CN115535266A - Two-stage adjustable guide vane of S-shaped guide duct of aircraft and control method thereof - Google Patents
Two-stage adjustable guide vane of S-shaped guide duct of aircraft and control method thereof Download PDFInfo
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- CN115535266A CN115535266A CN202211375030.1A CN202211375030A CN115535266A CN 115535266 A CN115535266 A CN 115535266A CN 202211375030 A CN202211375030 A CN 202211375030A CN 115535266 A CN115535266 A CN 115535266A
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- 230000007246 mechanism Effects 0.000 claims abstract description 59
- 230000005540 biological transmission Effects 0.000 claims description 20
- 230000008569 process Effects 0.000 claims description 5
- 238000013178 mathematical model Methods 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a two-stage adjustable guide vane of an S-shaped bent air guide passage of an aircraft and a control method thereof, wherein the two-stage adjustable guide vane of the S-shaped bent air guide passage of the aircraft comprises the following components: the supporting mechanism is connected to an S-shaped air guide channel of the aircraft; the first-stage guide vane adjusting mechanism is connected to the supporting mechanism and at least comprises a first-stage guide vane group and a first-stage driving structure, and the first-stage driving structure drives the blade corner of the first-stage guide vane group so as to adjust the flow rate and the air pressure of an input airflow; and the second-stage guide vane adjusting mechanism is connected to the supporting mechanism. On the basis of adjusting the flow of the input airflow, the speed angle of the input airflow can be adjusted, so that the state of the input airflow is more stable. Meanwhile, the opening and closing states of the blades of the two-stage adjustable guide vane mechanism are controlled, so that the additional flow resistance loss of input airflow can be reduced, the pneumatic efficiency is improved, and the accurate control of the input airflow on the system power is realized.
Description
Technical Field
The invention relates to the technical field of energy adjustment of an air guide channel of an aircraft, in particular to a two-stage adjustable guide vane of an S-shaped air guide channel of the aircraft and a control method thereof.
Background
In the process of air entraining of the aircraft, the speed and the air pressure of input ram air are different, so the air flow state in the S-shaped air entraining passage of the aircraft is quite complex and changeable, and in order to control the input state of the air flow, an air flow input power adjusting mechanism is installed in the air entraining passage of the aircraft.
The invention patent CN100487239C "built-in ducted ram air turbine power generation device" has a movable rear fairing matched with a convergent section, and changes the sectional area of an outlet of gas through movement, thereby adjusting the input power of the gas. Although the mechanism can control the air flow by continuously adjusting the opening of the sectional area of the outlet, the mechanism needs to additionally occupy the space of a flow channel and cannot control the speed angle of the input air in the S-shaped air inlet channel, so that the pneumatic efficiency is low, and the accurate control of the system power is difficult to realize.
The invention patents CN113682462A and CN111594484a respectively disclose an inlet guide vane adjusting mechanism, both of which can change the rotation angle of the guide vane according to the condition of the input air flow, thereby adjusting the input power of the air flow. Both mechanisms are single-stage guide vane mechanisms, and when the input airflow state is complex, the speed angle of the input airflow cannot be changed according to the flow and the pressure of the input airflow, so that the accurate control of the system power is difficult to realize in an environment with complex input airflow states such as an S-bend air guide channel.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art.
To this end, the invention provides, in a first aspect, a two-stage adjustable guide vane for an S-bend air duct of an aircraft.
The invention provides a control method of two-stage adjustable guide vanes of an S-shaped guide air passage of an aircraft in a second aspect.
The invention provides a two-stage adjustable guide vane of an S-shaped guide duct of an aircraft, which comprises:
the supporting mechanism is connected to an S-shaped air guide channel of the aircraft;
the first-stage guide vane adjusting mechanism is connected to the supporting mechanism and at least comprises a first-stage guide vane group and a first-stage driving structure, and the first-stage driving structure drives the blade corner of the first-stage guide vane group so as to adjust the flow rate and the air pressure of an input airflow;
and the second-stage guide vane adjusting mechanism is connected to the supporting mechanism and is positioned on one side of the first-stage guide vane adjusting mechanism, wherein the second-stage guide vane adjusting mechanism at least comprises a second-stage guide vane group and a second-stage driving structure, and the second-stage driving structure drives the blade corner of the second-stage guide vane group to adjust the speed angle of the input airflow.
