CN212567933U - Aeroengine test device exhaust system and aeroengine test device - Google Patents
Aeroengine test device exhaust system and aeroengine test device Download PDFInfo
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- CN212567933U CN212567933U CN202021561201.6U CN202021561201U CN212567933U CN 212567933 U CN212567933 U CN 212567933U CN 202021561201 U CN202021561201 U CN 202021561201U CN 212567933 U CN212567933 U CN 212567933U
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Abstract
The utility model relates to an aeroengine test device exhaust system and aeroengine test device, wherein aeroengine test device exhaust system include blast pipe (1), noise elimination section of thick bamboo (2), be used for reducing the first noise elimination spare (3) and second noise elimination spare (4) of noise elimination, noise elimination section of thick bamboo (2) connect in the export of blast pipe (1), first noise elimination spare (3) set up in noise elimination section of thick bamboo (2), second noise elimination spare (4) set up in the export of noise elimination section of thick bamboo (2), just second noise elimination spare (4) are constructed and are prevented that the rainwater from getting into noise elimination section of thick bamboo (2). The aircraft engine testing device comprises an aircraft engine testing device exhaust system. The exhaust system can effectively reduce exhaust noise and exhaust pressure loss, and has a rainproof function.
Description
Technical Field
The utility model relates to an aeroengine technical field especially relates to an aeroengine test device.
Background
The fan and the gas compressor are important and complex parts on the aircraft engine, and in order to ensure the safe operation of the fan and the gas compressor, before the fan and the gas compressor are put into use formally, experimental research needs to be carried out on the pneumatic acoustic performance of the fan and the engine so as to ensure that the pneumatic acoustic performance of the fan and the engine can reach a preset standard.
At present, when the test research is carried out on the pneumatic acoustic performance of the fan and the air compressor, a special test device is generally adopted, but the test device in the related technology is influenced by noise generated by exhaust of an exhaust port when in use, so that the research on the pneumatic acoustic performance of the fan and the air compressor is influenced.
It is noted that the information disclosed in this background section of the invention is only for enhancement of understanding of the general background of the invention, and should not be taken as an acknowledgement or any form of suggestion that this information constitutes prior art already known to a person skilled in the art.
SUMMERY OF THE UTILITY MODEL
An embodiment of the utility model provides an aeroengine test device exhaust system and aeroengine test device can reduce the noise that the exhaust produced to experimental influence.
According to the utility model discloses an aspect provides an aeroengine test device exhaust system, include:
an exhaust pipe;
the silencing cylinder is connected to the outlet of the exhaust pipe;
the first noise elimination piece is used for reducing noise and arranged in the noise elimination cylinder; and
and a second muffler for reducing noise, provided at an outlet of the muffler barrel, and configured to prevent rainwater from entering the muffler barrel.
In some embodiments, the second muffler component includes a support bracket coupled to the muffler cartridge and a muffler mounted to the support bracket.
In some embodiments, the support frame includes a first support portion disposed opposite to the outlet of the muffling cartridge and a second support portion connected between the first support portion and the muffling cartridge, the second support portion having an exhaust outlet.
In some embodiments, a muffler is mounted on the first support, the muffler including a flow directing surface configured to direct gas exhausted by the exhaust pipe to the exhaust outlet.
In some embodiments, the flow guiding surface comprises an arc-shaped surface, the convex surface of the arc-shaped surface facing the first support part.
In some embodiments, the support frame and the exhaust pipe are both vertically arranged, and the first support part is in a pyramid shape.
In some embodiments, the cross-sectional area of the upper end surface of the second support portion is greater than the cross-sectional area of the lower end surface of the second support portion.
In some embodiments, the cross-sectional area of the second support portion gradually decreases from top to bottom.
In some embodiments, the aircraft engine test unit exhaust system further comprises an expansion pipe connected to the outlet of the exhaust pipe, the expansion pipe being connected to the muffling cartridge.
In some embodiments, the aircraft engine test rig exhaust system further comprises an exhaust valve for regulating exhaust pipe flow, and a third muffling element is disposed upstream of the exhaust valve.
