阅读说明：本技术 一种安装边防外翻的航空发动机多级盘及其使用方法 (Aeroengine multistage disc with anti-flanging installation edge and use method thereof ) 是由 张宏远 乔嘉宇 孙汉铮 于 2020-12-23 设计创作，主要内容包括：本发明涉及航空发动机多级盘技术领域,尤其为一种安装边防外翻的航空发动机多级盘及其使用方法,包括多级盘和叶片,所述多级盘的四周固定连接有叶片,所述叶片的一端滑动连接有平衡块,所述平衡块的一端固定连接有缓冲装置,且缓冲装置与叶片固定连接,所述叶片的一端外侧固定连接有防外翻装置,本发明中,通过设置的加强杆、第二卡环、第二螺钉和第二挡板,通过加强杆对叶片的一端进行斜拉,使叶片的一端受到一个拉力,保证叶片在正常使用时不会出现局部外翻的现象,同时通过第一卡环以及第二卡环作用便于实现对加强杆的安装拆卸,且通过第二挡板可以实现对第一卡环以及第二卡环的限位支撑,保证第一卡环以及第二卡环工作时的稳定性。(The invention relates to the technical field of aero-engine multistage discs, in particular to an aero-engine multistage disc with an outward turning prevention function at the installation edge and a use method thereof, which comprises a multistage disc and blades, wherein the blades are fixedly connected to the periphery of the multistage disc, one end of each blade is slidably connected with a balance block, one end of each balance block is fixedly connected with a buffer device, the buffer devices are fixedly connected with the blades, and the outer side of one end of each blade is fixedly connected with the outward turning prevention device. The stability of first snap ring and second snap ring during operation is guaranteed.)

1. The utility model provides an aeroengine multistage dish of installation frontier defense evagination and application method thereof, includes multistage dish (1) and blade (2), its characterized in that: the multistage disc (1) is fixedly connected with blades (2) all around, one end of each blade (2) is connected with a balance block (3) in a sliding mode, one end of each balance block (3) is fixedly connected with a buffer device (4), the buffer devices (4) are fixedly connected with the blades (2), the outer side of one end of each blade (2) is fixedly connected with an anti-eversion device (6), one end of each anti-eversion device (6) is fixedly connected with a connecting device (5), the connecting devices (5) are detachably connected with the blades (2), each anti-eversion device (6) comprises a reinforcing rod (601), a first clamping ring (602), a second clamping ring (603), a second screw (604) and a second baffle (605), the outer side of each blade (2) is clamped with the first clamping ring (602), the right end of the first clamping ring (602) is provided with the second clamping ring (603), and the inner side of the second clamping ring (603) is spirally connected with the second screw (604, and second snap ring (603) passes through second screw (604) and first snap ring (602) fixed connection, the left end fixedly connected with stiffener (601) of first snap ring (602), and stiffener (601) and connecting device (5) fixed connection.

2. An aero-engine multistage disc mounted with edge protection turned out according to claim 1 wherein: the outside fixedly connected with second baffle (605) of blade (2), and second baffle (605) all laminate with first snap ring (602) and second snap ring (603).

3. An aero-engine multistage disc mounted with edge protection turned out according to claim 1 wherein: the number of the second screws (604) is two, and the second screws (604) are symmetrically distributed on the front side and the rear side of the horizontal center line of the first clamping ring (602) and the second clamping ring (603).

4. An aero-engine multistage disc mounted with edge protection turned out according to claim 1 wherein: buffer (4) include spacing axle (401), spring (402), stopper (403) and dog (404), the spacing axle of top fixedly connected with (401) of balancing piece (3), the outside sliding connection of spacing axle (401) has stopper (403), and stopper (403) and blade (2) fixed connection, the outside of spacing axle (401) is provided with spring (402), and the top and the bottom of spring (402) respectively with stopper (403) and balancing piece (3) fixed connection.

5. An aero-engine multistage disc for installing frontier defense eversion according to claim 4, wherein: the number of the springs (402) is two in total, and the springs are symmetrically distributed on the left side and the right side of the vertical center line of the balance block (3).

6. An aero-engine multistage disc for installing frontier defense eversion according to claim 4, wherein: the top end of the limiting shaft (401) is fixedly connected with a stop block (404).

