CN220929533U - Air inlet assembly for ventilation cooling of turbofan engine core cabin and turbofan engine - Google Patents
Air inlet assembly for ventilation cooling of turbofan engine core cabin and turbofan engine Download PDFInfo
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- CN220929533U CN220929533U CN202323190477.4U CN202323190477U CN220929533U CN 220929533 U CN220929533 U CN 220929533U CN 202323190477 U CN202323190477 U CN 202323190477U CN 220929533 U CN220929533 U CN 220929533U
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- turbofan engine
- air inlet
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- ventilation cooling
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- 238000009423 ventilation Methods 0.000 title claims abstract description 72
- 238000001816 cooling Methods 0.000 title claims abstract description 69
- 230000000694 effects Effects 0.000 claims abstract description 30
- 239000007921 spray Substances 0.000 claims abstract description 23
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 5
- 230000007704 transition Effects 0.000 claims description 6
- 230000009286 beneficial effect Effects 0.000 abstract description 21
- 238000013461 design Methods 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000005520 cutting process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
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Abstract
The utility model relates to an air inlet assembly for ventilation cooling of a turbofan engine core cabin and a turbofan engine. The air inlet assembly for ventilation cooling of the turbofan engine core cabin comprises an air inlet pipe and a recoil type spray pipe structure, wherein the upstream end of the air inlet pipe is connected with the surface of the core cabin wall, the downstream end of the air inlet pipe is connected with the recoil type spray pipe structure, the recoil type spray pipe structure is configured to guide ventilation air flow to be sprayed into the core cabin at a certain speed, and simultaneously, the recoil effect of the air flow is utilized to drive the recoil type spray pipe structure to rotate around the vertical central axis of the air inlet pipe, so that the air flow is ensured to flow out evenly. According to the technical scheme, the utility model has the following beneficial technical effects: the air circulation capacity and the air inlet uniformity of the turbofan engine core cabin can be considered.
Description
Technical Field
The utility model relates to an air inlet assembly for ventilation cooling of a turbofan engine core cabin and a turbofan engine comprising the air inlet assembly for ventilation cooling of the turbofan engine core cabin, and belongs to the technical field of ventilation cooling of aircraft power devices.
Background
When the civil aircraft turbofan engine runs, a large amount of heat is easy to accumulate in a core cabin of the engine, and the heat is easy to cause the temperature in the core cabin to rise through heat exchange activities such as radiation, convection and the like, so that the overtemperature of accessories of a power device system is directly caused, and the reliability of the system is affected. Meanwhile, due to the fact that flammable liquid possibly existing in the core cabin volatilizes and gathers, system ignition is easily caused under the fault condition. Therefore, the design of the ventilation cooling system of the power system core cabin is indispensable. In order to ensure that ventilation air flow in the core cabin is uniformly distributed and has no flowing dead zone, the cooling effect in the cabin is fully realized, and the design of the structural form of the ventilation cooling air inlet is extremely critical.
The air inlet structure of the prior ventilation and cooling system of the core cabin mainly has two forms:
A) One form is through-type air inlet, and this through-hole air inlet form has guaranteed the interior sufficient ventilation cooling air flow air inflow of core cabin, and along the radial velocity of flow of core cabin faster, can utilize comparatively quick radial air current to realize local forced heat transfer effect, obtain showing local cooling effect, but air current distribution homogeneity is relatively poor, especially in the regional apparent air current dead zone that easily appears in the surrounding area of this air inlet, also be unfavorable for fully realizing the circumference position ventilation cooling in the core cabin, the overall cooling effect is not good.
B) In another form, the straight-through air inlet is changed into a straight cylinder grille type air inlet, and air flow can only flow out along the circumferential direction of the straight cylinder, so that the uniformity of the air flow is improved to a certain extent. However, this structure inevitably comes at the cost of more total pressure loss, and the overall air flow and heat exchange cooling capacity in the core cabin is reduced, and is not suitable for the situation that local heat accumulation exists and concentrated cooling is required.
The ventilation and cooling scheme of the core cabin in the prior art cannot consider the air circulation capacity and the air inlet uniformity of the core cabin of the turbofan engine.
Disclosure of utility model
It is an object of the present utility model to provide an air intake assembly for ventilation cooling of a turbofan engine core that overcomes the drawbacks of the prior art and that combines both the gas flow capacity and the air intake uniformity of the turbofan engine core.
