Experimental stand for examining transient phenomena in aerodynamic cascades of turbomachines

Stel’makh, A. L.; Len, A. D.; Ivashkevich, O. V.; Kaminer, A. A.

doi:10.1007/bf01523425

Strength Mater

1983

DOI: 10.1007/bf01523425

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Experimental stand for examining transient phenomena in aerodynamic cascades of turbomachines

A. L. Stel’makh¹,

A. D. Len²,

O. V. Ivashkevich³

et al.

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1986

2009

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Cited by 4 publications

(2 citation statements)

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“…The selected airfoil cascades whose Reynolds number Re varied within the range (1.2-5) ×10 5 were tested in an experimental tested bench [5]. The cascades were strictly homogeneous and characterized by the absence of aerodynamic coupling of the airfoils.…”

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confidence: 99%

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

2009

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We consider the results of investigation of cross aerodynamic characteristics of compressor blades and their dynamic stability under flexural-torsional vibrations for the cases of attached and separated flows in broad ranges of variations of the phase shift, the ratio of amplitudes of the translational and angular components of displacements, the angle of attack, the reduced frequency of vibrations, and the geometry of the blade cascade. Introduction. The principal ideas of the procedure are described and the experimental equipment for the determination of nonstationary aerodynamic characteristics (NAC) of compressor blades in the presence of attached and separated flows are developed in [1] with regard for the aerodynamic cross couplings and mutual aerodynamic couplings based on the application of flat-plate airfoil cascades. The necessity of investigations of this sort is explained by the fact that, as shown in [2-4], the nature and conditions of excitation of the flexural-torsional flutter of blade rims of compressor and fan impellers are determined by the phase shift and the ratio of amplitudes of the translational and angular components of displacements of the blades and depend on the reduced frequency of their vibrations (the Strouhal number) and the angle of attack of the incident airflow.Thus, in what follows, we present the results of evaluation of the cross aerodynamic characteristics (CAC) and their influence on the flutter resistance of blades in the process of flexural-torsional vibrations in the absence of aerodynamic coupling with regard for the parameters of the indicated vibrations, parameters of the incident airflow, and geometry of the rim.Object and Conditions of Experimental Investigations. The CAC are determined by using a straight cascade of blade airfoils whose cross-section is shown in Fig. 1. The values of the parameters of blade airfoils are as follows:

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confidence: 99%

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

2009

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“…To realize the proposed procedure, the aerodynamic test bench was modified [19]. It is made in the form of an aerodynamic tunnel of direct action intended for the investigation of flat-plate cascades of blade airfoils in which the aerodynamic load and the mode of flow are estimated by recording the shape of wakes behind the cascade and pulsations on their boundary by special thermoanemometric and coordinate-measuring devices.…”

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confidence: 99%

Experimental-numerical investigation of the dynamic stability of flexural-torsional vibrations of compressor blades under conditions of attached and separated flow. Part 1. Procedure and equipment for the determination of nonstationary aerodynamic characteristics

2007

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We present the results of investigations of the aerodynamic stability of flexural-torsional vibrations of compressor blades under conditions of attached and separated flow with regard for the cross and mutual aerodynamic links of the blades in a broad range of variations of the phase shift, the ratio of the amplitudes of translational and angular components of their displacements, and the angle of attack. A procedure and equipment used for the experimental determination of the nonstationary aerodynamic characteristics of the blades are described on the basis of the model of flat-plate airfoil cascades.Statement of the Problem. In trying to get the highest possible specific parameters of the aircraft gas-turbine engines (AGTE), we inevitably encounter the problems of vibrations of blades in the rotors of these engines. Thus, one of the methods used to make turbomachines more compact and decrease their weight is based on the application of blades with high aspect ratios. This leads, on the one hand, to a shift of the spectrum of natural frequencies of vibrations of the blades to the region of lower frequencies and, on the other hand, to the excitation of of high-frequency flexural-torsional modes of vibrations of the blades characterized by the presence of a phase shift between the translational and angular components of displacements of the sections and different values of the ratio of their amplitudes.It is known [1] that the role of decisive factor in the loss of the stability of a wing in the case of classical flutter is played by the phase shift between the translational and the angular components of displacements of the wing responsible for the formation of aerodynamic crosslinks and the supply of energy from the flow. The principal features of the classical flutter of airplane wings are also typical of the loss of aerodynamic stability of the analyzed blades [2]. However, this process is complicated by the mutual influence of neighboring blades in the blade ring. A similar phenomenon is also typical of the lightened blade rings of fan and compressor stages containing either compliant disks or damping (antivibration) shroud platforms. The self-excited vibrations of these rings are realized in the form of running strain waves with various numbers of the nodal diameters and circles. Note that the phase shift between the translational and rotational components of displacements in the sections of blades located near the shroud 200 0039-2316/07/3902-0200

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Effect of the aerodynamic connectedness between blades on the aerodynamic damping of their vibrations, and origin of cascade flutter

Kaminer

Stel’makh

1982

Strength Mater

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Experimental stand for examining transient phenomena in aerodynamic cascades of turbomachines

Cited by 4 publications

References 1 publication

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

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

Experimental-numerical investigation of the dynamic stability of flexural-torsional vibrations of compressor blades under conditions of attached and separated flow. Part 1. Procedure and equipment for the determination of nonstationary aerodynamic characteristics

Effect of the aerodynamic connectedness between blades on the aerodynamic damping of their vibrations, and origin of cascade flutter

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