阅读说明：本技术 一种航空发动机喷管喉道面积调节机构 (Aircraft engine spray tube throat area adjustment mechanism ) 是由 王殿磊 周东旭 丛明辉 于 2021-01-15 设计创作，主要内容包括：本申请属于航空发动机喷管喉道面积调节设计技术领域,具体涉及一种航空发动机喷管喉道面积调节机构,包括：多个支撑梁,用以连接在喷管连接筒的外壁上,沿周向分布；多个摇臂,每个摇臂对应铰接在一个支撑梁上；多个拉杆,每个拉杆一端对应铰接在一个摇臂上,另一端用以对应铰接在一个收敛片的外壁上；多个作动筒,每个作动筒的筒体用以铰接在喷管连接筒的外壁上,活塞杆对应铰接在一个摇臂上,以能够带动对应的摇臂绕与对应支撑梁的铰接部位转动,以此通过对应的拉杆带动对应的收敛片运动,从而实现对喷管喉道面积的调节。(The application belongs to the technical field of the area adjustment design of aircraft engine spray tube throat, concretely relates to aircraft engine spray tube throat area adjustment mechanism, include: the supporting beams are connected to the outer wall of the spray pipe connecting cylinder and distributed along the circumferential direction; the rocker arms are correspondingly hinged on one support beam; one end of each pull rod is correspondingly hinged on one rocker arm, and the other end of each pull rod is correspondingly hinged on the outer wall of one convergence sheet; the cylinder body of each actuator cylinder is hinged to the outer wall of the spray pipe connecting cylinder, the piston rod is correspondingly hinged to one rocker arm so as to drive the corresponding rocker arm to rotate around the hinged part of the corresponding supporting beam, and the corresponding convergence sheet is driven to move through the corresponding pull rod, so that the throat area of the spray pipe is adjusted.)

1. The utility model provides an aeroengine spray tube throat area adjustment mechanism which characterized in that includes:

a plurality of supporting beams (1) which are connected to the outer wall of the spray pipe connecting cylinder (6) and distributed along the circumference;

a plurality of rocker arms (2), wherein each rocker arm (2) is correspondingly hinged on one support beam (1);

one end of each pull rod (3) is correspondingly hinged to one rocker arm (2), and the other end of each pull rod (3) is correspondingly hinged to the outer wall of one convergence sheet (4);

the actuating cylinders (5) are used for being hinged to the outer wall of the spray pipe connecting cylinder (6), the piston rods are correspondingly hinged to the rocker arms (2) to drive the corresponding rocker arms (2) to rotate around the hinged parts of the corresponding supporting beams (1), and the corresponding convergence plates (4) are driven to move through the corresponding pull rods (3), so that the throat area of the spray pipe is adjusted.

2. The aircraft engine nozzle throat area adjustment mechanism of claim 1,

the angle change range between each pull rod (3) and the corresponding convergence sheet (4) is within 70-110 degrees.

3. The aircraft engine nozzle throat area adjustment mechanism of claim 1,

further comprising:

and one end of each synchronous connecting rod (7) is correspondingly hinged on one rocker arm (2), the other end of each synchronous connecting rod (7) is correspondingly hinged on the outer wall of one convergence sheet (4), and the convergence sheet (4) is adjacent to the convergence sheet (4) hinged with the corresponding pull rod (3).

4. The aircraft engine nozzle throat area adjustment mechanism of claim 3,

the angle change range between each synchronous connecting rod (7) and the corresponding convergence sheet (4) is within 70-110 degrees.

5. The aircraft engine nozzle throat area adjustment mechanism of claim 1,

further comprising:

a plurality of brackets (8) for connecting to the outer wall of the nozzle connecting cylinder (6); each support (7) is correspondingly hinged with the cylinder body of one actuating cylinder (5) so as to support the corresponding actuating cylinder (5) on the outer wall of the connecting pipe connecting cylinder (6).

Technical Field

The application belongs to the technical field of jet pipe throat area adjusting design of aero-engines, and particularly relates to a jet pipe throat area adjusting mechanism of an aero-engine.