The air inlet assembly for ventilation cooling of the turbofan engine core cabin comprises an air inlet pipe and a recoil type spray pipe structure, wherein the upstream end of the air inlet pipe is connected with the surface of a core cabin wall, the downstream end of the air inlet pipe is connected with the recoil type spray pipe structure, the recoil type spray pipe structure is configured to guide ventilation air flow to be sprayed into the core cabin at a certain speed, and simultaneously, the recoil type spray pipe structure is driven to rotate around the vertical central axis of the air inlet pipe by utilizing the recoil action of the air flow, so that the air flow is ensured to flow out uniformly.
According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: the air circulation capacity and the air inlet uniformity of the turbofan engine core cabin can be considered.
Preferably, the backflushing nozzle structure comprises a main body pipe section and a backflushing pipe section which are connected with each other, wherein the backflushing pipe section is positioned at the downstream of the main body pipe section, and the longitudinal central axis of the backflushing pipe section forms a horizontal deflection angle relative to the longitudinal central axis of the main body pipe section in a horizontal section, and the horizontal deflection angle is 30-90 degrees.
According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: through the proper horizontal deflection angle of the recoil pipe section relative to the main pipe section, the recoil effect of the airflow can be achieved, the airflow can be ensured to flow outwards and uniformly, and the air inlet uniformity is further improved on the premise that the air circulation capacity of the core cabin of the turbofan engine is not reduced.
More preferably, the horizontal deflection angle is 45 to 75 degrees.
According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: through better horizontal deflection angle, can realize taking into account the gas circulation ability and the homogeneity of admitting air of turbofan engine core cabin better.
Preferably, the backflushing nozzle structure further comprises a transition pipe section connected between the air inlet pipe and the main body pipe section of the backflushing nozzle structure, so as to adjust the vertical deflection angle of the main body pipe section of the backflushing nozzle structure relative to the air inlet pipe in a vertical section.
According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: the vertical deflection angle of the main pipe section of the recoil type spray pipe structure relative to the air inlet pipe can be adjusted, so that the air outlet direction of the recoil type spray pipe structure is changed.
Preferably, the vertical deflection angle is 70 to 110 degrees.
According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: through the vertical deflection angle of preferred, can realize the transformation recoil spray tube structure's the direction of giving vent to anger betterly, satisfy the ventilation cooling demand in the core cabin.
More preferably, the vertical deflection angle is 90 degrees.
According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: through better vertical deflection angle, can realize taking into account the gas circulation ability and the homogeneity of admitting air of turbofan engine core cabin better.
Preferably, the air intake assembly for ventilation cooling of a turbofan engine core compartment further comprises a bearing arrangement between the air intake duct and the backflush nozzle arrangement such that the backflush nozzle arrangement is rotatable about a vertical central axis of the air intake duct.
According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: the recoil type spray pipe structure can better rotate around the vertical central axis of the air inlet pipe, so that the air circulation capacity and the air inlet uniformity of the turbofan engine core cabin can be better considered.
Preferably, in a horizontal section, the tube end face of the recoil tube segment is beveled inward at an angle of 0 to 30 degrees with respect to a longitudinal center axis of the main tube segment.
According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: by means of the inward beveling angle of the pipe end face of the proper backflushing pipe section, the backflushing efficiency of air flow is further improved on the premise that the air circulation capacity of the core cabin of the turbofan engine is not reduced, and therefore the air intake uniformity is further improved.
More preferably, the inward chamfer angle is 10 to 20 degrees.
According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: through the inward inclined cutting angle of the pipe end surface of the better recoil pipe section, the air circulation capacity and the air inlet uniformity of the turbofan engine core cabin can be better achieved.
The above object of the utility model is also achieved by a turbofan engine comprising an air intake assembly for ventilation cooling of a turbofan engine core compartment as described in any of the above aspects.
According to the technical scheme, the turbofan engine has the following beneficial technical effects: the air circulation capacity and the air inlet uniformity of the turbofan engine core cabin can be considered.
Drawings
FIG. 1 is a perspective view of an intake assembly for turbofan engine core compartment ventilation cooling in accordance with an embodiment of the present utility model.
FIG. 2 is a top view of an air intake assembly for ventilation cooling of a turbofan engine nacelle in accordance with an embodiment of the utility model.
FIG. 3 is a front view of an air intake assembly for ventilation cooling of a turbofan engine core compartment in accordance with an embodiment of the present utility model.
FIG. 4 is a schematic illustration of the mounting location of an air intake assembly for ventilation cooling of a turbofan engine nacelle in accordance with one embodiment of the utility model.
