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Aircraft engine rotor assembly method

An aero-engine and rotor assembly technology, which is applied in the field of aero-engines, can solve the problems of low efficiency, tedious and uncontrollable deformation of the low-pressure tie rod 13, etc., and achieve the effects of simple device structure, simplified assembly process, and convenient operation

Active Publication Date: 2018-04-13
CHINA HANGFA SOUTH IND CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the process of controlling the deformation of the low-pressure tie rod 13 is cumbersome and uncontrollable, and the efficiency is low

Method used

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Embodiment Construction

[0022] In order to have a clearer understanding of the technical features, purposes and effects of the present invention, the specific implementation manners of the present invention will now be described with reference to the accompanying drawings. Wherein, the same parts adopt the same reference numerals.

[0023] figure 1 It is a schematic cross-sectional structure diagram of a rotor assembly state of a turboprop engine; figure 2 It is a schematic diagram of a partial three-dimensional exploded structure principle of a device used in an aero-engine rotor assembly method according to a specific embodiment of the present invention; image 3 for figure 2 Schematic diagram of the cross-sectional structure of the device in use. In order to better explain the assembly principle, figure 2 The aero-engine rotor in the figure only shows some structures involved in the connection, omitting structures such as blades, image 3 The hydraulic pump, dial indicator and aeroengine r...

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Abstract

The invention discloses an aircraft engine rotor assembly method. An aircraft engine rotor comprises a first-grade rotor, a second-grade rotor, a low-pressure pull rod, a sound wheel and a locking nut; and the aircraft engine rotor assembly method comprises the following steps: (A) the rotor is assembled; (B) a device is provided, and comprises an outer support cylinder, an inner pull rod, a nut spanner, a hydraulic pump, a dial indicator and a handle; (C) a transmission rod is adjusted; the dial indicator is installed; and force applied on the transmission rod by the dial indicator is adjusted, so that the transmission rod is stably contacted with a step part of the inner pull rod; (D) pressure of 0.2 MPa is applied to the hydraulic pump; and then, the dial indicator is adjusted to zero;(E) the pressure of the hydraulic pump is increased; the nut is tightly screwed; and then, the pressure of the hydraulic pump is removed; and (F) the pressure of 0.2 MPa is applied to the hydraulic pump; and reading of the dial indicator is detected. The aircraft engine rotor assembly method simplifies the assembly process, and improves the assembly efficiency.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to an assembly method for rotor components of an aero-engine. Background technique [0002] In the assembly process of the rotor of an engine, especially an aero-engine, the tightening torque of fasteners such as bolts, nuts, and bearing lock nuts is a key element in the control of assembly state. figure 1 It is a schematic cross-sectional structure diagram of a rotor assembly state of a turboprop engine, see figure 1 As shown, the first-stage rotor 11 (the first-stage disc of the compressor) and the second-stage rotor 12 (the second-stage disc of the compressor) of the aero-engine rotor 1 are centered with a large interference stop, and the end faces of the low-pressure tie rods 13 are tensioned. In the actual assembly process, the second-stage rotor 12 is usually screwed to the low-pressure tie rod 13, and then the first-stage rotor 11 is set on the low-pressure tie rod 13, ...

Claims

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Application Information

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IPC IPC(8): B23P21/00
CPCB23P21/00
Inventor 程碧玉易海曹斐周斌
Owner CHINA HANGFA SOUTH IND CO LTD
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