CN115163565A - Adjustable air release mechanism of aviation turbofan engine intermediary cartridge receiver linkage - Google Patents
Adjustable air release mechanism of aviation turbofan engine intermediary cartridge receiver linkage Download PDFInfo
- Publication number
- CN115163565A CN115163565A CN202210903900.1A CN202210903900A CN115163565A CN 115163565 A CN115163565 A CN 115163565A CN 202210903900 A CN202210903900 A CN 202210903900A CN 115163565 A CN115163565 A CN 115163565A
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- arm
- linkage
- ring
- turbofan engine
- driving
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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
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
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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
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0223—Control schemes therefor
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Lift Valve (AREA)
Abstract
The invention belongs to the field of aero-engines, and particularly relates to an intermediate casing linkage adjustable air bleeding mechanism of an aero turbofan engine, which comprises an actuating cylinder (1), wherein the actuating cylinder (1) is connected with a driving linkage ring (7), the linkage ring (7) is sleeved on the outer side of the intermediate casing, the linkage ring (7) is connected with a plurality of executing mechanisms, the executing mechanisms comprise a plurality of executing mechanisms, the executing mechanisms are distributed along the circumferential direction of the linkage ring (7), each executing mechanism comprises a connecting rod and an air bleeding valve (10), and the linkage ring (7) drives the air bleeding valve (10) to be disconnected and connected through the connecting rod; on the other hand, the synchronous linkage of all the deflation valves at all positions is realized, and the synchronous consistency of the movement of the valves is improved.
Description
Technical Field
The application belongs to the field of aero-engines, and particularly relates to an adjustable air bleeding mechanism for linkage of an intermediate casing of an aero turbofan engine.
Background
The intermediate casing serves as a bearing frame of the aviation turbofan engine, a flow path is provided for inner and outer culvert air flow, and the inner space of the support plate provides a channel for a test lead and a pipeline. In order to solve the problem of matching of the air flow of the compressor, an adjustable bleed valve mechanism is designed at the flow path of the intermediate casing to adjust the air flow of an inner culvert and an outer culvert, and the adjustable bleed valve mechanism has the function of preventing engine surge.
Generally, a plurality of air discharge positions are designed in the intermediate casing and are uniformly distributed along the circumference, and each air discharge position is provided with a set of air discharge mechanism. Under the instruction of a control system, a piston rod in the actuating cylinder pushes a push rod, and the push rod drives the air bleeding valve to rotate around the fixed rotating shaft, so that the air bleeding valve is opened and closed, and the air flow of the inner duct and the outer duct is adjusted.
1. Each bleed position has 1 cylinder to drive independently, resulting in a greater number of cylinders required by the bleed mechanism, with a bleed position of 12 meaning 12 cylinders are required. On one hand, the increase of the number of the actuating cylinders occupies a large mounting space of the intermediate casing, so that the weight of the engine is increased, and the complexity of a control system is increased; on the other hand, the cost is increased, and the work efficiency of the air discharging mechanism is lower.
2. The opening and closing of the air bleeding valves at all positions are controlled by the independent actuating cylinders, and the opening and closing movement consistency of the air bleeding valves is poor.
Disclosure of Invention
In order to solve the above problem, the present application provides an adjustable air bleeding mechanism of intermediary cartridge receiver linkage of aviation turbofan engine, includes:
the actuating cylinder is connected with the driving linkage ring, the linkage ring is sleeved on the outer side of the intermediate casing, the linkage ring is connected with the executing mechanism, the executing mechanism comprises a plurality of executing mechanisms, the executing mechanisms are distributed along the circumferential direction of the linkage ring, each executing mechanism comprises a connecting rod and an air bleeding valve, and the linkage ring drives the air bleeding valve to be disconnected and disconnected through the connecting rods.
Preferably, the specific structure of the connection of the actuating cylinder and the driving linkage ring is as follows: the actuating cylinders are distributed along the circumferential direction of the linkage ring, each actuating cylinder is provided with a piston rod moving along the axial direction of the corresponding actuating cylinder, the tail end of each piston rod is hinged to a first arm of the corresponding driving rocker arm through a pull rod, each driving rocker arm is further provided with a second arm, a preset angle is formed between each first arm and each second arm, each second arm is hinged to the corresponding driving linkage ring, a hinge hole is formed in the joint between each first arm and each second arm, each driving rocker arm is hinged to the corresponding intermediate case through the hinge hole, and the axial direction of each hinge hole is the radial direction of the corresponding linkage ring.