List of reference numerals
1: A core bulkhead face;
2: an air intake assembly;
3: a core cabin;
4: circular seam at the tail end of the spray pipe;
21: an air inlet pipe;
22: a recoil nozzle structure;
221: a transition pipe section;
222: a main body pipe section;
223: recoil of the pipe section;
A: a horizontal deflection angle;
B: a vertical deflection angle;
C: an inward chamfer angle;
s1: a vertical central axis of the air inlet pipe;
S2: a longitudinal central axis of the main body pipe section;
s3: the longitudinal central axis of the recoil tube section.
Detailed Description
In the following, specific embodiments of the present utility model will be described, and it should be noted that in the course of the detailed description of these embodiments, it is not possible in the present specification to describe all features of an actual embodiment in detail for the sake of brevity. It should be appreciated that in the actual implementation of any of the implementations, as in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be appreciated that while such a development effort might be complex and lengthy, it would nevertheless be a routine undertaking of design, fabrication, or manufacture for those of ordinary skill having the benefit of this disclosure, and thus should not be construed as having the benefit of this disclosure.
Unless defined otherwise, technical or scientific terms used in the claims and specification should be given the ordinary meaning as understood by one of ordinary skill in the art to which this utility model belongs. The terms "first," "second," and the like in the description and in the claims, are not used for any order, quantity, or importance, but are used for distinguishing between different elements. The terms "a" or "an" and the like do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprising" or "comprises", and the like, is intended to mean that elements or items that are immediately preceding the word "comprising" or "comprising", are included in the word "comprising" or "comprising", and equivalents thereof, without excluding other elements or items. The terms "connected" or "connected," and the like, are not limited to physical or mechanical connections, nor to direct or indirect connections.
In the following description, for the purposes of clarity of presentation of the structure and manner of operation of the present utility model, the description will be made with the aid of directional terms, but such terms as "forward," "rearward," "left," "right," "outward," "inner," "outward," "inward," "upper," "lower," etc. are to be construed as convenience, and are not to be limiting.
FIG. 1 is a perspective view of an intake assembly for turbofan engine core compartment ventilation cooling in accordance with an embodiment of the present utility model. FIG. 2 is a top view of an air intake assembly for ventilation cooling of a turbofan engine nacelle in accordance with an embodiment of the utility model. FIG. 3 is a front view of an air intake assembly for ventilation cooling of a turbofan engine core compartment in accordance with an embodiment of the present utility model. FIG. 4 is a schematic illustration of the mounting location of an air intake assembly for ventilation cooling of a turbofan engine nacelle in accordance with one embodiment of the utility model.
As shown in fig. 1 to 4, according to an embodiment of the present utility model, an intake assembly 2 for ventilation cooling of a core cabin of a turbofan engine includes an intake duct 21, and a recoil nozzle structure 22, wherein an upstream end of the intake duct 21 is connected to a wall surface of the core cabin, and a downstream end is connected to the recoil nozzle structure 22, and the recoil nozzle structure 22 is configured to guide ventilation air flow to be injected into the core cabin at a certain speed, and simultaneously, to drive the recoil nozzle structure 22 to rotate around a vertical central axis S1 of the intake duct 21 by a recoil action of the air flow, thereby ensuring uniform outflow of the air flow.
According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: the air circulation capacity and the air inlet uniformity of the turbofan engine core cabin can be considered.
Specifically, the utility model absorbs the advantages of the two air inlet modes, fully considers the circumferential uniformity of ventilation cooling air flow, designs the air inlet structure of the ventilation air flow into a recoil type spray pipe structure, and is configured to guide the ventilation air flow to be sprayed into a core cabin from an outer duct through an air inlet pipe and the recoil type spray pipe structure at a certain speed, and spread in the space of the core cabin.
In some embodiments, as shown in fig. 1-2, the backflushing spout structure 22 includes a main body tube segment 222 and a backflushing tube segment 223 that are connected (e.g., integrally connected) to each other, the backflushing tube segment 223 being located downstream of the main body tube segment 222, the longitudinal central axis S3 of the backflushing tube segment 223 being at a horizontal deflection angle a relative to the longitudinal central axis S2 of the main body tube segment 222 in a horizontal cross-section (i.e., the plane shown in fig. 2), the horizontal deflection angle a being 30-90 degrees. According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: through the proper horizontal deflection angle of the recoil pipe section relative to the main pipe section, the recoil effect of the airflow can be achieved, the airflow can be ensured to flow outwards and uniformly, and the air inlet uniformity is further improved on the premise that the air circulation capacity of the core cabin of the turbofan engine is not reduced.
