CN220084192U - Turbine casing wall temperature sensor, mounting structure and aeroengine - Google Patents
Turbine casing wall temperature sensor, mounting structure and aeroengine Download PDFInfo
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- CN220084192U CN220084192U CN202321553458.0U CN202321553458U CN220084192U CN 220084192 U CN220084192 U CN 220084192U CN 202321553458 U CN202321553458 U CN 202321553458U CN 220084192 U CN220084192 U CN 220084192U
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- 239000000919 ceramic Substances 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 claims 1
- 238000001514 detection method Methods 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 description 5
- 238000009529 body temperature measurement Methods 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000008054 signal transmission Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Abstract
The utility model provides a turbine casing wall temperature sensor, a mounting structure and an aeroengine, wherein the turbine casing wall temperature sensor comprises a connector, a cable and a sensing part, the connector is electrically connected with the sensing part through the cable, the sensing part comprises a first sensing part and a second sensing part, the first sensing part and the second sensing part are respectively positioned at two sides of a casing side rib and are connected with the casing side rib, so that the temperature of the casing side rib is detected, the cable is used for transmitting a signal representing the temperature to the connector, and the first sensing part and the second sensing part for sensing the temperature are arranged at the same time, so that the detection reliability of the turbine casing wall temperature sensor is improved, and meanwhile, the basis of a clearance control system for judging the casing temperature sensor is increased.
Description
Technical Field
The utility model relates to the technical field of aeroengines, in particular to a turbine casing wall temperature sensor, an installation structure and an aeroengine.
Background
The clearance between the outer ring of the turbine casing and the tips of the rotor blades in an aeroengine has a great influence on the efficiency of the turbine and the fuel consumption of the engine. A certain gap exists between the blade tip and the stator casing, and under the action of pressure difference existing between the pressure surface and the suction surface of the blade, fuel gas can leak, so that the working efficiency of an engine is reduced, and the fuel consumption is increased. Therefore, it is desirable from the standpoint of fuel consumption that tip clearances be as small as possible. Due to the influence of various factors such as temperature, centrifugal force and the like, the clearance between the blade tip and the casing also changes under different working states of the engine due to different expansion responses of the blade and the casing. Too small a tip clearance can also lead to friction between the blades and the casing, reducing the working life of the engine. In order to prevent adverse effects due to the change in tip clearance, it is essential to control the thermal expansion of the casing. This object is achieved by a gap control system (Clearance Control). By the clearance control, the working efficiency of the engine is improved, and the fuel consumption is reduced.
Turbine active clearance control systems can be categorized in terms of control scheme: open-loop, semi-closed-loop, and full-closed-loop. The completely open-loop active clearance control system only has a pre-adjustment plan, and is not applicable to scenes with high control precision requirements; the semi-closed loop active clearance control measures state parameters of T495, N2, T3 and the like through an airborne sensor, calculates the opening of a clearance control valve according to a preset control plan or an EEC built-in clearance model, and has certain advantages due to high control accuracy; the key of the technology is a tip clearance sensor, and the problem of online measurement of the tip clearance is not thoroughly solved worldwide at present. Semi-closed loop control is therefore currently the most common approach in turbine clearance control.
In the semi-closed loop control scheme, although the turbine casing temperature is directly measured through a casing wall temperature sensor, the traditional casing wall temperature sensor is affected by high temperature and high vibration of the turbine casing, the reliability is low, and only a small number of machine types adopt the sensor to participate in the active clearance control logic.
Disclosure of Invention
The utility model aims to provide a turbine casing wall temperature sensor which can improve the reliability of temperature measurement in a high-temperature and high-pressure environment.
The present utility model also aims to provide a turbine casing wall temperature sensor mounting structure capable of improving temperature measurement reliability in a high-temperature and high-pressure environment.
It is also an object of the present utility model to provide an aeroengine capable of improving the reliability of temperature measurement in a high temperature and high pressure environment.
