CN218493686U

CN218493686U - Aeroengine core machine front axle cooling frock

Info

Publication number: CN218493686U
Application number: CN202222168632.1U
Authority: CN
Inventors: 张宇飞
Original assignee: Sichuan S Aero Engine Maintenance Co ltd
Current assignee: Sichuan S Aero Engine Maintenance Co ltd
Priority date: 2022-08-17
Filing date: 2022-08-17
Publication date: 2023-02-17
Anticipated expiration: 2032-08-17

Abstract

The utility model relates to the technical field of aero-engines, and discloses a front shaft cooling tool of an aero-engine core engine, which comprises a cooling pipe with one sealed end, a sealing cover arranged at the open end of the cooling pipe and a plurality of exhaust holes arranged on the side wall of the cooling pipe sealed end; the outer wall of the cooling pipe is provided with an assembly clamping plate for connecting with an engine core; the connector is installed to the outside of closing cap to be used for letting in the air current. A first placing hole is formed in the pipe wall of the cooling pipe, and a sealing mechanism is further installed on the cooling pipe and used for opening or sealing the first placing hole. The utility model discloses place the column dry ice in the cooling tube, to letting in high-pressure draught wherein through the connector to discharge each position of treating the cooling work piece with gasified dry ice through each exhaust hole, make the cooling more even, the effect is better.

Description

Aircraft engine core machine front axle cooling frock

Technical Field

The utility model relates to an aeroengine technical field particularly, relates to aeroengine core machine front axle cooling frock.

Background

At present, no special equipment for cooling the front shaft of the CFM56-3/-5/-7 engine core machine exists, and during work, dry ice is contained only by using a plastic bag or a cloth bag and then is plugged into the corresponding position of the front shaft of the core machine by using a stick. This cooling method has drawbacks: 1. the dry ice can not be completely and uniformly contacted with the front shaft of the core machine for one circle when being plugged; 2. only the lower part of dry ice is left due to gravity in the process of being quickly consumed, and the front shaft of the core machine cannot be uniformly and effectively cooled for 360 degrees; 3. the plastic bag is rapidly melt-bonded to the core machine front axle and related parts nearby when contacting the heated core machine front axle.

Therefore, the conventional cooling method has the defects of poor cooling effect, low efficiency, incapability of well cooling the front shaft of the core machine and protecting relevant parts of an engine, finally influencing the decomposition success rate of the core machine, increasing additional work and needing to subsequently input more human resources and aviation materials.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, the utility model provides an aeroengine core machine front axle cooling frock.

The utility model discloses a front axle cooling tool of an aeroengine core machine, which comprises a cooling pipe with one sealed end, a sealing cover arranged at the open end of the cooling pipe and a plurality of exhaust holes arranged on the side wall of the closed end of the cooling pipe;

the outer wall of the cooling pipe is provided with an assembling clamping plate for connecting with an engine core machine;

the connector is installed to the outside of closing cap to be used for letting in the air current.

Furthermore, a first placing hole is formed in the pipe wall of the cooling pipe, and a sealing mechanism is further installed on the cooling pipe and used for opening or sealing the first placing hole.

Further, sealing mechanism includes the sealed lid of sliding connection on the cooling tube outer wall, through guide rail sliding connection between the outer wall of sealed lid and cooling tube, and still be provided with two spacing platforms on the outer wall of cooling tube, two spacing platforms set up respectively in the relative both sides of sealed lid to with the sealed side seal contact who covers.

Furthermore, the surface of the sealing cover attached to the outer wall of the cooling pipe is provided with a circle of sealing gasket, and the sealing gasket can surround the periphery of the first placing hole.

Further, can dismantle the connection between closing cap and the cooling tube, and the one end of closing cap install with be located the intraductal grafting pipe of cooling, the outer wall of grafting pipe and the inner wall laminating of cooling tube, and seted up on the grafting pipe and placed hole two, the outer wall of cooling tube is installed along its axial flexible driving piece, the flexible end of driving piece is connected with the flange, the outer wall connection of flange and closing cap.

Furthermore, the driving part is an electric push rod or an air cylinder or a hydraulic cylinder.

