CN214121860U - Aeroengine casing pressure test device - Google Patents
Aeroengine casing pressure test device Download PDFInfo
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- CN214121860U CN214121860U CN202023004553.4U CN202023004553U CN214121860U CN 214121860 U CN214121860 U CN 214121860U CN 202023004553 U CN202023004553 U CN 202023004553U CN 214121860 U CN214121860 U CN 214121860U
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Abstract
The utility model relates to an aeroengine machine casket pressure test device, it includes: the casing is configured to be covered at a pressure outlet of the casing, and the open end is communicated with the pressure outlet; the boss is annular, is arranged on the inner wall of the shell and is positioned between the open end and the closed end; the first plate is arranged in the shell, the outer edge of the first plate is abutted against the boss, and the first plate and the boss are matched to seal the open end; and an elastic member abutting against the first plate, the elastic member being configured to have a pre-compression amount to provide an acting force to abut the first plate against the boss; the first plate is configured to be pushed by the pressure in the casing when the pressure in the casing is larger than a limited value, and move in a direction away from the open end against the action force of the elastic piece, so that the pressure in the casing is released. The utility model discloses can effectively inject the maximum pressure upper limit in the machine casket, eliminate the machine casket because of the interior unusual sudden increase destruction that leads to of pressure, reduce safe risk.
Description
Technical Field
The utility model relates to an aerospace equipment field especially relates to an aeroengine machine casket pressure test device.
Background
The pressure-bearing casing is an important static pressure-bearing part and a life-limiting part on a civil aircraft engine, and the pressure-bearing casing needs to carry out a pressure airworthiness test under the action of internal pressure load. The highest pressure of a pressure-bearing casing pressure test of an aero-engine reaches about 10MPa, the test is a test with extremely high safety risk, and various safety risk factors which may occur need to be considered in the test development process. Among them, the abnormal sudden increase of the pressure load of the casing is one of the safety risks. Therefore, it is necessary to develop a pressure limiting device, which can effectively limit the maximum upper pressure limit in the casing and eliminate the test safety risk caused by sudden pressure increase.
Disclosure of Invention
Some embodiments of the utility model provide an aeroengine machine casket pressure test device for alleviate the high problem of experimental safety risk.
Some embodiments of the utility model provide an aeroengine machine casket pressure test device, it includes:
a housing having a cavity formed therein, the housing including an open end and a closed end opposite the open end, the housing being configured to be housed at a pressure outlet of a casing and to communicate with the pressure outlet through the open end;
the boss is annular, is arranged on the inner wall of the shell and is positioned between the open end and the closed end;
the first plate is arranged in the shell and is far away from the open end relative to the boss, the outer edge of the first plate is abutted against the boss, and the first plate and the boss are matched to seal the open end of the shell; and
an elastic member pressing against the first plate, the elastic member being configured to have a pre-compression amount to provide a force pressing the first plate against the boss;
the first plate is configured to be pushed by the pressure in the casing when the pressure in the casing is larger than a limited value, and move in a direction away from the open end against the action force of the elastic piece, so that the pressure in the casing is released.
In some embodiments, the aircraft engine case pressure test apparatus further comprises:
the second plate is arranged in the shell and is far away from the open end of the shell relative to the first plate, and the elastic piece is arranged between the second plate and the first plate; and
the preload piece is connected with the shell and pressed against the second plate, and the preload piece is configured to provide preload to enable the second plate to be pressed towards the first plate through the elastic piece.
In some embodiments, the closed end is provided with at least one first vent hole, the second plate has a shape that matches the shape of the interior cross-section of the housing, the second plate is configured to divide the interior of the housing into a first region and a second region, and the second plate is provided with at least one second vent hole that communicates the first region and the second region.
In some embodiments, the preload member includes a bolt having a first end located outside of the housing and a second end located inside of the housing and pressing against the second plate, the bolt being in threaded connection with the closed end.
In some embodiments, the closed end is provided with at least one first venting hole.
In some embodiments, the housing includes a scale area, the scale area is located in an area where the elastic member is located, the scale area is provided with scales for quantifying a compression amount of the elastic member, and the scale area is made of a transparent material.