Preferably, the specific structure that the link ring is connected with the connecting rod and the deflation valve is as follows: one end of the deflation valve is hinged to the intermediary case through a pin shaft, the pin shaft is tangent to the cylindrical surface of the intermediary case, one end of the driven push rod is hinged to the deflation valve, the other end of the driven push rod is hinged to a first support arm of the driven rocker arm, the driven rocker arm is further provided with a second support arm, a preset angle is formed between the first support arm and the second support arm, the second support arm is hinged to the driving linkage ring, a hinge hole is formed in the joint between the first support arm and the second support arm, the driven rocker arm passes through the hinge hole and the intermediary case, and the axial direction of the hinge hole is the radial direction of the linkage ring.
Preferably, the first arm of the active rocker arm is further hinged with an active push rod, and the active push rod is further hinged with an active deflation valve.
Preferably, a joint bearing is installed at the hinged position of the first arm of the driving rocker arm and the driving push rod.
Preferably, the joint of the driven push rod and the air release valve is provided with a joint bearing.
Preferably, the driving push rod, the driven push rod and the pull rod are all length-adjustable connecting rods.
Preferably, the adjustable connecting rod comprises a screw rod and an adjusting nut, one end of the screw rod is provided with a hinged lug, and the screw rod is provided with an external thread; the adjusting nut is connected with the screw rod through the external thread; the outer wall of the adjusting nut is hinged with an installation lug.
Preferably, the link ring is lapped with a bracket, and the bracket is arranged on the outer wall surface of the intermediate casing.
The advantages of the present application include:
1. the invention can effectively reduce the number of actuating cylinders, optimize the installation space of the intermediary casing and simplify a control system.
2. The invention realizes the synchronous linkage of all the deflation valves at all positions and improves the synchronous consistency of the valve motion.
Drawings
FIG. 1 is a schematic view of an intermediate casing linkage adjustable bleed mechanism of an aircraft turbofan engine according to a preferred embodiment of the present application;
FIG. 2 is a schematic view of an intermediate casing linkage adjustable bleed mechanism of an aircraft turbofan engine according to a preferred embodiment of the present application;
FIG. 3 is a schematic view of a length adjustable linkage.
1-actuating cylinder, 2-piston rod, 3-pull rod, 4-driving rocker arm, 5-driving push rod, 6-driving air release valve, 7-linkage ring, 8-driven rocker arm, 9-driven push rod and 10-air release valve.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
In order to solve the problems of increased engine weight, increased complexity of a control system, lower working efficiency of an air bleeding mechanism and poor consistency of opening and closing movement of an air bleeding valve caused by occupation of a large amount of installation space of an intermediate casing due to excessive number of actuating cylinders, as shown in fig. 1-3, the application provides an intermediate casing linkage adjustable air bleeding mechanism of an aviation turbofan engine, wherein when the number of the air bleeding valves 10 of the intermediate casing is small, the embodiment 1 is adopted:
the adjustable bleed mechanism of aviation turbofan engine intermediary cartridge receiver linkage of embodiment 1 includes:
the actuating cylinder 1, actuating cylinder 1 connect drive link ring 7, and link ring 7 cover is in the outside of intermediary machine casket, and link ring 7 connects actuating mechanism, and actuating mechanism includes a plurality ofly, a plurality of actuating mechanism distributes along link ring 7 circumference, actuating mechanism includes connecting rod and gassing valve 10, and link ring 7 passes through the break-make of connecting rod drive gassing valve 10, and actuating cylinder 1 drive link ring 7 motion includes: the compound motion of rotation around the axis of the intermediate casing and translation along the axis of the intermediate casing.
The specific structure that actuating cylinder 1 and drive link ring 7 are connected is: the actuating cylinder 1 comprises a plurality of actuating cylinders 1 which are distributed along the circumferential direction of a linkage ring 7, each actuating cylinder 1 is provided with a piston rod 2 which moves along the axial direction of the actuating cylinder 1, the tail end of each piston rod 2 is hinged with a first arm of an active rocker arm 4 through a pull rod 3, each active rocker arm 4 is also provided with a second arm, a preset angle is formed between each first arm and each second arm, each second arm is hinged with the corresponding driving linkage ring 7, a hinge hole is formed in the joint between each first arm and each second arm, each active rocker arm 4 is hinged with a medium box through the corresponding hinge hole, and the axial direction of each hinge hole is the radial direction of the corresponding linkage ring 7.
Wherein, the concrete structure that link ring 7 and connecting rod, gassing valve 10 are connected is: one end of the deflation valve 10 is hinged to the intermediary case through a pin shaft, the pin shaft is tangent to the cylindrical surface of the intermediary case, one end of the driven push rod 9 is hinged to the deflation valve 10, the other end of the deflation valve is hinged to the first support arm of the driven rocker arm 8, the driven rocker arm 8 is further provided with a second support arm, a preset angle is formed between the first support arm and the second support arm, the second support arm is hinged to the driving linkage ring 7, a hinge hole is formed in the joint between the first support arm and the second support arm, the driven rocker arm 8 passes through the hinge hole and the intermediary case, the axial direction of the hinge hole is the radial direction of the linkage ring 7, a joint bearing is installed at the hinge position of the first arm of the driving rocker arm 4 and the driving push rod 5, and a joint bearing is installed at the hinge position of the driven push rod 9 and the deflation valve 10, in addition, joint bearings can be installed at other hinge points of the adjustable deflation mechanism of the application, and the phenomenon of blocking of the hinge points is avoided.