Furthermore, a plurality of rows of exhaust holes are arranged along the circumferential direction of the cooling pipe, and each row of exhaust holes are arranged along the axial direction of the cooling pipe.

Furthermore, the exhaust hole is round hole form, and all rotates in every exhaust hole and installs movable post, is provided with the venthole in the movable post, and the axis of venthole is the contained angle setting with the axis of movable post, and still installs the rotatory adjustment mechanism of drive movable post on the cooling tube.

Further, adjustment mechanism includes the drive rack that a plurality of set up along the cooling tube axial, the cover is established at two installation lagging of cooling tube outer wall and is connected the elastic recovery mechanism and the power pack of two installation lagging, and one of them installation lagging and all drive racks, and this installation lagging movable sleeve locates the cooling tube, another installation lagging and cooling tube are fixed, the one end of activity post all stretches out corresponding exhaust hole, and the ring gear has been cup jointed, drive rack and the ring gear meshing transmission that is located the each activity post outside of same row, power pack is used for the drive to connect the installation lagging activity of drive rack.

Furthermore, the power unit comprises a driving motor connected with the cooling pipe and a cam connected with the output end of the driving motor, and the annular surface of the cam can be in contact with the surface of a mounting sleeve plate connected with the driving rack so as to drive the mounting sleeve plate to move along the axial direction of the cooling pipe.

The beneficial effects of the utility model are that:

the utility model provides a front axle cooling tool of an aeroengine core machine, which comprises a cooling pipe with one sealed end, a sealing cover arranged at the open end of the cooling pipe and a plurality of exhaust holes arranged on the side wall of the closed end of the cooling pipe; the outer wall of the cooling pipe is provided with an assembling clamping plate for connecting with an engine core machine; the connector is installed to the outside of closing cap to be used for letting in the air current. The utility model discloses place the column dry ice in the cooling tube, to letting in high-pressure draught wherein through the connector to discharge each position of treating the cooling work piece with gasified dry ice through each exhaust hole, make the cooling more even, the effect is better.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

Fig. 1 is a schematic view of an overall structure of a cooling tool provided in embodiment 1 of the present invention;

fig. 2 is a schematic view of an overall structure of a cooling tool provided in embodiment 2 of the present invention;

fig. 3 is a schematic view of the overall structure of the cooling tool according to embodiment 3 of the present invention;

fig. 4 is a schematic view of the overall structure of the cooling tool provided in embodiment 3 of the present invention when dry ice is added;

fig. 5 is an external structural view of a cooling tool proposed in embodiment 4 of the present invention;

fig. 6 is a partial structural sectional view of a cooling tool proposed in embodiment 4 of the present invention.

Icon: the cooling device comprises a cooling pipe 1, an assembling clamping plate 2, a nylon limit 3, an exhaust hole 4, a sealing cover 5, a connector 6, a guide rail 7, a sealing cover 8, a first placing hole 9, a limit table 10, a second placing hole 12, an inserting pipe 13, a driving piece 14, a convex plate 15, a driving rack 16, a movable column 17, an elastic return mechanism 18, a driving motor 19, a cam 20, an installing sleeve plate 21 and an air outlet hole 22.

Detailed Description

To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the drawings of the embodiments of the present invention are combined to clearly and completely describe the technical solutions of the embodiments of the present invention, and obviously, the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments of the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms indicating orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplification of description, and do not indicate or imply that the equipment or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate the directions or positional relationships based on the directions or positional relationships shown in the drawings, or the directions or positional relationships that the products of the present invention are usually placed when used, and are only for the convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element indicated must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the present disclosure, unless otherwise expressly stated or limited, the first feature may comprise both the first and second features directly contacting each other, and also may comprise the first and second features not being directly contacting each other but being in contact with each other by means of further features between them. Also, the first feature may be over, above or on the second feature including the first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is at a higher level than the second feature. A first feature being below, beneath or beneath a second feature includes the first feature being directly below and obliquely below the second feature or simply indicating that the first feature is at a lesser level than the second feature.

