CN-121989018-A - Turbine blade assembly system of aero-engine

CN121989018ACN 121989018 ACN121989018 ACN 121989018ACN-121989018-A

Abstract

The invention discloses an aeroengine turbine blade assembly system which comprises a conveying mechanism, a moving mechanism, a feeding mechanism and a pressing mechanism, wherein the conveying mechanism is used for bearing and linearly conveying each turbine blade, the moving mechanism is used for bearing and positioning a turbine disc and driving the turbine disc to rotate so that each mortise of the turbine disc sequentially passes through a preset station, and the feeding mechanism is arranged at the tail end of the conveying mechanism and comprises a carrier and a feeding driving assembly, and the feeding driving assembly is connected with the carrier and used for driving the carrier to reciprocate between a first position and a second position. The turbine blade assembling system for the aero-engine has the advantages that the turbine blade assembling system for the aero-engine can realize self-assembly of turbine blades, ensure the consistency of the assembly precision of the turbine blades, reduce the experience dependence on operators, improve the assembly efficiency of the turbine blades, and meet the severe requirements of the new generation aero-engine on the assembly of the turbine rotor on high precision, high efficiency and high consistency.

Inventors

LI YIHAN
LI GUANGPING
CHEN ZHAN
LI XINGTONG
HUANG CHENGJIN
HUANG RENZHONG
YANG YUN
Jiang Bozhe
DENG HUI

Assignees

湖北超卓航空科技股份有限公司

Dates

Publication Date: 20260508
Application Date: 20260228

Claims (10)

