CN115264159B - Variable-circulation aero-engine inner and outer duct annular valve control structure - Google Patents
Variable-circulation aero-engine inner and outer duct annular valve control structure Download PDFInfo
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- CN115264159B CN115264159B CN202210976214.7A CN202210976214A CN115264159B CN 115264159 B CN115264159 B CN 115264159B CN 202210976214 A CN202210976214 A CN 202210976214A CN 115264159 B CN115264159 B CN 115264159B
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- annular valve
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- 230000005540 biological transmission Effects 0.000 claims abstract description 116
- 238000002347 injection Methods 0.000 claims description 10
- 239000007924 injection Substances 0.000 claims description 10
- 238000003466 welding Methods 0.000 abstract description 2
- 230000033001 locomotion Effects 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 210000001503 joint Anatomy 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K31/00—Actuating devices; Operating means; Releasing devices
- F16K31/44—Mechanical actuating means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Valve Device For Special Equipments (AREA)
Abstract
The application belongs to the technical field of control design of inner and outer duct annular valves of variable-cycle aeroengines, and particularly relates to a variable-cycle aeroengine inner and outer duct annular valve control structure, wherein a driving transmission shaft mounting seat, a driven transmission shaft mounting seat and an actuating cylinder mounting bracket are designed and integrated on a bearing ring, the bearing ring can be sleeved on an outer casing in a welding mode, the bearing ring has a larger contact area with the outer casing, larger local stress can be avoided to the outer casing during action, and the structure is compact as a whole.
Description
Technical Field
The application belongs to the technical field of control design of inner and outer duct annular valves of a variable-cycle aero-engine, and particularly relates to a control structure of an inner and outer duct annular valve of a variable-cycle aero-engine.
Background
The variable-circulation aeroengine is suitable for being used, and the annular valve is controlled to move along the axial direction to open or close the guide holes on the inner duct diverter ring and the outer duct diverter ring, so that the distribution of flow between the inner duct diverter ring and the outer duct diverter ring is controlled to adapt to different flight states of the aircraft, and the aeroengine keeps better performance.
At present, in the variable cycle aeroengine, the design has corresponding actuating mechanism, and drive ring valve is at axial motion, realizes opening or closing the injection hole on the split ring, and actuating mechanism passes through numerous mount pad, leg joint on outer receiver, and each mount pad, the leg joint of wherein is on outer receiver through welding or bolted connection's mode more, causes this kind of technical scheme to have following defect:
when the driving mechanism acts, the connection parts of the outer casing, each mounting seat and the support are easy to generate larger local stress, the outer casing is designed into a thin-wall structure, when the outer casing is subjected to larger local stress, larger deformation is easy to generate, the aerodynamic performance of the aeroengine is further influenced, the driving mechanism is caused to be eccentric, and serious deformation and clamping stagnation of the driving mechanism are caused to damage the driving mechanism when the driving mechanism is serious.
The present application has been made in view of the above-described technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present application, which is not necessarily prior art to the present patent application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
The application aims to provide an inner and outer bypass annular valve control structure of a variable cycle aero-engine, which overcomes or alleviates the technical defects of at least one aspect in the prior art.
