CN115523028A - Adjustable bleed valve link gear and contain its aeroengine - Google Patents
Adjustable bleed valve link gear and contain its aeroengine Download PDFInfo
- Publication number
- CN115523028A CN115523028A CN202110703676.7A CN202110703676A CN115523028A CN 115523028 A CN115523028 A CN 115523028A CN 202110703676 A CN202110703676 A CN 202110703676A CN 115523028 A CN115523028 A CN 115523028A
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- China
- Prior art keywords
- valve
- center
- link
- connecting arm
- crank
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/002—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by varying geometry within the pumps, e.g. by adjusting vanes
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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
- F16K31/52—Mechanical actuating means with crank, eccentric, or cam
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Fluid Mechanics (AREA)
- Mechanically-Actuated Valves (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses an adjustable deflation valve linkage mechanism and an aircraft engine comprising the same. The linkage mechanism of the adjustable deflation valve comprises; a linkage ring, an actuating connecting rod and a valve connecting rod; the crank has a first connecting arm, a second connecting arm and a third connecting arm which extend from the rotation center of the crank and are arranged at intervals around the rotation center, the first connecting arm is connected to the linkage ring, the second connecting arm is connected to the valve connecting rod, and the third connecting arm is connected to the valve connecting rod. The connecting center of the actuating connecting rod and the second connecting arm and the connecting center of the valve connecting rod and the third connecting arm are positioned on different sides of the rotating center. The valve connecting rod and the actuating connecting rod are connected to different connecting arms of the crank and are positioned on different sides of the rotation center, so that the valve connecting rod and the actuating connecting rod are separated, and compared with a common L-shaped crank, the length of the force arm is shorter, and the possibility of interference between the crank and the link ring is favorably reduced or avoided.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to an adjustable deflation valve linkage mechanism and an aero-engine comprising the same.
Background
VBV (variable bleed valve) is configured on a supercharging stage of an aero-engine for deflation regulation, the VBV is controlled through a link mechanism, a control source is an actuating cylinder, various types of adjustable link mechanisms exist, the existing main structural form is that the actuating cylinder pushes and pulls a driving link, the driving link is connected with a driving crank, the driving crank is connected with a linkage ring and a valve link, the driving link is actuated to drive the driving crank to rotate, so that the linkage ring is driven to move, one valve drives other driven cranks, and the driven cranks drive other deflation valves to actuate.
The general active crank adjusting mechanism is mainly an L-shaped crank, in the structure, a driving connecting rod and a valve connecting rod are positioned on one side of a crank rotating shaft, the driving connecting rod is positioned at the far end of the crank, the valve connecting rod is positioned in the middle, and a linkage ring is positioned on the other side. In addition, the L-shaped crank is unbalanced in stress, and the two ends of the crank are not positioned on the same plane, so that the lateral torque of the rotating shaft is increased, the crank and a bush of the crank are worn, and the service life of the crank and an adjusting mechanism, even the service life of a VBV (voltage source) is influenced.
Therefore, the VBV of the prior art aircraft engine has the defects that the crank and the link ring are easy to interfere, the lateral torque of the rotating shaft is increased, the crank and the bush thereof are worn, and the service life of the crank and the adjusting mechanism, even the VBV, is influenced.
Disclosure of Invention
The invention aims to overcome the defect that a crank and a link ring are easy to interfere in the prior art, and provides an adjustable air bleeding valve linkage mechanism and an aircraft engine comprising the same.
The invention solves the technical problems through the following technical scheme:
an adjustable deflation valve linkage mechanism comprises;
a linkage ring, an actuating connecting rod and a valve connecting rod;
the crank is provided with a first connecting arm, a second connecting arm and a third connecting arm, wherein the first connecting arm, the second connecting arm and the third connecting arm extend from the rotation center of the crank and are arranged at intervals around the rotation center;
the connecting center of the actuating connecting rod and the second connecting arm and the connecting center of the valve connecting rod and the third connecting arm are located on different sides of the rotating center.
In the scheme, the valve connecting rod and the actuating connecting rod are connected to different connecting arms of the crank and are positioned on different sides of the rotation center, the movable connecting rod and the actuating connecting rod are separated, and compared with a common L-shaped crank, the length of the force arm is shorter, so that the possibility of interference between the crank and the link ring is favorably reduced or avoided.
Preferably, the connecting center between the actuating link and the second connecting arm and the connecting center between the shutter link and the third connecting arm are located at different sides of the connecting center between the linkage ring and the first connecting arm.
