CN114776469A - Axisymmetric spray tube - Google Patents
Axisymmetric spray tube Download PDFInfo
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- CN114776469A CN114776469A CN202210395158.8A CN202210395158A CN114776469A CN 114776469 A CN114776469 A CN 114776469A CN 202210395158 A CN202210395158 A CN 202210395158A CN 114776469 A CN114776469 A CN 114776469A
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- expansion
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- convergence
- adjustment piece
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- 239000007921 spray Substances 0.000 title abstract description 17
- 238000007789 sealing Methods 0.000 claims description 15
- 230000007246 mechanism Effects 0.000 description 14
- 230000033001 locomotion Effects 0.000 description 7
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000001360 synchronised effect Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000008602 contraction Effects 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
-
- 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 an axisymmetric nozzle, wherein a plurality of actuating cylinders are circumferentially arranged on the outer side of the axisymmetric nozzle, 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 convergence adjustment piece is articulated with the adjustable ring through the convergence pull rod, and the articulated a plurality of fixed pull rods of outside circumference of barrel, fixed pull rod articulate same support ring, and the rear end of expansion adjustment piece articulates through the cylinder pair has outer adjustment piece, and the outer adjustment piece other end is articulated with the support ring, and the expansion adjustment piece 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 combustion engines, and particularly relates to an axisymmetric nozzle.
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 adjustable axisymmetric convergent-divergent nozzle, and the selection of the scheme depends on the requirement of airplane and engine on the performance parameters of the nozzle, the limitation of maximum dimension, traditional mature design method, mature degree of actuating system accessories, etc., 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 share 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 to maintain high thrust characteristics in the primary conditions. The advantage of this mode is that the structure and regulation are simple, and weight is lighter.
The actuating systems of the axisymmetric spray pipes are usually arranged on the force application cylinder body, and are uniformly arranged on the cylinder body in the circumferential direction, so that a longer axial space of the cylinder body is occupied; 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 and the adjustable structures are more and more, other flow passage area adjusting mechanisms need to be arranged on the force application cylinder, so that a simpler control mechanism of the axisymmetric nozzle is urgently needed to adapt to 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 problems, the application provides an axial symmetry spray pipe, which comprises a cylinder body, a plurality of actuating cylinders and a plurality of adjusting rings, wherein the actuating cylinders are circumferentially arranged on the outer side of the cylinder body; 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 expansion adjusting piece is hinged with the adjusting ring through an expansion pull rod, the convergence adjusting piece is hinged with the adjusting ring through a convergence pull rod, a rocker arm and a short pull rod which are sequentially hinged, the rocker arm is hinged with the barrel through a support, the rear end of the expansion adjusting piece is hinged with an outer adjusting piece through a cylinder pair, a plurality of fixing pull rods are hinged to the outer side of the barrel in the circumferential direction, the fixing pull rods are hinged with the same support ring, the rear end of the expansion adjusting piece is hinged with an outer adjusting piece through a cylinder pair, and the other end of the outer adjusting piece is hinged with the support ring.
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 piece and the included angle of the convergence pull rod, and the convergence section limiter is in contact with the convergence adjusting piece and the convergence pull rod after the convergence adjusting piece and the convergence pull rod reach a preset angle so as to realize limiting.
Preferably, an expansion section limiter is arranged between each expansion adjusting sheet and each expansion pull rod, and the expansion section limiter is in contact with the expansion adjusting sheets and the expansion pull rods after the expansion adjusting sheets and the expansion pull rods 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.
The advantages of the present application include: 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 spray tube control mechanism, reduce part quantity, make spray tube weight lighter.
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 cylinder body, so that the support ring can form a fixed 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 tie rod, the tensile stress can form compressive stress inside the support ring by the support ring.
The adjustable pull rod is hinged with the adjusting ring, relative motion between the expansion adjusting piece and the outer adjusting piece is carried out through the cylindrical pair, the convergence pull rod, the expansion pull rod, the convergence adjusting piece and the expansion adjusting piece form a plane four-bar mechanism, the plane four-bar mechanism can more effectively output torque and control the rod length relation and the motion relation of the adjusting piece, meanwhile, the adjusting ring is hinged with the rocker arm, the rocker arm is hinged with the short pull rod, the short pull rod is hinged with the convergence adjusting piece, the rocker arm is hinged with the barrel to bear the formation of transverse force in the motion process, and the thrust of the actuating cylinder is converted into force perpendicular to the convergence adjusting piece, so that the size of a pressure angle is greatly reduced, and the stress efficiency of the convergence adjusting piece is improved.
