阅读说明：本技术 一种航空发动机喷管及其扩张片拉杆结构 (Aero-engine spray pipe and expansion piece pull rod structure thereof ) 是由 王殿磊 周东旭 宁怀松 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结构设计技术领域,具体涉及一种航空发动机喷管扩张片拉杆结构,包括：第一连杆,一端开设有连接孔；第二连杆,一端插入连接孔,能够相对于第一连杆沿轴向运动,与连接孔之间形成有环形卡槽；弹性环,卡在环形卡槽中,能够在第二连杆与第一连杆间产生摩擦力,以阻止第二连杆相对于第一连杆沿轴向的运动。此外,涉及一种航空发动机喷管结构,该航空发动机喷管结构中包括上述的航空发动机喷管扩张片拉杆结构。(The application belongs to the technical field of aeroengine spray tube structural design, concretely relates to aeroengine spray tube expansion piece pull rod structure, include: one end of the first connecting rod is provided with a connecting hole; one end of the second connecting rod is inserted into the connecting hole, can move axially relative to the first connecting rod, and an annular clamping groove is formed between the second connecting rod and the connecting hole; the elastic ring is clamped in the annular clamping groove and can generate friction force between the second connecting rod and the first connecting rod so as to prevent the second connecting rod from moving relative to the first connecting rod along the axial direction. Furthermore, the aircraft engine nozzle structure comprises the aircraft engine nozzle expansion sheet pull rod structure.)

1. An aircraft engine nozzle vane drag link structure, comprising:

one end of the first connecting rod (1) is provided with a connecting hole;

one end of the second connecting rod (2) is inserted into the connecting hole, can move along the axial direction relative to the first connecting rod (1), and an annular clamping groove is formed between the second connecting rod and the connecting hole;

and the elastic ring (3) is clamped in the annular clamping groove and can generate friction force between the second connecting rod (2) and the first connecting rod (1) so as to prevent the second connecting rod (2) from moving relative to the first connecting rod (1) along the axial direction.

2. The aircraft engine nozzle expansion tab drawbar arrangement according to claim 1,

one end of the first connecting rod (1), which is back to the second connecting rod (2), is provided with a single lug connecting joint.

3. The aircraft engine nozzle expansion tab drawbar arrangement according to claim 1,

one end of the second connecting rod (2), which is back to the first connecting rod (1), is provided with a single lug connecting joint.

4. The aircraft engine nozzle expansion tab drawbar arrangement according to claim 1,

one end of the second connecting rod (2) inserted into the connecting hole is in clearance fit with the connecting hole.

5. The aircraft engine nozzle expansion tab drawbar arrangement according to claim 1,

the outer wall of one end, inserted into the connecting hole, of the second connecting rod (2) is provided with the annular clamping groove.

6. The aircraft engine nozzle expansion tab drawbar arrangement according to claim 5,

the outer ring of the elastic ring (3) is in elastic contact with the connecting hole.

7. The aircraft engine nozzle expansion tab drawbar arrangement according to claim 1,

the elastic ring (3) is provided with a notch.

8. The aircraft engine nozzle expansion tab drawbar arrangement according to claim 1,

the elastic rings (3) and the corresponding annular clamping grooves are multiple.

9. An aircraft engine nozzle structure, comprising:

a nozzle connecting cylinder (4);

one end of each convergence sheet (5) is hinged to the outlet end of the corresponding spray pipe connecting cylinder (4) and is distributed along the circumferential direction, and adjacent convergence sheets (5) are in sealing contact with each other to form a spray pipe convergence section; the radial dimension of the spray pipe convergent section gradually shrinks towards the direction far away from the spray pipe connecting cylinder (4) to form a spray pipe throat;

a plurality of expansion pieces (6), one end of each expansion piece (6) is correspondingly hinged to the other end of one convergence piece (5), and adjacent expansion pieces (6) are in sealing contact to form a nozzle expansion section; the radial dimension of the spray pipe expansion section is gradually expanded towards the direction far away from the spray pipe connecting cylinder (4) to form a spray pipe outlet;

the support ring (7) is sleeved on the spray pipe connecting cylinder (4);

-a plurality of aeroengine nozzle-expander strut arrangements according to claims 1 to 8, wherein the single lug connection joint of each first connecting rod (1) is hinged on the support ring (7); the single lug connecting joint on each second connecting rod (2) is correspondingly hinged on the outer wall of one expansion piece (6).

