CN210088187U

CN210088187U - Aeroengine test sealing system and sealing plug device thereof

Info

Publication number: CN210088187U
Application number: CN201920737438.6U
Authority: CN
Inventors: 黄风良; 刘兵兵; 李博书
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2019-05-21
Filing date: 2019-05-21
Publication date: 2020-02-18
Anticipated expiration: 2029-05-21

Abstract

An object of the utility model is to provide an aeroengine test seals end cap device, its accuracy that can guarantee aeroengine test piece test process security and test data. Another object of the utility model is to provide an aeroengine tests sealing system, it has aforementioned sealed end cap device. The sealing plug device for testing the aircraft engine comprises a sealing base and the sealing plug, wherein the sealing base is connected with the sealing plug in a sealing mode and defines a passage of wiring or a pipe together, and the inner peripheral wall of the sealing plug is provided with a necking convex ring, so that the passage is subjected to necking at the necking convex ring relative to the upstream side and the downstream side of the necking convex ring.

Description

Aeroengine test sealing system and sealing plug device thereof

Technical Field

The utility model relates to an aeroengine test sealing system and sealed end cap device thereof.

Background

When an aero-engine test is carried out, parameters such as temperature and pressure of key parts in the aero-engine need to be monitored, thermocouple wires and pressure pipes for temperature measurement need to be connected to a monitoring and recording device on the outer side of the aero-engine through a test sealing plug device, the interior of the aero-engine is usually in a high-temperature and high-pressure working environment, and when the thermocouple wires and the pressure pipes are led out of a casing of the aero-engine, it needs to be guaranteed that high-temperature and high-pressure gas in the aero-engine cannot leak.

The inventor finds that when an aircraft engine test piece is tested, repeated tests are needed to monitor various performances, and along with the increase of the pressure ratio and the continuous increase of the thrust performance of an aircraft engine, the traditional aircraft engine test sealing plug device can be out of work quickly under the repeated impact action of high temperature and high pressure, so that the leakage of high temperature and high pressure gas is caused, the test risk is increased, and the accuracy of test data is influenced. Therefore, a sealing plug device capable of ensuring the accuracy of test data and the safety of the test process is urgently needed.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an aeroengine test seals end cap device, its accuracy that can guarantee aeroengine test piece test process security and test data.

Another object of the utility model is to provide an aeroengine tests sealing system, it has aforementioned sealed end cap device.

The sealing plug device for testing the aircraft engine comprises a sealing base and the sealing plug, wherein the sealing base is connected with the sealing plug in a sealing mode and defines a channel for wiring or pipes together, and the inner peripheral wall of the sealing plug is provided with a necking convex ring, so that the channel is subjected to necking at the necking convex ring relative to the upstream side and the downstream side of the necking convex ring.

In one or more embodiments, the sealing base includes a lower collar and an upper collar in communication with the lower collar;

the sealing plug comprises an upper annular wall for limiting an upper inner cavity, a lower annular wall for limiting a lower inner cavity and the necking convex ring for limiting a necking channel, wherein the necking channel is spaced and communicated with the upper inner cavity and the lower inner cavity;

and the upper ring sleeve is sleeved outside one of the lower ring walls and connected with the other of the lower ring walls in a threaded manner.

In one or more embodiments, an inner wall surface of the inner one of the upper collar and the lower collar is roughened.

In one or more embodiments, the outer side is provided with a lower shoulder surface opposite to the end surface of the inner side, and a lower gasket for sealing is provided between the lower shoulder surface and the end surface.

In one or more embodiments, the lower gasket is a split gasket that also functions to cinch a wire or tube therethrough.

In one or more embodiments, the aircraft engine test seal plug apparatus further comprises a cap screw having a lower nipple that is threaded onto one of the upper annular walls and a threaded connection to the other, and an outlet that communicates with the channel to allow a wire or tube to pass therethrough.

In one or more embodiments, an inner wall surface of one of the lower adapter and the upper annular wall, which is located on an inner side, is a rough surface.

