Aero-engine gas generator rotor assembling tool and assembling method
A technology of gas generators and aero-engines, which is applied in the manufacture of tools, hand-held tools, etc., which can solve problems such as the inability of the rotor to stop, easy slippage when tightening, and difficulty in centering the rotor, so as to achieve the effect of improving reliability and stability
Pending Publication Date: 2022-02-11
CHINA HANGFA SOUTH IND CO LTD
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Problems solved by technology
[0005] The invention provides an assembly tool and an assembly method for the rotor of an aero-engine gas generator to solve the difficulty in assembling the turbine rotor during the assembly process of the existing aero-engine gas generator rotor, and the rotor existing during the assembly of the rear bearing compression nut and the lock ring Technical problems of inability to stop rotation, difficulty in rotor centering and easy slipping during tightening
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[0027] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered below.
[0028] figure 1 Structural diagram of the rear bearing compression nut and the turbine rotor compression nut in the prior art; figure 2 It is a structural schematic diagram of the nut installation assembly in the rotor assembly tool of the aero-engine gas generator in the preferred embodiment of the present invention; image 3 It is a schematic diagram of the structure of the nut installation assembly in the rotor assembly tool of the aero-engine gas generator in the preferred embodiment of the present invention when the nut is installed; Figure 4 It is a schematic diagram of the structure of the lock ring installation assembly in the rotor assembly tool of the aero-engine gas generator in the preferred embodiment of the present invention when the lock ring is ...
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The invention discloses an aero-engine gas generator rotor assembling tool. A nut mounting assembly firstly connects a fixing piece with a gas turbine secondary disc and then connects a mounting plate connected with the fixing piece with an engine case so that the gas turbine secondary disc is indirectly connected with the interior of the engine case; and rotation stopping of the gas turbine rotor is achieved, and rotor deflection and rotating piece slipping in the process that a rotating piece tightens a rear bearing compression nut are prevented. The rear bearing locking ring is mounted on the rear bearing compression nut through the mounting positioning rod, the pressing head and the hydraulic device so that the reliability of mounting the rear bearing compression nut on the rear bearing is guaranteed. According to the scheme, the rear bearing compression nut is installed through the nut mounting assembly so that the problems that in the rear bearing compression nut assembling process, a rotor is difficult to stop rotating, the rotor is difficult to center, and slipping is generated in the screwing process are solved, and then the assembling stability and the assembling reliability are improved; and the rear bearing locking ring is mounted on the rear bearing compression nut through the locking ring mounting assembly so that the reliability after mounting is improved.
Description
technical field [0001] The invention relates to the technical field of aero-engine component assembly, in particular to an aero-engine gas generator rotor assembly tool. In addition, the present invention also relates to an assembly method of an aero-engine gas generator rotor using the above-mentioned aero-engine gas generator rotor assembly tool. Background technique [0002] Aeroengine gas generator rotor is usually composed of three-stage axial flow, one-stage centrifugal compressor and two-stage gas turbine rotor. The centrifugal compressor and gas turbine rotor are connected by a central tie rod, and the centrifugal compressor and gas turbine rotor are respectively connected by compression nuts Install it on the central tie rod, and then install the lock ring insurance; the combustion engine rotor adopts 1-0-1 support mode, and its rear fulcrum is located at the rear journal of the gas turbine secondary disc, and the rear bearing is installed on the journal, which need...
Claims
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Login to View More IPC IPC(8): B25B27/14B25B27/02
CPCB25B27/14B25B27/026
Inventor 黄晓鸣高航胡亚飞黄超曾振旋彭军
Owner CHINA HANGFA SOUTH IND CO LTD