In some embodiments, the compression of the spring is Δ L:
ΔL＝(P×π×d2/4)/(N×k)
wherein, P is the pressure value in the casing; d is the inner diameter of the annular boss; n is the number of the elastic pieces; k is the stiffness of the spring.
In some embodiments, the housing is cylindrical, the first plate is circular, and the first plate has an outer diameter greater than an inner diameter of the boss and less than an inner diameter of the housing.
In some embodiments, a circle of pressing portion extending towards the boss is arranged at a position where the first plate abuts against the boss.
In some embodiments, the pressing portion is made of a rubber material.
Based on the technical scheme, the utility model discloses following beneficial effect has at least:
in some embodiments, the casing is used for covering the pressure outlet of the casing, when the pressure in the casing is smaller than a limit value, the first plate is pressed against the boss through the acting force provided by the elastic element to seal the pressure outlet of the casing, when the pressure in the casing is larger than or equal to the limit value, the first plate is pushed by the pressure in the casing, the first plate overcomes the elastic force of the elastic element to move towards the direction far away from the open end, the open end is opened, the pressure in the casing is released, the maximum upper limit of the pressure in the casing can be effectively limited, the damage of the casing caused by abnormal sudden increase of the internal pressure is eliminated, and the safety risk is reduced.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without undue limitation to the invention. In the drawings:
fig. 1 is a schematic cross-sectional view of an aircraft engine case pressure test apparatus provided in accordance with some embodiments of the present invention;
fig. 2 is an external structural schematic diagram of an aircraft engine casing pressure test device according to some embodiments of the present invention.
The reference numbers in the drawings illustrate the following:
1-a shell; 11-a first venting aperture; 12-a scale zone; 13-a mounting portion;
2-boss;
3-a first plate; 31-a pressing part;
4-an elastic member;
5-a second plate; 51-a second vent;
6-preload piece.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It is obvious that the described embodiments are only some of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill 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 "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the invention.
As shown in fig. 1 and 2, some embodiments provide an aircraft engine case pressure test device, which includes a case 1, a boss 2, a first plate 3, and an elastic member 4.
The casing 1 has a cavity formed therein, the casing 1 includes an open end and a closed end opposite to the open end, and the casing 1 is configured to be housed at a pressure outlet of the casing and to communicate with the pressure outlet through the open end.
The boss 2 is annular and is arranged on the inner wall of the shell 1 and positioned between the open end and the closed end.
The first plate 3 is arranged in the shell 1, the outer edge of the first plate 3 is abutted to the boss 2, and the first plate 3 and the boss 2 are matched with the open end of the closed shell 1. The first plate 3 is remote from the open end with respect to the boss 2.
The elastic member 4 presses against the first plate 3, and the elastic member 4 is configured to have a pre-compression amount to provide an elastic force that presses the first plate 3 against the boss 2. Optionally, the elastic member 4 comprises a spring.
Wherein the first plate 3 is configured to be pushed by the pressure in the casing when the pressure in the casing is greater than a limit value, and move in a direction away from the open end against the elastic force of the elastic member 4, so that the pressure in the casing is released.
When the pressure test of the casing is carried out, the pressure in the casing is suddenly increased due to misoperation or other abnormal conditions, so that the safety risk of the unexpected damage of the casing is caused. The casing pressure test apparatus in the related art cannot completely reliably define the upper limit of the pressure inside the casing, and therefore cannot eliminate the above-described safety risk.
Based on this, according to the aeroengine casing pressure test device provided by the disclosure, during testing, the shell 1 is covered at the pressure outlet of the casing, when the pressure in the casing is smaller than a limited value, the first plate 3 is pressed against the boss 2 through the acting force provided by the elastic piece 4, the pressure outlet of the casing is sealed, when the pressure in the casing is larger than or equal to the limited value, the first plate 3 is pushed by the pressure in the casing, the elastic force of the elastic piece 4 is overcome, the first plate moves towards the direction far away from the open end, the open end is opened, so that the pressure in the casing is released, the maximum upper pressure limit in the casing can be effectively limited, and the damage of the casing caused by abnormal and sudden increase of the internal pressure is eliminated.
In some embodiments, the closed end of the casing 1 is provided with at least one first exhaust hole 11, when the pressure in the casing is greater than or equal to a limit value, the first plate 3 is separated from the boss 2, the open end is opened, and the compressed gas in the casing is exhausted through the first exhaust hole 11, so that the pressure in the casing is released.