The technical scheme of the application is as follows:
an inner and outer duct annular valve control structure of a variable cycle aero-engine, comprising:
the outer casing is provided with a driving perforation and a driven perforation;
the split ring is arranged in the outer casing, an outer duct is formed between the split ring and the outer casing, an inner duct is formed in the split ring, and the side wall of the split ring is provided with an injection hole;
The annular valve is attached to the shunt ring;
the bearing ring is sleeved on the outer casing and provided with a driving via hole and a driven via hole;
The driving transmission shaft mounting seat is connected to the bearing ring and provided with a driving transmission shaft mounting hole;
The driving transmission shaft penetrates through the driving perforation, the driving through hole and the driving transmission shaft mounting hole, and one end of the driving transmission shaft extending into the outer casing is hinged with the annular valve;
the driven transmission shaft mounting seat is connected to the bearing ring and provided with a driven transmission shaft mounting hole;
The driven transmission shaft penetrates through the driven perforation, the driven via hole and the driven transmission shaft mounting hole, and one end of the driven transmission shaft extending into the outer casing is hinged with the annular valve;
the linkage ring is sleeved on the periphery of the outer casing;
the driving rocker arm connecting bracket is connected to the linkage ring;
the driving rocker arm is connected to one end of the driving transmission shaft, which is exposed out of the outer casing, and one end of the driving rocker arm is hinged to the driving rocker arm connecting bracket;
The driven rocker arm connecting bracket is connected to the linkage ring;
one end of the driven rocker arm is connected with one end of the driven transmission shaft, which is exposed out of the casing, and the other end of the driven rocker arm is hinged on the driven rocker arm connecting bracket;
The actuator cylinder mounting bracket is connected to the bearing ring;
The actuating cylinder is hinged between the other end of the driving rocker arm and the actuating cylinder mounting bracket, so that the driving rocker arm can be driven to swing, the driving transmission shaft is driven to rotate, the linkage ring is driven to rotate, the driven transmission shaft is driven to rotate, and the annular valve moves along the axial direction to open or close the guide hole.
According to at least one embodiment of the application, in the variable cycle aero-engine inner and outer duct annular valve control structure, a plurality of injection holes are distributed along the circumferential direction.
According to at least one embodiment of the application, in the variable cycle aeroengine inner and outer duct annular valve control structure, the annular valve is abutted against the inner side of the flow dividing ring.
According to at least one embodiment of the present application, in the above-mentioned variable cycle aero-engine inner and outer duct annular valve control structure, further comprises:
the driving connecting rod is hinged between one end of the driving rocker arm, which faces the driving rocker arm connecting bracket, and the driving rocker arm connecting bracket;
and the driven connecting rod is hinged between one end of the driven rocker arm, which faces the driven rocker arm connecting bracket, and the driven rocker arm connecting bracket.
According to at least one embodiment of the present application, in the above-mentioned variable cycle aero-engine inner and outer duct annular valve control structure, further comprises:
the first roller mounting seat is connected to the bearing ring and provided with a first roller mounting hole;
the first roller is arranged in the first roller mounting hole;
the second roller mounting seat is connected to the bearing ring and provided with a second roller mounting hole;
And the second idler wheel is installed in the second idler wheel installation hole and is matched with the first idler wheel oppositely, and is pressed on the linkage ring from two sides.
According to at least one embodiment of the present application, in the variable cycle aero-engine inner and outer duct annular valve control structure, the first roller mounting seat and the corresponding first roller, second roller mounting seat and second roller are plural and distributed along the circumferential direction.
According to at least one embodiment of the application, in the variable cycle aero-engine inner and outer duct annular valve control structure, the outer wall of the annular valve is provided with a driving transmission protrusion and a driven transmission protrusion;
Further comprises:
One end of the inner side active transmission rocker arm is connected with one end of the active transmission shaft extending into the outer casing;
the inner side driving transmission connecting rod is hinged between the other end of the inner side driving transmission rocker arm and the driving transmission bulge;
one end of the inner driven transmission rocker arm is connected with one end of the driven transmission shaft extending into the outer casing;
the inner driven transmission connecting rod is hinged between the other end of the inner driven transmission rocker arm and the driven transmission bulge.
According to at least one embodiment of the present application, in the above-mentioned variable cycle aero-engine inner and outer duct annular valve control structure, further comprises:
the active transmission bearing bush is sleeved on the active transmission shaft, and the spigot is arranged in the active transmission shaft mounting hole;
The driven transmission bearing bushing is sleeved on the driven transmission shaft, and the spigot is arranged in the mounting hole of the driven transmission shaft.
According to at least one embodiment of the application, in the variable cycle aero-engine inner and outer duct annular valve control structure, a plurality of driving transmission shafts and corresponding component structures are distributed along the circumferential direction;
The driven transmission shaft and the corresponding part structure are multiple and distributed along the circumferential direction.