Technical Field

The application belongs to the technical field of structural design of aircraft engine spray pipes, and particularly relates to an aircraft engine spray pipe and an expansion segment pull rod structure thereof.

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 order to obtain better thrust performance in the working process of an aircraft engine, the area of a throat of a spray pipe and the area of an outlet of the spray pipe need to be adjusted according to actual working conditions, currently, a convergent plate adjusting mechanism is designed to drive each convergent plate to rotate around a connecting part with the outlet end of a connecting cylinder of the spray pipe so as to adjust the area of the throat of the spray pipe, a plurality of pull rods are designed to be connected with each expansion plate and a fixed end, each expansion plate rotates under the driving of the corresponding convergent plate, and therefore the area of the outlet of the spray pipe is changed, because the length of each pull rod is fixed, when the area of the throat of the spray pipe is fixed, the area of the outlet of the spray pipe is also determined, namely, the area of the outlet of the spray pipe and the area of the throat of the spray pipe have one-to-one correspondence, the correspondence limits the engine to obtain the optimal thrust, the thrust loss is large, the air flow is unstable, and the vibration of the expansion sheet is easy to cause.

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 and its expansion segment drawbar arrangement which overcomes or mitigates at least one of the technical disadvantages of the known prior art.

The technical scheme of the application is as follows:

one aspect provides an aircraft engine nozzle vane extender rod structure comprising:

one end of the first connecting rod is provided with a connecting hole;

one end of the second connecting rod is inserted into the connecting hole, can move axially relative to the first connecting rod, and an annular clamping groove is formed between the second connecting rod and the connecting hole;

the elastic ring is clamped in the annular clamping groove and can generate friction force between the second connecting rod and the first connecting rod so as to prevent the second connecting rod from moving relative to the first connecting rod along the axial direction.

According to at least one embodiment of the application, in the aircraft engine nozzle expansion piece pull rod structure, one end of the first connecting rod, which faces away from the second connecting rod, is provided with a single lug connecting joint.

According to at least one embodiment of the application, in the aircraft engine nozzle expansion piece pull rod structure, one end, facing away from the first connecting rod, of the second connecting rod is provided with a single lug connecting joint.

According to at least one embodiment of the application, in the aircraft engine nozzle expansion piece pull rod structure, one end, inserted into the connecting hole, of the second connecting rod is in clearance fit with the connecting hole.

According to at least one embodiment of the application, in the pull rod structure of the nozzle extension piece of the aircraft engine, an annular clamping groove is formed in an outer wall of one end, inserted into the connecting hole, of the second connecting rod.

According to at least one embodiment of the application, in the aircraft engine nozzle expansion piece pull rod structure, the outer ring of the elastic ring is in elastic contact with the connecting hole.

According to at least one embodiment of the application, in the aircraft engine nozzle expansion piece pull rod structure, the elastic ring is provided with a notch.

According to at least one embodiment of the application, in the above-mentioned structure of the nozzle expansion piece pull rod of the aircraft engine, the number of the elastic rings and the corresponding annular clamping grooves thereof is multiple.

