Experimental-numerical investigation of the dynamic stability of flexural-torsional vibrations of compressor blades under conditions of attached and separated flow. Part 2. Cross aerodynamic characteristics

Stel’makh, A. L.; Zinkovskii, A. P.; Stel’makh, Ya. A.

doi:10.1007/s11223-009-9141-4

Cited by 2 publications

(1 citation statement)

References 5 publications

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“…IV.E, we will give an example of a blade whose overall stability prediction does not coincide with the prediction obtained through the 2-D cross section taken at 90% of the blade span. At the present day, the 2-D approach is verified by tests of cylindrical blades (i.e., blades whose cross section is constant along the span) [18][19][20][21][22][23][24]. A study [25] is devoted to the comparison of energy and modal methods based on a quasi-3-D approach.…”

Section: Introductionmentioning

confidence: 99%

Experimental Validation of Numerical Blade Flutter Prediction

Vedeneev

Kolotnikov

Макаров³

2015

Journal of Propulsion and Power

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Blade flutter of modern gas-turbine engines is one of the main issues that engine designers have to face. The most used numerical method that is employed for flutter prediction is the energy method. Although a lot of papers are devoted to the analysis of different blade wheels, this method was rarely validated by experiments. Typical mesh size, time step, and various modeling approaches that guarantee reliable flutter prediction are not commonly known, whereas some examples show that predictions obtained through nonvalidated codes can be inaccurate. In this paper, we describe our implementation of the energy method. Analysis of convergence and sensitivity to various modeling abstractions are carefully investigated. Numerical results are verified by compressor and full engine flutter test data. It is shown that the prediction of flutter onset is rather reliable so that the modeling approaches presented in this paper can be used by other researchers for the flutter analysis of industrial compressor blades. Nomenclature f = natural frequency m = number of nodal diameters N = number of blades n = rotor speed W = work done by the unsteady pressure over one cycle of blade oscillation α = inlet angle of attack φ = 2π m∕N, interblade phase shift ω = 2πf, circular frequency

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Section: Introductionmentioning

confidence: 99%

Experimental Validation of Numerical Blade Flutter Prediction

Vedeneev

Kolotnikov

Макаров³

2015

Journal of Propulsion and Power

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Experimental-numerical investigation of the dynamic stability of flexural-torsional vibrations of compressor blades under conditions of attached and separated flow. part 3. mutual aerodynamic couplings

2010

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The paper considers the results of a study of mutual aerodynamic couplings which give rise to nonstationary aerodynamic interactions between the translational and angular components displacements of neighboring ring blades in the case of variation of attack angle, reduced vibration frequency and the geometric parameters of the blade cascade. The effect of mutual aerodynamic couplings between neighboring blades on the aerodynamic stability of flexural-torsional vibrations of the blades of the peripheral section of the shrouded fan blade ring of gas turbine engine for an attack angle of 15°has been estimated.Introduction. In our earlier work [1], results of determining cross aerodynamic characteristics (CAC) and their effect on the flutter stability of compressor and fan blades were reported. In the case of flexural-torsional vibrations of blades, these characteristics are determined by aerodynamic interaction between translational and angular displacements of their sections. However, during the operation of axial flow turbomachines, mutual aerodynamic couplings also arise from interaction in the stream between the components of displacements of neighboring ring blades. As is pointed out in [2], they may be responsible for the appearance of cascade flutter of blades under the conditions of both attached and separated flow over them. Survey of scientific and technical literature shows that the character of the variation of this type of couplings as a function of flow conditions and blade vibration parameters and their effect on the aerodynamic stability of blade rings have been practically not studied. Therefore, the aim of the present study is to establish the laws governing the variation of mutual aerodynamic couplings as a function of attack angle and reduced vibration frequency for different geometric characteristics (pitch-chord ratio and deflection angle) of blade ring and their effect on its aerodynamic stability. Peculiarities of the Experimental Determination of Mutual Aerodynamic Couplings between Blades.Mutual aerodynamic couplings between blades were determined by using planar blade cascades (Fig. 1) in their tests on an experimental test bench [3]. On the reference blade airfoil (n = 0) vibrating with predetermined amplitudes of translational ( y) and angular (α) displacements and phase angle θ α

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Experimental-numerical investigation of the dynamic stability of flexural-torsional vibrations of compressor blades under conditions of attached and separated flow. Part 2. Cross aerodynamic characteristics

Cited by 2 publications

References 5 publications

Experimental Validation of Numerical Blade Flutter Prediction

Experimental Validation of Numerical Blade Flutter Prediction

Experimental-numerical investigation of the dynamic stability of flexural-torsional vibrations of compressor blades under conditions of attached and separated flow. part 3. mutual aerodynamic couplings

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