Preferably, the driving push rod 5, the driven push rod 9 and the pull rod 3 are all length-adjustable connecting rods.
In order to compensate the accumulated influence caused by the dimensional tolerance of each component of the mechanism, the driving push rod 5, the driven push rod 9 and the pull rod 3 are designed into structures with adjustable lengths, so that the size of a component is slightly adjusted, and the movement accuracy of the mechanism is improved. As shown in fig. 3, the length-adjustable connecting rod comprises a screw and an adjusting nut, one end of the screw is provided with a hinged lug, and the screw is provided with an external thread; the adjusting nut is connected with the screw rod through the external thread; the outer wall of the adjusting nut is hinged with an installation lug.
Preferably, the link ring 7 is lapped with a bracket, the bracket is arranged on the outer wall surface of the intermediate casing, the link ring 7 slides on the bracket, and the bracket can limit the eccentric deformation of the link ring and improve the rigidity of the link ring.
Example 2:
the embodiment is mainly applied to the situation that the number of the air bleeding valves 10 of the intermediate casing is large, and is different from the intermediate casing linkage adjustable air bleeding mechanism of the aviation turbofan engine in the embodiment 1, the first arm of the driving rocker arm 4 is further hinged with a driving push rod 5, the driving push rod 5 is hinged with a driving air bleeding valve 6, in the embodiment 2, under the condition that the number of the air bleeding valves is large, the position space of an actuator cylinder conflicts with the position space of an air bleeding valve device, and the active push rod 5 and the active air bleeding valve 6 are designed to avoid the position conflict of the actuator cylinder and the air bleeding valve.
According to the first aspect of the application, the linkage ring is designed, the number of actuating cylinders is reduced, and the synchronous movement of the air release valve is realized; in the second aspect, the connecting rod with the adjustable length is designed, so that the manufacturing tolerance is compensated. The third aspect designs a link ring support for increasing the rigidity of the deflation mechanism.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. The utility model provides an adjustable air bleeding mechanism of medium cartridge receiver linkage of aviation turbofan engine which characterized in that includes:
the actuating cylinder (1) is connected with a driving linkage ring (7), the linkage ring (7) is sleeved on the outer side of the intermediate casing, the linkage ring (7) is connected with a plurality of executing mechanisms, the executing mechanisms are distributed along the circumferential direction of the linkage ring (7), each executing mechanism comprises a connecting rod and an air bleeding valve (10), and the linkage ring (7) drives the air bleeding valve (10) to be switched on and off through the connecting rod.
2. The mechanism of claim 1, wherein the actuator cylinder (1) is connected to the driving link ring (7) by a specific structure comprising: the actuating cylinder (1) comprises a plurality of actuating cylinders (1) which are distributed along the circumferential direction of the linkage ring (7), the actuating cylinder (1) is provided with a piston rod (2) which moves along the axial direction of the actuating cylinder (1), the tail end of the piston rod (2) is hinged with a first arm of the driving rocker arm (4) through a pull rod (3), the driving rocker arm (4) is further provided with a second arm, a preset angle is formed between the first arm and the second arm, the second arm is hinged with the driving linkage ring (7), a hinge hole is formed in the joint between the first arm and the second arm, the driving rocker arm (4) is hinged with the intermediary casing through the hinge hole, and the axial direction of the hinge hole and the radial direction of the linkage ring (7) are in the same direction.
3. The mechanism of claim 1, wherein the linkage ring (7) is connected to the connecting rod and the bleed valve (10) by a specific structure comprising: the one end of gassing valve (10) is articulated on intermediary machine casket through the round pin axle, the round pin axle is tangent with the cylinder of intermediary machine casket, and gassing valve (10) are articulated to the one end of driven push rod (9), and the first support arm of the articulated driven rocking arm (8) of the other end, driven rocking arm (8) still have the second support arm, first support arm with preset angle has between the second support arm, the second support arm is articulated with drive link ring (7), and the junction between first support arm and the second support arm has the hinge hole, and driven rocking arm (8) pass through the hinge hole is articulated with intermediary machine casket, the axial direction of hinge hole is the radial direction of link ring (7).
4. The intermediary case linkage adjustable air bleeding mechanism of an aviation turbofan engine according to claim 2 wherein the first arm of the active rocker arm (4) is further articulated with an active push rod (5), the active push rod (5) in turn being articulated with an active bleed valve (6).