Embodiments of the present utility model may be implemented by:
a turbine casing wall temperature sensor, the turbine casing wall temperature sensor comprising: the device comprises a connector, a cable and a sensing part, wherein the connector is electrically connected with the sensing part through the cable; the sensing part is used for being connected with the side rib of the case so as to detect the temperature of the side rib of the case; the cable is used for transmitting a signal representing the temperature to the connector; the sensing part comprises a first sensing part and a second sensing part, and the first sensing part and the second sensing part are respectively positioned at two sides of the casing side rib.
Optionally, the cable includes a main cable, a first cable and a second cable, one end of the main cable is connected with the connector, the other end of the main cable is connected with the first cable and the second cable, the first cable is connected with the first sensitive part, and the second cable is connected with the second sensitive part.
Optionally, the first cable is connected with the first sensing part through an elastic section; and/or the number of the groups of groups,
the second branching cable is connected with the second sensing part through an elastic section.
Optionally, the turbine casing wall temperature sensor further includes a clamp, the clamp includes a connection portion, and a first clamping portion and a second clamping portion that are disposed at two ends of the connection portion, the first sensing portion is clamped at one side of the first clamping portion and the casing side rib, and the second sensing portion is clamped at the second clamping portion and the other side of the casing side rib.
Optionally, the turbine casing wall temperature sensor further comprises a clamp bolt; the first clamping part and the first sensing part are fastened on the side rib of the casing through a clamp bolt, and the second clamping part and the second sensing part are fastened on the side rib of the casing through a clamp bolt.
Optionally, a ceramic spacer is disposed between the first sensing portion and the first clamping portion; and/or the number of the groups of groups,
and a ceramic gasket is arranged between the second sensing part and the second clamping part.
The mounting structure of the turbine casing wall temperature sensor comprises a mounting bracket, a casing and the turbine casing wall temperature sensor; the casing has casing side rib and casing main part, the casing side rib protrusion the casing main part sets up, the installing support is fixed the one end of casing main part, turbine casing wall temperature sensor's connector fixed mounting is in the one end of installing support, the other end of installing support extends to the casing side rib, the cable is connected the one end of receiving the portion is fixed the other end of installing support.
Optionally, the mounting bracket comprises a first bracket and a second bracket, the connector is mounted on the first bracket, and the cable is fixed on the second bracket; one end of the first bracket is fixedly arranged on the flange edge of the casing main body, and the other end of the first bracket is fixedly connected with the second bracket through a connecting bolt.
Optionally, a mounting housing is fixed to the cable, and the mounting housing is fixedly connected to the second bracket, so as to fix the cable on the second bracket.
An aeroengine comprising the turbine casing wall temperature sensor mounting structure.
The turbine casing wall temperature sensor, the mounting structure and the aeroengine provided by the embodiment of the utility model have the beneficial effects that:
the embodiment of the utility model provides a turbine casing wall temperature sensor, which comprises a connector, a cable and a sensing part, wherein the connector is electrically connected with the sensing part through the cable, the sensing part comprises a first sensing part and a second sensing part, the first sensing part and the second sensing part are respectively positioned at two sides of a casing side rib and are connected with the casing side rib so as to detect the temperature of the casing side rib, and the cable is used for transmitting a signal representing the temperature to the connector.
The embodiment of the utility model also provides a mounting structure of the turbine casing wall temperature sensor, which comprises a mounting bracket, a casing and the turbine casing wall temperature sensor. The mounting structure of the turbine casing wall temperature sensor comprises the turbine casing wall temperature sensor, so that the mounting structure has the beneficial effects of improving the detection reliability and being beneficial to increasing the basis of judging the casing temperature by a clearance control system.
The embodiment of the utility model also provides an aeroengine, which comprises the turbine casing wall temperature sensor mounting structure, so that the aeroengine has the beneficial effects of improving the detection reliability and being beneficial to increasing the basis of judging the casing temperature by a clearance control system.
Drawings
The above features and advantages of the present utility model will be better understood after reading the detailed description of embodiments of the present disclosure in conjunction with the following drawings. In the drawings, the components are not necessarily to scale and components having similar related features or characteristics may have the same or similar reference numerals.