Background

The spray pipe is an important part of an aeroengine and is used for discharging high-temperature and high-pressure gas after a turbine out of an engine body after expanding and accelerating so as to generate engine thrust, and the spray pipe mainly comprises: the nozzle comprises a nozzle connecting cylinder, a plurality of convergence sheets and a plurality of expansion sheets, wherein one end of each convergence sheet is hinged to the outlet end of the nozzle connecting cylinder and is distributed along the circumferential direction, adjacent convergence sheets are in sealing contact to form a nozzle convergence section, and the radial dimension of the nozzle convergence section gradually shrinks towards the direction far away from the nozzle connecting cylinder to form a nozzle throat; one end of each expansion piece is correspondingly hinged to the other end of one convergence piece, the adjacent expansion pieces are in sealing contact to form a spray pipe expansion section, and the radial size of the spray pipe expansion section gradually expands towards the direction far away from the spray pipe connecting cylinder to form a spray pipe outlet.

In the working process of the aircraft engine, in order to obtain better thrust performance, the area of the nozzle throat needs to be adjusted according to actual working conditions, and for this reason, a nozzle throat area adjusting mechanism is designed to drive each convergence sheet to rotate around a connecting part with the outlet end of the nozzle connecting cylinder, so that the adjustment of the area of the nozzle throat is realized, and the existing nozzle throat area adjusting mechanism has the following defects:

1) the structure is complex, and a large space is occupied;

2) in order to synchronize the adjustment of each convergent vane, a complex synchronization mechanism is designed, the load is large, the adjustment efficiency is low, the adjustment of the convergent vanes has hysteresis, the adjustment of the throat area of the spray pipe is delayed, and the improvement of the performance of the engine is limited.

The present application has been made in view of the above-mentioned technical drawbacks.

It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.

Disclosure of Invention

It is an object of the present application to provide an aircraft engine nozzle throat area adjustment mechanism to overcome or mitigate at least one of the technical disadvantages of the known prior art.

The technical scheme of the application is as follows:

an aircraft engine nozzle throat area adjustment mechanism comprising:

the supporting beams are connected to the outer wall of the spray pipe connecting cylinder and distributed along the circumferential direction;

the rocker arms are correspondingly hinged on one support beam;

one end of each pull rod is correspondingly hinged on one rocker arm, and the other end of each pull rod is correspondingly hinged on the outer wall of one convergence sheet;

the cylinder body of each actuator cylinder is hinged to the outer wall of the spray pipe connecting cylinder, the piston rod is correspondingly hinged to one rocker arm so as to drive the corresponding rocker arm to rotate around the hinged part of the corresponding supporting beam, and the corresponding convergence sheet is driven to move through the corresponding pull rod, so that the throat area of the spray pipe is adjusted.

According to at least one embodiment of the application, in the aircraft engine nozzle throat area adjusting mechanism, the angle between each pull rod and the corresponding convergent plate is changed within the range of 70-110 degrees.

According to at least one embodiment of the present application, the above-mentioned aircraft engine nozzle throat area adjustment mechanism further includes:

and one end of each synchronous connecting rod is correspondingly hinged on one rocker arm, the other end of each synchronous connecting rod is correspondingly hinged on the outer wall of one convergence sheet, and the convergence sheet is adjacent to the convergence sheet hinged with the corresponding pull rod.

According to at least one embodiment of the application, in the aircraft engine nozzle throat area adjustment mechanism, the angle between each synchronization link and the corresponding convergent plate is within a range of 70-110 degrees.

According to at least one embodiment of the present application, the above-mentioned aircraft engine nozzle throat area adjustment mechanism further includes:

the brackets are used for connecting the outer wall of the spray pipe connecting cylinder; each support is correspondingly hinged with the cylinder body of one actuating cylinder so as to support the corresponding actuating cylinder on the outer wall of the connecting cylinder of the nozzle connecting pipe.

