CN114776468A - Double-ring control mechanism for axisymmetric convergent-divergent nozzle - Google Patents
Double-ring control mechanism for axisymmetric convergent-divergent nozzle Download PDFInfo
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- CN114776468A CN114776468A CN202210395146.5A CN202210395146A CN114776468A CN 114776468 A CN114776468 A CN 114776468A CN 202210395146 A CN202210395146 A CN 202210395146A CN 114776468 A CN114776468 A CN 114776468A
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- 230000007246 mechanism Effects 0.000 title claims abstract description 29
- 239000007921 spray Substances 0.000 claims abstract description 17
- 238000007789 sealing Methods 0.000 claims description 17
- 230000008901 benefit Effects 0.000 description 4
- 230000033001 locomotion Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 230000001360 synchronised effect Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000003416 augmentation Effects 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
- 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)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Abstract
The application belongs to the field of aviation gas turbines, and particularly relates to a double-ring control mechanism of an axisymmetric converging-diverging nozzle, wherein a plurality of actuating cylinders are circumferentially arranged on the outer side of the double-ring control mechanism, and actuating shafts of the actuating cylinders are hinged with a same adjusting ring; the rear end of the cylinder body is hinged with convergence adjusting sheets which are distributed circumferentially, and the rear end of each convergence adjusting sheet is hinged with an expansion adjusting sheet; the convergent flap is articulated with the adjustable ring through the convergent pull rod, and a plurality of fixed pull rods are articulated to the outside circumference of barrel, and fixed pull rod articulates same support ring, and the rear end of expansion flap articulates through the vice outer adjustment piece that articulates of cylinder, and the outer adjustment piece other end is articulated with the support ring, and the expansion flap is articulated with the support ring through the expansion pull rod, and the synchro control of spray tube can be realized to this application to simple structure saves space.
Description
Technical Field
The application belongs to the field of aviation gas turbines, and particularly relates to a double-ring control mechanism for an axisymmetric converging-diverging spray pipe.
Background
The axial symmetry contraction and expansion spray pipe has good thrust characteristics, the spray pipe still belongs to the most applied spray pipe type at present, the inner flow surface of the spray pipe is a convergence-expansion surface, the movable adjusting sheet and the sealing sheet are mutually overlapped to form an inner flow channel of the spray pipe, and the actuating system changes the opening degree of the convergence section adjusting sheet/sealing sheet and the expansion section adjusting sheet/sealing sheet through the adjusting mechanism so as to adjust the throat area and the outlet area. There are many schemes for actuating system and adjusting mechanism of the adjustable axisymmetric convergent-divergent nozzle, and the selection of the scheme depends on the requirements of the airplane and engine on the performance parameters of the nozzle, the limitation of maximum outline dimension, the traditional mature design method, the maturity of the actuating system accessories, and the like, and can be basically divided into two categories: one type is double-ring adjustment, namely the spray pipe is provided with 2 sets of actuating systems to respectively adjust the area of a throat and the area of an outlet; the other type is single-ring regulation, namely the regulation of the throat area and the outlet area shares one set of actuating system. The single-ring regulation scheme has only 1 set of actuating system in the jet pipe, and is mainly used for regulating the throat area of the jet pipe, and the outlet area is generally determined by mechanical positioning or combination of mechanical positioning and pneumatic positioning. The mechanical positioning of the exit area is realized by 1 set of following mechanism, which is a four-bar mechanism consisting of an expansion section, a convergence section and a pull rod, and the exit area is correspondingly changed while the throat area is adjusted. The linkage must be optimized in the design to take into account all flight conditions and maintain high thrust characteristics in the prevailing conditions. The advantage of this mode is that the structure and regulation are simple, and weight is lighter.