FIG. 1 shows a schematic structural view of an aeroengine provided according to an aspect of the present utility model;
FIG. 2 illustrates a schematic structural view of a turbine casing wall temperature sensor mounting structure provided in accordance with an aspect of the present utility model;
fig. 3 is a schematic view showing a part of a structure of a turbine casing wall temperature sensor mounting structure provided in an aspect of the present utility model.
Detailed Description
The utility model is described in detail below with reference to the drawings and the specific embodiments. It is noted that the aspects described below in connection with the drawings and the specific embodiments are merely exemplary and should not be construed as limiting the scope of the utility model in any way.
In the description of the present utility model, it should be noted that, if the terms "upper," "lower," "inner," "outer," "vertical," and the like indicate an orientation or a positional relationship based on that shown in the drawings or that the inventive product is conventionally put in place when used, it does not indicate or imply that the apparatus or element in question must have a specific orientation or be constructed and operated in a specific orientation, and therefore, the present utility model should not be construed as being limited thereto.
Meanwhile, it should be noted that the terms "first," "second," and the like, if any, are used solely for distinguishing descriptions and not to be construed as indicating or implying relative importance.
In the description of the present utility model, it should also be noted that, unless explicitly specified or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly and may be, for example, fixedly connected, integrally connected, or detachably connected; can be mechanically or electrically connected; may be directly connected, or may be indirectly connected through an intermediate medium, or may be communicated with the inside of two elements. The specific meaning of the above terms in the present utility model can be understood as appropriate by those of ordinary skill in the art.
Fig. 1 shows a schematic structural view of an aircraft engine 10 provided in the present embodiment. Referring to FIG. 1, the present embodiment provides an aircraft engine 10.
The aircraft engine 10 is disposed in the nacelle 21, and the aircraft engine 10 includes a low-pressure compressor including a fan 30 and a plurality of booster stages 31, a high-pressure compressor 32, a combustion chamber 33, a high-pressure turbine 34, a low-pressure turbine 35, and a casing 40 (an optional structure of the casing 40 is shown in fig. 2), the fan 30, the plurality of booster stages 31, the high-pressure compressor 32, the combustion chamber 33, the high-pressure turbine 34, and the low-pressure turbine 35 being sequentially distributed in the airflow direction. The low-pressure compressor and low-pressure turbine 35 are connected to a low-pressure shaft (not shown), and the high-pressure compressor 32 and high-pressure turbine 34 are connected to a high-pressure shaft (not shown). The casing 40 is placed in the core nacelle 24, and the plurality of booster stages 31, the high-pressure compressor 32, the combustor 33, and the low-pressure turbine 35 are surrounded by the casing 40 in the axial and circumferential directions.
When the aeroengine 10 works, the air flow 50 sequentially passes through the fan 30 and the flow dividing ring 22 on the booster stage 31 and is divided into a first air flow 51 and a second air flow 52, the first air flow 51 enters an inclusion flow passage through the booster stage 31, then compressed by the high-pressure compressor 32 and flows into the combustion chamber 33 to be mixed with fuel oil for combustion, the combustion gas drives the high-pressure turbine 34 and the low-pressure turbine 35, the high-pressure turbine 34 drives the high-pressure compressor 32 to rotate through a high-pressure shaft, and the low-pressure turbine 35 drives the fan 30 to rotate through a low-pressure shaft. The second air flow 52 directly enters the outer culvert channel through the support plate 23 behind the fan 30, and is ejected backwards through the outer culvert channel formed by the nacelle 21 and the core nacelle 24 to generate thrust.
By means of which the aircraft engine 10 also has a clearance control system, one construction of which is shown in fig. 1. As shown in fig. 1, the aeroengine 10 is provided with a bleed air device 11 for collecting a second air flow 52 in an outer culvert flow passage, part of the second air flow 52 enters the bleed air device 11 to form a collected air flow 53, enters a circumferential distribution manifold 14 above a casing which needs to be subjected to clearance control along a bleed air pipeline 12, enters a manifold 16 through the distribution manifold 14 and a gas collecting cavity 15, is ejected from impact holes on the manifold 16 to impact the casing 40, and realizes clearance adjustment by deforming the casing 40 and a rotor clearance.