The application has at least the following beneficial technical effects:

the utility model provides an aeroengine spray tube throat area adjustment mechanism, its flexible each convergent flap motion of drive of each actuator cylinder piston rod of accessible makes the spray tube throat enlarge or shrink to realize the regulation to spray tube throat area, this aeroengine spray tube throat area adjustment mechanism simple structure, required occupation space is less, in addition, the biography is carried directly, has higher biography and carries efficiency, and the regulating efficiency is higher.

Drawings

FIG. 1 is a schematic view of an aircraft engine nozzle throat area adjustment mechanism according to an embodiment of the present disclosure driving a convergent motion to enlarge a nozzle throat;

FIG. 2 is a schematic view of an aircraft engine nozzle throat area adjustment mechanism according to an embodiment of the present disclosure driving a converging motion to cause a nozzle throat to contract;

wherein:

1-a support beam; 2-a rocker arm; 3-a pull rod; 4-convergence sheet; 5-an actuator cylinder; 6-nozzle connecting cylinder; 7-a synchronous connecting rod; 8-bracket.

For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.

Detailed Description

In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.

In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.

Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.

The present application is described in further detail below with reference to fig. 1-2.

An aircraft engine nozzle throat area adjustment mechanism comprising:

a plurality of supporting beams 1 which are used for being connected to the outer wall of the spray pipe connecting cylinder 6 and are distributed along the circumferential direction;

a plurality of rocker arms 2, wherein each rocker arm 2 is correspondingly hinged on one support beam 1;

one end of each pull rod 3 is correspondingly hinged on one rocker arm 2, and the other end of each pull rod 3 is correspondingly hinged on the outer wall of one convergence sheet 4;

the actuating cylinders 5 are used for being hinged to the outer wall of the spray pipe connecting cylinder 6, the cylinder body of each actuating cylinder 5 is correspondingly hinged to one rocker arm 2, so that the corresponding rocker arm 2 can be driven to rotate around the hinged part of the corresponding supporting beam 1, the corresponding convergence sheet 4 is driven to move through the corresponding pull rod 3, and the throat area of the spray pipe is adjusted.

For the aircraft engine nozzle throat area adjusting mechanism disclosed in the above embodiment, as can be understood by those skilled in the art, the contraction of the piston rod of each actuator cylinder 5 can drive each convergence plate 4 to move, so that the nozzle throat is expanded or contracted, thereby adjusting the nozzle throat area.

In some alternative embodiments, in the aircraft engine nozzle throat area adjusting mechanism, the angle between each pull rod 3 and the corresponding convergent plate 4 is in a range of 70 to 110 degrees, so that the aircraft engine nozzle throat area adjusting mechanism is subjected to a small load and has high adjusting efficiency.

In some optional embodiments, the above-mentioned aircraft engine nozzle throat area adjustment mechanism further includes:

and one end of each synchronous connecting rod 7 is correspondingly hinged on one rocker arm 2, the other end of each synchronous connecting rod 7 is correspondingly hinged on one convergence sheet 4, the convergence sheet 4 is adjacent to the convergence sheet 4 hinged to the corresponding pull rod 3, namely the pull rod 3 hinged to the same rocker arm 2, and the synchronous connecting rods 7 are hinged to the two adjacent convergence sheets 4, so that the convergence sheets 4 can be linked under the driving of the actuating cylinders 5, the motion synchronism is kept, and the synchronism of adjustment of the convergence sheets 4 is realized by a simpler structure.

In some alternative embodiments, in the aircraft engine nozzle throat area adjusting mechanism, the angle between each synchronization link 7 and the corresponding convergent plate 4 is within 70-110 °, so that the aircraft engine nozzle throat area adjusting mechanism is subjected to a smaller load and has higher adjusting efficiency.

In some optional embodiments, the above-mentioned aircraft engine nozzle throat area adjustment mechanism further includes:

a plurality of brackets 8 for connecting to the outer wall of the nozzle connecting cylinder 6; each bracket 7 is hinged to the body of a respective actuator cylinder 5 to support the respective actuator cylinder 5 on the outer wall of the nozzle connecting cylinder 6.

The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.

Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.