Preferably, in a horizontal cross-section (i.e., the plane shown in fig. 2), the main body section 222 extends substantially along the diameter of the air inlet pipe 21 (i.e., the longitudinal central axis S2 of the main body section 222 is substantially coincident with or parallel to the diameter of the air inlet pipe 21), so that the main body section 222 does not substantially directly impart an air flow backflushing action that causes the backflushing nozzle structure to rotate; since the longitudinal center axis S3 of the backflushing tube segment 223 is horizontally offset by an angle a of 30-90 degrees with respect to the longitudinal center axis S2 of the main body tube segment 222, the backflushing tube segment 223 imparts an air flow backflushing action that rotates the backflushing nozzle structure. Of course, the main body section 222 also functions as a moment arm, and the air flow recoil force imparted by the recoil section 223 needs to be combined with the moment arm of the main body section 222 so that the recoil nozzle structure 22 can rotate about the vertical central axis S1 of the air intake pipe 21.
More preferably, as shown in fig. 1 to 2, the horizontal deflection angle a is 45 to 75 degrees. According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: through better horizontal deflection angle, can realize taking into account the gas circulation ability and the homogeneity of admitting air of turbofan engine core cabin better.
Preferably, the kick section 223 may not be rigidly deflected relative to the main body section 222, but rather may have a radiused transition section therebetween (as shown in fig. 1-2) to provide a smoother flow of ventilation air through the main body section 222 and the kick section 223.
In some embodiments, as shown in fig. 1 and 3, the swozzle structure 22 further includes a transition pipe section 221, the transition pipe section 221 being connected between the air inlet pipe 21 and the main body pipe section 222 of the swozzle structure 22, such that a vertical deflection angle B of the main body pipe section 222 of the swozzle structure 22 relative to the air inlet pipe 21 in a vertical cross section (i.e., the plane shown in fig. 3) (i.e., a vertical deflection angle B of a longitudinal central axis S2 of the main body pipe section 222 relative to a vertical central axis S1 of the air inlet pipe 21) is adjusted. According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: the vertical deflection angle of the main pipe section of the recoil type spray pipe structure relative to the air inlet pipe can be adjusted, so that the air outlet direction of the recoil type spray pipe structure is changed.
In some embodiments, as shown in fig. 1 and 3, the vertical deflection angle B is 70-110 degrees. According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: through the vertical deflection angle of preferred, can realize the transformation recoil spray tube structure's the direction of giving vent to anger betterly, satisfy the ventilation cooling demand in the core cabin.
More preferably, as shown in fig. 1 and 3, the vertical deflection angle B is 90 degrees. In this case, since the intake pipe 21 is vertically arranged, the main body pipe section 222 of the recoil nozzle structure 22 is horizontally arranged. According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: through the better vertical deflection angle, the ventilation air flow entering the core cabin is adjusted to be in a straight direction, the air flow recoil of the downstream recoil pipe section is supported to realize rotation around the vertical central axis S1, and the air circulation capacity and the air inlet uniformity of the turbofan engine core cabin can be better realized.
In some embodiments, the intake assembly for turbofan engine core compartment ventilation cooling further includes a bearing structure (not shown) located between the intake duct 21 and the backflush nozzle structure 22 such that the backflush nozzle structure 22 is rotatable about the vertical central axis S1 of the intake duct 21. According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: the recoil type spray pipe structure can better rotate around the vertical central axis of the air inlet pipe, so that the air circulation capacity and the air inlet uniformity of the turbofan engine core cabin can be better considered.
In some embodiments, as shown in fig. 1-2, in a horizontal cross-section, the tube end face of the recoil tube segment 223 is at an inward chamfer angle C relative to the longitudinal central axis S2 of the body tube segment 222 (i.e., also relative to an axis S2') parallel to the longitudinal central axis S2 of the body tube segment 222, the inward chamfer angle C being 0-30 degrees. According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: by means of the inward beveling angle of the pipe end face of the proper backflushing pipe section, the backflushing efficiency of air flow is further improved on the premise that the air circulation capacity of the core cabin of the turbofan engine is not reduced, and therefore the air intake uniformity is further improved.
More preferably, the inward chamfer angle C is 10 to 20 degrees, as shown in fig. 1 to 2. According to the technical scheme, the air inlet assembly for ventilation and cooling of the turbofan engine core cabin has the following beneficial technical effects: through the inward inclined cutting angle of the pipe end surface of the better recoil pipe section, the air circulation capacity and the air inlet uniformity of the turbofan engine core cabin can be better achieved.