In one or more embodiments, the outer side has an upper shoulder surface facing the inner side end surface, and an upper gasket for sealing is provided between the upper shoulder surface and the end surface.

In one or more embodiments, the upper gasket is a split gasket that also functions to cinch a wire or tube therethrough.

The aeroengine test sealing system for achieving the other purpose is arranged on an aeroengine casing and is characterized by comprising the aeroengine test sealing plug device, wherein the sealing base is welded on the aeroengine casing, a wire or a pipe penetrates through the channel, the gap between the wire or the pipe and the channel is filled with soft packing, and high-temperature glue or cement is poured into the channel.

The beneficial effects of the utility model reside in that:

through set up the throat bulge loop in sealed end cap, can be sealed with the cooperation of throat bulge loop in the upstream side of throat bulge loop and downstream side department like wadding such as high temperature resistant flexible asbestos rope jam and high temperature glue or cement to even if there is a little air current to flow, because the reason of throat bulge loop, it is very big to lead to pneumatic loss, with this can reduce the air current and leak, improve sealing quality, and then ensured aeroengine experimental security of experimenting piece and the accuracy of test data.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:

FIG. 1 is a schematic cross-sectional view of one embodiment of an aircraft engine test seal plug apparatus.

Detailed Description

The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.

It should be noted that, where used, the following description of upper, lower, left, right, front, rear, top, bottom, positive, negative, clockwise, and counterclockwise are used for convenience only and do not imply any particular fixed orientation. In fact, they are used to reflect the relative position and/or orientation between the various parts of the object.

Fig. 1 is a schematic cross-sectional view of an embodiment of a sealing plug device for testing an aircraft engine, where the sealing plug device includes a sealing plug 1 and a sealing base 2. The sealing base 2 and the sealing plug 1 are connected in a sealing manner, and the inner peripheral sides of the sealing base 2 and the sealing plug 1 jointly define a channel 10 for arranging thermocouple wires or pressure tubes for temperature measurement.

The inner circumferential wall 11 of the sealing plug 1 has a collar 12 projecting toward the channel 10, so that the inner diameter of the channel 10 decreases at the collar 12, so that the channel 10 projects at the collar 12 on both the upstream side 12a and the downstream side 12b of the collar 12.

In one embodiment, the aero-engine test seal plug device shown in fig. 1 is used in an aero-engine test seal system disposed on a casing of an aero-engine, which is not shown in the drawings, wherein the seal base 2 is connected to the casing of the aero-engine by welding, and a wire or a pipe (not shown in the drawings) passes through the passage 10 from the inside of the casing. In one embodiment, the line or tube may be a test line or tube, such as a thermocouple line or a pressure tube. The gap between the line or tube and the channel 10 is filled with a soft filler (not shown) such as a high temperature resistant flexible asbestos cord, to prevent high temperature and high pressure gas from leaking along the gap between the line or tube and the sealing plug device. Meanwhile, high temperature glue or cement (not shown in the figure) is poured into the channel 10 to further fill the gap between the line or pipe and the sealing plug device, so as to prevent the leakage of high temperature and high pressure gas.

Through setting up throat bulge loop 12 in sealed end cap 1, can cooperate with throat bulge loop 12 at the upstream side 12a and the downstream side 12b department of throat bulge loop 12 sealed with the cooperation of high temperature glue or cement etc. like wadding such as high temperature resistant flexible asbestos rope jam to even if there is a little air current to flow, because the reason of throat bulge loop 12, it is very big to lead to pneumatic loss, with this can reduce the air current and leak, improve sealing quality, and then ensured aeroengine experimental security of experimenting piece and the accuracy of test data.

Although one embodiment of the present sealing system and its sealing plug device is described above, in other embodiments of the present sealing system and its sealing plug device, the sealing plug device may have many more details than the embodiments described above, and at least some of these details may vary widely. At least some of these details and variations are described below in several embodiments.