The two-stage adjustable guide vane of the S-shaped guide duct of the aircraft according to the technical scheme of the invention can also have the following additional technical characteristics:
in the above technical solution, the first-stage guide vane adjusting mechanism further includes:
the first linkage ring is arranged along the radial direction of the first linkage ring, and one end of the first guide vane group and at least part of the supporting mechanism form a hinged structure;
the other end of the first guide vane connecting rod group is connected with the first guide vane connecting rod group, and the end part of the first guide vane connecting rod group and the first linkage ring form a hinge structure;
the first-stage driving structure is meshed with the first linkage ring to be connected so as to drive the first linkage ring to radially rotate and drive the first-stage guide vane connecting rod group to drive the blades of the first-stage guide vane group to swing.
In the above technical solution, at least a portion of the first link ring is formed with a first convex tooth portion, a driving end of the primary driving structure is connected with a first transmission gear, and the first transmission gear is in meshed connection with the first convex tooth portion.
In the above technical scheme, the primary driving structure is a first motor, and a driving end of the first motor is connected with the first transmission gear to drive the first transmission gear to rotate.
In the above technical solution, the two-stage guide vane adjusting mechanism further includes:
the second linkage ring is arranged along the radial direction of the second linkage ring, and one end of the second-stage guide vane group and at least part of the supporting mechanism form a hinged structure;
the other end of the second guide vane connecting rod group is connected with the second guide vane connecting rod group, and the end part of the second guide vane connecting rod group and the second linkage ring form a hinged structure;
and the second-stage driving structure and the second linkage ring form meshing connection so as to drive the second linkage ring to radially rotate and drive the second-stage guide vane connecting rod group to drive the blades of the second-stage guide vane group to swing.
In the above technical solution, at least a part of the second coupling ring is formed with a second convex tooth portion, a driving end of the secondary driving structure is connected with a second transmission gear, and the second transmission gear is in meshed connection with the second convex tooth portion.
In the above technical scheme, the secondary driving structure is a second motor, and a driving end of the second motor is connected with the second transmission gear to drive the second transmission gear to rotate.
In the above technical solution, the support mechanism includes:
the shape of the profile support frame is matched with that of the S-shaped air guide channel of the aircraft, and the profile support frame is fixed in the S-shaped air guide channel of the aircraft;
and the middle axial flow nose cone is arranged on the central axis of the outline support frame, wherein one ends of the blades of the first-stage guide blade group and the second-stage guide blade group form a hinged structure with the middle axial flow nose cone.
The invention also provides a control method of the two-stage adjustable guide vane of the S-shaped guide duct of the aircraft, which comprises the following steps:
desired input power W to the airflow at the airflow utilization section r As input quantity of the control system;
control system pair W r Actual input power W to the gas flow a Comparing to obtain a difference value delta W;
the difference value delta W, the airflow input flow P and the airflow input pressure Q jointly act on the controller C 1 Controller C 1 The solved first motor rotation angle variation delta theta 1 Sent to the first motor M 1 Thereby controlling M 1 Outputting the current angle theta 1 ；
The difference value delta W, the airflow input flow P, the airflow input pressure Q and the first motor rotation angle variation theta 1 Acting together on the controller C 2 Controller C 2 The solved second motor rotation angle variation delta theta 2 Sent to the second motor M 2 Thereby controlling M 2 Outputting the current angle theta 2 ；
Airflow input flow P, airflow input pressure Q and first motor rotation angle variation theta 1 And the current angle theta 2 After the parameters jointly act on the mathematical model S of the two-stage adjustable guide vane mechanism, the actual input power W of the airflow can be obtained a (ii) a And then continuously carrying out real-time iteration through a negative feedback process, and finally realizing the accurate control of the input airflow on the system power.
Compared with the prior art, the two-stage adjustable guide vane of the S-shaped guide air passage of the aircraft and the control method thereof provided by the invention have the following beneficial effects:
according to the technical scheme provided by the invention, on the basis of adjusting the flow of the input airflow, the speed angle of the input airflow can be adjusted, so that the state of the input airflow is more stable. Meanwhile, the opening and closing states of the blades of the two-stage adjustable guide vane mechanisms are controlled, so that the additional flow resistance loss of input airflow can be reduced, the pneumatic efficiency is improved, and the accurate control of the input airflow on the system power is realized.
Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is a schematic view of the installation of two-stage adjustable guide vanes of the S-bend air duct of the aircraft of the present invention;
FIG. 2 is one of the perspective views of the two-stage adjustable vane of the S-bend air duct of the aircraft of the present invention;
FIG. 3 is a second perspective view of the two-stage adjustable vane of the S-bend air duct of the aircraft of the present invention;
FIG. 4 is a perspective view of the one-stage vane adjustment mechanism in the two-stage adjustable guide vane of the S-bend air duct of the aircraft of the present invention;
FIG. 5 is a perspective view of the two-stage vane adjustment mechanism in the two-stage adjustable guide vane of the S-bend air duct of the aircraft of the present invention;
FIG. 6 is a control logic diagram of a control method of two-stage adjustable guide vanes of an S-bend air guide passage of the aircraft.
Wherein, the correspondence between the reference numbers and the part names in fig. 1 to 6 is:
1. the aircraft 2.S is provided with a bent air guide channel 3, a two-stage adjustable guide vane mechanism 4, a supporting mechanism 5, a first-stage guide vane adjusting mechanism 6, a second-stage guide vane adjusting mechanism 7, an outline supporting frame 8, a central axial flow head cone 9, a first-stage guide vane group 10, a first linkage ring 11, a first-stage guide vane connecting rod group 12, a first motor 13, a first transmission gear 14, a second-stage guide vane group 15, a second linkage ring 16, a second-stage guide vane connecting rod group 17, a second motor 18 and a second transmission gear.
Detailed Description
In order that the above objects, features and advantages of the present invention can be more clearly understood, a more particular description of the invention will be rendered by reference to the appended drawings. It should be noted that the embodiments and features of the embodiments of the present application may be combined with each other without conflict.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced otherwise than as specifically described herein, and thus the scope of the present invention is not limited by the specific embodiments disclosed below.
Two-stage adjustable guide vanes for an aircraft S-bend air duct and methods of controlling the same provided according to some embodiments of the present invention are described below with reference to fig. 1-6.
Some embodiments of the present application provide a two-stage adjustable vane for an aircraft S-bend air duct.
As shown in fig. 1 to 5, a first embodiment of the invention proposes a two-stage adjustable guide vane for an S-bend bleed duct of an aircraft, which is installed in an S-bend bleed duct 2 of an aircraft 1. The two-stage adjustable guide vane mechanism 3 is composed of a supporting mechanism 4, a first-stage guide vane adjusting mechanism 5 and a second-stage guide vane adjusting mechanism 6.
In the present embodiment, the support mechanism 4 includes a profile support frame 7 and a central axial nose cone 8. The outline support frame 7 is fixed in the S-shaped air guide channel 2 of the aircraft 1 and is used for supporting the whole two-stage adjustable guide vane mechanism 3; the middle axial flow nose cone 8 is positioned on the central axis of the two-stage adjustable guide vane mechanism 3. The outline support frame 7 and the middle axial flow nose cone 8 jointly provide a support structure for the first-stage guide vane adjusting mechanism 5 and the second-stage guide vane adjusting mechanism 6.
In the present embodiment, the first-stage guide vane adjusting mechanism 5 includes a first-stage guide vane group 9, a first link ring 10, a first-stage guide vane link group 11, a first motor 12, and a first transmission gear 13. The first-stage guide vane group 9 is hinged between the outline support frame 7 and the middle axial flow nose cone 8, and the tail end of each guide vane is fixedly connected with the first-stage guide vane connecting rod group 11; the tail end of each connecting rod of the first-stage guide vane connecting rod group 11 is hinged to the first linkage ring 10; the first motor 12 is fixed on the profile supporting frame 7, the first motor 12 can drive the first transmission gear 13, the first transmission gear 13 is meshed with the gear ring part on the first linkage ring 10, and therefore the rotating angle of each guide vane in the first-stage guide vane group 9 can be controlled by controlling the rotating angle of the output shaft of the first motor 12, and the function of adjusting the flow rate and the air pressure of input air flow is further achieved.