Further, the bleed air line 12 is provided with a control valve 13 by means of which the flow of the collected air flow 53 is regulated to obtain an optimal deformation match.
It should be noted that the position of the manifold 16 in fig. 1 is merely illustrative, and is not meant to be limiting of the need to adjust only the casing-to-rotor clearance at the high pressure turbine 34, and in other embodiments, the position of the manifold 16 may be varied, and the rotor for clearance adjustment may be the rotor of the high pressure turbine 34, the low pressure turbine 35, or the high pressure compressor 32.
Fig. 2 shows a schematic structural view of a turbine casing wall temperature sensor mounting structure provided by the present embodiment, and fig. 3 shows a schematic structural view of a portion of the turbine casing wall temperature sensor mounting structure provided by the present embodiment. Referring to fig. 1-3, the present embodiment further provides a turbine casing wall temperature sensor 60 and a turbine casing wall temperature sensor mounting structure, which is a structure for mounting the turbine casing wall temperature sensor 60 to the casing 40.
The casing 40 includes a casing body 41 and a casing side rib 42, and the casing side rib 42 is provided protruding from one side of the casing body 41.
The turbine casing wall temperature sensor 60 includes a connector 64, a cable, and a sensing portion, the connector 64 and the sensing portion are electrically connected by the cable, the sensing portion includes a first sensing portion 61 and a second sensing portion 62, the first sensing portion 61 and the second sensing portion 62 are respectively located at two sides of the casing side rib 42 and are connected with the casing side rib 42, thereby detecting a temperature of the casing side rib 42, the cable is used for transmitting a signal representing the temperature to the connector 64, and since the turbine casing wall temperature sensor 60 has both the first sensing portion 61 and the second sensing portion 62 for sensing the temperature, a detection reliability of the turbine casing wall temperature sensor 60 is improved.
In the present embodiment, the number of the sensing parts is two, and the two sensing parts are the first sensing part 61 and the second sensing part 62, respectively, and it is understood that in other embodiments, two or more sensing parts may be provided.
The turbine casing wall temperature sensor mounting structure further includes a mounting bracket 70, one end of the mounting bracket 70 is connected to the flange of the casing body 41, and the other end of the mounting bracket 70 extends at least to the casing side rib 42, so that one end of the cable connection receiving portion may be fixed to the other end of the mounting bracket 70, that is, the mounting bracket 70 extends to one end of the casing side rib 42. At this time, the first sensing portion 61 and the second sensing portion 62 are closer to the case side rib 42 than the connector 64, and the first sensing portion 61 and the second sensing portion 62 are respectively bonded and fixed to both sides of the case side rib 42, so that at least one of the first sensing portion 61 and the second sensing portion 62 can be bonded to the case side rib 42 when the case 40 vibrates, thereby ensuring the temperature sensing of the case 40.
Further, the mounting bracket 70 includes a first bracket 71 and a second bracket 72, the connector 64 is mounted on the first bracket 71, and the cable is fixed on the second bracket 72. One end of the first bracket 71 is fixedly mounted on the casing body 41, and the other end of the first bracket 71 is fixedly connected with the second bracket 72 through a connecting bolt, which is a first connecting bolt 73.
Alternatively, the first bracket 71 is fixedly mounted to the flange side of the casing body 41 by a second connecting bolt 74, and the connector 64 is fixedly mounted to the first bracket 71 by a third connecting bolt 75.
In the present embodiment, the cable includes a main cable 65, a first branch cable 661, and a second branch cable 662, one end of the main cable 65 is connected to the connector 64, and the first branch cable 661 and the second branch cable 662 are both provided at the other end of the main cable 65. The first cable 661 is connected to the first sensing portion 61, and signal transmission with the connector 64 is achieved by the first cable 661 and the main cable 65. The second cable 662 is connected to the second sensing portion 62, so that signal transmission with the connector 64 is realized through the second cable 662 and the main cable 65.