Drawings
FIG. 1 is a schematic diagram of an inner and outer duct annular valve control structure of a variable cycle aircraft engine provided by an embodiment of the application;
Fig. 2-4 are schematic diagrams of partial structures of an inner and outer duct annular valve control structure of a variable cycle aero-engine provided by an embodiment of the present application;
FIG. 5 is a schematic view of a load ring provided by an embodiment of the present application;
wherein:
1-an outer casing; 2-a split ring; 3-ring valve; 4-a force-bearing ring; 5-a driving transmission shaft mounting seat; 6-a driving transmission shaft; 7-a driven transmission shaft mounting seat; 8-a driven transmission shaft; 9-a linkage ring; 10-an active rocker arm connecting bracket; 11-an active rocker; 12-a driven rocker arm connecting bracket; 13-a driven rocker arm; 14-actuator mounting bracket; 15-an actuator cylinder; 16-an active link; 17-a driven link; 18-a first roller mount; 19-a first roller; 20-a second roller mounting seat; 21-a second roller; 22-inner active drive rocker arm; 23-inboard active drive links; 24-inboard driven drive rocker arm; 25-inboard driven drive links; 26-active drive bearing bushing.
For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application and not for limitation of the present application. It should be noted that, for convenience of description, only the part related to the present application is shown in the drawings, and other related parts may refer to the general design, and the embodiments of the present application and the technical features of the embodiments may be combined with each other to obtain new embodiments without conflict.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in the description of the present application are merely used for indicating relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and that the relative positional relationships may be changed when the absolute position of the object to be described is changed, thus not being construed as limiting the application. The terms "first," "second," "third," and the like, as used in the description of the present application, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the application are not to be construed as limiting the amount absolutely, but rather as existence of at least one. As used in this description of the application, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term as such, but does not exclude other elements or articles from the list of elements or articles that appear after the term.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description of the present application are used in a broad sense, and for example, the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The application is described in further detail below with reference to fig. 1 to 5.
An inner and outer duct annular valve control structure of a variable cycle aero-engine, comprising:
the outer casing 1 is provided with a driving perforation and a driven perforation;
the split ring 2 is arranged in the outer casing 1, an outer duct is formed between the split ring and the outer casing 1, an inner duct is formed in the split ring, and the side wall of the split ring is provided with an injection hole;
the annular valve 3 is abutted against the shunt ring 2;
The bearing ring 4 is sleeved on the outer casing 1 and provided with a driving via hole and a driven via hole;
the driving transmission shaft mounting seat 5 is connected to the bearing ring 4 and is provided with a driving transmission shaft mounting hole;
the driving transmission shaft 6 penetrates through the driving perforation, the driving through hole and the driving transmission shaft mounting hole, and one end of the driving transmission shaft extending into the outer casing 1 is hinged with the annular valve 3;
The driven transmission shaft mounting seat 7 is connected to the bearing ring 4 and is provided with a driven transmission shaft mounting hole;
the driven transmission shaft 8 penetrates through the driven perforation, the driven via hole and the driven transmission shaft mounting hole, and one end of the driven transmission shaft extending into the outer casing 1 is hinged with the annular valve 3;
The linkage ring 9 is sleeved on the periphery of the outer casing 1;
The active rocker arm connecting bracket 10 is connected to the linkage ring 9;
the driving rocker arm 11 is connected to one end of the driving transmission shaft 6, which is exposed out of the outer casing 1, and one end of the driving rocker arm is hinged to the driving rocker arm connecting bracket 10;
The driven rocker arm connecting bracket 12 is connected to the linkage ring 9;
One end of the driven rocker arm 13 is connected with one end of the driven transmission shaft 8 exposed out of the outer casing 1, and the other end of the driven rocker arm is hinged on the driven rocker arm connecting bracket 12;
the actuator cylinder mounting bracket 14 is connected to the bearing ring 4;
the actuator cylinder 15 is hinged between the other end of the driving rocker arm 11 and the actuator cylinder mounting bracket 14, so as to drive the driving rocker arm 11 to swing, further drive the driving transmission shaft 6 to rotate, and drive the linkage ring 9 to rotate, so that the driven rocker arm 13 swings, and drive the driven transmission shaft 8 to rotate, thereby enabling the annular valve 3 to axially move and opening or closing the injection hole.