7. An aero-engine multistage disc mounted with edge protection turned out according to claim 1 wherein: connecting device (5) include first baffle (501), first screw (502), fixed frame (503) and connecting plate (504), the first baffle of outside fixedly connected with (501) of blade (2), the downside of baffle (501) is provided with fixed frame (503), the inboard screwed connection of fixed frame (503) has first screw (502), and first screw (502) and blade (2) screwed connection, the bottom fixedly connected with connecting plate (504) of fixed frame (503), and connecting plate (504) and stiffener (601) fixed connection.

8. An aero-engine multistage disc mounted with edge protection turned out according to claim 7 wherein: the number of the first screws (502) is four in total, and the first screws are uniformly distributed on the periphery of the fixing frame (503).

9. The use method of an aeroengine multistage disc for installing a frontier defense eversion according to claim 1, characterized in that: the method comprises the following steps:

the method comprises the following steps: firstly, fixedly connecting a connecting device (5) with a blade (2);

step two: then the anti-eversion device (6) is fixedly connected with the blade (2);

step three: when the blade (2) starts to work, the buffer device (4) and the anti-eversion device (6) start to work.

Technical Field

The invention relates to the technical field of aero-engine multistage discs, in particular to an aero-engine multistage disc with an outward turning prevention device and a using method thereof.

Background

An aero-engine (aero-engine) is a highly complex and precise thermal machine, provides an engine with power required by flying for an aircraft, is known as 'industrial flower' as the heart of the aircraft, directly influences the performance, reliability and economy of the aircraft, is an important embodiment of national science and technology, industry and national defense strength, and has to perform dynamic balance for a rotor system in order to reduce the unbalance amount and avoid harmful vibration during the operation of the rotor system, so that an aero-engine fan or a compressor rotor is generally designed with a balance surface and a balance block.

At present, when the multistage disc is started in the twinkling of an eye, the balancing piece can produce momentary striking to the blade under the effect of centrifugal force, wearing and tearing appear easily in the balancing piece of having a specified duration to the life of balancing piece has been reduced, and general multistage disc only prevents the phenomenon that the blade installation limit appears turning up through the balancing piece, but the phenomenon that local turning up appears easily through the balancing piece, consequently, proposes an aeroengine multistage disc and application method that the installation limit turned up to above-mentioned problem.

Disclosure of Invention

The invention aims to provide an aeroengine multistage disc with a flange protection device and a use method thereof, and aims to solve the problems in the background technology.

In order to achieve the purpose, the invention provides the following technical scheme:

an aero-engine multistage disc with an outward turning prevention function at the installation side and a using method thereof comprise a multistage disc and blades, wherein the blades are fixedly connected to the periphery of the multistage disc, one end of each blade is slidably connected with a balance block, one end of each balance block is fixedly connected with a buffer device, the buffer devices are fixedly connected with the blades, the outer side of one end of each blade is fixedly connected with an outward turning prevention device, one end of each outward turning prevention device is fixedly connected with a connecting device, the connecting devices are detachably connected with the blades, each outward turning prevention device comprises a reinforcing rod, a first clamping ring, a second screw and a second baffle plate, the outer side of each blade is clamped with the first clamping ring, the right end of the first clamping ring is provided with the second clamping ring, the inner side of the second clamping ring is spirally connected with the second screw, the second clamping ring is fixedly connected with the first clamping ring through the second screw, the left end of the, and the reinforcing rod is fixedly connected with the connecting device.

Preferably, the outer side of the blade is fixedly connected with a second baffle, and the second baffle is attached to the first clamping ring and the second clamping ring.

Preferably, the number of the second screws is two, and the second screws are symmetrically distributed on the front side and the rear side of the horizontal center line of the first clamping ring and the second clamping ring.

Preferably, buffer includes spacing axle, spring, stopper and dog, the spacing axle of top fixedly connected with of balancing piece, the outside sliding connection of spacing axle has the stopper, and stopper and blade fixed connection, the outside of spacing axle is provided with the spring, and the top and the bottom of spring respectively with stopper and balancing piece fixed connection.

Preferably, the number of the springs is two, and the springs are symmetrically distributed on the left side and the right side of the vertical center line of the balance block.