Actuating systems of axisymmetric spray pipes are usually placed on a force application cylinder body, and the actuating systems are uniformly arranged on the cylinder body in the circumferential direction and occupy a longer axial space of the cylinder body; the conventional stressing cylinder is long in axial length and has a relatively abundant space for arranging a nozzle actuating system. However, as the functions of the engine are more and more complex, the adjustable structures are more and more, and other flow passage area adjusting mechanisms also need to be arranged on the force application cylinder body, so that a more concise axisymmetric spray pipe control mechanism is urgently needed to be provided to meet new requirements; meanwhile, with the continuous requirement of light weight of an aircraft engine, the requirement of a nozzle control mechanism scheme with a simple structure and light weight is more urgent, and meanwhile, the traditional actuator cylinder and the adjusting sheet are connected to cause the condition that the traditional actuator cylinder cannot be synchronous, or the condition that the adjusting sheet cannot act individually due to the failure of the actuator cylinder can influence the normal flight of the aircraft.
Disclosure of Invention
In order to solve the above problem, the present application provides an axisymmetric convergent-divergent nozzle double-ring control mechanism, including: the actuating shafts of the actuating cylinders are hinged with the same adjusting ring; the rear end of the cylinder body is hinged with convergence adjusting sheets which are distributed circumferentially, and the rear end of each convergence adjusting sheet is hinged with an expansion adjusting sheet; the convergence adjusting sheet is hinged with the adjusting ring through a convergence pull rod.
The outer side of the barrel is circumferentially hinged with a plurality of fixed pull rods, the fixed pull rods are hinged with the same support ring, the rear end of the expansion adjusting sheet is hinged with an outer adjusting sheet through a cylindrical pair, the other end of the outer adjusting sheet is hinged with the support ring, and the expansion adjusting sheet is hinged with the support ring through the expansion pull rods.
Preferably, the adjacent two outer adjusting sheets are arranged in a stacked manner at the edge.
Preferably, the rear ends of the expansion adjustment piece and the outer adjustment piece are serrated.
Preferably, the number of the actuators is 0.1 to 0.5 of the number of the convergence adjusting pieces.
Preferably, the rams are equally spaced circumferentially along the barrel.
Preferably, a convergence section limiter is arranged between each convergence adjusting sheet and the included angle of the convergence pull rod, and the convergence section limiter is in contact with the convergence adjusting sheets and the convergence pull rod after the convergence adjusting sheets and the convergence pull rod reach a preset angle so as to achieve limiting.
Preferably, an expansion section limiter is arranged between each expansion adjusting sheet and the expansion pull rod, and the expansion section limiter is contacted with the expansion adjusting sheets and the expansion pull rod after the expansion adjusting sheets and the expansion pull rod reach a preset angle so as to realize limiting.
Preferably, the edges of two adjacent converging flaps and two adjacent diverging flaps are stacked on top of each other.
Preferably, sealing sheets are arranged at the edge stacking positions of two adjacent convergence adjusting sheets and two adjacent expansion adjusting sheets.
Preferably, the fixed pull rod is hinged along the radial direction of the cylinder body, and has a degree of freedom of rotation along the radial direction of the cylinder body.
The advantages of the present application include:
the support ring is connected in a mode of installing a plurality of fixing pull rods in the circumferential direction, and the fixing pull rods have freedom degree of rotating along the radial direction of the barrel, so that the support ring can form a fixing annular support, the thrust force borne by the support ring can be changed into the compression stress of the fixing pull rods, and the damage caused by the shear stress can be reduced; meanwhile, when the support ring is subjected to tensile stress from the pull rod, the tensile stress can form compressive stress inside the support ring through the support ring;
the actuating cylinders are uniformly arranged in the circumferential direction, a plurality of acting forces are linked into a uniform and synchronous force through the adjusting ring, the condition that the individual adjusting sheets cannot operate according to normal conditions under the condition of an accident of the actuating cylinders can be avoided, in the practical process, the adjusting sheets generate different adjusting sheets due to individual differences, the movement effects of the adjusting sheets under the same actuating cylinders are different, the supporting rings can unify the magnitude of the force, and the actuating cylinders can still be normally used when the individual actuating cylinders are clapped. The number of the actuating cylinders is reduced, and the space occupation of a thrust application cylinder body by a jet pipe actuating system is saved; the number of connecting pipelines of the actuating cylinders is reduced, and the assembly performance is improved; simplify the spray tube control mechanism, reduce the part quantity, make the spray tube lighter in weight.