In some embodiments, the aircraft engine case pressure testing apparatus further comprises a second plate 5 and a preload member 6.
The second plate 5 is arranged in the housing 1 and is away from the open end of the housing 1 relative to the first plate 3, and the elastic member 4 is arranged between the second plate 5 and the first plate 3.
The preload member 6 is coupled to the housing 1 and presses against the second plate 5, and the preload member 6 is configured to provide a preload force to press the second plate 5 against the first plate 3 through the elastic member 4.
By the preload member 6 pressing against the second plate 5, the second plate 5 is pressed against the elastic member 4, maintaining the initial compression amount of the elastic member 4. When the pressure in the casing is lower than a limit value, the first plate 3 is contacted with the boss 2 under the action of the elastic element 4 to realize the sealing of the casing; when the air pressure in the casing exceeds a limit value, the first plate 3 is separated from the boss 2 under the action of the internal pressure load, and the compressed air in the casing is released to realize the pressure reduction in the casing.
In some embodiments, the closed end of the housing 1 is provided with at least one first venting hole 11. The second plate 5 has a shape adapted to the inner sectional shape of the case 1, the second plate 5 is configured to divide the interior of the case 1 into a first region and a second region, and the second plate 5 is provided with at least one second vent hole 51, and the second vent hole 51 communicates the first region and the second region. When the first plate 3 is separated from the boss 2, the open end is opened, and compressed gas in the casing is released, the compressed gas is discharged through the second exhaust hole 51 and the first exhaust hole 11, so that the pressure reduction in the casing is realized.
In some embodiments, the preload member 6 comprises a bolt, a first end of which is located outside the housing 1 and a second end of which is located inside the housing 1 and presses against the second plate 5, the bolt being in threaded connection with the closed end of the housing 1.
By tightening the bolts, the initial amount of compression of the elastic member 4 is maintained. When the pressure in the casing is lower than a limit value, the first plate 3 is contacted with the boss 2 under the action of the elastic element 4 to realize the sealing of the casing; when the air pressure in the casing exceeds a limit value, the first plate 3 is separated from the boss 2 under the action of the internal pressure load, and the compressed air in the casing is discharged through the second exhaust hole 51 and the first exhaust hole 11, so that the internal pressure reduction of the casing is realized.
In some embodiments, the housing 1 includes a calibration area 12, the calibration area 12 is located in a region where the elastic member 4 is located, and the calibration area 12 is provided with a scale for quantifying the compression amount of the elastic member 4, so as to satisfy a pressure limiting threshold in the casing. The scale area 12 is made of transparent material, so that the compression amount of the elastic member 4 can be observed conveniently.
In some embodiments, the compression of the elastic member 4 is Δ L:
ΔL＝(P×π×d2/4)/(N×k)
wherein, P is the pressure value in the casing; d is the inner diameter of the annular boss 2; n is the number of the elastic members 4; k is the stiffness of the spring 4.
In some embodiments, the housing 1 is cylindrical, the first plate 3 is circular, the outer diameter of the first plate 3 is greater than the inner diameter of the boss 2, and the outer diameter of the first plate 3 is less than the inner diameter of the housing 1.
In some embodiments, the portion of the first plate 3 abutting against the boss 2 is provided with a ring of pressing portions 31 extending towards the boss 2. The abutment 31 has an inner diameter equal to the inner diameter of the boss 2.
In some embodiments, the pressing part 31 is made of a rubber material, which improves the sealing degree between the pressing part 31 and the boss 2.
In some embodiments, the open end of the housing 1 is externally provided with a ring of connecting portions 13, and the connecting portions 13 are provided with bolt holes for fixedly connecting with the outer surface of the casing through bolts. Optionally, the connection portion 13 may be provided with a sealing gasket for sealing with the casing.
Optionally, the connecting portion 13 includes a flange edge, the flange edge is provided with bolt holes, and the housing is fixed to the outer surface of the casing through the flange edge and the bolts.
One embodiment of an aircraft engine case pressure test apparatus is described in detail below with reference to fig. 1 and 2.