Preferably, the top end of the limit shaft is fixedly connected with a stop block.

Preferably, connecting device includes first baffle, first screw, fixed frame and connecting plate, the first baffle of the outside fixedly connected with of blade, the downside of baffle is provided with fixed frame, the inboard screwed connection of fixed frame has first screw, and first screw and blade screwed connection, the bottom fixedly connected with connecting plate of fixed frame, and connecting plate and stiffener fixed connection.

Preferably, the number of the first screws is four in total, and the first screws are uniformly distributed around the fixing frame.

Preferably, the method comprises the following steps:

the method comprises the following steps: firstly, fixedly connecting a connecting device with a blade;

step two: then fixedly connecting the anti-eversion device with the blades;

step three: when the blade starts to work, the buffer device and the anti-eversion device start to work.

Compared with the prior art, the invention has the beneficial effects that:

1. according to the invention, through the arrangement of the reinforcing rod, the first snap ring, the second screw and the second baffle, one end of the blade is obliquely pulled through the reinforcing rod, so that one end of the blade is subjected to a tensile force, the blade is ensured not to be partially turned outwards in normal use, meanwhile, the reinforcing rod is convenient to mount and dismount through the action of the first snap ring and the second snap ring, the first snap ring and the second snap ring can be limited and supported through the second baffle, and the working stability of the first snap ring and the second snap ring is ensured.

2. According to the invention, through the arrangement of the limiting shaft, the spring, the limiting block and the stop block, when the multistage disc rotates instantly, the speed reduction buffering can be carried out on the balancing block under the action of the spring, so that the phenomenon that the balancing block instantly collides with the blade can be avoided, the abrasion of the balancing block can be reduced, the service life of the balancing block is prolonged, and the cost is saved.

3. According to the invention, through the arrangement of the first baffle, the first screw, the fixing frame and the connecting plate, the reinforcing rod and the blades can be quickly connected together under the action of the fixing frame, so that the operation of workers is facilitated, and the limiting and fixing of the fixing frame can be realized under the action of the first baffle.

Drawings

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a schematic structural diagram of the multi-stage disk of the present invention;

FIG. 3 is a schematic view of the structure of FIG. 1 at point A according to the present invention;

FIG. 4 is a schematic view of the structure of FIG. 1 at B according to the present invention;

FIG. 5 is a schematic view of an installation structure of the first snap ring and the second snap ring of the present invention.

In the figure: 1-multistage disc, 2-blade, 3-balance block, 4-buffer device, 401-limit shaft, 402-spring, 403-limit block, 404-stop block, 5-connecting device, 501-first baffle, 502-first screw, 503-fixing frame, 504-connecting plate, 6-anti-eversion device, 601-reinforcing rod, 602-first snap ring, 603-second snap ring, 604-second screw and 605-second baffle.

Detailed Description

Referring to fig. 1-5, the present invention provides a technical solution:

an aeroengine multistage disc with an anti-eversion edge and a using method thereof are disclosed, the aeroengine multistage disc comprises a multistage disc 1 and blades 2, the blades 2 are fixedly connected to the periphery of the multistage disc 1, one end of each blade 2 is slidably connected with a balance block 3, one end of each balance block 3 is fixedly connected with a buffer device 4, the buffer devices 4 are fixedly connected with the blades 2, the outer side of one end of each blade 2 is fixedly connected with an anti-eversion device 6, one end of each anti-eversion device 6 is fixedly connected with a connecting device 5, the connecting devices 5 are detachably connected with the blades 2, each anti-eversion device 6 comprises a reinforcing rod 601, a first snap ring 602, a second snap ring 603, a second screw 604 and a second baffle 605, the first snap ring 602 is clamped on the outer side of each blade 2, the second snap ring 603 is arranged at the right end of the first snap ring 602, the second screw 604 is spirally connected on the, and the second snap ring 603 is fixedly connected with the first snap ring 602 through a second screw 604, the left end of the first snap ring 602 is fixedly connected with the reinforcing rod 601, and the reinforcing rod 601 is fixedly connected with the connecting device 5.

