CN114687886A - Axisymmetric convergent-divergent nozzle - Google Patents
Axisymmetric convergent-divergent nozzle Download PDFInfo
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- CN114687886A CN114687886A CN202210393713.3A CN202210393713A CN114687886A CN 114687886 A CN114687886 A CN 114687886A CN 202210393713 A CN202210393713 A CN 202210393713A CN 114687886 A CN114687886 A CN 114687886A
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- convergent
- expansion
- adjusting
- hinged
- pull rod
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- 238000007789 sealing Methods 0.000 claims description 17
- 239000007921 spray Substances 0.000 abstract description 18
- 230000007246 mechanism Effects 0.000 description 18
- 230000033001 locomotion Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 230000004323 axial length Effects 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
- 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)
- Catching Or Destruction (AREA)
Abstract
The application belongs to the field of aviation gas turbines, and particularly relates to an axisymmetric convergent-divergent nozzle, wherein a plurality of actuating cylinders are circumferentially arranged on the outer side of the axisymmetric convergent-divergent nozzle, and 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 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 gas turbines, and particularly relates to an axisymmetric convergent-divergent 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 shares one set of actuating system. The single-ring adjusting scheme has only 1 set of actuating system of the spray pipe, is mainly used for adjusting the throat area of the spray pipe, and the outlet area is generally determined by mechanical positioning or a mode of combining the 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 advantages of this approach are simple structure and adjustment, light weight,
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 lightening of the aircraft engine, the requirement of a spray pipe control mechanism scheme with a simple structure and lighter weight is more urgent.
Disclosure of Invention
In order to solve the above problem, the present application provides an axisymmetric convergent-divergent nozzle, 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 expansion adjusting sheet is hinged with the adjusting ring through an expansion pull rod, and the convergence adjusting sheet is hinged with the adjusting ring through a convergence pull rod.
Preferably, a plurality of fixed pull rods are hinged to the outer side of the barrel in the circumferential direction, the fixed pull rods are hinged to the same support ring, the rear end of the expansion adjusting piece is hinged to an outer adjusting piece through a cylindrical pair, and the other end of the outer adjusting piece is hinged to 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 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 pieces are provided at the edge stacking positions of two adjacent convergence adjusting pieces and two adjacent expansion adjusting pieces
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 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 outer adjusting piece, the expansion pull rod and an output shaft of the actuating cylinder form a plane four-bar mechanism, the convergence pull rod, the expansion pull rod, the convergence adjusting piece and the expansion adjusting piece form a second plane four-bar mechanism, and the biplane four-bar mechanism can more effectively output torque and control the rod length relation and the motion relation of the adjusting piece.
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.
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;
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-a convergent pull rod; 8-expanding the 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 segment stop; 16-an expansion segment stop; a-expanding a hinge point of the pull rod; b-a converging pull rod hinge point; c-the hinge point of the outer adjusting piece.
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 3, determining a structural composition scheme of an axisymmetric convergent-divergent nozzle; the axisymmetric convergent-divergent nozzle mainly comprises a cylinder body 1, an actuating cylinder mounting seat 2, an actuating cylinder 3, a fixed pull rod 4, an adjusting ring 5, a support ring 6, a convergent pull rod 7, an expansion pull rod 8, a convergent adjusting sheet 9, an expansion adjusting sheet 10, an external adjusting sheet 11, a convergent sealing sheet 12, an expansion sealing sheet 13, a convergent section limiter 14, an expansion section limiter 15, an expansion section limiter 16 and the like.
The number of the cylinder body 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 uniformly arranged in the circumferential direction; the number of the fixed pull rod 4, the expansion 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 expansion 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 convergent pull rods 7 are provided; are axially and uniformly arranged.
The supporting ring is connected with the cylinder through a fixed pull rod, 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 convergence pull rod and the convergence adjusting sheet form a 4-link mechanism, the actuating cylinder is a driving element, the actuating cylinder drives the adjusting ring, the adjusting ring drives the convergence pull rod, and the convergence pull rod drives the convergence adjusting sheet, 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 as to realize the adjustment and control of the outlet area of the spray pipe; one end of the outer adjusting piece is hinged with the support 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 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, a position limiter on the expansion sealing sheet is hung on the two expansion adjusting sheets to play the role of limiting,
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 pull rod, the tensile stress can form compressive stress inside the support ring through 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, the outer adjusting sheet, the expansion pull rod and an output shaft of the actuating cylinder form a plane four-bar mechanism, the convergence pull rod 7, the expansion pull rod 8, the convergence adjusting sheet 9 and the expansion adjusting sheet 10 form a second plane four-bar mechanism, and the biplane four-bar mechanism can more effectively output torque and control the rod length relation and the motion relation of the adjusting sheets.
