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Research Papers

Aeroelasticity at Reversed Flow Conditions — Part II: Application to Compressor Surge

[+] Author and Article Information
Harald Schoenenborn

MTU Aero Engines GmbH, D-80995 Munich, GermanyHarald.Schoenenborn@mtu.de

Thomas Breuer

MTU Aero Engines GmbH, D-80995 Munich, GermanyThomas.Breuer@mtu.de

J. Turbomach 134(6), 061031 (Sep 17, 2012) (8 pages) doi:10.1115/1.4006309 History: Received July 14, 2011; Revised July 29, 2011; Published September 17, 2012

The prediction of blade loads during surge is still a challenging task. In the literature, the blade loading during surge is often referred to as “surge load,” which suggests that there is a single source of blade loading. In the second part of our paper it is shown that, in reality, the “surge load” may consist of two physically different mechanisms: the pressure shock when the pressure breaks down and aeroelastic excitation (flutter) during the blow-down phase in certain cases. This leads to a new understanding of blade loading during surge. The front block of a multistage compressor is investigated. For some points of the backflow characteristic, the quasi steady-state flow conditions are calculated using a Reynolds averaged Navier-Stokes (RANS)-solver. The flow enters at the last blade row, goes backwards through the compressor and leaves the compressor in front of the inlet guide vane. The results show a very complex flow field characterized by large recirculation regions on the suction sides of the airfoils and stagnation regions close to the trailing edges of the airfoils. Based on these steady solutions, unsteady calculations are performed with a linearized aeroelasticity code. It can be shown that some of the rotor stages are aerodynamically unstable in the first torsional mode. Thus, in addition to the pressure shock, the blades may be excited by flutter during the surge blow-down phase. In spite of the short blow-down phase typical for aero-engine high pressure compressors, this may lead to very high blade stresses due to high aeroelastic excitation at these special flow conditions. The analytical results compare very well with the observations during rig testing. The correct nodal diameter of the blade vibration is reproduced and the growth rate of the blade vibration is predicted quite well, as a comparison with tip-timing measurements shows. A new flutter region in the compressor map was experimentally and analytically detected.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 14

Calculated normalized aerodynamic damping versus IBPA for the rotor

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Figure 15

Tip-timing measurement results for the rotor

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Figure 16

Compressor map with flutter regions

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Figure 1

Pressure and stress over a surge cycle

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Figure 2

Crack at the airfoil trailing edge after surge

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Figure 3

Compressor map and surge cycle

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Figure 4

Investigation setup of compressor front block

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Figure 5

Part compressor map stage 1–4

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Figure 6

Flow field at backflow conditions of the rotor

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Figure 7

Mach-isosurface at backflow conditions of the rotor

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Figure 8

Static pressure distribution at backflow conditions of the rotor

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Figure 9

First torsional vibration mode shape of the rotor

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Figure 10

Pressure disturbance and flow vectors at p0 during backflow

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Figure 11

Local excitation during backflow conditions at p0 of the rotor

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Figure 12

Measured rotor tip deflections during a surge cycle and fitted growth rate

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Figure 13

Normalized aerodynamic damping versus relative mass flow rate for the rotor

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