CN113530706A - Connecting structure of active adjusting sheet and active adjusting sheet of engine tail nozzle - Google Patents
Connecting structure of active adjusting sheet and active adjusting sheet of engine tail nozzle Download PDFInfo
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- CN113530706A CN113530706A CN202110950533.6A CN202110950533A CN113530706A CN 113530706 A CN113530706 A CN 113530706A CN 202110950533 A CN202110950533 A CN 202110950533A CN 113530706 A CN113530706 A CN 113530706A
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- active
- adjusting sheet
- tab
- sheet
- connecting structure
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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
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/11—Varying effective area of jet pipe or nozzle by means of pivoted eyelids
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a connecting structure of an active adjusting sheet and an active adjusting sheet of an engine tail nozzle, which comprises: an outer adjusting piece with the front end fixed on the aircraft head supporting ring; the active adjusting sheet is connected with the outer adjusting sheet through an active adjusting mechanism and can synchronously do radial retracting movement. When the active adjusting piece is driven by the actuating system to carry out retraction and extension movement in the radial direction, the synchronous retraction and extension movement of the outer adjusting piece along with the active adjusting piece is realized through the active adjusting mechanism, the retraction and extension flexibility is ensured, and the problem that the outer adjusting piece is connected with the active adjusting piece through the synchronizing mechanism to drive the synchronous movement, and the belt jamming or failure is easy to occur is solved.
Description
Technical Field
The invention relates to a connecting structure of an active adjusting sheet and an active adjusting sheet of an engine tail nozzle, and belongs to the technical field of aero-engines.
Background
The simple and reliable mechanism, the high-efficient accurate motion, the light weight high-strength structure has proposed the more and more rigorous requirement to aeroengine tail jet system, especially actuating system and regulating flap and movement mechanism driven by it. For the adjustable spray pipe, as the area of the spray nozzle needs to be adjusted along with the working state of the engine host, the spray nozzle needs to have the retractable movement capability, even other movement capabilities with special requirements. Generally, the axisymmetric adjustable nozzle is formed by matching a plurality of driving and driven adjusting sheets one by one. The outer adjustment piece then wraps other connection structure of adjustment piece external surface, forms the pneumatic profile of comparatively smooth efficient, is favorable to reducing the afterbody resistance of aircraft, reduces the radiant heat of adjustment piece to the aircraft.
The traditional external adjusting sheet is similar to the adjusting sheet and is divided into a driving adjusting sheet and a driven external adjusting sheet according to the mode of connecting with an actuating system and transferring load, and the driving adjusting sheet is connected with the driving adjusting sheet and driven by the driving adjusting sheet to do retraction movement; the driven outer adjusting piece is connected with the driving adjusting piece through the synchronizing mechanism and driven by the driving adjusting piece to move synchronously.
Disclosure of Invention
In order to solve the technical problem, the invention provides a connecting structure of an active adjusting sheet and an active adjusting sheet of an engine tail nozzle.
The invention is realized by the following technical scheme.
The invention provides a connecting structure of an active adjusting sheet and an active adjusting sheet of an engine tail nozzle, which comprises:
an outer adjustment tab having a front end secured to a support ring adjacent the aircraft head;
the active adjusting sheet is connected with the outer adjusting sheet through an active adjusting mechanism and can synchronously do radial retracting movement.
The active adjusting mechanism comprises a support fixedly connected with the inner surface of the outer adjusting sheet;
the mounting seat is fixedly connected with the support;
one end of the pull rod is rotatably hinged to the pull rod on the inner surface of the support, and the other end of the pull rod is rotatably connected with the active adjusting sheet, so that the two ends of the pull rod can rotate around respective hinged connection pivots in a plane formed by the central lines of the outer adjusting sheet and the active adjusting sheet, and the outer adjusting sheet can be ensured to do radial folding and unfolding motion along with the active adjusting sheet;
one end of the support is connected with the end part of the reinforcing rib close to the side of the support ring in a rotatable and movable manner, and the other end of the support is fixedly connected with the inner surface of the support ring.
The pull rod support is rotatably hinged on the inner surface of the support through a hinge formed by a hinge seat and a hinge shaft.
The outer adjusting sheet and the support are fixed in a welding or riveting mode.
The other end of the pull rod is rotatably connected with the active adjusting sheet through a pin shaft.
The support is connected with the end part of the reinforcing rib close to the side of the supporting ring in a rotatable movement mode through a connecting shaft.
When the active adjusting piece is subjected to the retracting movement in the radial direction by the actuating system, the active adjusting mechanism consisting of the reinforcing ribs, the support, the pull rod, the connecting shaft and the support realizes that the outer adjusting piece also performs synchronous retracting movement along with the active adjusting piece, so that the retracting flexibility is ensured, and the problem that the outer adjusting piece is connected with the active adjusting piece through the synchronizing mechanism to realize synchronous movement and is easy to cause belt jamming or failure is solved.
The outer adjusting piece is slender along the axial direction, and only one part of the outer adjusting piece is deflected inwards along the course direction on the left side or the right side of the base plate which is flat or slightly cambered and takes the flight direction of an aircraft as the reference.