According to an embodiment of the utility model, the turbofan engine comprises an air intake assembly for ventilation cooling of a turbofan engine core compartment as described in any of the above aspects. According to the technical scheme, the turbofan engine has the following beneficial technical effects: the air circulation capacity and the air inlet uniformity of the turbofan engine core cabin can be considered.
The whole ventilation and cooling system of the core cabin is shown in fig. 4, the upstream end of an air inlet pipe of an air inlet assembly 2 for ventilation and cooling of the core cabin of the turbofan engine is connected with a wall surface 1 of the core cabin, cooling air led from an outer duct flows through the air inlet pipe and enters a recoil type spray pipe structure of the air inlet assembly 2, then the air flow is discharged to the surrounding space through the recoil type spray pipe structure at a certain speed, air near the air inlet assembly 2 flows to the downstream of the core cabin along an arrow in the drawing, heat in the core cabin 3 is absorbed through convection heat exchange, and finally high-temperature air is discharged from a circular seam 4 at the tail end of the spray pipe, so that the ventilation and cooling heat exchange process is completed, and the air circulation capacity and the air inlet uniformity of the core cabin of the turbofan engine can be considered.
While the utility model has been described in terms of specific embodiments, those skilled in the art will recognize that the utility model is not limited thereto, but that many modifications can be made by those skilled in the art without departing from the scope of the utility model.
Claims (10)
1. The utility model provides an intake assembly for turbofan engine core cabin ventilation cooling, its characterized in that, an intake assembly for turbofan engine core cabin ventilation cooling includes intake pipe, recoil nozzle structure, wherein, the upstream end of intake pipe links to each other with core bulkhead face, the downstream end with recoil nozzle structure links to each other, recoil nozzle structure is constructed and is guided ventilation air current and sprays into the core cabin with certain speed, utilizes the recoil effect of air current simultaneously, drives recoil nozzle structure is rotatory around the vertical central axis of intake pipe, guarantee air current evenly flows.
2. An air intake assembly for ventilation cooling of a turbofan engine core compartment of claim 1 wherein the backflushing nozzle structure comprises a main body section and a backflushing section connected to each other, the backflushing section being downstream of the main body section, the longitudinal central axis of the backflushing section being at a horizontal deflection angle relative to the longitudinal central axis of the main body section in a horizontal cross section, the horizontal deflection angle being 30-90 degrees.
3. An air intake assembly for turbofan engine core compartment ventilation cooling as claimed in claim 2, wherein the horizontal deflection angle is 45-75 degrees.
4. The intake assembly for turbofan engine core compartment ventilation cooling of claim 2 wherein the backflushing nozzle structure further comprises a transition tube segment connected between the intake duct and the body tube segment of the backflushing nozzle structure to adjust the vertical deflection angle of the body tube segment of the backflushing nozzle structure relative to the intake duct in vertical cross section.
5. An air intake assembly for turbofan engine core compartment ventilation cooling as claimed in claim 4, wherein the vertical deflection angle is 70 to 110 degrees.
6. An air intake assembly for turbofan engine core compartment ventilation cooling as defined in claim 5, wherein the vertical deflection angle is 90 degrees.
7. The intake assembly for turbofan engine core ventilation cooling of claim 1 further comprising a bearing structure between the intake duct and the recoil nozzle structure such that the recoil nozzle structure is rotatable about a vertical central axis of the intake duct.
8. An air intake assembly for turbofan engine core compartment ventilation cooling of claim 2 wherein in horizontal cross section the tube end face of the recoil tube section is beveled inward relative to the longitudinal central axis of the main body tube section by an angle of 0 to 30 degrees.
9. An air intake assembly for turbofan engine core compartment ventilation cooling as claimed in claim 8, wherein the inward chamfer angle is 10 to 20 degrees.
10. A turbofan engine comprising an air intake assembly for ventilation cooling of a turbofan engine core compartment according to any of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323190477.4U CN220929533U (en) | 2023-11-24 | 2023-11-24 | Air inlet assembly for ventilation cooling of turbofan engine core cabin and turbofan engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323190477.4U CN220929533U (en) | 2023-11-24 | 2023-11-24 | Air inlet assembly for ventilation cooling of turbofan engine core cabin and turbofan engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220929533U true CN220929533U (en) | 2024-05-10 |
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ID=90936669
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323190477.4U Active CN220929533U (en) | 2023-11-24 | 2023-11-24 | Air inlet assembly for ventilation cooling of turbofan engine core cabin and turbofan engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220929533U (en) |
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2023
- 2023-11-24 CN CN202323190477.4U patent/CN220929533U/en active Active
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