The outer side of the blade 2 is fixedly connected with a second baffle 605, the second baffle 605 is attached to the first snap ring 602 and the second snap ring 603, the second baffle 605 can limit and support the first snap ring 602 and the second snap ring 603, the working stability of the first snap ring 602 and the second snap ring 603 is ensured, the number of the second screws 604 is two, the second screws 604 are symmetrically distributed on the front side and the rear side of the horizontal central line of the first snap ring 602 and the second snap ring 603, the first snap ring 602 and the second snap ring 603 can be mounted and dismounted through the second screws 604, the buffer device 4 comprises a limiting shaft 401, a spring 402, a limiting block 403 and a stop block 404, the top end of the balance block 3 is fixedly connected with the limiting shaft 401, the outer side of the limiting shaft 401 is slidably connected with the limiting block 403, the limiting block 403 is fixedly connected with the blade 2, the limiting and support of the balance block 3 can be realized through the limiting block 403, the outer side of the limiting shaft 401 is provided with two springs 402, the top end and the bottom end of each spring 402 are respectively and fixedly connected with a limiting block 403 and a balance block 3, the number of the springs 402 is two, the springs 402 are symmetrically distributed on the left side and the right side of the vertical central line of the balance block 3, when the multistage disc 1 drives the blades 2 to do centrifugal motion, the balance block 3 can extrude the springs 402, and the balance block 3 can not generate instant impact with the blades 2 under the buffering of the springs 402, so that the abrasion of the balance block 3 is reduced, the service life of the balance block 3 is prolonged, the top end of the limiting shaft 401 is fixedly connected with a stop block 404, the limiting of the limiting shaft 401 can be realized through the stop block 404, the connecting device 5 comprises a first baffle plate 501, a first screw 502, a fixed frame 503 and a connecting plate 504, the outer side of the blades 2 is fixedly connected with a first baffle plate, the inner side of the fixing frame 503 is spirally connected with first screws 502, the first screws 502 are spirally connected with the blade 2, the bottom end of the fixing frame 503 is fixedly connected with a connecting plate 504, the connecting plate 504 is fixedly connected with a reinforcing rod 601, the reinforcing rod 601 has certain diagonal tension to the blade 2 in the rotating process of the multistage disc 1, the blade 2 cannot be turned outwards locally through the diagonal tension, the number of the first screws 502 is four, the first screws are uniformly distributed around the fixing frame 503, and the fixing frame 503 is convenient to install and detach through the first screws 502.

The method comprises the following steps:

the method comprises the following steps: firstly, fixedly connecting the connecting device 5 with the blade 2;

step two: then the anti-eversion device 6 is fixedly connected with the blade 2;

step three: when the blade 2 starts to operate, the damping device 4 and the anti-eversion device 6 start to operate.

The working process is as follows: in the invention, firstly, a first baffle 501 is welded on the outer side of one end of a blade 2 by a welding mode, then a worker fixes a fixing frame 503 and the blade 2 together by a first screw 502, simultaneously fixes a connecting plate 504 and the fixing frame 503 together by a welding mode, then the worker regulates a second baffle 605 and the blade 2 together by a welding mode, simultaneously fixes a first snap ring 602 and a second snap ring 603 together by a second screw 604, and fixes a reinforcing rod 601 with the first snap ring 602 and the connecting plate 504 together by a welding mode, when a multistage disc 1 carries the blade 2 to work, when the multistage disc 1 carries the blade 2 to carry out centrifugal motion, a balance weight 3 extrudes a spring 402, and the balance weight 3 can not generate instant impact with the blade 2 under the buffer of the spring 402, thereby reducing the abrasion of the balance weight 3, increase the life of balancing piece 3, and at the rotation in-process of multistage dish 1, stiffener 601 also can have certain oblique tension to blade 2, can make blade 2 can not appear the phenomenon of local valgus through oblique tension.

The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts of the present invention. The foregoing is only a preferred embodiment of the present invention, and it should be noted that there are objectively infinite specific structures due to the limited character expressions, and it will be apparent to those skilled in the art that a plurality of modifications, decorations or changes may be made without departing from the principle of the present invention, and the technical features described above may be combined in a suitable manner; such modifications, variations, combinations, or adaptations of the invention using its spirit and scope, as defined by the claims, may be directed to other uses and embodiments.