In this embodiment, the aircraft engine casing pressure test device includes a cylindrical casing 1, and a cavity is formed in the casing 1, and a first end of the casing 1 is an open end and a second end of the casing 1 is a closed end. The shell 1 is used for covering the outer surface of the casing, and the open end is communicated with a pressure outlet of the casing. The outside of the opening end of the shell 1 is provided with a circle of flange edge, the flange edge is provided with four bolt holes, the shell 1 is fixedly connected with the outer surface of the casing through the bolt holes and the bolts on the flange edge, and a sealing gasket is arranged between the flange edge and the outer surface of the casing for further sealing.
The position that the inner wall of casing 1 is close to the opening end is equipped with round boss 2, and boss 2 is the loop configuration, is equipped with first board 3 in the casing 1, and one side that first board 3 and boss 2 are close to is equipped with round suppressing part 31, and suppressing part 31 and boss 2 butt seal the opening end for prevent the compressed air leakage in the machine casket.
A second plate 5 is provided in the housing 1, the second plate 5 being remote from the open end with respect to the first plate 3. Be equipped with four springs (elastic component 4) in the casing 1, the first end of four springs all with the 5 butt of second board, the second end of four springs all with 3 butts of first board.
Four bolts (preload piece 6) are arranged at the closed end of the shell 1 in a penetrating mode, the first ends of the four bolts are located outside the shell 1, and the second ends of the four bolts are located inside the shell 1 and abut against the second plate 5. The four bolts are all in threaded connection with the closed end of the shell 1.
The closed end of the shell 1 is provided with a plurality of first exhaust holes 11, the second plate 5 is provided with a plurality of second exhaust holes 51, and the second exhaust holes 51 are communicated with the first exhaust holes 11 and used for releasing compressed air in the casing.
Through the rotation bolt, adjust the pretightning force, compress tightly second board 5, make second board 5 compression spring, apply initial compression volume for the spring, the spring supports and presses first board 3, and the portion 31 of pressing of first board 3 compresses tightly with boss 2, sealed open end.
When the pressure in the casing is lower than a limit value, the first plate 3 is contacted with the boss 2 under the action of the spring to realize the sealing of the casing; when the air pressure in the casing exceeds a limit value, the first plate 3 is separated from the boss 2 under the action of the internal pressure load, and the compressed air in the casing is discharged through the second exhaust hole 51 and the first exhaust hole 11, so that the internal pressure reduction of the casing is realized.
The specific implementation process comprises the following steps: setting the pressure limit value in the casing as P and calculating the required spring compression amount Delta L ═ P x pi x d2/4)/(nxk); are all made ofFour bolts are uniformly tightened, the compression of the spring is observed through the graduated area 12 on the housing 1, and when Δ L is reached, the tightening of the bolts is stopped.
In order to more accurately use the set of devices to limit the internal pressure of the casing, before implementation, a pressure calibration process is included: mounting the shell 1 on the outer surface of a standard pressure container, and placing the spring at an initial length; the pressure value P in the pressure container is controlled, different compression amounts delta L of the compression spring are measured, and the following corresponding relation between P and delta L is established:
N×k×ΔL＝P×π×d2/4
in the formula: n is the number of springs, k is the stiffness of the springs, and d is the inner diameter of the boss 2.
The aero-engine casing pressure test device provided by the embodiment prevents the internal pressure of the casing from exceeding a limited upper limit value by sealing the casing with limited pressure, and is suitable for a pressure airworthiness test of a pressure-bearing casing of a civil aero-engine.
Based on the above embodiments of the present invention, the technical features of one of the embodiments can be advantageously combined with one or more other embodiments without explicit negatives.
In the description of the present invention, it should be understood that the terms "first", "second", "third", etc. are used to define the components, and are only used for the convenience of distinguishing the components, and if not stated otherwise, the terms have no special meaning, and thus, should not be construed as limiting the scope of the present invention.
Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present invention and not for limiting the same; although the present invention has been described in detail with reference to preferred embodiments, it should be understood by those skilled in the art that: the invention can be modified or equivalent substituted for some technical features; without departing from the spirit of the present invention, it should be understood that the scope of the claims is intended to cover all such modifications and variations.