For the variable cycle aeroengine inner and outer duct annular valve control structure disclosed in the above embodiment, those skilled in the art can understand that the design integrates the driving transmission shaft mounting seat 5, the driven transmission shaft mounting seat 7 and the actuator cylinder mounting bracket 14 on the bearing ring 4, the bearing ring 4 can be sleeved on the outer casing 1 in a welded mode, and the bearing ring has a larger contact area with the outer casing 1, so that when the variable cycle aeroengine inner and outer duct annular valve control structure can avoid acting, larger local stress is generated on the outer casing 1.
For the variable cycle aeroengine inner and outer duct annular valve control structure disclosed in the above embodiment, it can be understood by those skilled in the art that the variable cycle aeroengine inner and outer duct annular valve control structure is designed with a linkage ring 9 connected with an actuator 15 through an active rocker 11, when the actuator 15 drives the active rocker 11 to swing, the active transmission shaft 6 is driven to rotate, the driven rocker 13 is driven to swing, the driven transmission shaft 8 is driven to rotate, the active transmission shaft 6 and the driven transmission shaft 8 cooperatively drive the annular valve 3 to axially move, the injection holes are opened or closed, the annular valve 3 is driven at multiple points, the stability of the annular valve 3 in the axial movement is ensured, and the actuator 15 with a large number is not required to be designed.
In some alternative embodiments, in the above-mentioned control structure for the inner and outer duct ring valve of the variable cycle aeroengine, the injection holes are distributed circumferentially, and the specific number and the position distribution thereof can be determined by the related technicians according to specific practical implementation when the application is applied, and will not be described in detail herein.
In some alternative embodiments, in the above-mentioned control structure for the annular valve of the inner and outer ducts of the variable cycle aeroengine, the annular valve 3 is abutted against the inner side of the split-flow ring 2, so as to ensure the tightness of the abutted part between the annular valve and the split-flow ring 2.
In some optional embodiments, the variable cycle aeroengine inner and outer duct annular valve control structure further includes:
The driving connecting rod 16 is hinged between one end of the driving rocker arm 11 facing the driving rocker arm connecting bracket 10 and the driving rocker arm connecting bracket 10;
the driven connecting rod 17 is hinged between the end of the driven rocker arm 13 facing the driven rocker arm connecting bracket 12 and the driven rocker arm connecting bracket 12.
In some optional embodiments, the variable cycle aeroengine inner and outer duct annular valve control structure further includes:
a first roller mounting seat 18 connected to the load ring 4 and having a first roller mounting hole thereon;
a first roller 19 mounted in the first roller mounting hole;
The second roller mounting seat 20 is connected to the bearing ring 4 and is provided with a second roller mounting hole;
The second idler wheel 21 is installed in the second idler wheel installation hole and is matched with the first idler wheel 19 relatively, and is pressed on the linkage ring 9 from two sides, so that the linkage ring 9 can only rotate circumferentially under the drive of the actuator cylinder 15 due to the limitation, the circumferential and radial compound motion is avoided, the linkage ring 9 is prevented from being deformed greatly, the synchronism of the rotation of the driven transmission shaft 8 and the driving transmission shaft 6 can be effectively guaranteed, and the cooperativity of the driving of the annular valve 3 is further guaranteed.
In some alternative embodiments, in the above-mentioned control structure for the inner and outer duct ring valve of the variable cycle aeroengine, the first roller mounting seat 18 and the corresponding first roller 19, second roller mounting seat 20 and second roller 21 are plural and distributed circumferentially, and the specific number and the position distribution thereof can be determined by the relevant technicians according to specific practical implementation when applying the present application, and will not be described in detail herein.