5. The intermediary case linkage adjustable air bleeding mechanism of an aviation turbofan engine according to claim 4, wherein a joint bearing is installed at the joint of the first arm of the driving rocker arm (4) and the driving push rod (5).
6. The intermediate case linkage adjustable bleed mechanism of an aircraft turbofan engine according to claim 3 wherein a joint bearing is installed at the joint of the driven push rod (9) and the bleed valve (10).
7. The intermediate case linkage adjustable bleed mechanism of an aircraft turbofan engine according to any one of claims 3 and 4 wherein the driving push rod (5), the driven push rod (9) and the tie rod (3) are all length adjustable links.
8. The aircraft turbofan engine intermediate case linkage adjustable bleed mechanism of claim 7 wherein the adjustable link comprises a threaded rod having a hinged tab at one end and an adjusting nut having external threads thereon; the adjusting nut is connected with the screw rod through the external thread; the outer wall of the adjusting nut is hinged with a mounting lug.
9. The intermediate case linkage adjustable bleed mechanism of an aircraft turbofan engine according to claim 1 wherein the link ring (7) is attached with a bracket, said bracket being mounted on the outer wall surface of the intermediate case.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210903900.1A CN115163565B (en) | 2022-07-29 | 2022-07-29 | Medium casing linkage adjustable air release mechanism of aviation turbofan engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210903900.1A CN115163565B (en) | 2022-07-29 | 2022-07-29 | Medium casing linkage adjustable air release mechanism of aviation turbofan engine |
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| Publication Number | Publication Date |
|---|---|
| CN115163565A true CN115163565A (en) | 2022-10-11 |
| CN115163565B CN115163565B (en) | 2023-08-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210903900.1A Active CN115163565B (en) | 2022-07-29 | 2022-07-29 | Medium casing linkage adjustable air release mechanism of aviation turbofan engine |
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| CN (1) | CN115163565B (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 |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0436807A1 (en) * | 1989-12-14 | 1991-07-17 | Austria Metall Aktiengesellschaft | Impregnation nozzle for manufacturing metal-matrix composite material |
| FR2961251A1 (en) * | 2010-06-15 | 2011-12-16 | Snecma | Hub for use in intermediate casing of e.g. ducted-fan turbine engine of aircraft, has flange including air outlet orifices formed downstream from bleed valves, and deflectors permitting guiding of air between inlet and outlet orifices |
| CN102641999A (en) * | 2012-04-24 | 2012-08-22 | 王东 | Device and method for continuously preparing bulk amorphous alloy ingots |
| EP3502484A1 (en) * | 2017-12-19 | 2019-06-26 | Siemens Aktiengesellschaft | Adjustment linkage |
| CN114427503A (en) * | 2022-01-21 | 2022-05-03 | 中国航发沈阳发动机研究所 | Three-duct intermediate casing duct conversion mechanism of variable-cycle aero-engine |
| CN114570900A (en) * | 2022-03-03 | 2022-06-03 | 大连交通大学 | Device and method for continuous casting and extrusion forming of copper and copper alloy |
| CN114653906A (en) * | 2020-12-23 | 2022-06-24 | 中国科学院江西稀土研究院 | Preparation method and system device of metal-based composite board |
-
2022
- 2022-07-29 CN CN202210903900.1A patent/CN115163565B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0436807A1 (en) * | 1989-12-14 | 1991-07-17 | Austria Metall Aktiengesellschaft | Impregnation nozzle for manufacturing metal-matrix composite material |
| FR2961251A1 (en) * | 2010-06-15 | 2011-12-16 | Snecma | Hub for use in intermediate casing of e.g. ducted-fan turbine engine of aircraft, has flange including air outlet orifices formed downstream from bleed valves, and deflectors permitting guiding of air between inlet and outlet orifices |
| CN102641999A (en) * | 2012-04-24 | 2012-08-22 | 王东 | Device and method for continuously preparing bulk amorphous alloy ingots |
| EP3502484A1 (en) * | 2017-12-19 | 2019-06-26 | Siemens Aktiengesellschaft | Adjustment linkage |
| CN114653906A (en) * | 2020-12-23 | 2022-06-24 | 中国科学院江西稀土研究院 | Preparation method and system device of metal-based composite board |
| CN114427503A (en) * | 2022-01-21 | 2022-05-03 | 中国航发沈阳发动机研究所 | Three-duct intermediate casing duct conversion mechanism of variable-cycle aero-engine |
| CN114570900A (en) * | 2022-03-03 | 2022-06-03 | 大连交通大学 | Device and method for continuous casting and extrusion forming of copper and copper alloy |
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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| Publication number | Publication date |
|---|---|
| CN115163565B (en) | 2023-08-04 |
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