The outer adjusting pieces are a plurality of pieces which are arranged along the circumferential direction of the supporting ring in a whole circle along the forward direction,
the deflection part of the outer adjusting piece and the edge tangent line of the original molded surface form an included angle alpha, the included angle is overlapped with another adjacent outer adjusting piece or a small amount of clearance is reserved, and in the overlapped area, the other outer adjusting piece is arranged outside the deflection part; the minimum working state of the engine needs to pass through the width l of the deflection area and the total width l of the outer adjusting sheet0The ratio and the angle alpha ensure that two adjacent outer adjusting pieces can move freely without interference.
The invention has the beneficial effects that: when the active adjusting piece is driven by the actuating system to carry out retraction and extension movement in the radial direction, the synchronous retraction and extension movement of the outer adjusting piece along with the active adjusting piece is realized through the active adjusting mechanism, the retraction and extension flexibility is ensured, and the problem that the outer adjusting piece is connected with the active adjusting piece through the synchronizing mechanism to realize synchronous movement, and a belt is easily clamped or fails is solved.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
FIG. 3 is an enlarged view of a portion of FIG. 1 at B;
FIG. 4 is a schematic view of the maximum state of the nozzle of the present invention;
FIG. 5 is an enlarged schematic view at C of FIG. 4;
FIG. 6 is a schematic view of the minimum state of the nozzle of the present invention;
FIG. 7 is an enlarged schematic view at D of FIG. 6;
in the figure: 1-a support ring; 2-external adjustment sheet; 3-reinforcing ribs; 4-support; 5-a pull rod; 6-a pin shaft; 7-active adjustment sheet; 8-a connecting shaft; 9-bracket.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
As shown in fig. 1-7.
The invention relates to a connecting structure of an active adjusting sheet and an active adjusting sheet of an engine tail nozzle, which comprises:
the front end is fixed on the outer adjusting sheet 2 of the aircraft head supporting ring 1;
a reinforcement 3 fixedly attached to the inner surface of the outer tab 2 by welding or riveting;
a support 4 fixedly connected with the reinforcement 3;
one end of the pull rod 5 is rotatably hinged to a pull rod 5 on the inner surface of the reinforcement 3 through a hinge formed by a hinge seat and a hinge shaft, and the other end of the pull rod 5 is rotatably connected with the active adjusting sheet 7 through a pin shaft 6, so that both ends of the pull rod 5 can rotate around respective hinge connecting fulcrums in a plane formed by the central lines of the outer adjusting sheet 2 and the active adjusting sheet 7, and the outer adjusting sheet 2 can be ensured to do radial retraction movement along with the active adjusting sheet 7;
one end of the bracket 9 is connected with the end part of the reinforcing rib 3 close to the side of the supporting ring 1 in a rotatable way through a connecting shaft 8, and the other end of the bracket 9 is fixedly connected with the inner surface of the supporting ring 1.
When the active adjusting piece 7 is subjected to the retracting movement in the radial direction by the actuating system, the synchronous retracting movement of the outer adjusting piece 2 along with the active adjusting piece 7 is realized through an active adjusting mechanism consisting of the reinforcing rib 3, the support 4, the pull rod 5, the connecting shaft 8 and the support 9, the retracting flexibility is ensured, and the problem that the outer adjusting piece is connected with the active adjusting piece through the synchronizing mechanism to realize the synchronous movement, and the belt jamming or the failure is easy to occur is solved.
The whole outer adjusting piece 2 is slender along the axial direction, only one part is deflected inwards at the left side or the right side (taking the flying direction of an aircraft as the reference and following the course) of the substrate which is flat or slightly in a radian shape, the included angle between the deflected part and the edge tangent line of the original profile is alpha, the deflected part is in lap joint with the adjacent other outer adjusting piece 2 or a small amount of clearance is left, and in the lap joint area, the other outer adjusting piece 2 is outside the deflected part. FIGS. 4-7 illustrate uniform left inward deflection; likewise, the right inward deflection may also be uniform.
The outer adjusting pieces 2 are a plurality of pieces which are arranged along the circumferential direction of the supporting ring 1 in a whole circle along the forward direction, each outer adjusting piece 2 can be provided with the active adjusting mechanism to realize the adjustment of synchronous retracting and releasing movement with the active adjusting piece 7, the maximum state of the nozzle is shown in figures 4 to 5, the minimum state of the nozzle is shown in figures 6 to 7, and the minimum state needs to pass through the width l of a deflection area and the total width l of the outer adjusting pieces0The ratio and the angle alpha ensure that two adjacent outer adjusting pieces 2 can move freely without interference.
Claims (9)
1. The utility model provides a connection structure of initiative adjustment flap and initiative adjustment flap of engine exhaust nozzle which characterized in that includes:
the front end of the outer adjusting piece (2) is fixed on the aircraft supporting ring (1);
the active adjusting sheet (7) is connected with the outer adjusting sheet (2) through an active adjusting mechanism and can synchronously do radial retracting movement.
