CN218201788U - Tool for nondestructive testing of aviation turbine disc - Google Patents

Abstract

The application discloses a frock for aircraft turbine dish nondestructive test relates to hoist frock technical field, includes: the lifting claw assembly comprises a plurality of openable lifting claws, and the plurality of lifting claws surround to clamp the aircraft turbine disc; the adjusting assembly comprises a connecting arm and a limiting mechanism, the connecting arm is used for driving the lifting claw to open and close, and the limiting mechanism is used for locking the opening and closing degree of the lifting claw so as to maintain the clamping of the lifting claw on the aviation turbine disc. This application links the lifting claw subassembly through the adjusting part and opens the lifting claw and cliies the aircraft turbine dish and lock, can reach quick, safe hoist and mount requirement, is worth promoting.

Description

Tool for nondestructive testing of aviation turbine disc

Technical Field

The application relates to the technical field of lifting tool tools, in particular to a tool for nondestructive testing of an aviation turbine disc.

Background

The quality of the engine turbine disc directly influences the performance of an engine, and generally, the engine turbine disc needs to be subjected to water immersion ultrasonic detection after being formed so as to detect whether the quality of the engine turbine disc is qualified.

For an aviation turbine disc, the weight of the aviation turbine disc is dozens to hundreds of kilograms, the aviation turbine disc needs to be hung in equipment (ultrasonic water immersion equipment) with the height of about three meters in the nondestructive testing process, and the operation table is only arranged in one of four directions around the equipment (ultrasonic water immersion equipment), so that inconvenience is caused during unloading and completing detection and hoisting. Moreover, during hoisting, the hoisting claw usually only partially contacts the bearing surface of the aviation turbine disc, which usually causes the disc to fall off and even causes serious injury to personnel.

Certainly, at present, there are also special turbine disc hoisting tools, for example, in the existing patent CN208308260U, the patent name is a special hoisting tool for a turbine disc, but the hoisting tool is complicated in use steps, and the operability needs to be further improved.

SUMMERY OF THE UTILITY MODEL

The application mainly aims to provide a frock for aircraft turbine dish nondestructive test, aims at further improving security and the maneuverability of current aircraft turbine dish hoist.

The technical scheme adopted by the application is as follows:

a frock for aeronautical turbine disk nondestructive test, includes:

the lifting claw assembly comprises a plurality of openable lifting claws, and the plurality of lifting claws surround to clamp the aircraft turbine disc;

the adjusting assembly comprises a connecting arm and a limiting mechanism, the connecting arm is used for driving the lifting claw to open and close, and the limiting mechanism is used for locking the opening and closing degree of the lifting claw so as to maintain the clamping of the lifting claw on the aviation turbine disc.

Optionally, the lifting claw assembly further comprises:

the lifting claws are circumferentially arrayed on the outer peripheral surface of the first connecting disc, and the first connecting disc is movably hinged with the lifting claws;

and the lifting ring is arranged on the upper end surface of the first connecting disc in the middle.

Optionally, the peripheral surface of the first connecting disc is circumferentially arrayed with lifting claw mounting seats, and the lifting claws are mounted on the lifting claw mounting seats through pin shafts.

Optionally, the adjusting assembly further includes:

the second connecting disc can freely slide along the vertical direction, the connecting arms are circumferentially arrayed on the second connecting disc, one end of each connecting arm is movably hinged with the second connecting disc, and the other end of each connecting arm is movably connected with the lifting claw;

the guide sliding rod penetrates through the middle position of the second connecting disc, and the limiting mechanism is installed on the guide sliding rod.

Optionally, the limiting mechanism includes:

the upper limiting sleeve and the lower limiting sleeve are sleeved on the guide sliding rod and are respectively positioned at the upper end and the lower end of the second connecting disc;

and the locking spring is sleeved on the guide sliding rod and is positioned between the second connecting disc and the lower limiting sleeve.

Optionally, the second connection pad with all be provided with the connection otic placode on the lifting claw, the both ends of linking arm are provided with the connection clamp body, the connection support body centre gripping in connect the otic placode, and the two is through connecting pin swing joint.

Optionally, the tail end of the lifting claw is provided with a bearing hook bent at a right angle.

Compared with the prior art, the beneficial effects of this application are:

the tool for nondestructive testing of the aircraft turbine disc provided by the embodiment of the application is characterized in that the aircraft turbine disc is clamped and locked by opening the lifting claw through the adjusting component in linkage with the lifting claw component, so that the hoisting requirements on rapidness and safety can be met, and the tool is worthy of popularization.

Drawings

FIG. 1 is a schematic structural diagram of a tool for nondestructive testing of an aircraft turbine disk, provided by an embodiment of the present application, at one viewing angle;

fig. 2 is a schematic structural diagram of the tool for nondestructive testing of an aircraft turbine disc provided in the embodiment of the present application in a working state.