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 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. An axisymmetric convergent-divergent 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 (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 expansion adjusting sheet (10) is hinged with the adjusting ring (5) through an expansion pull rod (8), and the convergence adjusting sheet (9) is hinged with the adjusting ring (5) through a convergence pull rod (7).
2. The axisymmetric convergent-divergent nozzle of claim 1, characterized in that a plurality of fixed tie rods (4) are hinged to the outer circumference of the cylinder (1), the fixed tie rods (4) are hinged to the same support ring (6), the rear end of the divergent flap (10) is hinged to an outer flap (11), and the other end of the outer flap (11) is hinged to the support ring (6).
3. The axisymmetric convergent-divergent nozzle of claim 1, characterized in that adjacent two outer adjusting pieces (11) are arranged in a stacked manner at the edges thereof.
4. 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.
5. The axisymmetric convergent-divergent nozzle of claim 1, characterized in that the number of the actuators (3) is 0.1 to 0.5 of the number of the convergent flaps (9).
6. The axisymmetric convergent-divergent nozzle of claim 1, characterized in that the actuators (3) are arranged at equal intervals in the circumferential direction of the cylinder (1).
7. The axisymmetric convergent-divergent nozzle of claim 1, characterized in that a convergent section stopper (14) is provided between each convergent flap (9) and the convergent drawbar (7), and the convergent section stopper (14) is contacted 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 the position limitation.
8. The axisymmetric convergent-divergent nozzle of claim 1, characterized in that an expansion segment stopper (15) is provided between each expansion adjustment piece (10) and the expansion pull rod (8), and the expansion segment stopper (15) is contacted with the expansion adjustment piece (10) and the expansion pull rod (8) after the expansion adjustment piece (10) and the expansion pull rod (8) reach a preset angle to realize the limiting.
9. 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.
10. The axisymmetric convergent-divergent nozzle of claim 9, characterized in that sealing strips are provided at the edge stacks of two adjacent convergent flaps (9) and two adjacent divergent flaps (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210393713.3A CN114687886A (en) | 2022-04-14 | 2022-04-14 | Axisymmetric convergent-divergent nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210393713.3A CN114687886A (en) | 2022-04-14 | 2022-04-14 | Axisymmetric convergent-divergent nozzle |
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| Publication Number | Publication Date |
|---|---|
| CN114687886A true CN114687886A (en) | 2022-07-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210393713.3A Pending CN114687886A (en) | 2022-04-14 | 2022-04-14 | Axisymmetric convergent-divergent nozzle |
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4176792A (en) * | 1977-07-11 | 1979-12-04 | General Electric Company | Variable area exhaust nozzle |
| US4440346A (en) * | 1981-12-28 | 1984-04-03 | United Technologies Corporation | Axially translatable variable area convergent/divergent nozzle |
| US5082182A (en) * | 1990-08-23 | 1992-01-21 | United Technologies Corporation | Thrust vectoring exhaust nozzle |
| US5176323A (en) * | 1991-04-15 | 1993-01-05 | General Electric Company | Reduced weight nozzle actuation mechanism |
| JPH11182344A (en) * | 1997-12-24 | 1999-07-06 | Ishikawajima Harima Heavy Ind Co Ltd | Multishaft thrust deflection nozzle for gas turbine |
| 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 |
| CN114109645A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Axial symmetry contraction and expansion spray pipe movement mechanism |
-
2022
- 2022-04-14 CN CN202210393713.3A patent/CN114687886A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4176792A (en) * | 1977-07-11 | 1979-12-04 | General Electric Company | Variable area exhaust nozzle |
| US4440346A (en) * | 1981-12-28 | 1984-04-03 | United Technologies Corporation | Axially translatable variable area convergent/divergent nozzle |
| US5082182A (en) * | 1990-08-23 | 1992-01-21 | United Technologies Corporation | Thrust vectoring exhaust nozzle |
| US5176323A (en) * | 1991-04-15 | 1993-01-05 | General Electric Company | Reduced weight nozzle actuation mechanism |
| JPH11182344A (en) * | 1997-12-24 | 1999-07-06 | Ishikawajima Harima Heavy Ind Co Ltd | Multishaft thrust deflection nozzle for gas turbine |
| 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 |
| CN114109645A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Axial symmetry contraction and expansion spray pipe movement mechanism |
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