Drawings
FIG. 1 is a schematic view of an axisymmetric convergent-divergent nozzle control mechanism;
FIG. 2 is a schematic view of an axisymmetric convergent-divergent nozzle structure;
FIG. 3 is a schematic view of an axisymmetric convergent-divergent nozzle structure;
wherein, 1-cylinder body; 2-actuator cylinder mounting seat; 3-an actuator cylinder; 4-fixing the pull rod; 5-an adjusting ring; 6-support ring; 7-short pull rod; 8-an adjustable pull rod; 9-convergence regulation tablet; 10-a dilatation modulator blade; 11-an external adjustment tab; 12-convergent sealing patch; 13-expanding the sealing sheet; 14-a convergence section limiter; 15-an expansion section stopper; 16-an expansion segment stop.
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 accompanying 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 implementations that are part of this application and not all implementations. The embodiments described below with reference to the 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.
The axial symmetry contraction and expansion spray pipe control mechanism comprises the following design steps:
determining a structural composition scheme of the axisymmetric converging-diverging spray pipe; as shown in fig. 1 to 3, the axisymmetric convergent-divergent nozzle mainly comprises a cylinder 1, an actuator cylinder mounting base 2, an actuator cylinder 3, a fixed pull rod 4, an adjusting ring 5, a support ring 6, a short pull rod 7, an adjustable pull rod 8, a convergent adjustment sheet 9, an expansive adjustment sheet 10, an external adjustment sheet 11, a convergent sealing sheet 12, an expansive sealing sheet 13, a convergent section limiter 14, an expansive section limiter 15, an expansive section limiter 16 and the like.
The number of the cylinder 1, the adjusting ring 5 and the supporting rings 6 is 1; the actuating cylinder mounting seats 2 and the actuating cylinders 3 are 3 in number and are circumferentially and uniformly arranged; the number of the fixed pull rod 4, the adjustable pull rod 8, the convergence adjusting sheet 9, the expansion adjusting sheet 10, the outer adjusting sheet 11, the convergence sealing sheet 12, the expansion sealing sheet 13, the convergence section limiter 14, the expansion section limiter 15 and the expansion section limiter 16 is 15, and the fixed pull rod, the adjustable pull rod 8, the convergence adjusting sheet 9, the expansion adjusting sheet 10, the outer adjusting sheet, the convergence sealing sheet 13, the expansion sealing sheet, the convergence section limiter 14, the expansion section limiter 15 and the expansion section limiter 16 are uniformly arranged in the circumferential direction; 30 short pull rods 7 are provided; are axially and uniformly arranged.
The supporting ring 6 is connected with the cylinder 1 through a fixed pull rod 4, and the cylinder, the fixed pull rod and the supporting ring form a bearing frame;
the motion principle of the spray pipe control mechanism is as follows: the cylinder body, the adjusting ring, the short pull rod and the convergence adjusting sheet form a 4-link mechanism, the actuating cylinder is a driving element and drives the adjusting ring 5, the adjusting ring 5 drives the short pull rod 7, and the short pull rod drives the convergence adjusting sheet so as to realize the adjustment and control of the throat area of the spray pipe; the convergence adjusting sheet, the expansion adjusting sheet, the adjustable pull rod and the support ring form a 4-link mechanism, and the expansion adjusting sheet moves along with the movement of the convergence adjusting sheet; one end of the outer adjusting piece is hinged with the supporting ring, the other end of the outer adjusting piece is connected with the expansion adjusting piece in a sliding mode, and the outer adjusting piece moves along with the expansion adjusting piece.