In some alternative embodiments, in the variable cycle aeroengine inner and outer duct annular valve control structure, the outer wall of the annular valve 3 is provided with a driving transmission protrusion and a driven transmission protrusion;
Further comprises:
An inner driving transmission rocker arm 22, one end of which is connected to one end of the driving transmission shaft 6 extending into the outer casing 1;
An inner active transmission link 23 hinged between the other end of the inner active transmission rocker 22 and the active transmission projection;
an inner driven transmission rocker arm 24 having one end connected to one end of the driven transmission shaft 8 extending into the outer casing 1;
An inner driven transmission link 25 hinged between the other end of the inner driven transmission rocker arm 24 and the driven transmission projection.
In some optional embodiments, the variable cycle aeroengine inner and outer duct annular valve control structure further includes:
The active transmission bearing bush 26 is sleeved on the active transmission shaft 6, and the spigot is arranged in the active transmission shaft mounting hole;
the driven transmission bearing bush is sleeved on the driven transmission shaft 8, and the spigot is arranged in the driven transmission shaft mounting hole.
In some alternative embodiments, in the above-mentioned variable cycle aeroengine inner and outer duct annular valve control structure, the driving transmission shaft 6 and corresponding component structures thereof are plural and distributed along the circumferential direction;
The driven transmission shaft 8 and its corresponding component structure are plural, distributed along the circumferential direction, and the specific number and position thereof can be determined by the skilled person according to the specific practice when applying the present application, and will not be described in detail herein.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments shown in the drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the related technical features without departing from the principle of the present application, and those changes or substitutions will fall within the scope of the present application.
Claims (9)
1. An inner and outer duct annular valve control structure of a variable cycle aero-engine is characterized by comprising:
The outer casing (1) is provided with a driving perforation and a driven perforation;
a split ring (2) which is arranged in the outer casing (1) and forms an outer duct with the outer casing (1), an inner duct is formed in the split ring, and the side wall of the split ring is provided with an injection hole;
the annular valve (3) is abutted against the flow dividing ring (2);
the bearing ring (4) is sleeved on the outer casing (1) and provided with a driving via hole and a driven via hole;
The driving transmission shaft mounting seat (5) is connected to the bearing ring (4) and is provided with a driving transmission shaft mounting hole;
The driving transmission shaft (6) penetrates through the driving perforation, the driving through hole and the driving transmission shaft mounting hole, and one end of the driving transmission shaft extending into the outer casing (1) is hinged with the annular valve (3);
The driven transmission shaft mounting seat (7) is connected to the bearing ring (4) and is provided with a driven transmission shaft mounting hole;
The driven transmission shaft (8) penetrates through the driven perforation, the driven through hole and the driven transmission shaft mounting hole, and one end of the driven transmission shaft extending into the outer casing (1) is hinged with the annular valve (3);
The linkage ring (9) is sleeved on the periphery of the outer casing (1);
the driving rocker arm connecting bracket (10) is connected to the linkage ring (9);
The driving rocker arm (11) is connected to one end of the driving transmission shaft (6) exposed out of the outer casing (1), and one end of the driving rocker arm is hinged to the driving rocker arm connecting bracket (10);
The driven rocker arm connecting bracket (12) is connected to the linkage ring (9);
one end of the driven rocker arm (13) is connected with one end of the driven transmission shaft (8) exposed out of the outer casing (1), and the other end of the driven rocker arm is hinged on the driven rocker arm connecting bracket (12);
the actuator cylinder mounting bracket (14) is connected to the bearing ring (4);
The actuating cylinder (15) is hinged between the other end of the driving rocker arm (11) and the actuating cylinder mounting bracket (14), so that the driving rocker arm (11) can be driven to swing, the driving transmission shaft (6) is driven to rotate, the linkage ring (9) is driven to rotate, the driven rocker arm (13) is driven to swing, the driven transmission shaft (8) is driven to rotate, and the annular valve (3) moves along the axial direction to open or close the injection hole.
2. The variable cycle aeroengine inner and outer duct annular valve control structure of claim 1, wherein,
The injection holes are distributed in the circumferential direction.
3. The variable cycle aeroengine inner and outer duct annular valve control structure of claim 1, wherein,
The annular valve (3) is abutted against the inner side of the flow dividing ring (2).