Preferably, a center of connection of the link ring and the first link arm is located directly above the center of rotation.
In this scheme, adopt above-mentioned structure setting, be favorable to reducing articulate volume, and then be favorable to reducing the space that adjustable gassing valve link gear took in aeroengine.
Preferably, the connecting center of the actuating link and the second connecting arm, the connecting center of the shutter link and the third connecting arm, and the connecting center of the link ring and the first connecting arm are located on the same plane.
In the scheme, the three force points are positioned on the same plane and move around the rotating shaft of the rotating center, so that the mounting seats on the rotating shaft and the casing can be protected in a changeable mode, compared with a crank on the existing machine type, the force arm of a linkage ring and the force arm of a connecting rod are not positioned on the same plane, so that larger torque can be generated, the direction deviates from the rotating shaft, the scheme avoids the generation of the torque, and the service life of the crank is prolonged. Therefore, the scheme increases the reliability of the VBV, optimizes the stress of the adjusting mechanism, reduces the abrasion of the crank and the damage of the mounting seat of the casing, and prolongs the service life of the VBV and the casing.
Preferably, at least one of the first, second and third connecting arms is adjustable in length.
In this scheme, the length of linking arm is adjustable for the arm of force of crank can be according to actual need change, is favorable to increasing adjustable gassing valve link gear's application scope.
Preferably, a rotating shaft connecting hole is formed in the position, corresponding to the rotating center, of the crank, and an anti-abrasion bushing is arranged in the rotating shaft connecting hole.
Preferably, a first connecting hole, a second connecting hole and a third connecting hole are formed in the positions, corresponding to the linkage ring, the actuating connecting rod and the shutter connecting rod, of the first connecting arm, the second connecting arm and the third connecting arm respectively;
and bearings are connected in the first connecting hole, the second connecting hole and the third connecting hole respectively.
Preferably, the adjustable deflation valve linkage mechanism further comprises an actuating cylinder, a valve and a front positioning plate, wherein the actuating cylinder is connected with the actuating connecting rod, and the valve is connected with the valve connecting rod;
when the shutter is in an open state, the shutter is separated from the front positioning plate;
when the valve is in a closed state, the valve is attached to and hermetically connected with the front positioning plate.
Preferably, the shutter is of an inward opening structure.
In this scheme, adopt above-mentioned structure setting, the valve required space that opens and shuts is less relatively, is favorable to reducing the space that adjustable gassing valve link gear took in aeroengine.
The invention also provides an aircraft engine which comprises the adjustable deflation valve linkage mechanism.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.
The positive progress effects of the invention are as follows:
in the adjustable deflation valve linkage mechanism, the valve connecting rod and the actuating connecting rod are connected to different connecting arms of the crank and are positioned on different sides of the rotation center, the movable connecting rod and the actuating connecting rod are separated, and compared with a common L-shaped crank, the length of the force arm is shorter, so that the possibility of interference between the crank and a linkage ring is favorably reduced or avoided;
the three force points are on the same plane, and move around the rotating shaft of the rotating center, so that the mounting seats on the rotating shaft and the casing can be protected in a changeable manner. Therefore, the scheme increases the reliability of the VBV, optimizes the stress of the adjusting mechanism, reduces the abrasion of the crank and the damage of the mounting seat of the casing, and prolongs the service life of the VBV and the casing.
Drawings
FIG. 1 is a schematic structural view of an adjustable deflation valve linkage mechanism in accordance with a preferred embodiment of the present invention.
FIG. 2 is a schematic structural view of the crank in the adjustable deflation valve linkage mechanism in accordance with a preferred embodiment of the present invention.
Figure 3 is a schematic view of the adjustable deflation valve linkage mechanism of the present invention with the valve in the closed position.
Figure 4 is a schematic view of the adjustable deflation valve linkage mechanism of the present invention with the valve in an open position.
Description of the reference numerals:
10 crank
101 first connecting arm
102 second connecting arm
103 third connecting arm
104 rotating shaft connecting hole
105 first connection hole
106 second connecting hole
107 third connection hole
20 linkage ring
30 valve connecting rod
40 actuating link
50 valve
60 front positioning plate
Detailed Description
The invention is further illustrated by the following examples, which are not intended to limit the invention thereto.