Reference numerals in the drawings indicate:

100-a lifting claw component, 101-a lifting claw, 102-a lifting ring, 103-a first connecting disc, 104-a lifting claw mounting seat, 105-a pin shaft, 200-an adjusting component, 201-a connecting arm, 202-a second connecting disc, 203-a connecting column, 204-an upper limiting sleeve, 205-a lower limiting sleeve, 206-a locking spring, 300-a connecting pin, 400-a bearing hook and 500-an aircraft turbine disc.

Detailed Description

The technical solutions in the embodiments of the present application will be described clearly and completely with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only some embodiments of the present application, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

It should be noted that all directional indicators (such as up, down, left, right, front, back \8230;) in the embodiments of the present application are only used to explain the relative positional relationship between the components, the motion situation, etc. in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicator is changed accordingly.

In this application, unless expressly stated or limited otherwise, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be interconnected within two elements or in a relationship where two elements interact with each other unless otherwise specifically limited. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

In addition, if there is a description of "first", "second", etc. in the embodiments of the present application, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, the meaning of "and/or" appearing throughout includes three juxtapositions, exemplified by "A and/or B" including either A or B or both A and B. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present application.

Examples

Referring to fig. 1, the present application provides a tool for nondestructive testing of an aircraft turbine disc, including a lifting claw assembly 100 and an adjusting assembly 200, where the lifting claw 101 is used to clamp an aircraft turbine disc 500, and the adjusting assembly 200 is used to adjust the opening and closing degree of the lifting claw 101 in the lifting claw assembly 100, so that the lifting claw 101 can clamp the aircraft turbine disc 500.

Specifically, in the present embodiment, referring to fig. 1, the lifting claw assembly 100 includes a lifting claw 101, a first connection plate 103, and a lifting ring 102, wherein a central position of the first connection plate 103 is provided with a threaded hole, and the lifting ring 102 is screwed into the threaded hole and is located on an upper end surface of the first connection plate 103. The plurality of lifting claws 101 are circumferentially arrayed on the outer circumferential surface of the first connecting disc 103, and the lifting claws 101 can be freely opened and closed, so that all the lifting claws 101 clamp the aircraft turbine disc 500 after being surrounded.

In one embodiment, in order to realize the movable hinge of the hanging claw 101 to the first connecting plate 103, referring to fig. 1, at least three hanging claw installing seats 104 are circumferentially arrayed on the outer circumferential surface of the first connecting plate 103, each hanging claw installing seat 104 comprises two opposite plate bodies, shaft holes are formed in the plate bodies, the upper end of the hanging claw 101 is placed between the two plate bodies, and the hanging claw 101 is installed in the hanging claw installing seat 104 through a pin shaft 105, so that the hanging claw 101 can freely rotate through the pin shaft 105 to realize the opening and closing.

In this embodiment, in order to enable the lifting claw 101 to clamp the aero turbine disc 500, as described with reference to fig. 1, the adjusting assembly 200 includes the second connecting disc 202, the connecting arm 201, the guide sliding rod, the upper limiting sleeve 204, the lower limiting sleeve 205 and the locking spring 206, wherein the upper limiting sleeve 204, the lower limiting sleeve 205 and the locking spring 206 form a limiting mechanism, specifically, the guide sliding rod is centrally disposed on the lower end surface of the first connecting disc 103, the guide sliding rod vertically passes through the central position of the second connecting disc 202 downwards, the upper limiting sleeve 204 and the lower limiting sleeve 205 are both sleeved on the guide sliding rod, the upper limiting sleeve 204 is disposed on the upper side of the second connecting disc 202, the lower limiting sleeve 205 is disposed on the lower side of the second connecting disc 202, and the locking spring 206 is sleeved on the guide sliding rod between the second connecting disc 202 and the lower limiting sleeve 205. The connecting arms 201 are circumferentially arrayed on the outer circumferential surface of the second connecting disc 202, one end of each connecting arm 201 is movably hinged with the second connecting disc 202, and the other end of each connecting arm 201 is movably hinged with the lifting claw 101.

In one embodiment, in order to realize the movable hinge connection between the connection arm 201 and the second connection pad 202 and the hanging claw 101, referring to fig. 1, connection ear plates are disposed on the second connection pad 202 and the hanging claw 101, U-shaped connection clamps are disposed at both ends of the connection arm 201, and correspondingly, both ends of the connection arm 201 are clamped with the connection ear plates on the second connection pad 202 and the hanging claw 101 through the connection clamps respectively and are mounted together through the connection pin 300.