According to the utility model discloses a further aspect provides an aeroengine test device, including foretell aeroengine test device exhaust system.
Based on the technical scheme, the embodiment of the utility model provides an outlet at the blast pipe is equipped with the noise elimination section of thick bamboo, is equipped with first noise elimination spare in the inside of noise elimination section of thick bamboo, is provided with the second noise elimination spare in the outlet of noise elimination section of thick bamboo, through first noise elimination spare and second noise elimination spare, can effectively reduce the noise that the exhaust produced, reduce the influence to the test result, improve experimental measurement accuracy; moreover, the second silencing piece has a rainproof function, can prevent rainwater from carrying out the silencing tube, and effectively protects the test device.
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 structural diagram of an embodiment of the exhaust system of the aircraft engine testing device of the present invention.
Fig. 2 is the internal structure schematic diagram of the support frame in an embodiment of the exhaust system of the aircraft engine testing device of the present invention.
In the figure:
1. an exhaust pipe; 2. an acoustic elimination cylinder; 3. a first muffler member; 4. a second muffler; 41. a support frame; 411. a first support section; 412. a second support portion; 42. a muffler; 5. an expansion tube; 6. an exhaust valve; 7. a third sound attenuating element.
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", "lateral", "longitudinal", "front", "rear", "left", "right", "up", "down", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the scope of the invention.
As shown in fig. 1, in an embodiment of the exhaust system of the aircraft engine testing device provided by the present invention, the exhaust system includes an exhaust pipe 1, a silencing pot 2, a first silencing piece 3 for reducing noise and a second silencing piece 4 for reducing noise, the silencing pot 2 is connected to the outlet of the exhaust pipe 1, the first silencing piece 3 is disposed in the silencing pot 2, the second silencing piece 4 is disposed in the outlet of the silencing pot 2, and the second silencing piece 4 is configured to prevent rainwater from entering the silencing pot 2.
In the above embodiment, the muffler tube 2 is arranged at the outlet of the exhaust pipe 1, the first muffler part 3 is arranged inside the muffler tube 2, the second muffler part 4 is arranged at the outlet of the muffler tube 2, and the first muffler part 3 and the second muffler part 4 can effectively reduce the noise generated by exhaust, reduce the influence on the test result, and improve the test measurement precision; moreover, the second silencing part 4 has a rainproof function, can prevent rainwater from carrying out a silencing barrel, effectively protects the test device, and improves the adaptability of the test device to severe weather such as wind, rain and the like.
The exhaust system in the embodiment of the invention can effectively reduce the noise generated by exhaust, reduce the influence of background noise on noise collection in a pneumatic acoustic performance test and improve the accuracy of a test result; also has the function of rain protection.
In some embodiments, the muffling cylinder 2 includes a cylinder portion and a connecting portion connected to a side of the cylinder portion close to the exhaust pipe 1. The silencing tube 2 can be fixedly connected to a fixed part, such as a test bed or a wall or other objects which are fixed relative to the ground, through a connecting part, so as to ensure the stability of the silencing tube 2,
in some embodiments, the second muffler element 4 includes a support bracket 41 and a muffler 42, the support bracket 41 is connected to the muffler barrel 2, and the muffler 42 is mounted to the support bracket 41.
Through setting up support frame 41, can make the silencer 42 that sets up in the export of silencing tube 2 more firm, prevent that silencer 42 from receiving carminative impact force and taking place to rock, influence noise cancelling effect.
In some embodiments, the supporting frame 41 includes a first supporting portion 411 and a second supporting portion 412, the first supporting portion 411 is disposed opposite to the outlet of the muffling cylinder 2, the second supporting portion 412 is connected between the first supporting portion 411 and the muffling cylinder 2, and the second supporting portion 412 is provided with an exhaust outlet.
By providing the first support portion 411 disposed opposite to the outlet of the muffling cylinder 2, the exhaust gas of the exhaust pipe 1 can be blocked so that the exhaust gas is discharged from the exhaust outlet on the second support portion 412.