As shown in fig. 1-4, the present embodiment discloses an adjustable deflation valve linkage mechanism comprising a linkage ring 20, an actuator link 40, a valve link 30, and a crank 10. The crank 10 has a first connecting arm 101, a second connecting arm 102, and a third connecting arm 103 extending from the rotation center of the crank 10 and spaced around the rotation center, the first connecting arm 101 being connected to the link ring 20, the second connecting arm 102 being connected to the shutter link 30, and the third connecting arm 103 being connected to the shutter link 30. The connecting center of the actuating link 40 and the second connecting arm 102 and the connecting center of the shutter link 30 and the third connecting arm 103 are located on different sides of the rotation center.
Wherein the valve link 30 and the actuating link 40 are connected to different connecting arms of the crank 10 and located at different sides of the rotation center, the movable link and the actuating link 40 are separated, and the length of the arm is shorter than that of a general L-shaped crank 10, thereby being beneficial to reducing or avoiding the possibility of interference between the crank 10 and the link ring 20.
As shown in fig. 1-2, the connection centers of the actuating link 40 and the second connecting arm 102 and the shutter link 30 and the third connecting arm 103 are located at different sides of the connection center of the link ring 20 and the first connecting arm 101.
As shown in fig. 1-2, the crank 10 is of a see-saw like construction.
As shown in fig. 1-2, in a preferred embodiment, the center of the linkage ring 20 to the first link arm 101 is located directly above the center of rotation. In this way, it is advantageously possible to reduce the volume of the crank 10 and therefore the space occupied by the linkage of the adjustable bleed valve in the aircraft engine.
It should be noted that, in an alternative embodiment, the connection center of the link ring 20 and the first connection arm 101 may be disposed not directly above the rotation center, but only adjacently.
In another preferred embodiment, as shown in fig. 1-2, the connection center of the actuating link 40 and the second connecting arm 102, the connection center of the shutter link 30 and the third connecting arm 103, and the connection center of the link ring 20 and the first connecting arm 101 are located on the same plane.
Compared with the crank 10 in the existing model, the force arm of the linkage ring 20 and the force arm of the connecting rod are not in the same plane, so that larger torque can be generated and the direction deviates from the rotating shaft, and the scheme avoids the generation of the torque and prolongs the service life of the crank 10. Therefore, the scheme increases the reliability of the VBV, optimizes the stress of the adjusting mechanism, reduces the abrasion of the crank 10 and the damage of the mounting seat of the casing, and prolongs the service life of the VBV and the casing.
In another preferred embodiment, at least one of the first, second and third connecting arms 101, 102, 103 is adjustable in length. The length of the connecting arm is adjustable, so that the force arm of the crank 10 can be changed according to actual requirements, and the application range of the adjustable deflation valve linkage mechanism is favorably widened.
As shown in fig. 1-2, a rotating shaft connecting hole 104 is formed at a position corresponding to the rotation center of the crank 10, and an anti-wear bushing (not shown) is disposed in the rotating shaft connecting hole 104.
As shown in fig. 1-2, the first, second and third connecting arms 101, 102 and 103 are provided with first, second and third connecting holes 105, 106 and 107 at positions corresponding to the interlocking ring 20, the actuating link 40 and the shutter link 30, respectively. Wherein bearings are respectively connected in the first connection hole 105, the second connection hole 106 and the third connection hole 107.
As shown in fig. 1 and 3-4, the adjustable deflation valve linkage mechanism further comprises an actuator cylinder (not shown), a valve 50 and a front positioning plate 60, wherein the actuator cylinder is connected to the actuator link 40, and the valve 50 is connected to the valve link 30. When the shutter 50 is in the opened state, the shutter 50 is separated from the front positioning plate 60. When the shutter 50 is in the closed state, the shutter 50 is attached to and hermetically sealed with the front positioning plate 60.
Wherein, the shutter 50 is matched with the positioning plate through the shutter link 30 to realize opening and closing, and simultaneously exhausts and discharges foreign matters, the working mode is simpler. The valve 50 is in contact with the front positioning plate 60 to form a flow channel, so that stable discharge of airflow can be guaranteed, and the adhesive tape is attached to and sealed with the front positioning plate 60, so that sealing can be guaranteed.
In another preferred embodiment, the shutter 50 is of an inwardly open configuration. With such an arrangement, the valve 50 requires relatively little space for opening and closing, which is beneficial for reducing the space occupied by the adjustable bleed valve linkage mechanism in the aircraft engine.
In the linkage mechanism of the adjustable deflation valve, the actuator cylinder drives the actuating link 40 to move, which drives the crank 10 to rotate and also drives the linkage ring 20 to move, the crank 10 rotates, and the valve link 30 drives the valve 50 to open or close.