Performing sawtooth modification design on outlets of the expansion adjusting sheet and the outer adjusting sheet for improving the stealth performance of the radar; the adjacent two outer adjusting pieces are designed in a superposition way;
a convergence sealing sheet is arranged between two adjacent convergence adjusting sheets, and a limiter on the convergence sealing sheet is hung on the two adjusting sheets to play a role in limiting; an expansion sealing sheet is arranged between two adjacent expansion adjusting sheets, and a limiter on the expansion sealing sheet is hung on the two expansion adjusting sheets to play a role in limiting;
the invention has the advantages that the support ring 6 is connected in a mode of installing a plurality of fixed pull rods 4 in the circumferential direction, the fixed pull rods 4 have the freedom degree of rotating along the radial direction of the cylinder 1, thus the support ring 6 can form a fixed annular support, the thrust force borne by the support ring 6 can be changed into the compressive stress of the fixed pull rods 4, and the damage caused by the shear stress can be reduced; meanwhile, when the support ring 6 is subjected to tensile stress from the tie rod, the tensile stress can form compressive stress inside the support ring 6 by the support ring 6;
through a plurality of actuating cylinders which are uniformly arranged in the circumferential direction, a plurality of acting forces are linked into a uniform and synchronous force through an adjusting ring, the phenomenon that the actuating cylinders cannot operate according to normal conditions due to accident can be avoided, in the actual process, different adjusting pieces generated by the adjusting pieces due to individual differences have different motion effects under the same actuating cylinder, the supporting rings 6 can unify the magnitude of the force, and the actuating cylinders can still be normally used when being clapped.
The scheme is simple in force transmission route, the actuating cylinders directly control the adjusting rings, the adjusting rings drive the convergence adjusting pieces to move, the number of the actuating cylinders is small, and the number of transmission parts is small, so that the thrust augmentation barrel space occupied by a nozzle actuating system is small; the hydraulic pipelines are only connected with three actuating cylinders, so that the number of the hydraulic pipelines is small, and the assembly is simple; this solution is lighter in weight than the conventional multi-ram solution.
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 (10)
1. The utility model provides an axial symmetry receipts expand spray tube dicyclo control mechanism which characterized in that includes:
the cylinder body (1) is provided with a plurality of actuating cylinders (3) in the circumferential direction on the outer side, and actuating shafts of the actuating cylinders (3) are hinged with the same adjusting ring (5); the rear end of the barrel body (1) is hinged with a plurality of convergence adjusting sheets (9) which are distributed circumferentially, and the rear end of each convergence adjusting sheet (9) is hinged with an expansion adjusting sheet (10); the convergence adjusting sheet (9) is hinged with the adjusting ring (5) through a convergence pull rod (7);
the outer side of the barrel body (1) is circumferentially hinged with a plurality of fixed pull rods (4), the fixed pull rods (4) are hinged with the same support ring (6), the rear end of an expansion adjusting sheet (10) is hinged with an outer adjusting sheet (11) through a cylinder pair, the other end of the outer adjusting sheet (11) is hinged with the support ring (6), and the expansion adjusting sheet (10) is hinged with the support ring (6) through an expansion pull rod (8).
2. The double-ring control mechanism of the axisymmetric convergent-divergent nozzle of claim 1, characterized in that the edges between two adjacent outer adjusting pieces (11) are arranged in a stacked manner.
3. The double-ring control mechanism of the axisymmetric convergent-divergent nozzle of claim 1, characterized in that the rear ends of the divergent flap (10) and the outer flap (11) are serrated.
4. The double-ring control mechanism of the axisymmetric convergent-divergent nozzle of claim 1, wherein the number of the actuators (3) is 0.1 to 0.5 of the number of the convergent flaps (9).
5. The double-ring control mechanism of the axisymmetric convergent-divergent nozzle as claimed in claim 1, characterized in that the actuators (3) are arranged at equal intervals in the circumferential direction of the cylinder (1).
6. The double-ring control mechanism of the axisymmetric convergent-divergent nozzle of claim 1, characterized in that a convergent section limiter (14) is provided between each convergent flap (9) and the convergent drawbar (7), and the convergent section limiter (14) contacts with the convergent flap (9) and the convergent drawbar (7) after the convergent flap (9) and the convergent drawbar (7) reach a predetermined angle to realize limiting.
7. The double-ring control mechanism of the axisymmetric convergent-divergent nozzle of claim 1, characterized in that an expansion segment stopper (15) is provided between each expansion adjustment tab (10) and the expansion pull rod (8), and the expansion segment stopper (15) contacts with the expansion adjustment tab (10) and the expansion pull rod (8) after the expansion adjustment tab (10) and the expansion pull rod (8) reach a preset angle to realize the limit.