In the present embodiment, the two-stage guide vane adjusting mechanism 6 includes a two-stage guide vane set 14, a second link ring 15, a two-stage guide vane link set 16, a second motor 17, and a second transmission gear 18. The secondary guide vane group 14 is hinged between the outline support frame 7 and the middle axial flow nose cone 8, and the tail end of each guide vane is fixedly connected with the secondary guide vane connecting rod group 16; the tail end of each connecting rod of the two-stage guide vane connecting rod group 16 is hinged on the second linkage ring 15; the second motor 17 is fixed on the profile supporting frame 7, the second motor 17 can drive the second transmission gear 18, the second transmission gear 18 is meshed with the gear ring part on the second linkage ring 15, so that the rotation angle of each guide vane in the secondary guide vane group 14 can be controlled by controlling the rotation angle of the output shaft of the second motor 17, and the function of adjusting the flow rate angle of the input air is further realized. By simultaneously controlling the opening and closing angles of the guide vanes in the first-stage guide vane adjusting mechanism 5 and the second-stage guide vane adjusting mechanism 6, the additional flow resistance loss of the input air flow can be reduced, the pneumatic efficiency is improved, and the accurate control of the input air flow on the system power is realized.
A second embodiment of the present invention provides a method for controlling two-stage adjustable guide vanes of an S-bend air guide duct of an aircraft, as shown in fig. 6, including the following steps:
first, the desired input power W to the airflow from the airflow utilization section r As an input to the control system, the control system will control W r Actual input power W to the gas flow a Comparing to obtain a difference value delta W;
the difference value delta W, the airflow input flow P and the airflow input pressure Q act on the controller C together 1 (both P and Q are measured by sensors in the aircraft), controller C 1 The solved first motor rotation angle variation delta theta 1 Sent to the first motor M 1 Thereby controlling M 1 Outputting the current angle theta 1 。
Similar to the process described above, Δ W, P, Q and θ 1 Acting together on the controller C 2 Controller C 2 The solved second motor rotation angle variation delta theta 2 Sent to the second motor M 2 Thereby controlling M 2 Outputting the current angle theta 2 。
Due to M 1 And M 2 Also corresponds to the rotation angle of each blade in the first-stage guide vane group 9 and the second-stage guide vane group 14, so P, Q, θ 1 And theta 2 After the equal parameters jointly act on a mathematical model S of the two-stage adjustable guide vane mechanism, the actual input power W of the air flow can be obtained a . And then continuously carrying out real-time iteration through a negative feedback process, and finally realizing the accurate control of the input airflow on the system power.
In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A two-stage adjustable guide vane of an S-bend air guide duct of an aircraft, comprising:
the supporting mechanism is connected to an S-shaped air guide channel of the aircraft;
the first-stage guide vane adjusting mechanism is connected to the supporting mechanism and at least comprises a first-stage guide vane group and a first-stage driving structure, and the first-stage driving structure drives the blade corner of the first-stage guide vane group so as to adjust the flow rate and the air pressure of an input airflow;
and the second-stage guide vane adjusting mechanism is connected to the supporting mechanism and is positioned on one side of the first-stage guide vane adjusting mechanism, wherein the second-stage guide vane adjusting mechanism at least comprises a second-stage guide vane group and a second-stage driving structure, and the second-stage driving structure drives the blade corner of the second-stage guide vane group to adjust the speed angle of the input airflow.
2. The two-stage adjustable vane of an aircraft S-bend air duct of claim 1, said one-stage vane adjustment mechanism further comprising:
the first linkage ring is arranged along the radial direction of the first linkage ring, and one end of the first guide vane group and at least part of the supporting mechanism form a hinged structure;
the other end of the first guide vane connecting rod group is connected with the first guide vane connecting rod group, and the end part of the first guide vane connecting rod group and the first linkage ring form a hinge structure;
the first-stage driving structure is meshed with the first linkage ring to drive the first linkage ring to radially rotate so as to drive the first-stage guide vane connecting rod group to drive the blades of the first-stage guide vane group to swing.
3. The two-stage adjustable guide vane of an aircraft S-bend air guide duct of claim 2, wherein at least a portion of the first linkage ring is formed with a first spur gear, the drive end of the primary drive structure is connected with a first transmission gear, and the first transmission gear is in meshed connection with the first spur gear.