In the linkage mechanism of the adjustable deflation valve, the valve connecting rod 30 and the actuating connecting rod 40 are connected to different connecting arms of the crank 10 and are positioned at different sides of the rotation center, so that the movable connecting rod and the actuating connecting rod 40 are separated, compared with the common L-shaped crank 10, the length of the force arm is shorter, and the possibility of interference between the crank 10 and the linkage ring 20 is favorably reduced or avoided. In addition, the three force application points are positioned on the same plane, the three force application points move around the rotating shaft of the rotating center, the rotating shaft and the mounting seat on the casing can be protected in a changeable mode, compared with the crank 10 on the existing machine type, the force arm of the linkage ring 20 and the force arm of the connecting rod are not positioned on the same plane, therefore, larger torque can be generated, the direction deviates from the rotating shaft, the scheme avoids the generation of the torque, and the service life of the crank 10 is prolonged. Therefore, the scheme increases the reliability of the VBV, optimizes the stress of the adjusting mechanism, reduces the abrasion of the crank 10 and the damage of the mounting seat of the casing, and prolongs the service life of the VBV and the casing.
The embodiment also provides an aircraft engine which comprises the adjustable deflation valve linkage mechanism.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes or modifications to these embodiments may be made by those skilled in the art without departing from the principle and spirit of this invention, and these changes and modifications are within the scope of this invention.
Claims (10)
1. An adjustable deflation valve linkage mechanism is characterized by comprising;
a linkage ring, an actuating connecting rod and a valve connecting rod;
a crank having a first connecting arm, a second connecting arm, and a third connecting arm extending from a rotation center of the crank and disposed at intervals around the rotation center, the first connecting arm being connected to the link ring, the second connecting arm being connected to the shutter link, the third connecting arm being connected to the shutter link;
the connecting center of the actuating connecting rod and the second connecting arm and the connecting center of the valve connecting rod and the third connecting arm are located on different sides of the rotating center.
2. An adjustable deflation valve linkage mechanism as in claim 1 wherein the center of connection of the actuator link to the second connecting arm and the center of connection of the valve link to the third connecting arm are located on different sides of the center of connection of the linkage ring to the first connecting arm.
3. An adjustable deflation valve linkage as in claim 2 wherein the center of connection of the linkage ring to the first connecting arm is directly above the center of rotation.
4. An adjustable deflation valve linkage mechanism as in claim 2 wherein the center of connection of the actuation link to the second connecting arm, the center of connection of the valve link to the third connecting arm, and the center of connection of the linkage ring to the first connecting arm are located on the same plane.
5. An adjustable deflation valve linkage as in claim 1 wherein at least one of the first, second and third connecting arms is adjustable in length.
6. An adjustable deflation valve linkage mechanism as in claim 1 wherein the crank has a pivot attachment hole at a location corresponding to the center of rotation, the pivot attachment hole having an anti-wear bushing disposed therein.
7. An adjustable deflation valve linkage mechanism as in claim 1 wherein the first, second and third connecting arms are provided with first, second and third connecting holes at locations corresponding to the positions of the linkage ring, the actuating link and the valve link, respectively;
and bearings are connected in the first connecting hole, the second connecting hole and the third connecting hole respectively.
8. An adjustable deflation valve linkage as in claim 1 further comprising an actuator cylinder, a valve and a front positioning plate, the actuator cylinder being connected to the actuator link and the valve being connected to the valve link;
when the shutter is in an open state, the shutter is separated from the front positioning plate;
when the valve is in a closed state, the valve is attached to and hermetically connected with the front positioning plate.
9. An adjustable deflation valve linkage as in claim 8 wherein the valve is of inwardly open construction.
10. An aircraft engine, characterised in that it comprises an adjustable bleed valve linkage as claimed in any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110703676.7A CN115523028A (en) | 2021-06-24 | 2021-06-24 | Adjustable bleed valve link gear and contain its aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110703676.7A CN115523028A (en) | 2021-06-24 | 2021-06-24 | Adjustable bleed valve link gear and contain its aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115523028A true CN115523028A (en) | 2022-12-27 |
Family
ID=84694105
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110703676.7A Pending CN115523028A (en) | 2021-06-24 | 2021-06-24 | Adjustable bleed valve link gear and contain its aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115523028A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116104602A (en) * | 2023-02-28 | 2023-05-12 | 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 |
-
2021
- 2021-06-24 CN CN202110703676.7A patent/CN115523028A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116104602A (en) * | 2023-02-28 | 2023-05-12 | 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 |
| 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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