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 configuration;
FIG. 4 is a schematic view of an axisymmetric convergent-divergent nozzle configuration;
wherein, 1-cylinder body; 2-actuator cylinder mounting seat; 3-an actuator cylinder; 4-an adjusting ring; 5-a support; 6-rocker arm; 7-short pull rod; 8-a convergent pull rod; 9-expanding the pull rod; 10-convergence adjustment sheet; 11-a dilatation modulator blade; 12-an external adjustment sheet; 13-converging sealing sheet; 14-expanding the sealing sheet; 15-a convergent section limiter; 16-an expansion segment stop; 17-an expansion segment stop; 18-a support ring; 19-fixing the pull rod; a-the hinge point of the outer adjusting piece; b-expanding a hinge point of the pull rod; c-short pull rod hinge point.
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 some, but not all embodiments of the present application. 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.
As shown in fig. 1 to 4, an axisymmetric convergent-divergent nozzle control mechanism is characterized in that the design is implemented by the following steps:
determining a structural composition scheme of the axisymmetric convergent-divergent nozzle; the axisymmetric convergent-divergent nozzle mainly comprises a barrel 1, an actuating cylinder mounting seat 2, an actuating cylinder 3, an adjusting ring 4, a bracket 5, a rocker arm 6, a short pull rod 7, a convergent pull rod 8, an expansion pull rod 9, a convergent adjusting sheet 10, an expansion adjusting sheet 11, an external adjusting sheet 12, a convergent sealing sheet 13, an expansion sealing sheet 14, a convergent section limiter 15, an expansion section limiter 16, an expansion section limiter 17, a support ring 18, a fixed pull rod 19 and the like.
The number of the cylinder 1, the adjusting ring 4 and the supporting ring 18 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 brackets 5, the rocker arms 6, the short pull rods 7, the expansion pull rods 9, the convergence adjusting sheets 10, the expansion adjusting sheets 11, the outer adjusting sheets 12, the convergence sealing sheets 13, the expansion sealing sheets 14, the convergence section limiter 15, the expansion section limiter 16, the expansion section limiter 17 and the fixed pull rods 19 is 15, and the brackets are circumferentially and uniformly arranged; 30 convergent pull rods 8 are provided;
the motion principle of the spray pipe control mechanism is as follows: the actuator cylinder drives an adjusting ring, the adjusting ring drives a short pull rod, the short pull rod drives a rocker arm, the rocker arm drives a convergence pull rod, and the convergence pull rod drives a convergence adjusting piece to move, so that the adjustment control of the throat area of the spray pipe is realized; the adjusting ring drives the expansion pull rod, and the expansion pull rod drives the expansion adjusting sheet, so that the adjustment of the outlet area is realized; one end of the outer adjusting piece is connected with the expansion adjusting piece in a sliding mode, the other end of the outer adjusting piece is hinged with the supporting ring, 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 overlapped;
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 limiting stopper on the expansion sealing sheet is hung on the two expansion adjusting sheets to play a limiting role;
the rocker arm is fixed through the bracket, the same rocker arm is connected with the two convergence pull rods, and the two convergence pull rods are respectively connected with the adjacent convergence adjusting sheets;
the load of the outer adjusting piece can be effectively transmitted to the cylinder body through the support ring, so that the load of the adjusting ring is only acted by the load of the inner flow path, the load borne by the actuating cylinder is single, and the control reliability of the actuating cylinder can be effectively improved.
The support ring only serves as the supporting function of one end of the outer adjusting piece, so that the support ring is only under the action of an external load, the design of the support ring is only under the action of the external load, the structural design variable is reduced, and the design difficulty is reduced.
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 situation that the actuating cylinders are unexpected and individual adjusting pieces cannot operate according to normal conditions can be avoided, in the actual process, the adjusting pieces generate different adjusting pieces due to individual differences, the moving effects of the adjusting pieces under the same actuating cylinders are different, the supporting rings can unify the force, and the actuating cylinders can still be normally used when the individual actuating cylinders clap. The number of the actuating cylinders is reduced, and the occupation of a nozzle actuating system on the space of a force application cylinder is saved; the number of connecting pipelines of the actuating cylinders is reduced, and the assembly performance is improved; simplify spray tube control mechanism, reduce part quantity, make spray tube weight lighter.
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 tie rod, the tensile stress can form compressive stress inside the support ring by the support ring.