With continued reference to fig. 1, in one embodiment of the sealing plug device, specifically, the sealing base 2 includes a lower collar 21 and an upper collar 20 in communication with the lower collar 21, and the sealing plug 1 further includes an upper annular wall 13 and a lower annular wall 14, wherein the upper annular wall 13 defines an upper cavity 130 inside the sealing plug 1, the lower annular wall 14 defines a lower cavity 140 inside the sealing plug 1, and the necking collar 12 defines a necking channel 120. The throat passage 120 is spaced from and communicates with the upper lumen 130 and the lower lumen 140. Wherein, between the upper ring cover 20 and the lower ring wall 14, as shown in the figure: an internal thread is provided on the inner peripheral side of the lower annular wall 14, and an external thread is provided on the outer peripheral side of the upper collar 20, and the lower annular wall 14 is screwed to the upper collar 20 by being externally fitted. The threaded connection can ensure that the joint between the sealing plug 1 and the sealing base 2 has good sealing performance. In an embodiment different from the one shown in the drawings, an external thread is provided on the outer peripheral side of the lower annular wall 14, and an internal thread is provided on the inner peripheral side of the upper ring 20, and the upper ring 20 is screwed to the lower annular wall 14 so as to be externally fitted.

In one embodiment of the sealing plug device, the sealing plug 1 and the sealing base 2 are connected by screwing the lower annular wall 14 onto the upper annular sleeve 20, and in this embodiment, the inner wall surface of the upper annular sleeve 20 on the inner side is rough, so as to enhance the adhesion between high temperature glue or cement and the inner wall surface of the upper annular sleeve 20, further increase the sealing effect, and prevent the leakage of high temperature and high pressure gas. In an embodiment different from that shown in the drawings, the sealing plug 1 and the sealing base 2 are screwed together by means of an upper ring 20 fitted around the lower ring wall 14, and the inner wall surface of the lower ring wall 14 located inside is roughened.

In one embodiment of the sealing plug device, the sealing plug 1 and the sealing base 2 are connected by screwing the lower annular wall 14 around the upper annular sleeve 20, as shown in the figure, in which embodiment the lower annular wall 14 on the outer side is provided with a lower shoulder surface 15 opposite to the end surface of the upper annular sleeve 20 on the inner side, and a lower gasket 4 for sealing is arranged between the lower shoulder surface 15 and the end surface of the upper annular sleeve 20, thereby further increasing the sealing effect. In an embodiment of the sealing plug device different from that shown in the figure, the sealing plug 1 and the sealing base 2 are screwed together by means of an upper collar 20 fitted around the lower collar 14, in which case the lower shoulder 15 is provided by the upper collar 20 and faces the end face of the lower collar 14, and the lower washer 4 is arranged between the lower shoulder provided by the upper collar 20 and the end face of the lower collar 14.

In one embodiment of the sealed plug arrangement, the lower gasket 4 is an open gasket capable of gripping a wire or tube passing therethrough to act as a securement for the test wire or tube.

In one embodiment of the sealed plug device, the sealed plug device further includes a cap screw 3, the cap screw 3 has an outlet 30 and a lower sleeve 31, wherein, as shown in the figure, an inner circumference of the lower sleeve 31 is provided with an inner thread, correspondingly, the upper ring wall 13 of the sealed plug 1 is provided with an outer thread, the cap screw 3 and the sealed plug 1 are connected by screwing the lower sleeve 31 on the upper ring wall 13, as shown in the figure, and the connected outlet 30 is communicated with the channel 10 to allow a wire or a pipe to pass through. By arranging the pressing cap bolt 3, the sealing plug is further sealed at the outlet 30, so that the sealing performance of the sealing plug is improved. In an embodiment different from the illustrated embodiment, the outer peripheral side of the lower sleeve 31 is provided with male threads, the upper ring wall 13 of the seal plug 1 is provided with female threads, and the cap bolt 3 and the seal plug 1 are screwed together by externally fitting the upper ring wall 13 over the lower sleeve 31.