Example 1:

as shown in figure 1, the front shaft cooling tool for the core engine of the aircraft engine comprises a cooling pipe 1 with one sealed end, a sealing cover 5 installed at the open end of the cooling pipe 1, and a plurality of exhaust holes 4 formed in the side wall of the sealed end of the cooling pipe 1. The outer wall of the cooling pipe 1 is provided with a mounting clip 2 for connection with an engine core. The outside of the cover 5 is fitted with a connector 6 for letting in air flow. Wherein, place the column dry ice in cooling tube 1, through connector 6 to letting in high-pressure draught wherein to discharge each position of waiting to cool off the work piece with gasified dry ice through each exhaust hole 4, make the cooling more even, the effect is better.

Example 2:

referring to fig. 2 in particular, in the present embodiment, a first placing hole 9 is formed in the tube wall of the cooling tube 1, and a sealing mechanism is further installed on the cooling tube 1 for opening or sealing the first placing hole 9. Through placing hole 9, can add the dry ice under the prerequisite of not dismantling closing cap 5, compare the scheme in embodiment 1, can conveniently add coolant fast, improve the convenience of during operation.

As an optional implementation manner of this scheme, the sealing mechanism includes sealed lid 8 of sliding connection on cooling tube 1 outer wall, passes through guide rail 7 sliding connection between sealed lid 8 and the cooling tube 1 outer wall, and still is provided with two spacing platforms 10 on the outer wall of cooling tube 1, and two spacing platforms 10 set up respectively in sealed lid 8 opposite sides to and with the sealed side of 8 of sealing contact. The sealing effect of the device is improved, and the cooling medium is prevented from escaping from the gas places except the exhaust hole 4.

As an alternative embodiment of the present scheme, the surface of the sealing cover 8 attached to the outer wall of the cooling pipe 1 is provided with a circle of sealing gasket, and the sealing gasket can surround the periphery of the placing hole one 9.

Example 3:

referring to fig. 3-4 specifically, in this embodiment, different from embodiment 2, in this embodiment, the sealing cap 5 is detachably connected to the cooling pipe 1, and one end of the sealing cap is mounted with an insertion pipe 13 located in the cooling pipe 1, an outer wall of the insertion pipe 13 is attached to an inner wall of the cooling pipe 1, the insertion pipe 13 is provided with a second placing hole 12, the outer wall of the cooling pipe 1 is mounted with a driving member 14 extending and retracting along an axial direction of the cooling pipe, a protruding plate 15 is connected to an extending end of the driving member 14, and the protruding plate 15 is connected to an outer wall of the sealing cap 5. The driving member 14 is an electric push rod or an air cylinder or a hydraulic cylinder. Through above-mentioned structure, can have better leakproofness than the scheme in embodiment 2, its operation is got up and is also more automatic, convenient and fast.

Example 4:

in the solutions of embodiments 1 to 3, after the air flow is exhausted from the exhaust holes, the direction of the air flow is fixed, so that there is a problem that the cooling medium cannot sufficiently contact with the workpiece to be cooled, and in order to solve the above problem, referring to fig. 5 to 6, the exhaust holes 4 in this embodiment are arranged in several rows along the circumferential direction of the cooling pipe 1, and each row of the exhaust holes 4 is arranged along the axial direction of the cooling pipe 1.

As an optional implementation mode of the scheme, the exhaust holes 4 are circular holes, the movable column 17 is rotatably mounted in each exhaust hole 4, an air outlet 22 is formed in each movable column 17, the axis of each air outlet 22 and the axis of each movable column 17 form an included angle, and an adjusting mechanism for driving each movable column 17 to rotate is further mounted on the cooling pipe 1.

As an optional implementation manner of this scheme, the adjusting mechanism includes a plurality of driving racks 16 disposed along the axial direction of the cooling pipe 1, two mounting straps 21 sleeved on the outer wall of the cooling pipe 1, an elastic restoring mechanism 18 connected to the two mounting straps 21, and a power unit, where one of the mounting straps 21 and all of the driving racks 16 is movably sleeved on the cooling pipe 1, the other mounting strap 21 is fixed to the cooling pipe 1, one end of each movable column 17 extends out of the corresponding exhaust hole 4 and is sleeved with a gear ring, the driving racks 16 are in meshing transmission with the gear rings located outside each movable column 17 in the same column, and the power unit is used for driving the mounting straps 21 connected to the driving racks 16 to move.