Further, an end of the main cable 65 remote from the connector 64 is provided with a mounting housing 76, and is fixedly mounted on the mounting bracket 70 through the mounting housing 76, thereby realizing a fixed connection of the cable and the mounting bracket 70.
In this embodiment, the turbine casing wall temperature sensor 60 further includes an elastic section 63, the first cable 661 is connected to the first sensing portion 61 through the elastic section 63, and the second cable 662 is also connected to the second sensing portion 62 through the elastic section 63. That is, in the present embodiment, the number of the elastic sections 63 is two, and one of the two elastic sections 63 is used for connecting the first cable 661 to the first sensing portion 61, and the other is used for connecting the second cable 662 to the second sensing portion 62 through the elastic sections 63. Alternatively, the elastic section 63 may be a spring.
By arranging the elastic section 63 to connect the sensing part and the cable, the degree of freedom can be released in the vibration environment, and the damage to the connection between the sensing part and the cable when the sensing part random box 40 moves relative to the cable is avoided, so that the reliability of the turbine casing wall temperature sensor 60 is guaranteed.
Referring to fig. 3, in the present embodiment, the turbine casing wall temperature sensor 60 further includes a clip 68, and the clip 68 includes a connection portion 681, and a first clamping portion 682 and a second clamping portion 683 disposed at two ends of the connection portion. The first sensing portion 61 is clamped at one side of the first clamping portion 682 and the case side rib 42, thereby ensuring the reliability of the attachment of the first sensing portion 61 to the case side rib 42. The second sensing portion 62 is clamped to the second clamping portion 683 and the other side of the case side rib 42, thereby ensuring the reliability of the adhesion of the second sensing portion 62 to the case side rib 42.
Further, the turbine casing wall temperature sensor 60 further includes a clamp bolt 69, the first clamping portion 682 and the first sensing portion 61 are fastened to the casing side rib 42 by a clamp bolt 69, and the second clamping portion 683 and the second sensing portion 62 are fastened to the casing side rib 42 by a clamp bolt 69. Specifically, in the present embodiment, there are two clamp bolts 69, one clamp bolt 69 fastening the first clamping portion 682 and the first sensed portion 61 to the case side rib 42, and the other clamp bolt 69 fastening the second clamping portion 683 and the second sensed portion 62 to the case side rib 42. It will be appreciated that in other embodiments, only one clamp bolt 69 may be provided, and the clamp bolt 69 cooperates with the first clamping portion 682, the first sensed portion 61, the case side rib 42, the second sensed portion 62, and the second clamping portion 683 at the same time, thereby locking the first clamping portion 682, the first sensed portion 61, the case side rib 42, the second sensed portion 62, and the second clamping portion 683 together.
Further, the turbine casing wall temperature sensor 60 further includes ceramic shims 67, and in this embodiment, the ceramic shims 67 are two in number, one being disposed between the first sensed portion 61 and the first clamping portion 682, and the other being disposed between the second sensed portion 62 and the second clamping portion 683. By providing ceramic shims 67, the validity of the temperature measurements is facilitated.
According to the turbine casing wall temperature sensor 60, the mounting structure and the aeroengine 10 provided by the embodiment of the utility model, the two sensing parts are arranged on the turbine casing wall temperature sensor 60, and meanwhile, the temperature at two sides of the casing measurement 42 is detected, so that the reliability of the turbine casing wall temperature sensor 60 is improved, the basis of judging the turbine casing wall temperature sensor 60 by a clearance control system is increased, the sensing parts are fixed with the casing side ribs 42 in a clamping mode by adopting the clamp bolts 69, the permanent contact between the sensing parts and the casing 40 is ensured, the high vibration environment is resisted, and the reliability of temperature detection is improved. By providing the ceramic pad 67, the effectiveness of the temperature measurement can be ensured by reducing heat dissipation loss in the control algorithm when in use. Specifically, the heat dissipation loss can be calibrated in advance through experiments.
The foregoing is merely illustrative of the present utility model, and the present utility model is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the technical scope of the present utility model should be included in the scope of the present utility model.
