Research Papers

Design and Experimental Verification of Mistuning of a Supersonic Turbine Blisk

[+] Author and Article Information
Pieter Groth, Hans Mårtensson

Department of Aerothermodynamics, Volvo Aero Corporation, SE-461 81 Trollhättan, Sweden

Clas Andersson

Department of Turbines and Rotors, Volvo Aero Corporation, SE-461 81 Trollhättan, Sweden

J. Turbomach 132(1), 011012 (Sep 17, 2009) (9 pages) doi:10.1115/1.3072492 History: Received August 28, 2008; Revised October 15, 2008; Published September 17, 2009

A rotor blisk of a supersonic space turbine has previously been designed to allow for free flutter to occur in an air test rig (GrothMårtensson, and Edin, 2010, “Experimental and Computational Fluid Dynamics Based Determination of Flutter Limits in Supersonic Space Turbines,” 132(1), p. 011010). Flutter occurred at several operating conditions, and the flutter boundary for the test turbine was established. In this paper the rotor blisk is redesigned in order to inhibit flutter. The design strategy chosen is to introduce a mistuning concept. Based on aeroelastic analyses using a reduced order model a criterion for the required level of mistuning is established in order to stabilize the lower system modes. Proposals in literature suggest and analyze mistuning by varying blade mode frequencies in random patterns or by modifying blades in an odd-even pattern. Here a modification of sectors of the blisk is introduced in order to bring a sufficient split of the system mode frequencies. To verify that the redesigned blisk efficiently could inhibit flutter, an experiment similar to that in the work of Groth is performed with the mistuned rotor blisk. By running the redesigned blisk at operating conditions deep into the unstable region of the tuned blisk, it is demonstrated that a relative low level of mistuning is sufficient to eliminate rotor flutter.

Copyright © 2010 by American Society of Mechanical Engineers
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Figure 1

A two-dimensional layout of a two-stage impulse turbine

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Figure 2

Scaled critical damping versus nodal diameters for backward traveling disk modes

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Figure 3

Contours of relative Mach number (range from 0.0 to 2.3)

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Figure 4

The critical two ND mode damping as a function of the frequency separation parameter df∗ under different operating conditions (— ref. point, -⋅- and ⋅⋅⋅ limit operating points, and - - - double pressure)

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Figure 5

Damping as a function of df∗ for different nodal diameters (-⋅- one ND, — two NDs, - - - three NDs, and ⋅⋅⋅ four NDs)

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Figure 6

The design of the rotor blisk with detuning

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Figure 7

Standing eigenmodes of nodal diameter 2 in the disk frame of reference

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Figure 8

Drawing of test turbine

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Figure 9

Instrumented blisk

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Figure 14

Time spectral map 20–1500 Hz; test sequence 7 in Fig. 1

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Figure 15

Coherent output power spectrum for the one ND and two ND modes

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Figure 16

Coherent output power spectrum for the three ND mode

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Figure 10

Operating conditions in test

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Figure 11

Time spectral map 20–750 Hz for test sequence with Nk 0.11

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Figure 12

Time spectral map 750–1500 Hz for test sequence with Nk 0.11

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Figure 13

Time spectral map 20–1500 Hz; test sequence 6 in Fig. 1




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