

Averaged circumferential speed

Xi:

Relative aerodynamic speed i

ADP:

Aerodynamic design point

amb:

Ambient

i:

Considered test case

inj:

Injection

inlet:

Inlet of considered stage

MFP:

Mass flow parameter

OL:

Operating line

outlet:

Outlet of considered stage

PR:

Total pressure ratio

Ref:

Reference case

SL:

Surge line

1:

Operating line

2:

Surge line

25:

Inlet of agreed control volume

3:

Outlet of agreed control volume

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Acknowledgments

The authors would like to thank the European Community for its support of the investigation which was funded by the NEWAC project (No. FP6-030876). Further thanks also go to several colleagues for inspiring discussions and MTU Aero Engines for the permission to publish this paper.

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Authors and Affiliations

  1. MTU Aero Engines GmbH, Dachauer Straße 665, 80995, Munich, Germany

    M. Kern, W. Horn & S.-J. Hiller

  2. Institute of Aircraft Propulsion Systems, University of Stuttgart, Pfaffenwaldring 6, 70569, Stuttgart, Germany

    S. Staudacher

Authors
  1. M. Kern
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  2. W. Horn
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  3. S.-J. Hiller
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  4. S. Staudacher
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Corresponding author

Correspondence to M. Kern.

Additional information

This paper is based on a presentation at the German Aerospace Congress, September 27–29, 2011, Bremen, Germany.

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Kern, M., Horn, W., Hiller, SJ. et al. Effects of tip injection on the performance of a multi-stage high-pressure compressor. CEAS Aeronaut J 2, 99–110 (2011). https://doi.org/10.1007/s13272-011-0035-3

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  • DOI: https://doi.org/10.1007/s13272-011-0035-3

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