4. The two-stage adjustable guide vane of an aircraft S-bend air guide way according to claim 3, wherein the primary drive structure is a first motor, and a drive end of the first motor is connected with the first transmission gear to drive the first transmission gear to rotate.
5. The two-stage adjustable vane of an aircraft S-bend air duct of claim 4, said two-stage vane adjustment mechanism further comprising:
the secondary guide vane set is arranged along the radial direction of the second linkage ring, and one end of the secondary guide vane set and at least part of the supporting mechanism form a hinge structure;
the other end of the second guide vane connecting rod group is connected with the second guide vane connecting rod group, and the end part of the second guide vane connecting rod group and the second linkage ring form a hinge structure;
and the second-stage driving structure and the second linkage ring form meshing connection so as to drive the second linkage ring to radially rotate and drive the second-stage guide vane connecting rod group to drive the blades of the second-stage guide vane group to swing.
6. The two-stage adjustable guide vane of an aircraft S-bend air duct of claim 5, wherein at least a portion of the second link ring is formed with a second male tooth portion, and a drive end of the secondary drive structure is connected with a second drive gear, and the second drive gear is in meshed connection with the second male tooth portion.
7. The two-stage adjustable guide vane of an aircraft S-bend air bleed duct of claim 6 wherein the secondary drive structure is a second motor, the drive end of the second motor being connected to the second drive gear to drive the second drive gear to rotate.
8. The two-stage adjustable vane of an aircraft S-bend air duct of claim 7, said support mechanism comprising:
the shape of the outer contour support frame is matched with that of the aircraft S-shaped air guide channel, and the outer contour support frame is fixed in the aircraft S-shaped air guide channel;
and the middle axial flow nose cone is arranged on the central axis of the outline support frame, wherein one ends of the blades of the first-stage guide blade group and the second-stage guide blade group form a hinged structure with the middle axial flow nose cone.
9. Method for controlling two-stage adjustable guide vanes of an aircraft S-bend air duct according to any of claims 1 to 8, characterized in that it comprises the following steps:
desired input power W to the airflow from the airflow utilization section r As input quantity of the control system;
control system pair W r Actual input power W to the gas flow a Comparing to obtain a difference value delta W;
the difference value delta W, the airflow input flow P and the airflow input pressure Q jointly act on the controller C 1 Controller C 1 The solved first motor rotation angle variation delta theta 1 Sent to the first motor M 1 Thereby controlling M 1 Outputting the current angle theta 1 ；
Difference Δ W, airflow input flow P, airflow inputPressure Q and first motor rotation angle variation theta 1 Acting together on the controller C 2 Controller C 2 The solved second motor rotation angle variation delta theta 2 Sent to the second motor M 2 Thereby controlling M 2 Outputting the current angle theta 2 ；
Airflow input flow P, airflow input pressure Q and first motor rotation angle variation theta 1 And the current angle theta 2 After the parameters jointly act on the mathematical model S of the two-stage adjustable guide vane mechanism, the actual input power W of the airflow can be obtained a (ii) a And then continuously carrying out real-time iteration through a negative feedback process, and finally realizing the accurate control of the input airflow on the system power.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211375030.1A CN115535266A (en) | 2022-11-04 | 2022-11-04 | Two-stage adjustable guide vane of S-shaped guide duct of aircraft and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211375030.1A CN115535266A (en) | 2022-11-04 | 2022-11-04 | Two-stage adjustable guide vane of S-shaped guide duct of aircraft and control method thereof |
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| CN115535266A true CN115535266A (en) | 2022-12-30 |
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| CN202211375030.1A Pending CN115535266A (en) | 2022-11-04 | 2022-11-04 | Two-stage adjustable guide vane of S-shaped guide duct of aircraft and control method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117662524A (en) * | 2024-01-29 | 2024-03-08 | 诺顿风机(潍坊)有限公司 | Movable vane adjustable axial flow fan with movable guide vane |
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2022
- 2022-11-04 CN CN202211375030.1A patent/CN115535266A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117662524A (en) * | 2024-01-29 | 2024-03-08 | 诺顿风机(潍坊)有限公司 | Movable vane adjustable axial flow fan with movable guide vane |
| CN117662524B (en) * | 2024-01-29 | 2024-04-23 | 诺顿风机(潍坊)有限公司 | Movable vane adjustable axial flow fan with movable guide vane |
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