1. An aircraft engine turbine blade assembly system, comprising: the material conveying mechanism is used for bearing and linearly conveying each turbine blade; the movement mechanism is used for bearing and positioning the turbine disc and driving the turbine disc to rotate so that each mortise of the turbine disc sequentially passes through a preset station; The feeding mechanism is arranged at the tail end of the feeding mechanism and comprises a carrier and a feeding driving assembly, the feeding driving assembly is connected with the carrier and used for driving the carrier to reciprocate between a first position and a second position, when the carrier reaches the first position, the feeding assembly is in butt joint with the outlet end of the feeding mechanism and used for receiving a single turbine blade at the tail end of the feeding mechanism, when the carrier reaches the second position, the feeding assembly is in butt joint with a tongue-and-groove at a preset station, and And the pressing mechanism is arranged at a preset station and used for pressing tenons of the turbine blades on the carrier into the mortises.
2. The aircraft engine turbine blade assembly system of claim 1, wherein the feed mechanism comprises a guide base, a pushing member and a pushing driving assembly, the guide base is provided with a guide channel, the cross section of the guide channel is matched with the cross section of the tenon of the turbine blade, both ends of the guide channel are open, the bottom of the guide channel is provided with a first notch extending along the length direction of the guide channel, the inside of the guide channel is used for sliding the tenon of the turbine blade, the blade of the turbine blade penetrates through the first notch and extends out of the guide channel, the pushing member is arranged at the head end of the guide channel, the pushing driving assembly is connected with the pushing member and used for driving the pushing member to reciprocate along the length direction of the guide channel, so that the pushing member is abutted with the tenon of the turbine blade at the head end and pushes the tenon of each turbine blade to move in the guide channel, and each turbine blade sequentially reaches the tail end of the guide channel.
3. The aircraft engine turbine blade assembly system of claim 2, wherein the top of the guide channel has a second notch extending along the length direction thereof, the lower end of the pushing member is located in the guide channel, the upper end of the pushing member passes through the second notch and extends out of the guide channel, the pushing driving assembly comprises a sliding rail, a first rack, a moving seat, a first gear and a first rotating driving member, the sliding rail and the first rack are fixedly connected with the guide substrate and are parallel to the guide channel, the moving seat is slidably connected with the sliding rail, the moving seat is fixedly connected with the upper end of the pushing member, the first gear is meshed with the first rack, the fixed end of the first rotating driving member is fixedly connected with the moving seat, and the output end of the first rotating driving member is coaxially and fixedly connected with the first gear and is used for driving the first gear to rotate so as to enable the moving seat to reciprocate along the length direction of the sliding rail.
4. The aircraft engine turbine blade assembly system of claim 1, wherein the movement mechanism comprises a rotating table, a plurality of positioning pieces and a second rotation driving piece, the rotating table is used for placing a turbine disc, the positioning pieces are distributed in an annular array structure by taking a circle center of the rotating table as a base point, the lower ends of the positioning pieces are detachably and fixedly connected with the rotating table, the upper ends of the positioning pieces correspondingly slide through mounting holes of the turbine disc one by one, and the output end of the second rotation driving piece is fixedly connected with the rotating table coaxially and used for driving the rotating table to rotate.
5. The aircraft engine turbine blade assembly system of claim 1, wherein the carrier has a cavity adapted to receive the tenons of the turbine blades, the cavity opening to one side of the feed mechanism to form a feed port for the cavity, the feed port being closable, the cavity opening to one side of the motion mechanism to form a discharge port for the cavity, the discharge port being closable, the bottom of the cavity having a third slot extending in the feed direction and a fourth slot extending in the discharge direction, the feed port interfacing with the outlet end of the feed mechanism when the carrier reaches the first position, the cavity being adapted to slidably receive a single turbine blade tenon at the upper end of the feed mechanism, the discharge port interfacing with the top opening of the mortise at the predetermined station when the carrier reaches the second position.
6. The aircraft engine turbine blade assembly system of claim 5, wherein the loading mechanism further comprises a dam, one side of the dam is in contact with the outlet end of the delivery mechanism, a material passing opening is formed in the dam and is communicated with the outlet end of the delivery mechanism, the side of the material feeding opening is in sliding contact with the other side of the dam, and when the carrier reaches the first position, the material feeding opening is in contact with the material passing opening.
7. The aircraft engine turbine blade assembly system of claim 6, wherein the rabbet of the turbine blade entering the cavity is in sliding abutment with the other side of the dam plate, the loading mechanism further comprising a load rail fixedly connected to the other side of the dam plate, the load rail being configured to bear one side of the rabbet of the turbine blade in the cavity.
8. The aircraft engine turbine blade assembly system of claim 6, wherein the loading mechanism further comprises a blocking plate fixedly connected to the carrier and slidably abutting against the other side of the blocking plate, wherein the blocking plate is configured to block the feed gap during reciprocal movement of the carrier between the first position and the second position.
9. The aircraft engine turbine blade assembly system of claim 6, wherein the loading mechanism further comprises an opening and closing assembly coupled to the carrier to open or close the discharge port.
10. The aircraft engine turbine blade assembly system of claim 9, wherein the carrier is provided with a first guide groove communicated with the cavity, the carrier is also provided with a second guide groove communicated with the first guide groove, the second guide groove is mutually perpendicular to the first guide groove, the second guide groove is mutually parallel to the conveying direction of the material conveying mechanism, the opening and closing assembly comprises a stop block, a sliding shaft, an elastic piece and a pushing block, the stop block is in sliding connection with the first guide groove and can reciprocate along the length direction of the first guide groove, the sliding block is in sliding connection with the second guide groove and can reciprocate along the length direction of the second guide groove, the sliding block is provided with a chute, one end of the sliding shaft is fixedly connected with the stop block, and the other end of the sliding shaft is in sliding connection with the chute, and can move along the length direction of the chute, when the sliding block is positioned at one end of the second guide groove, the sliding shaft is positioned at one end of the chute, one end of the stop block extends into the cavity to block the rabbet of the turbine blade in the cavity, when the sliding block is positioned at the other end of the second guide groove, the sliding shaft is positioned at the other end of the chute, one end of the stop block is contracted into the first guide groove, the rabbet of the turbine blade in the cavity is released, the elastic piece is arranged in the second guide groove and connected with the carrier and the sliding block, so that the sliding block reaches one end of the second guide groove, the pushing block is arranged at the second position and fixedly connected with the baffle plate, the pushing block is provided with a slope, the carrier is used for sliding along the slope in the process of reaching the second position from the first position, when the sliding block reaches the highest position of the slope, the sliding block reaches the other end of the second guide groove.