In another aspect, an aircraft engine nozzle structure is provided, comprising:

a nozzle connecting cylinder;

one end of each convergence sheet is hinged to the outlet end of the corresponding spray pipe connecting cylinder and is distributed along the circumferential direction, and adjacent convergence sheets are in sealing contact with each other to form a spray pipe convergence section; the radial dimension of the nozzle convergent 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, and adjacent expansion pieces are in sealing contact to form a spray pipe expansion section; the radial dimension of the expansion section of the spray pipe gradually expands towards the direction far away from the spray pipe connecting cylinder to form a spray pipe outlet;

the support ring is sleeved on the spray pipe connecting cylinder;

a plurality of any of the above-described aero-engine nozzle vane extender brace configurations wherein the single lug link joint of each first link is hinged to the support ring; the single lug connecting joint on each second connecting rod is correspondingly hinged on the outer wall of one expansion piece.

Drawings

FIG. 1 is a schematic view of an aircraft engine nozzle vane extender brace construction provided in an embodiment of the present application;

FIG. 2 is a schematic view of the axial movement of a second link relative to a first link in an exemplary embodiment of an aircraft engine nozzle vane extender pull rod configuration provided herein;

FIG. 3 is a partial schematic view of an aircraft engine nozzle vane extender drag link configuration provided in accordance with an embodiment of the present application;

FIG. 4 is a partial schematic view of an aircraft engine nozzle configuration provided by an embodiment of the present application;

wherein:

1-a first link; 2-a second link; 3-an elastic ring; 4-a nozzle connecting cylinder; 5-convergence sheet; 6-expansion sheet; 7-support ring.

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 to 4.

One aspect provides an aircraft engine nozzle vane extender rod structure comprising:

one end of the first connecting rod 1 is provided with a connecting hole;

one end of the second connecting rod 2 is inserted into the connecting hole, can move axially relative to the first connecting rod 1, and an annular clamping groove is formed between the second connecting rod and the connecting hole;

the elastic ring 3 is clamped in the annular clamping groove, and can generate friction force between the second connecting rod 2 and the first connecting rod 1 so as to prevent the second connecting rod 2 from moving relative to the first connecting rod 1 along the axial direction.

For the structure of the nozzle extension piece pull rod of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that the structure can be used as a pull rod of a nozzle extension piece of an aircraft engine, when the structure is used as a pull rod of a nozzle extension piece of an aircraft engine, one end of each first connecting rod 1, which faces away from the second connecting rod 2, in the pull rod structure of a plurality of nozzle extension pieces of an aircraft engine can be hinged at a fixed end, one end of each second connecting rod 2, which faces away from the first connecting rod 1, is correspondingly hinged at the outer wall of one extension piece 6, when the engine works, each convergent piece 5 can be driven by a convergent piece adjusting mechanism to rotate around a connecting part with the outlet end of a nozzle connecting cylinder according to actual working conditions, so as to realize the adjustment of the throat area of the nozzle, in the process, each expansion piece 5 rotates under the driving of the corresponding convergent piece 5, each expansion piece 5 can drive the corresponding second connecting rod 2 to move relative to the first connecting rod 1 along the axial direction until the elastic ring 3 generates friction between the second connecting rod 2 and the first connecting rod 1 and the aerodynamic force of the airflow is balanced, so that the self-adaptive adjustment of the outlet area of the spray pipe is realized, the airflow flowing through the spray pipe is fully expanded, the aircraft engine obtains better thrust performance, the airflow flowing through the spray pipe is stable, and the expansion pieces 6 are prevented from generating violent vibration.

With regard to the structure of the nozzle extension piece pull rod of the aircraft engine disclosed in the above embodiment, it can be further understood by those skilled in the art that when the second connecting rod 2 moves axially relative to the first connecting rod 1, the elastic ring 3 generates a friction force between the second connecting rod 2 and the first connecting rod 1, so as to prevent the second connecting rod 2 from moving axially relative to the first connecting rod 1, and besides, the elastic ring 3 itself can also generate elastic deformation, so that when the structure is used as a pull rod of an aircraft engine nozzle extension piece, the elastic ring 3 can buffer the vibration of the extension piece 6 by virtue of the elastic deformation.

In some alternative embodiments, in the above-mentioned structure of the nozzle extension piece pull rod of the aircraft engine, in order to avoid the second connecting rod 2 from being excessively inserted into the connecting hole, a stop protrusion may be provided on the outer wall of the second connecting rod, or the effective depth of the connecting hole may be designed.

