CN111337192B

CN111337192B - Oxygen nozzle test fixture for aircraft engine

Info

Publication number: CN111337192B
Application number: CN202010201539.9A
Authority: CN
Inventors: 郭鸿志
Original assignee: Aecc Guizhou Aviation Engine Maintenance Co ltd
Current assignee: Aecc Guizhou Aviation Engine Maintenance Co ltd
Priority date: 2020-03-20
Filing date: 2020-03-20
Publication date: 2021-10-12
Anticipated expiration: 2040-03-20
Also published as: CN111337192A

Abstract

The application discloses aeroengine oxygen gas nozzle test fixture in test fixture technical field, including connecting the chamber, the one side of connecting the chamber is equipped with the test joint, the opposite side intercommunication of connecting the chamber has the connecting pipe, the inner skleeve has been cup jointed to the connecting pipe is coaxial, a plurality of slip mouths have been seted up to the lateral wall of inner skleeve, slip mouth sliding connection has and is used for the spacing stopper to the oxygen gas nozzle, it rotates to connect the chamber and is connected with the outer sleeve, the inner wall of outer sleeve is equipped with the extrusion piece, the thickness of extrusion piece prolongs anticlockwise crescent, stopper and extrusion piece butt. Carry out accurate spacing to the oxygen mouth through the stopper, guarantee the test effect of oxygen mouth to improve the maintenance quality of oxygen mouth.

Description

Oxygen nozzle test fixture for aircraft engine

Technical Field

The invention relates to the technical field of testing devices, in particular to an oxygen nozzle testing tool for an aircraft engine.

Background

The oxygen air cock that aeroengine used need test its leakproofness when maintaining, and the test procedure includes and aerifys the test many times under three kinds of different pressures, because the oxygen air cock is in the test tube of disect insertion test equipment, needs the manual work to press the oxygen air cock to fix during the experiment, and the operation degree of difficulty has been increaseed to this kind of mode, and the oxygen nozzle inspection is not in place when also leading to sealed test very easily, can't guarantee the maintenance quality of oxygen air cock, easily takes safety hidden danger.

Disclosure of Invention

The invention aims to provide an oxygen nozzle testing tool for an aircraft engine, and solves the problem that the oxygen nozzle needs to be fixed manually during testing in the prior art.

In order to solve the above problems, the present invention provides the following technical solutions: the utility model provides an oxygen nozzle test fixture for aeroengine, is including connecting the chamber, the one side of connecting the chamber is equipped with the test joint, the opposite side intercommunication of connecting the chamber has the connecting pipe, the coaxial inner skleeve that has cup jointed of connecting pipe, a plurality of slip mouths have been seted up to the lateral wall of inner skleeve, slip mouth sliding connection has and is used for the spacing stopper to the oxygen nozzle, it is connected with the outer sleeve to connect the chamber rotation, the inner wall of outer sleeve is equipped with the extrusion piece, the thickness of extrusion piece prolongs the anticlockwise crescent gradually, stopper and extrusion piece butt.

The oxygen nozzle is inserted into the connecting pipe, the outer sleeve is rotated, the extrusion block extrudes the limiting block, and the limiting block accurately limits the oxygen nozzle.

The invention has the beneficial effects that: carry out accurate spacing to the oxygen mouth through the stopper, guarantee the test effect of oxygen mouth to improve the maintenance quality of oxygen mouth.

Furthermore, the number of the limiting blocks is two. The limit of the oxygen nozzle can be realized by arranging two limit blocks in different directions, so that the oxygen nozzle is attached to the pipe orifice of the connecting pipe.

Furthermore, one side of the limiting block, which is far away from the extrusion block, inclines downwards towards the connecting pipe. Because the space in the inner skleeve is less, can't place it when placing the oxygen air cock in order to prevent, the oxygen air cock is destroyed by the extrusion piece extrusion, consequently sets up towards the connecting pipe downward sloping with stopper one side, and the stopper can push the oxygen mouth towards the connecting pipe gradually to replace the artifical process of placing, convenient operation can not destroy the oxygen air cock yet.

Furthermore, the surface of the limiting block is provided with a rubber pad. The friction between the rubber pad and the oxygen nozzle is large, so that the fixation of the oxygen nozzle can be enhanced, and meanwhile, the elasticity of the rubber pad is also beneficial to clamping the oxygen nozzle.

Further, the connecting cavity is connected with a lifting support. Because the test equipment is bulky, the lifting support is convenient for lifting the test equipment, and the oxygen nozzle can be conveniently tested.

Further, the number of the connecting pipes is multiple. The device can be used for testing a plurality of oxygen nozzles simultaneously.

Furthermore, the limiting block is connected with a return spring. When the extrusion block does not extrude the limiting block, the limiting block automatically resets under the elasticity of the reset spring.

Drawings

FIG. 1 is a front view of an aircraft engine oxygen nozzle testing fixture;

FIG. 2 is a cross-sectional view of the outer sleeve of FIG. 1;

FIG. 3 is a schematic structural view of an oxygen nozzle.