Since the first support portion 411 is disposed opposite to the outlet of the muffling cartridge 2 and the exhaust outlet is disposed on the second support portion 412, the flow direction of the exhaust gas is changed before the exhaust.
In order to reduce noise generated when the flow direction of the exhaust gas is changed, in some embodiments, the muffler 42 is mounted on the first support portion 411, and the muffler 42 includes a guide surface configured to guide the gas discharged from the exhaust pipe 1 to the exhaust outlet.
Through setting up the water conservancy diversion face, can guide the exhaust, be favorable to making carminative flow more smooth and easy, be favorable to reducing the noise.
In some embodiments, the flow guiding surface comprises an arc-shaped surface, the convex surface of which faces the first supporting portion 411. Through setting up the arcwall face, can make carminative flow direction transition gently, the air current flows more evenly and stably, reduces the exhaust flow loss, avoids the great noise that the right angle change brought.
In some embodiments, the supporting frame 41 and the exhaust pipe 1 are both vertically disposed, and the first supporting portion 411 has a pyramid shape. The rain-proof function can be effectively realized by the arrangement, so that the rainwater is dispersed to the periphery along the inclined outer surface from the top of the pyramid, and the rainwater is effectively prevented from entering the silencing barrel 2 and even the exhaust pipe 1 to influence the test device.
In some embodiments, the first supporting portion 411 may have a triangular pyramid shape, a rectangular pyramid shape, a hexagonal pyramid shape, or the like.
In some embodiments, the cross-sectional area of the upper end surface of the second support part 412 is greater than the cross-sectional area of the lower end surface of the second support part 412.
This arrangement allows the second support portion 412 to form an expanding structure in the air flow direction, so as to reduce the exhaust flow rate and also contribute to reducing the noise generated by the exhaust.
In some embodiments, the cross-sectional area of the second support part 412 gradually decreases from top to bottom. The structure arrangement can make the exhaust flow smoother, reduce the airflow disturbance and reduce the noise generated by the airflow disturbance.
In some embodiments, the second support part 412 includes a first support bar connected between an outer edge of the second support part 412 and the muffling cartridge 2, and a second support bar connected to a center of the second support part 412.
The number of the first supporting rods can be multiple, and an exhaust outlet is formed between every two adjacent supporting rods. The second supporting rod can play a good supporting role for the first supporting part 411 to prevent the first supporting part 411 from being crushed by excessive rain.
The second support part 412 with the above structure can increase the area of the exhaust outlet, so that the exhaust can be discharged more smoothly, and the overall weight of the support frame 41 can be reduced.
The muffler 42 may be disposed between the second support part 412 and the second support bar to facilitate the formation of the arc-shaped flow guide surface.
In some embodiments, the aircraft engine test unit exhaust system further comprises an expansion pipe 5 connected to the outlet of the exhaust pipe 1, the expansion pipe 5 being connected to the muffling cartridge 2.
By providing the extension pipe 5 at the outlet of the exhaust pipe 1, the flow velocity at the outlet of the exhaust pipe 1 can be reduced, and the noise generated by the exhaust gas can be reduced.
In some embodiments, the exhaust system of the aircraft engine test device further comprises an exhaust valve 6 for regulating the flow of the exhaust pipe 1, and a third silencing piece 7 is arranged upstream of the exhaust valve 6.
The exhaust valve 6 is arranged on the exhaust pipe 1, and the exhaust flow can be effectively controlled by arranging the exhaust valve 6. By providing the third muffler element 7 upstream of the exhaust valve 6, the noise generated by the exhaust valve 6 when the flow rate is varied can be reduced.
In other embodiments, a noise damper may be provided downstream of the exhaust valve 6 to further reduce the noise generated at the exhaust valve 6.
In the above embodiments, the first silencing part 3, the silencer 42 and the third silencing part 7 may adopt an inner liner made of sound absorbing material and/or a perforated sound absorbing plate filled with sound absorbing material to absorb sound, reduce exhaust noise reflection and reduce noise.