Description

Turbine blade assembly system of aero-engine Technical Field The invention relates to the technical field of aircraft part maintenance, in particular to an aircraft engine turbine blade assembly system. Background An aeroengine turbine is a key component of an aeroengine and is used for converting energy of high-temperature high-pressure gas into mechanical energy to drive the engine to operate. As shown in fig. 1, a turbine 100 of a certain type is composed of a turbine disc 110 and turbine blades 120, a plurality of mounting holes 111 are formed in the turbine disc 110, the mounting holes 111 are distributed in an annular array structure by taking the center of a circle of the turbine disc 110 as a base point, and the turbine blades 120 are connected with a mortise 112 of the turbine disc 110 through tenons 121. The turbine blade is used as a hot end core component of the aeroengine, and the assembly quality of the turbine blade is directly related to the overall performance, safety and service life of the engine. Conventional turbine blade assembly relies primarily on manual operations, and the specific process generally includes the steps of a worker aligning correspondingly numbered blade tenons with correspondingly numbered turbine disk mortises, and loading the blades into the mortises one by one using a tapping pattern. However, the existing assembly method faces the following prominent problems in practical application: 1. the assembly precision consistency is poor, the matching of the turbine blade tenon and the turbine disc tenon groove is multi-tooth complex profile contact, the assembly gesture and the tenon insertion path are extremely sensitive, the manual operation is difficult to ensure the accurate repeatability of the loading gesture of each blade, and the installation deviation of the single blade or the inconsistent matching state among the blades are easy to cause, so that the dynamic balance and the pneumatic sealing effect of the rotor are influenced. 2. The method has high experience dependence on operators, and in the assembly process, key parameters such as fit clearance between the blades and the disc body, pretightening force control and the like are highly dependent on experience judgment of the operators, so that the intervention of the artificial factors not only easily causes large assembly quality fluctuation, but also is difficult to realize standardization and digital management of assembly process parameters. 3. The efficiency is low, potential safety hazards exist, the manual assembly rhythm is low, particularly for turbine rotors with a plurality of stages and a large number of blades, the assembly period is long, meanwhile, the heavy blade is carried and precisely adjusted to consume large physical power for operators, the risk of accidental falling or collision damage of parts exists, and the product qualification rate is affected. In recent years, although some modes of grabbing the blade by adopting a mechanical arm appear, a systematic solution is still lacking in how to realize the core links of high-precision self-adaptive centering guide, compliant tenon-in control, intelligent scheduling of accurate control of assembly force and the like of the blade tenon and the turbine disc tenon groove. The whole assembly system has insufficient level of intellectualization, integration and flexibility, and is difficult to meet the severe requirements of the new generation of aeroengines on the assembly of the turbine rotor, such as high precision, high efficiency and high consistency. Accordingly, there is a need to develop an air engine turbine blade assembly system that overcomes the above-described deficiencies of the prior art. Disclosure of Invention The invention aims to overcome the technical defects, and provides an aeroengine turbine blade assembly system which solves the technical problems of poor assembly accuracy consistency, high experience dependence on operators, low assembly efficiency and potential safety hazard existing in the manual assembly of turbine blades in the prior art. In order to achieve the technical purpose, the technical scheme of the invention provides an aircraft engine turbine blade assembly system, which comprises: the material conveying mechanism is used for bearing and linearly conveying each turbine blade; the movement mechanism is used for bearing and positioning the turbine disc and driving the turbine disc to rotate so that each mortise of the turbine disc sequentially passes through a preset station; The feeding mechanism is arranged at the tail end of the feeding mechanism and comprises a carrier and a feeding driving assembly, the feeding driving assembly is connected with the carrier and used for driving the carrier to reciprocate between a first position and a second position, when the carrier reaches the first position, the feeding assembly is in butt joint with the outlet end of the feeding mechanism and used for receiving a