In one embodiment of the sealing plug device, the pressing cap bolt 3 and the sealing plug 1 are in threaded connection by sleeving the lower sleeve 31 on the upper annular wall 13 as shown in the figure, and the inner wall surface of the upper annular wall 13 located on the inner side is a rough surface, so that the bonding between high-temperature glue or cement and the inner wall surface of the upper annular wall 13 can be enhanced, the sealing effect is further increased, and the leakage of high-temperature and high-pressure gas is prevented. In an embodiment different from that shown in the drawings, the cap bolt 3 and the sealing plug 1 are screwed together by sleeving the upper annular wall 13 on the lower sleeve 31, and the inner wall surface of the lower sleeve 31 on the inner side is rough.

In one embodiment of the plug sealing device, the cap screw 3 and the plug 1 are screwed together by means of a lower sleeve 31 that is fitted over the upper annular wall 13 as shown in the drawing, the outer lower sleeve 31 has an upper shoulder surface 32 that faces the inner end surface of the upper annular wall 13, and an upper gasket 5 for sealing is provided between the upper shoulder surface 32 and the end surface of the upper annular wall 13, thereby further increasing the sealing effect. In an embodiment of the plug device different from that shown in the figure, the cap bolt 3 and the plug 1 are screwed together by means of the upper annular wall 13 being sleeved on the lower sleeve 31, the upper shoulder surface 32 is provided by the upper annular wall 13 and faces the end surface of the lower sleeve 31, and the upper washer 5 is disposed between the lower shoulder surface provided by the upper annular wall 13 and the end surface of the lower sleeve 31.

In one embodiment of the sealed plug arrangement, the upper gasket 5 is an open gasket capable of gripping a wire or tube passing therethrough to act as a securement for the test wire or tube.

Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.

Claims

1. The sealing plug device for testing the aero-engine comprises a sealing base and is characterized by further comprising a sealing plug, the sealing base is connected with the sealing plug in a sealing mode and defines a wiring or pipe channel together, and a necking convex ring is arranged on the inner peripheral wall of the sealing plug, so that the channel is subjected to both the convex shrinkage at the position of the necking convex ring and is opposite to the upstream side and the downstream side of the necking convex ring.

2. The aero-engine test seal plug apparatus according to claim 1, wherein the seal base includes a lower collar and an upper collar in communication with the lower collar;

3. The aircraft engine test seal plug apparatus as claimed in claim 2, wherein an inner wall surface of an inner one of said upper collar and said lower collar is roughened.

4. The aircraft engine test seal plug apparatus as claimed in claim 2, wherein the side located on the outer side is provided with a lower shoulder surface opposite to the end surface of the side located on the inner side, and a lower gasket for sealing is provided between the lower shoulder surface and the end surface.

5. The aircraft engine test seal plug apparatus of claim 4, wherein said lower gasket is a split gasket and is further adapted to grip a wire or tube passing therethrough.

6. The aircraft engine test seal plug apparatus as defined in claim 2, further comprising a cap bolt having a lower socket that is received over one of said upper annular walls and is threadably received in the other of said upper annular walls, and an outlet in communication with said channel to permit a wire or tube to pass therethrough.

7. The aircraft engine test seal plug apparatus as defined in claim 6, wherein an inner wall surface of an inboard one of said lower nipple and said upper annular wall is roughened.

8. The aircraft engine test seal plug device according to claim 6, wherein the outer side has an upper shoulder surface opposite to the inner side end surface, and an upper gasket for sealing is provided between the upper shoulder surface and the end surface.

9. The aircraft engine test seal plug apparatus of claim 8, wherein said upper gasket is a split gasket and is further adapted to grip a wire or tube passing therethrough.

10. An aircraft engine test sealing system arranged on an aircraft engine casing, characterized by comprising the aircraft engine test sealing plug device according to any one of claims 1 to 9, wherein the sealing base is welded on the aircraft engine casing, a wire or a pipe passes through the channel, a gap between the wire or the pipe and the channel is filled with a soft filler, and the channel is further poured with high-temperature glue or cement.