In some alternative embodiments, in the above-mentioned structure of the nozzle plate tie-rod of the aircraft engine, the end of the first connecting rod 1 facing away from the second connecting rod 2 is provided with a single lug connection joint, which can be connected to a fixed end when used as a tie-rod of the nozzle plate of the aircraft engine.

In some alternative embodiments, in the above-mentioned structure of the nozzle-expander stay, the end of the second link 2 facing away from the first link 1 is provided with a single lug connection joint, which can be connected to the outer wall of the expander 6 when used as a stay for the nozzle-expander.

In some alternative embodiments, in the above-mentioned structure of the nozzle plate of the aircraft engine, one end of the second connecting rod 2 inserted into the connecting hole is in clearance fit with the connecting hole, so that the second connecting rod 2 can freely move in the axial direction relative to the first connecting rod 1.

In some optional embodiments, in the above-mentioned aircraft engine nozzle expansion piece pull rod structure, an annular clamping groove is formed in an outer wall of one end of the second connecting rod 2, which is inserted into the connecting hole.

In some optional embodiments, in the above-mentioned structure of the nozzle expansion piece pull rod for an aircraft engine, the outer ring of the elastic ring 3 is in elastic contact with the connecting hole, so as to ensure that the elastic ring 3 can effectively generate friction force between the first connecting rod 1 and the second connecting rod 2.

In some alternative embodiments, the aircraft engine nozzle expansion piece pull rod structure described above has a notch in the elastic ring 3.

For the aircraft engine nozzle expansion piece pull rod structure disclosed in the above embodiment, those skilled in the art can understand that the elastic ring 3 has a larger elastic deformation capability by providing the notch on the elastic ring 3, so that on one hand, the elastic ring 3 is conveniently clamped into the annular clamping groove, and on the other hand, after the elastic ring 3 is clamped into the annular clamping groove, the outer ring of the elastic ring can effectively keep elastic contact with the connecting hole.

In some alternative embodiments, in the above-mentioned structure of the nozzle extension piece pull rod of the aircraft engine, the number of the elastic rings 3 and the corresponding annular clamping grooves is plural, and the specific number can be designed by a person skilled in the art according to specific practical application.

In another aspect, an aircraft engine nozzle structure is provided, comprising:

a nozzle connecting cylinder 4;

one end of each of the plurality of convergent flaps 5 is hinged to the outlet end of the spray pipe connecting cylinder 4 and is distributed along the circumferential direction, and adjacent convergent flaps 5 are in sealing contact with each other to form a spray pipe convergent section; the radial dimension of the nozzle convergent section gradually shrinks towards the direction far away from the nozzle connecting cylinder 4 to form a nozzle throat;

one end of each expansion sheet 6 is correspondingly hinged to the other end of one convergence sheet 5, and adjacent expansion sheets 6 are in sealing contact to form a nozzle expansion section; the radial dimension of the expansion section of the spray pipe is gradually expanded towards the direction far away from the spray pipe connecting cylinder 4 to form a spray pipe outlet;

the support ring 7 is sleeved on the spray pipe connecting cylinder 4;

a plurality of any one of the above-described aero-engine nozzle vane extender brace configurations wherein the single lug connection tab of each first link 1 is hinged to a support ring 7; the single lug connection joint on each second connecting rod 2 is correspondingly hinged on the outer wall of one expansion piece 6.

For the nozzle structure of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that the nozzle structure of the aircraft engine disclosed in the above embodiment includes the nozzle expansion piece pull rod structure of the aircraft engine disclosed in the above embodiment, and specific relevant points may be referred to the description of relevant parts of the nozzle expansion piece pull rod structure of the aircraft engine, and the technical effects may also refer to the technical effects of relevant parts of the nozzle expansion piece pull rod structure of the aircraft engine, and are not described herein again.

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.