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Rotor assembly of compressor test piece and compressor test piece

A technology for compressors and test pieces, which is applied to gas turbine devices, machines/engines, pump components, etc., can solve problems such as insufficient critical speed and weak rotor stiffness, so as to increase critical speed margin, reduce support span, The effect of reducing bending deflection

Active Publication Date: 2020-12-01
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention provides a rotor assembly of a compressor test piece and a compressor test piece to solve the problem that the rotor is prone to bending deflection when the rotor assembly of the compressor test piece is rotating, which makes the rotor rigidity weak and the critical rotational speed insufficient technical problem

Method used

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  • Rotor assembly of compressor test piece and compressor test piece

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Embodiment Construction

[0025] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0026] figure 1 It is a schematic diagram of the rotor assembly of the compressor test piece of the preferred embodiment of the present invention.

[0027] Such as figure 1 As shown, the rotor assembly of the compressor test piece of this embodiment, the rotor assembly includes: a compressor blade disk 1 for increasing the gas flow rate and gas pressure, and is used to balance the axial force and be coaxial with the compressor blade disk 1 The set balance disc 2 is used to tighten the rotor assembly and transmit the central tie rod 4 of the axial force. The central tie rod 4 penetrates and locks the compressor blade disc 1 and the balance disc 2, and is used for torque transmission of the axi...

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Abstract

The invention discloses a rotor assembly of a gas compressor test part and the gas compressor test part. The rotor assembly comprises a gas compressor blade disc used for increasing the gas flow speedand gas pressure, a balance disc used for balancing axial acting force and arranged coaxially with the gas compressor blade disc, a center pull rod used for tensioning the rotor assembly and transmitting axial force, a power input shaft used for transmitting axial force of torque and fixedly connected with the balance disc and a supporting structure used for supporting the rotor assembly on a casing. The center pull rod penetrates through and locks the gas compressor blade disc and the balance disc. The supporting structure comprises a first supporting part and a second supporting part, the first supporting part and the second supporting part are arranged at the front end and the rear end of the gas compressor blade disc correspondingly, and the balance disc is arranged behind the secondsupporting part. By means of the structural design of the rotor assembly, the supporting span of a rotor is obviously reduced, bending deflection generated when the rotor assembly rotates is reduced,the rigidity and strength of the rotor assembly are increased, and the critical rotation speed margin of the rotor assembly is improved.

Description

technical field [0001] The invention relates to the field of aero-engine test pieces, in particular to a rotor assembly of a compressor test piece. In addition, the present invention also relates to a compressor test piece comprising the above-mentioned rotor assembly of the compressor test piece. Background technique [0002] Aeroengine is a kind of highly complex and precise thermodynamic machinery, which provides the power for aircraft to fly. With the development of science and technology, the performance of aeroengine continues to improve. After the overall structure of the engine is determined, such as the compressor, combustion chamber, turbine and other components, test pieces should be designed for testing to obtain the aerodynamic performance and vibration characteristics of the components, and provide support for the matching and optimization of the components of the whole machine. [0003] Compared with the engine, the axial force of the compressor test piece ca...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D25/16F04D29/66F04D29/60F02C3/08
CPCF02C3/08F04D25/163F04D29/601F04D29/662
Inventor 吕顺日景晓明
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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