Detailed Description

The following is further detailed by way of specific embodiments:

reference numerals in the drawings of the specification include: the device comprises an inner sleeve 1, a test joint 2, a connecting cavity 3, an outer sleeve 4, a support rod 5, an extrusion block 6, a limiting block 7, a sliding opening 8, a return spring 9, an oxygen nozzle 10, a connecting pipe 11, an air inlet 12 and a connecting seat 13.

Example 1: as shown in figures 1 and 2, an oxygen nozzle test fixture for an aircraft engine comprises a connecting cavity 3, a supporting rod 5 is welded at the bottom of the connecting cavity 3, the connecting cavity 3 is made of cast steel materials, a test connector 2 is welded on the left side of the connecting cavity 3, external threads are arranged on the outer surface of the test connector 2, the test connector 2 is in threaded connection with an interface of test equipment, the test equipment inflates air into the connecting cavity 3 through the test connector 2, and the inflation pressure is 0.0098MPa or 1.47 MPa.

The bottom of connecting chamber 3 is welded and is communicated with connecting pipe 11, and the coaxial welding in outside of connecting pipe 11 has inner skleeve 1, and inner skleeve 1 has seted up two slip mouths 8 correspondingly, and slip mouth 8 lateral sliding connection has stopper 7. As shown in fig. 3, oxygen nozzle 10 includes air inlet 12 and connecting seat 13, and the outer diameter of connecting seat 13 is far greater than the outer diameter of air inlet 12, and the distance between stopper 7 and the nozzle of connecting pipe 11 is equal to the thickness of connecting seat 13. The connecting cavity 3 is further rotatably connected with an outer sleeve 4 surrounding the inner sleeve 1, an extrusion block 6 for extruding the limiting block 7 is welded on the inner side wall of the outer sleeve 4, the thickness of the extrusion block 6 is gradually increased along the counterclockwise direction, and the limiting block 7 is abutted against the extrusion block 6.

Insert the connecting pipe 11 with the air inlet 12 of oxygen mouth 10 during the test in, the connecting seat 13 of oxygen mouth 10 and the mouth of pipe butt of connecting pipe 11, connecting seat 13 is located outside connecting pipe 11, anticlockwise rotation outer sleeve 4 this moment, the rotation of outer sleeve 4 drives the extrusion piece 6 rotatory, extrusion piece 6 extrudees stopper 7, stopper 7 moves towards connecting seat 13 in sliding opening 8, stopper 7 and connecting seat 13 contact the back, reach spacing purpose on connecting pipe 11 at connecting seat 13 chucking. The test equipment is used for inflating the connecting cavity 3 through the test connector 2 to complete the sealing test of the inflating nozzle.

Example 2: example 2 differs from example 1 only in that: the side of the limiting block 7 away from the squeezing block 6 is inclined downwards towards the connecting pipe 11. Because the space in inner skleeve 1 is less, can't place it when placing oxygen air cock 10 in order to prevent, lead to oxygen air cock 10 to be destroyed by the extrusion of extrusion piece 6, consequently set up one side of stopper 7 towards connecting pipe 11 downward sloping, stopper 7 can push oxygen air cock 10 towards connecting pipe 11 gradually, with the process that replaces artifical the placing, convenient operation can not destroy oxygen air cock 10 yet.

Example 3: example 2 differs from example 1 only in that: the limiting block 7 is connected with a return spring 9. When the extrusion block 6 does not extrude the limiting block 7, the limiting block 7 automatically resets under the elasticity of the return spring 9.

Example 4: example 4 differs from example 1 only in that: the connecting tube 11 is welded to the right side of the connecting chamber 3.

It should be noted that, for those skilled in the art, without departing from the structure of the present invention, many variations and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.

Claims

1. The utility model provides an oxygen mouth test fixture for aeroengine, is including connecting the chamber, the one side of connecting the chamber is equipped with test connector, the opposite side intercommunication of connecting the chamber has connecting pipe, its characterized in that: the connecting pipe is coaxially sleeved with an inner sleeve, a plurality of sliding ports are formed in the side wall of the inner sleeve, each sliding port is connected with a limiting block used for limiting an oxygen nozzle in a sliding mode, the connecting cavity is connected with an outer sleeve surrounding the inner sleeve in a rotating mode, an extrusion block is arranged on the inner wall of the outer sleeve, the thickness of the extrusion block is gradually increased along the anticlockwise direction, and the limiting blocks are abutted to the extrusion block.

2. The oxygen nozzle test fixture for aircraft engines of claim 1, characterized in that: the number of the limiting blocks is two.

3. The oxygen nozzle test fixture for aircraft engines of claim 2, characterized in that: one side of the limiting block, which is far away from the extrusion block, inclines downwards towards the connecting pipe.

4. The oxygen nozzle test fixture for aircraft engines of claim 3, characterized in that: the surface of the limiting block is provided with a rubber pad.

5. The oxygen nozzle test fixture for aircraft engines of claim 4, characterized in that: the connecting cavity is connected with a lifting support.

6. The oxygen nozzle test fixture for aircraft engines of claim 5, characterized in that: the number of the connecting pipes is multiple.

7. The aircraft engine oxygen nozzle test fixture of any one of claims 1 to 6, characterized in that: the limiting block is connected with a return spring.