As an alternative embodiment of the present solution, the power unit comprises a driving motor 19 connected with the cooling pipe 1, a cam 20 connected with the output end of the driving motor 19, and the annular surface of the cam 20 can be in surface contact with a mounting strap 21 connected with the driving rack 16 to drive the mounting strap 21 to move along the axial direction of the cooling pipe 1.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The front shaft cooling tool for the core engine of the aircraft engine comprises a cooling pipe with one sealed end, a sealing cover arranged at the open end of the cooling pipe and a plurality of exhaust holes formed in the side wall of the sealed end of the cooling pipe;

the outer wall of the cooling pipe is provided with an assembling clamping plate for connecting with an engine core;

the connector is installed in the outside of closing cap to be used for letting in the air current.

2. The aircraft engine core front axle cooling tool of claim 1, characterized in that: a first placing hole is formed in the pipe wall of the cooling pipe, and a sealing mechanism is further mounted on the cooling pipe and used for opening or sealing the first placing hole.

3. The aircraft engine core front axle cooling tool of claim 2, characterized in that: sealing mechanism includes the sealed lid of sliding connection on the cooling tube outer wall, pass through guide rail sliding connection between the outer wall of sealed lid and cooling tube, and still be provided with two spacing platforms on the outer wall of cooling tube, two spacing platforms set up respectively in the relative both sides of sealed lid to with the side sealing contact of sealed lid.

4. The aircraft engine core front axle cooling frock of claim 3 characterized in that: and the surface of the sealing cover, which is attached to the outer wall of the cooling pipe, is provided with a circle of sealing gasket, and the sealing gasket can surround the periphery of the first placing hole.

5. The aircraft engine core front axle cooling tool of claim 1, characterized in that: can dismantle the connection between closing cap and the cooling tube, and the one end of closing cap install with be located the spliced tube of cooling tube, the outer wall of spliced tube and the inner wall laminating of cooling tube, and seted up on the spliced tube and placed hole two, the flexible driving piece of its axial is followed to the outer wall installation of cooling tube, and the flexible end of driving piece is connected with the flange, the outer wall connection of flange and closing cap.

6. The aircraft engine core front axle cooling frock of claim 5 characterized in that: the driving piece is an electric push rod or an air cylinder or a hydraulic cylinder.

7. The aircraft engine core front axle cooling tool of any one of claims 1-6, characterized in that: the exhaust hole sets up a plurality of rows along the circumference of cooling tube, and every row of exhaust hole all sets up along the axial of cooling tube.

8. The aircraft engine core front axle cooling frock of claim 7, characterized in that: the exhaust hole is the round hole form, and every all rotate in the exhaust hole and install movable post, be provided with the venthole in the movable post, the axis of venthole is the contained angle setting with the axis of movable post, and still installs the rotatory adjustment mechanism of drive movable post on the cooling tube.

9. The aircraft engine core front axle cooling tool of claim 8, characterized in that: adjustment mechanism includes that drive rack, cover that a plurality of set up along the cooling tube axial establish two installation lagging and connect two at the cooling tube outer wall the elastic recovery mechanism and the power pack of installation lagging, and one of them installation lagging and all drive racks, and this installation lagging movable sleeve locates the cooling tube, another installation lagging and cooling tube are fixed, and the one end of activity post all stretches out corresponding exhaust hole to cup jointed the ring gear, drive rack and the ring gear meshing transmission that is located the each activity post outside of same row, the power pack is used for the drive to connect the installation lagging activity of drive rack.

10. The aircraft engine core front axle cooling tool of claim 9, characterized in that: the power unit comprises a driving motor connected with the cooling pipe and a cam connected with the output end of the driving motor, and the annular surface of the cam can be in contact with the surface of the mounting sleeve plate connected with the driving rack so as to drive the mounting sleeve plate to move along the axial direction of the cooling pipe.