Claims (10)
1. A turbine casing wall temperature sensor, the turbine casing wall temperature sensor comprising: the device comprises a connector, a cable and a sensing part, wherein the connector is electrically connected with the sensing part through the cable; the sensing part is used for being connected with the side rib of the case so as to detect the temperature of the side rib of the case; the cable is used for transmitting a signal representing the temperature to the connector; the method is characterized in that:
the sensing part comprises a first sensing part and a second sensing part, and the first sensing part and the second sensing part are respectively positioned at two sides of the casing side rib.
2. The turbine casing wall temperature sensor of claim 1, wherein:
the cable comprises a main cable, a first branching cable and a second branching cable, one end of the main cable is connected with the connector, the other end of the main cable is simultaneously connected with the first branching cable and the second branching cable, the first branching cable is connected with the first sensitive part, and the second branching cable is connected with the second sensitive part.
3. The turbine casing wall temperature sensor of claim 2, wherein:
the first branching cable is connected with the first sensing part through an elastic section; and/or the number of the groups of groups,
the second branching cable is connected with the second sensing part through an elastic section.
4. The turbine casing wall temperature sensor of claim 1, wherein:
the turbine casing wall temperature sensor further comprises a clamp, the clamp comprises a connecting portion, a first clamping portion and a second clamping portion, the first clamping portion and the second clamping portion are arranged at two ends of the connecting portion, the first sensing portion is clamped at one side of the first clamping portion and one side of the casing side rib, and the second sensing portion is clamped at the second clamping portion and the other side of the casing side rib.
5. The turbine casing wall temperature sensor of claim 4, wherein:
the turbine casing wall temperature sensor further comprises a clamp bolt; the first clamping part and the first sensing part are fastened on the side rib of the casing through a clamp bolt, and the second clamping part and the second sensing part are fastened on the side rib of the casing through a clamp bolt.
6. The turbine casing wall temperature sensor of claim 4, wherein:
a ceramic gasket is arranged between the first sensing part and the first clamping part; and/or the number of the groups of groups,
and a ceramic gasket is arranged between the second sensing part and the second clamping part.
7. The utility model provides a turbine receiver wall temperature sensor mounting structure which characterized in that:
the turbine casing wall temperature sensor mounting structure comprises a mounting bracket, a casing and the turbine casing wall temperature sensor according to any one of claims 1-6; the casing has casing side rib and casing main part, the casing side rib protrusion the casing main part sets up, the installing support is fixed the one end of casing main part, turbine casing wall temperature sensor's connector fixed mounting is in the one end of installing support, the other end of installing support extends to the casing side rib, the cable is connected the one end of receiving the portion is fixed the other end of installing support.
8. The turbine casing wall temperature sensor mounting structure according to claim 7, wherein:
the mounting bracket comprises a first bracket and a second bracket, the connector is mounted on the first bracket, and the cable is fixed on the second bracket; one end of the first bracket is fixedly arranged on the flange edge of the casing main body, and the other end of the first bracket is fixedly connected with the second bracket through a connecting bolt.
9. The turbine casing wall temperature sensor mounting structure according to claim 8, wherein:
the cable is fixed with the installation casing outward, the installation casing with second support fixed connection is in order to fix the cable on the second support.
10. An aeroengine, characterized in that:
the aircraft engine includes the turbine casing wall temperature sensor mounting structure of any one of claims 7 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321553458.0U CN220084192U (en) | 2023-06-16 | 2023-06-16 | Turbine casing wall temperature sensor, mounting structure and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321553458.0U CN220084192U (en) | 2023-06-16 | 2023-06-16 | Turbine casing wall temperature sensor, mounting structure and aeroengine |
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| Publication Number | Publication Date |
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| CN220084192U true CN220084192U (en) | 2023-11-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321553458.0U Active CN220084192U (en) | 2023-06-16 | 2023-06-16 | Turbine casing wall temperature sensor, mounting structure and aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220084192U (en) |
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2023
- 2023-06-16 CN CN202321553458.0U patent/CN220084192U/en active Active
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