2. The connecting structure of the active adjusting piece and the active adjusting piece of the engine tail pipe according to claim 1, characterized in that: the active adjusting mechanism comprises a reinforcing rib (3) fixedly connected with the inner surface of the outer adjusting sheet (2);
the support (4) is fixedly connected with the reinforcing rib (3);
one end of the pull rod (5) is rotatably hinged on the inner surface of the support (4), and the other end of the pull rod (5) is rotatably connected with the active adjusting sheet (7), so that both ends of the pull rod (5) can rotate around respective hinged connection pivots in a plane formed by the central lines of the outer adjusting sheet (2) and the active adjusting sheet (7), and the outer adjusting sheet (2) can do radial retractable movement along with the active adjusting sheet (7);
one end of the support is connected with the end part of the reinforcing rib (3) close to the side of the support ring (1) in a rotatable movement way to form a support (9), and the other end of the support (9) is fixedly connected with the inner surface of the support ring (1).
3. The connecting structure of the active regulator tab and the active regulator tab of the engine nozzle according to claim 2, wherein: the pull rod (5) and the reinforcing rib (3) are rotatably hinged on the inner surface of the reinforcing rib (3) through a hinge formed by the hinge seat and the hinge shaft.
4. The connecting structure of the active regulator tab and the active regulator tab of the engine nozzle according to claim 2, wherein: the outer adjusting sheet (2) and the reinforcing ribs (3) are fixed in a welding or riveting mode.
5. The connecting structure of the active regulator tab and the active regulator tab of the engine nozzle according to claim 2, wherein: the other end of the pull rod (5) is rotatably connected with the active adjusting sheet (7) through a pin shaft (6).
6. The connecting structure of the active regulator tab and the active regulator tab of the engine nozzle according to claim 2, wherein: the bracket (9) is connected with the end part of the reinforcing rib (3) close to the side of the supporting ring (1) in a rotatable movement way through a connecting shaft (8).
7. The connecting structure of the active regulator tab and the active regulator tab of the engine nozzle according to claim 2, wherein: the outer adjusting piece (2) is slender along the axial direction, and only one part of the outer adjusting piece is deflected inwards along the course direction on the left side or the right side of the base plate which is flat or slightly cambered and takes the flight direction of an aircraft as the reference.
8. The connecting structure of the active regulator tab and the active regulator tab of the engine nozzle according to claim 7, wherein: the outer adjusting pieces (2) are a plurality of pieces which are arranged along the circumferential direction of the supporting ring (1) in a whole circle along the forward direction.
9. The connecting structure of the active regulator tab and the active regulator tab of the engine nozzle according to claim 8, wherein: the deflection part of the outer adjusting sheet (2) forms an included angle alpha with the tangent line of the edge of the original molded surface, and is overlapped with another adjacent outer adjusting sheet (2) or a small amount of clearance is left in the overlapping area; the other external adjusting sheet (2) is arranged outside the deflection part; the minimum state needs to pass through the width l of the deflection area and the total width l of the outer adjusting sheet0The ratio and the angle alpha ensure that two adjacent outer adjusting pieces (2) can move freely without interference.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110950533.6A CN113530706B (en) | 2021-08-18 | 2021-08-18 | Connecting structure of outer adjusting piece and active adjusting piece of engine tail nozzle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110950533.6A CN113530706B (en) | 2021-08-18 | 2021-08-18 | Connecting structure of outer adjusting piece and active adjusting piece of engine tail nozzle |
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| CN113530706A true CN113530706A (en) | 2021-10-22 |
| CN113530706B CN113530706B (en) | 2022-08-05 |
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| CN202110950533.6A Active CN113530706B (en) | 2021-08-18 | 2021-08-18 | Connecting structure of outer adjusting piece and active adjusting piece of engine tail nozzle |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113464976A (en) * | 2021-05-12 | 2021-10-01 | 深圳市万泽航空科技有限责任公司 | Flame stabilizer and manufacturing method thereof |
| CN114352434A (en) * | 2022-01-27 | 2022-04-15 | 北京盈天航空动力科技有限公司 | Adjustable tail spray pipe structure of micro turbojet engine |
| CN114776467A (en) * | 2022-04-14 | 2022-07-22 | 中国航发沈阳发动机研究所 | Single-ring control mechanism for axisymmetric convergent-divergent nozzle |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113464976A (en) * | 2021-05-12 | 2021-10-01 | 深圳市万泽航空科技有限责任公司 | Flame stabilizer and manufacturing method thereof |
| CN113464976B (en) * | 2021-05-12 | 2022-08-05 | 深圳市万泽航空科技有限责任公司 | Flame stabilizer and manufacturing method thereof |
| CN114352434A (en) * | 2022-01-27 | 2022-04-15 | 北京盈天航空动力科技有限公司 | Adjustable tail spray pipe structure of micro turbojet engine |
| CN114352434B (en) * | 2022-01-27 | 2023-01-17 | 北京盈天航空动力科技有限公司 | Adjustable tail spray pipe structure of micro turbojet engine |
| CN114776467A (en) * | 2022-04-14 | 2022-07-22 | 中国航发沈阳发动机研究所 | Single-ring control mechanism for axisymmetric convergent-divergent nozzle |
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| CN113530706B (en) | 2022-08-05 |
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