4. The variable cycle aeroengine inner and outer duct annular valve control structure of claim 1, wherein,
Further comprises:
the driving connecting rod (16) is hinged between one end of the driving rocker arm (11) facing the driving rocker arm connecting bracket (10) and the driving rocker arm connecting bracket (10);
and the driven connecting rod (17) is hinged between one end of the driven rocker arm (13) facing the driven rocker arm connecting bracket (12) and the driven rocker arm connecting bracket (12).
5. The variable cycle aeroengine inner and outer duct annular valve control structure of claim 1, wherein,
Further comprises:
The first roller mounting seat (18) is connected to the bearing ring (4) and is provided with a first roller mounting hole;
a first roller (19) mounted in the first roller mounting hole;
the second roller mounting seat (20) is connected to the bearing ring (4) and is provided with a second roller mounting hole;
and the second roller (21) is arranged in the second roller mounting hole, is matched with the first roller (19) oppositely, and is pressed on the linkage ring (9) from two sides.
6. The variable cycle aeroengine inner and outer duct annular valve control structure of claim 5, wherein,
The first roller mounting seat (18) and the corresponding first roller (19), second roller mounting seat (20) and second roller (21) are multiple and distributed along the circumferential direction.
7. The variable cycle aeroengine inner and outer duct annular valve control structure of claim 1, wherein,
The outer wall of the annular valve (3) is provided with a driving transmission protrusion and a driven transmission protrusion;
Further comprises:
An inner side driving transmission rocker arm (22), one end of which is connected with one end of the driving transmission shaft (6) extending into the outer casing (1);
An inner active transmission connecting rod (23) hinged between the other end of the inner active transmission rocker arm (22) and the active transmission bulge;
an inner driven transmission rocker arm (24) one end of which is connected to one end of the driven transmission shaft (8) extending into the outer casing (1);
and the inner driven transmission connecting rod (25) is hinged between the other end of the inner driven transmission rocker arm (24) and the driven transmission bulge.
8. The variable cycle aeroengine inner and outer duct annular valve control structure of claim 1, wherein,
Further comprises:
a driving transmission bearing bushing (26) sleeved on the driving transmission shaft (6), and a spigot is arranged in the driving transmission shaft mounting hole;
The driven transmission bearing bush is sleeved on the driven transmission shaft (8), and the spigot is arranged in the driven transmission shaft mounting hole.
9. The variable cycle aeroengine inner and outer duct annular valve control structure of claim 1, wherein,
The driving transmission shaft (6) and the corresponding part structures thereof are distributed along the circumferential direction;
The driven transmission shaft (8) and the corresponding part structures are multiple and distributed along the circumferential direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210976214.7A CN115264159B (en) | 2022-08-15 | 2022-08-15 | Variable-circulation aero-engine inner and outer duct annular valve control structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210976214.7A CN115264159B (en) | 2022-08-15 | 2022-08-15 | Variable-circulation aero-engine inner and outer duct annular valve control structure |
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| CN115264159A CN115264159A (en) | 2022-11-01 |
| CN115264159B true CN115264159B (en) | 2024-09-06 |
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| CN116104602B (en) * | 2023-02-28 | 2024-04-12 | 中国空气动力研究与发展中心空天技术研究所 | Force transmission mechanism for engine compressor deflation |
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| CN109372592B (en) * | 2018-11-27 | 2019-09-24 | 中国航发沈阳发动机研究所 | A kind of regulating mechanism with displacement coordination ability |
| CN113719623B (en) * | 2021-09-15 | 2023-09-22 | 中国航空发动机研究院 | Valve for annular channel of aero-engine |
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|---|---|---|---|---|
| CN101624937A (en) * | 2009-08-17 | 2010-01-13 | 北京航空航天大学 | Passive control type mode conversion valve in mode conversion mechanism of variable cycle engine |
| CN103993983A (en) * | 2014-04-24 | 2014-08-20 | 北京航空航天大学 | Parallel-air inlet type rear duct ejector in variable cycle engine adjustable mechanism |
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| CN115264159A (en) | 2022-11-01 |
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