SU1196719A1 - Method of inspecting manufacture and assembly quality of unit rotor aerodynamic supports - Google Patents

Abstract

THE METHOD OF CONTROL THE QUALITY OF MANUFACTURING AND ASSEMBLING AERODYNAMIC SUPPORTS OF ROTORS OF THE KNOTS, which consists in creating forced oscillations of the node and measuring the resonant frequencies of the node, characterized in that, in order to improve the accuracy of control, by accounting for changes in the resonant frequencies during ascent and landing of supports, they create axially accurate monitoring by account of changes in resonant frequencies during ascent and landing of supports, create axial frequencies when the ascent and landing of the supports improve the accuracy of control by accounting for changes in the resonant frequencies during ascent and landing of supports. forced oscillations with a phase shift of 90 ° C; and axial and radial resonance frequencies of the node are measured continuously at the moment of ascent or landing of the supports. S (L O5; o

Description

The invention relates to the bearing industry and can be primarily used to control the quality of the manufacture and assembly of aerodynamic bearings.

The purpose of the invention is to improve the accuracy of quality control of manufacturing and assembly by taking into account, changing the resonant frequencies during the ascent and landing of supports.

FIG. 1 shows a functional diagram of the device that implements the proposed method; in fig. 2 is a circular diagram of signals for the CCT plane, where 1 is a diagram of the transient start-up or run-down of the rotor, II is the rotor operating mode diagram, III is the diagram after the rotor has landed; in fig. 3 - similar pie charts for the plane YOZ.

The device comprises a base 1, a frame 2, elastic elements 3, through which the frame 2 is attached to the base I, as well as a plate 4 and elastic elements 5 through which the plate 4 is attached to the frame 2.

In addition, the device contains sensors 6 and 7 oscillations mounted on frame 2 and plate 4, respectively, control blocks 8 and 9, connected by positive feedback to the corresponding sensors 6 and 7, two-coordinate recording device 10, as well as the node 11 having the rotor 12 mounted on the aerodynamic supports 13.

The method is carried out as follows.

Using the oscillation sensor 7 and the control unit 9, the plate 4, on which the node 11 is mounted, reports resonant oscillations along the Y axis. At the same time, oscillations along the X axis are created. The oscillation phases along the axes X and Y differ by 90 °. The stiffness of the elastic elements 3 and 5 is selected such that oscillations along the axes X and Y occur at the same 1 | 1x frequencies.

The frequencies of these vibrations are determined by the formulas

stiffness coefficients of elastic elements 3 and 5, respectively;

oscillating masses according to axis X and Y, respectively.

When the start-and-run-out mode, the rotor 12, mounted on the aerodynamic supports 13, makes a complicated movement, for example, in the HOU plane, carried out

J ascent or landing relative to the supports 13. As part of the masses mi and gpg is the connected mass of the rotor 12 in the axes X and Y, respectively, disconnecting the mass of the rotor in any of these axes dramatically changes the resonant frequency fx.

 . Therefore, during a transient (ascending or landing of the rotor), the oscillations in the axes X and Y are frequency modulated.

With the help of blocks 8 and 9, the change (frequency modulation) of these oscillations is recorded, and with the aid of the recorder 10 of the signals obtained at the outputs of blocks 8 and 9, a pie chart is drawn (Fig. 2).

With a complex movement of the rotor 12 (near the ascent or landing) the circular pattern is a complex curve (curve I, fig. 2), after the ascent or landing of the rotor 12 the diagrams are circles (curves II and III, fig 2) of different diameters because the frequencies of oscillating systems

5, these modes change in opposite directions.

Similarly,

these operations are also in the yOZ plane.

Depending on the quality of the assembly of supports

13 (pressure of lubricating gases, gaps,

0 skews, etc.) moments of ascent or landing occur at different speeds of rotation of the rotor 12, the transition processes are also different, therefore pie charts (Fig. 3) are also different for each node.

Further, according to the shape of the circular diagrams, the various modes of the rotor 12 are judged.

Thus, by informing the node under study of resonant oscillations in two coordinates, one of which passes along the axis of rotation of the rotor, in each of two perpendicular planes passing through the axis of rotation of the rotor, fixing the change in the frequencies of these oscillations and constructing the corresponding circular diagrams makes it possible to accurately determine the moment of ascent and landing, as well as the transient process of the rotors of finally assembled and closed nodes.

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FIG. 2

fig.Z

Claims (1)

METHOD FOR QUALITY CONTROL OF MANUFACTURE AND ASSEMBLY OF AERODINE OF THE MECHANICAL SUPPORT OF KNOTS ROTORS, which consists in the creation of forced vibrations of the assembly and in measuring the resonant frequencies of the assembly, characterized in that, in order to increase the control accuracy by taking into account changes in the resonant frequencies during the ascent and landing of the supports, axial and radial forced vibrations with shear are created. phase 90 ° and continuously measure the axial and radial resonant frequencies of the node at the time of the ascent or landing of the supports. 6U96II nS