Claims (10)
1. The utility model provides an aeroengine machine casket pressure test device which characterized in that includes:
a housing (1) having a cavity formed therein, the housing (1) including an open end and a closed end opposite to the open end, the housing (1) being configured to be housed at a pressure outlet of a casing and to communicate with the pressure outlet through the open end;
the boss (2) is annular, is arranged on the inner wall of the shell (1), and is positioned between the open end and the closed end;
the first plate (3) is arranged in the shell (1) and is far away from the open end relative to the boss (2), the outer edge of the first plate (3) is abutted against the boss (2), and the first plate (3) and the boss (2) are matched to seal the open end of the shell (1); and
-an elastic member (4) pressing against the first plate (3), the elastic member (4) being configured with a pre-compression amount to provide a force pressing the first plate (3) against the boss (2);
wherein the first plate (3) is configured to be pushed by the pressure in the casing when the pressure in the casing is larger than a limit value, and move in a direction away from the open end against the action force of the elastic element (4) so as to release the pressure in the casing.
2. An aircraft engine case pressure test device according to claim 1, further comprising:
the second plate (5) is arranged in the shell (1) and is far away from the open end of the shell (1) relative to the first plate (3), and the elastic piece (4) is arranged between the second plate (5) and the first plate (3); and
a preload member (6) coupled to the housing (1) and pressing against the second plate (5), the preload member (6) being configured to provide a preload force to press the second plate (5) against the first plate (3) via the elastic member (4).
3. The aircraft engine case pressure test device according to claim 2, characterized in that the closed end is provided with at least one first vent hole (11), the shape of the second plate (5) is adapted to the internal cross-sectional shape of the casing (1), the second plate (5) is configured to divide the interior of the casing (1) into a first zone and a second zone, the second plate (5) is provided with at least one second vent hole (51), and the second vent hole (51) communicates the first zone and the second zone.
4. The aircraft engine case pressure test device according to claim 2, characterized in that said preload element (6) comprises a bolt, a first end of which is located outside said casing (1), a second end of which is located inside said casing (1) and presses against said second plate (5), said bolt being screwed to said closed end.
5. An aircraft engine casing pressure test device according to claim 1, characterised in that said closed end is provided with at least one first venting orifice (11).
6. The aircraft engine receiver pressure test device according to claim 1, characterized in that the housing (1) comprises a scale area (12), the scale area (12) is located in the area of the elastic member (4), the scale area (12) is provided with scales for quantifying the compression amount of the elastic member (4), and the scale area (12) is made of a transparent material.
7. The aircraft engine case pressure test device according to claim 1, characterized in that the compression of the elastic member (4) is Δ L:
ΔL＝(P×π×d2/4)/(N×k)
wherein, P is the pressure value in the casing; d is the inner diameter of the annular boss (2); n is the number of the elastic pieces (4); k is the stiffness of the elastic member (4).
8. The aircraft engine case pressure test device according to claim 1, wherein the housing (1) is cylindrical, the first plate (3) is circular, and the outer diameter of the first plate (3) is greater than the inner diameter of the boss (2) and less than the inner diameter of the housing (1).
9. The aircraft engine casing pressure test device of claim 1, characterized in that a circle of pressing part (31) extending towards the boss (2) is arranged at the part of the first plate (3) abutting against the boss (2).
10. The aircraft engine case pressure test device according to claim 9, wherein the pressing portion (31) is made of a rubber material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023004553.4U CN214121860U (en) | 2020-12-14 | 2020-12-14 | Aeroengine casing pressure test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023004553.4U CN214121860U (en) | 2020-12-14 | 2020-12-14 | Aeroengine casing pressure test device |
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| Publication Number | Publication Date |
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| CN214121860U true CN214121860U (en) | 2021-09-03 |
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| CN202023004553.4U Active CN214121860U (en) | 2020-12-14 | 2020-12-14 | Aeroengine casing pressure test device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526919A (en) * | 2022-02-21 | 2022-05-24 | 中国航发贵阳发动机设计研究所 | Test method and tool for verifying strength of special-shaped jet pipe of aircraft engine |
-
2020
- 2020-12-14 CN CN202023004553.4U patent/CN214121860U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526919A (en) * | 2022-02-21 | 2022-05-24 | 中国航发贵阳发动机设计研究所 | Test method and tool for verifying strength of special-shaped jet pipe of aircraft engine |
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