In some embodiments, the end of the exhaust pipe 1 is inserted into the interior of the muffling barrel 2 to facilitate the tight connection between the exhaust pipe 1 and the muffling barrel 2, thereby preventing exhaust leakage and noise generated by the exhaust leakage.
In some embodiments, the inner wall of the muffling cartridge 2 is provided with a sound absorbing plate. The sound absorption plate comprises a perforated plate, sound absorption materials are filled in the perforated plate, pneumatic noise of exhaust airflow can be partially absorbed, and noise reflection of the wall surface is reduced.
Based on foretell aeroengine test device exhaust system, the utility model discloses still provide an aeroengine test device, this aeroengine test device includes foretell aeroengine test device exhaust system.
The test device can comprise a device for carrying out pneumatic acoustic performance research on components such as a fan, an air compressor, a turbine and the like of an aircraft engine, and can also comprise other test devices with an exhaust system.
The positive technical effects of the exhaust system of the aircraft engine testing device in the above embodiments are also applicable to the aircraft engine testing device, and are not described herein again.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention and not to limit it; 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 utility model discloses a do not deviate from under the prerequisite of the principle, still can be right the utility model discloses a specific embodiment modifies or carries out the equivalent replacement to some technical features, and these are modified and should be covered with the equivalent replacement in the middle of the technical scheme scope of the utility model.
Claims (10)
1. An aircraft engine test device exhaust system, comprising:
an exhaust pipe (1);
the silencing cylinder (2) is connected to the outlet of the exhaust pipe (1);
a first muffler (3) for reducing noise, provided in the muffler barrel (2); and
a second muffler member (4) for reducing noise, provided at an outlet of the muffler cylinder (2), and the second muffler member (4) is configured to prevent rainwater from entering the muffler cylinder (2).
2. The aircraft engine test unit exhaust system according to claim 1, characterised in that the second muffler (4) comprises a support bracket (41) connected to the muffler cartridge (2) and a muffler (42) mounted to the support bracket (41).
3. The aircraft engine test unit exhaust system according to claim 2, characterized in that the support frame (41) comprises a first support (411) arranged opposite to the outlet of the muffling cartridge (2) and a second support (412) connected between the first support (411) and the muffling cartridge (2), the second support (412) being provided with an exhaust outlet.
4. The aircraft engine testing device exhaust system according to claim 3, characterized in that the muffler (42) is mounted on the first support (411), the muffler (42) comprising a flow guiding surface configured to guide gas exiting the exhaust pipe (1) to the exhaust outlet.
5. The aircraft engine test unit exhaust system according to claim 4, wherein the deflector surface comprises an arc-shaped surface with a convex surface facing the first support part (411).
6. The aircraft engine testing device exhaust system according to claim 3, characterized in that the support frame (41) and the exhaust pipe (1) are both arranged vertically, the first support part (411) being pyramid-shaped.
7. The aircraft engine test unit exhaust system according to claim 3, wherein the cross-sectional area of the upper end face of the second support portion (412) is greater than the cross-sectional area of the lower end face of the second support portion (412).
8. The aircraft engine test unit exhaust system of claim 3, wherein the cross-sectional area of the second support portion (412) decreases from top to bottom.
9. The aircraft engine test unit exhaust system according to claim 1, further comprising an exhaust valve (6) for regulating the flow of the exhaust pipe (1), wherein a third sound attenuation element (7) is arranged upstream of the exhaust valve (6).
10. An aircraft engine testing device, characterized by comprising an aircraft engine testing device exhaust system according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021561201.6U CN212567933U (en) | 2020-07-31 | 2020-07-31 | Aeroengine test device exhaust system and aeroengine test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021561201.6U CN212567933U (en) | 2020-07-31 | 2020-07-31 | Aeroengine test device exhaust system and aeroengine test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212567933U true CN212567933U (en) | 2021-02-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021561201.6U Active CN212567933U (en) | 2020-07-31 | 2020-07-31 | Aeroengine test device exhaust system and aeroengine test device |
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| Country | Link |
|---|---|
| CN (1) | CN212567933U (en) |
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- 2020-07-31 CN CN202021561201.6U patent/CN212567933U/en active Active
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