The adjustable pull rod is hinged with the adjusting ring, relative motion between the expansion adjusting sheet and the outer adjusting sheet is carried out through the cylindrical pair, meanwhile, the adjusting ring is hinged with the rocker arm, the rocker arm is hinged with the short pull rod, the short pull rod is hinged with the convergence adjusting sheet, the rocker arm bears transverse force in the motion process through being hinged with the cylinder body to form, thrust of the actuating cylinder is converted into force perpendicular to the convergence adjusting sheet, the size of a pressure angle is greatly reduced, and the stress efficiency of the convergence adjusting sheet is improved.
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. An axisymmetric nozzle, comprising:
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 (4); the rear end of the barrel body (1) is hinged with a plurality of convergence adjusting sheets (10) which are distributed circumferentially, and the rear end of each convergence adjusting sheet (10) is hinged with an expansion adjusting sheet (11); expansion adjustment piece (11) are articulated with adjusting ring (4) through expansion pull rod (9), convergence adjustment piece (10) are articulated with adjusting ring (4) through successively articulated convergence pull rod (8), rocker arm (6) and short pull rod (7), rocker arm (6) are also articulated with barrel (1) through support (5), the rear end of expansion adjustment piece (11) is articulated with outer adjustment piece (12) through the cylinder pair, the outside circumference of barrel (1) is articulated with a plurality of fixed pull rods (19), fixed pull rod (19) is articulated with same support ring (18), the rear end of expansion adjustment piece (11) is articulated with outer adjustment piece (12) through the cylinder pair, the other end of outer adjustment piece (12) is articulated with support ring (18).
2. Axisymmetric nozzle according to claim 1, characterized in that adjacent two outer adjustment tabs (12) are arranged one above the other at their edges.
3. The axisymmetric nozzle of claim 1, characterized in that the rear ends of the expansion adjustment piece (11) and the outer adjustment piece (12) are serrated.
4. An axisymmetric nozzle according to claim 1, characterized in that the number of actuators (3) is 0.1-0.5 of the number of convergent flaps (10).
5. An axisymmetric nozzle according to claim 1, characterized in that the actuators (3) are equally spaced circumferentially along the barrel (1).
6. An axisymmetric nozzle according to claim 1, characterized in that a convergent section limiter (14) is provided between each convergent flap (10) and the convergent drawbar (8), the convergent section limiter (14) being in contact with the convergent flap (10) and the convergent drawbar (8) after the convergent flap (10) and the convergent drawbar (8) have reached a predetermined angle, thereby achieving the limiting.
7. Axisymmetric nozzle of claim 1, characterized in that an expansion segment stopper (15) is provided between each expansion adjustment tab (11) and the expansion link (9), the expansion segment stopper (15) being brought into contact with the expansion adjustment tab (11) and the expansion link (9) after a predetermined angle is reached, thereby achieving the stopper.
8. An axisymmetric nozzle according to claim 1, characterized in that edges of two adjacent converging flaps (10) and two adjacent diverging flaps (11) are stacked on each other.
9. The axisymmetric nozzle of claim 8, characterized in that sealing strips are provided at the edge stacks of two adjacent convergent flaps (10) and two adjacent divergent flaps (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210395158.8A CN114776469A (en) | 2022-04-14 | 2022-04-14 | Axisymmetric spray tube |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210395158.8A CN114776469A (en) | 2022-04-14 | 2022-04-14 | Axisymmetric spray tube |
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| CN114776469A true CN114776469A (en) | 2022-07-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210395158.8A Pending CN114776469A (en) | 2022-04-14 | 2022-04-14 | Axisymmetric spray tube |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS52140200A (en) * | 1976-03-17 | 1977-11-22 | Rolls Royce | Variable area nozzle for gas turbine engine |
| US6067793A (en) * | 1996-12-26 | 2000-05-30 | Sener, Ingenieria Y Sistemas, S.A. | Variable geometry axisymmetric nozzle with 2-d thrust vectoring intended for a gas turbine engine |
| 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 CN202210395158.8A patent/CN114776469A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS52140200A (en) * | 1976-03-17 | 1977-11-22 | Rolls Royce | Variable area nozzle for gas turbine engine |
| US6067793A (en) * | 1996-12-26 | 2000-05-30 | Sener, Ingenieria Y Sistemas, S.A. | Variable geometry axisymmetric nozzle with 2-d thrust vectoring intended for a gas turbine engine |
| 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 |
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