8. The double-ring control mechanism of the axisymmetric convergent-divergent nozzle of claim 1, characterized in that the edges of two adjacent convergent flaps (9) and two adjacent divergent flaps (10) are overlapped with each other.
9. The double-ring control mechanism of the axisymmetric convergent-divergent nozzle of claim 9, characterized in that the edge of two adjacent convergent flaps (9) and two adjacent divergent flaps (10) are overlapped to form a sealing sheet.
10. The double-ring control mechanism of the axisymmetric convergent-divergent nozzle of claim 1, characterized in that the fixed pull rod (4) is hinged in the radial direction of the cylinder (1) and has a degree of freedom to rotate in the radial direction of the cylinder (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210395146.5A CN114776468A (en) | 2022-04-14 | 2022-04-14 | Double-ring control mechanism for axisymmetric convergent-divergent nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210395146.5A CN114776468A (en) | 2022-04-14 | 2022-04-14 | Double-ring control mechanism for axisymmetric convergent-divergent nozzle |
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| Publication Number | Publication Date |
|---|---|
| CN114776468A true CN114776468A (en) | 2022-07-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210395146.5A Pending CN114776468A (en) | 2022-04-14 | 2022-04-14 | Double-ring control mechanism for axisymmetric convergent-divergent nozzle |
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| CN (1) | CN114776468A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116163853A (en) * | 2023-02-16 | 2023-05-26 | 南京航空航天大学 | Lobe-adjustable spray pipe structure |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4176792A (en) * | 1977-07-11 | 1979-12-04 | General Electric Company | Variable area exhaust nozzle |
| US5176323A (en) * | 1991-04-15 | 1993-01-05 | General Electric Company | Reduced weight nozzle actuation mechanism |
| US6378781B1 (en) * | 1999-05-13 | 2002-04-30 | Industria De Turbo Propulsores S.A. | Exit area control mechanism for convergent divergent nozzles |
| CN1796757A (en) * | 2004-12-31 | 2006-07-05 | 联合工艺公司 | Turbine engine nozzle |
| CN103696873A (en) * | 2013-12-04 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Axisymmetric vectoring nozzle with good stealth function |
| CN112761813A (en) * | 2021-01-15 | 2021-05-07 | 中国航发沈阳发动机研究所 | Jet pipe adjusting mechanism of aircraft engine |
| CN113250854A (en) * | 2021-04-28 | 2021-08-13 | 中国航发沈阳发动机研究所 | Spray pipe structure |
| CN114017198A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳发动机研究所 | Axisymmetric convergent-divergent nozzle |
-
2022
- 2022-04-14 CN CN202210395146.5A patent/CN114776468A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4176792A (en) * | 1977-07-11 | 1979-12-04 | General Electric Company | Variable area exhaust nozzle |
| US5176323A (en) * | 1991-04-15 | 1993-01-05 | General Electric Company | Reduced weight nozzle actuation mechanism |
| US6378781B1 (en) * | 1999-05-13 | 2002-04-30 | Industria De Turbo Propulsores S.A. | Exit area control mechanism for convergent divergent nozzles |
| CN1796757A (en) * | 2004-12-31 | 2006-07-05 | 联合工艺公司 | Turbine engine nozzle |
| CN103696873A (en) * | 2013-12-04 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Axisymmetric vectoring nozzle with good stealth function |
| CN112761813A (en) * | 2021-01-15 | 2021-05-07 | 中国航发沈阳发动机研究所 | Jet pipe adjusting mechanism of aircraft engine |
| CN113250854A (en) * | 2021-04-28 | 2021-08-13 | 中国航发沈阳发动机研究所 | Spray pipe structure |
| CN114017198A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳发动机研究所 | Axisymmetric convergent-divergent nozzle |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116163853A (en) * | 2023-02-16 | 2023-05-26 | 南京航空航天大学 | Lobe-adjustable spray pipe structure |
| CN116163853B (en) * | 2023-02-16 | 2023-08-11 | 南京航空航天大学 | Lobe-adjustable spray pipe structure |
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