As can be seen from the above, the tool for nondestructive testing of an aircraft turbine disk provided in the embodiment of the present application is shown in fig. 2, and when the aircraft turbine disk 500 is hoisted, the method and the operating principle are as follows:

firstly, hanging the hanging ring 102 with a crane, and moving the crane to move the whole hanger to be right above the aerial turbine disc 500;

then, by pulling any one of the claws 101 to open outwards, the claw 101 drives the second connecting plate 202 to move downwards through the connecting arm 201, so that the rest claws 101 are all opened by the downward movement of the second connecting plate 202,

slowly descending to the bottom of the aircraft turbine disc 500, slowly loosening the hand, and enabling the second connecting disc 202 to slide upwards again under the action of the locking spring 206, so that in the process that the second connecting disc 202 moves upwards, all the lifting claws 101 are driven to be closed through the connecting arm 201, and the lifting claws 101 are fastened to the bottom of the aircraft turbine disc 500;

finally, the movement of the aero turbine disc 500 is achieved by moving the crane.

In one embodiment, in order to ensure the clamping stability of the lifting claw 101 to the aircraft turbine disk 500, as shown in fig. 1, the end of the lifting claw 101 is provided with a bearing hook 400 bent at a right angle, as shown in fig. 2, the bearing hook 400 bent at a right angle fastens the bottom of the aircraft turbine disk 500, so that the aircraft turbine disk 500 can be effectively prevented from falling off in the hoisting process, and the safety is very high.

To sum up, the frock that is used for aviation turbine dish nondestructive test that this application embodiment provided, it has following advantage:

this hoist frock not only design has link gear, realizes the linkage function, has guaranteed the convenience of hoist and mount staff operation. In addition, through the installation locking spring make three claw shrink under the effect of elasticity and press from both sides tight dish spare, prevent that the in-process part of hoist and mount from taking place to drop, can protect work piece and personnel, the security is high, is worth wideling popularize.

The above description is only exemplary of the present application and should not be taken as limiting the present application, as any modification, equivalent replacement, or improvement made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims (7)

1. The utility model provides a frock for aircraft turbine dish nondestructive test which characterized in that includes:

a lifting claw assembly (100), wherein the lifting claw assembly (100) comprises a lifting claw (101) which can be opened and closed, and a plurality of lifting claws (101) surround to clamp an aircraft turbine disk (500);

the adjusting assembly (200) comprises a connecting arm (201) and a limiting mechanism, the connecting arm (201) is used for driving the lifting claw (101) to open and close, and the limiting mechanism is used for locking the opening and closing degree of the lifting claw (101) so as to maintain the lifting claw (101) to clamp the aviation turbine disc (500).

2. The tooling for nondestructive testing of an aircraft turbine disc according to claim 1, wherein the lifting claw assembly (100) further comprises:

the hanging claws (101) are circumferentially arrayed on the outer peripheral surface of the first connecting disc (103), and the first connecting disc (103) is movably hinged with the hanging claws (101);

the hanging ring (102), the hanging ring (102) is arranged on the upper end face of the first connecting disc (103) in the middle.

3. The tool for the nondestructive testing of the aircraft turbine disc as recited in claim 2, wherein the peripheral surface of the first connecting disc (103) is circumferentially arrayed with lifting claw mounting seats (104), and the lifting claws (101) are mounted on the lifting claw mounting seats (104) through pin shafts (105).

4. The tooling for the nondestructive testing of aircraft turbine disks according to claim 1, wherein the adjustment assembly (200) further comprises:

the second connecting disc (202) can freely slide along the vertical direction, the connecting arms (201) are circumferentially arrayed on the second connecting disc (202), one end of each connecting arm (201) is movably hinged with the second connecting disc (202), and the other end of each connecting arm (201) is movably connected with the lifting claw (101);

the guide sliding rod penetrates through the middle position of the second connecting plate (202), and the limiting mechanism is installed on the guide sliding rod.

5. The tool for nondestructive testing of an aircraft turbine disk according to claim 4, wherein the limiting mechanism includes:

the upper limiting sleeve (204) and the lower limiting sleeve (205) are sleeved on the guide sliding rod and are respectively positioned at the upper end and the lower end of the second connecting disc (202);

the locking spring (206) is sleeved on the guide sliding rod and is positioned between the second connecting disc (202) and the lower limiting sleeve (205).

6. The tool for nondestructive testing of an aircraft turbine disc as claimed in claim 4, wherein the second connection disc (202) and the lifting claw (101) are both provided with connection lug plates, and two ends of the connection arm (201) are provided with connection clamp bodies which are clamped on the connection lug plates and are movably hinged through a connection pin (300).

7. The tool for nondestructive testing of an aircraft turbine disc as claimed in claim 1, wherein the end of the lifting claw (101) is provided with a bearing hook (400) bent at a right angle.

Images