CN113883089A - Angle adjusting mechanism for stator blade of aero-engine - Google Patents
Angle adjusting mechanism for stator blade of aero-engine Download PDFInfo
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- CN113883089A CN113883089A CN202111272338.9A CN202111272338A CN113883089A CN 113883089 A CN113883089 A CN 113883089A CN 202111272338 A CN202111272338 A CN 202111272338A CN 113883089 A CN113883089 A CN 113883089A
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- stator
- stator blade
- stator casing
- casing
- angle adjustment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/322—Blade mountings
- F04D29/323—Blade mountings adjustable
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application belongs to the technical field of aero-engine stator blade angle adjustment design, concretely relates to aero-engine stator blade angle adjustment mechanism, include: the plurality of dowel bars are distributed along the circumferential direction of the stator casing; each force transmission rod is correspondingly meshed and connected with the insection between the upper journals of the stator blades extending out of the mounting holes of the stator casing; and the linkage ring is sleeved on the stator casing and is connected with one end of each force transmission rod, and can move along the axial direction of the stator casing so as to drive each force transmission rod to synchronously move along the axial direction of the stator casing and enable each stator blade to synchronously rotate.
Description
Technical Field
The application belongs to the technical field of aero-engine stator blade angle adjustment design, and particularly relates to an aero-engine stator blade angle adjusting mechanism.
Background
In order to stably work in a compressor of an engine, the gas flow flowing through the compressor needs to be adjusted according to actual conditions, the angle of each stator blade in the compressor is adjustable, and the angle of each stator blade is adjusted to synchronously rotate through an angle adjusting mechanism so as to synchronously change the angle of each stator blade, thereby adjusting the gas flow flowing through the compressor.
Each stator blade in the gas compressor is arranged between a stator casing and an inner ring of the gas compressor and distributed along the circumferential direction, a lower shaft neck of each stator blade is inserted into a mounting hole in the stator inner ring, and an upper shaft neck extends out of the mounting hole in the stator casing. The existing angle adjusting mechanism for the stator blade of the aero-engine mainly comprises a plurality of rocker arms, a linkage ring and an actuating cylinder, wherein one end of each rocker arm is correspondingly connected with an upper journal of one stator blade extending out of a mounting hole of a stator casing; the linkage ring is sleeved on the stator casing and is hinged with the other end of each rocker arm; the actuating cylinder is arranged on the stator casing, and a piston rod of the actuating cylinder is connected with the linkage ring so as to drive the linkage ring to move, so that each rocker arm is driven to synchronously swing in the circumferential direction of the stator casing, each stator blade synchronously rotates, and the synchronous adjustment of the rotating angle of each stator blade is realized, as shown in fig. 1, the angle adjusting mechanism has the following defects:
1) in the process that the actuating cylinder drives the linkage ring to adjust the angle of the stator blade, the linkage ring rotates along the circumferential direction of the stator casing and moves axially along the stator casing, namely, the linkage ring bears both axial force and axial force, so that the linkage ring is easy to deform greatly, the accurate adjustment of the rotation angle of the stator blade cannot be realized, and the improvement of the performance of an engine is severely limited;
2) in order to ensure that the angle adjusting mechanism acts smoothly, each rocker arm is connected with the pin through a bearing, and the situation of clamping stagnation of the bearing is easy to cause due to errors in processing and assembly.
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 stator vane angle 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 stator blade angle adjustment mechanism comprising:
the plurality of dowel bars are distributed along the circumferential direction of the stator casing; each force transmission rod is correspondingly meshed and connected with the insection between the upper journals of the stator blades extending out of the mounting holes of the stator casing;
and the linkage ring is sleeved on the stator casing and is connected with one end of each force transmission rod, and can move along the axial direction of the stator casing so as to drive each force transmission rod to synchronously move along the axial direction of the stator casing and enable each stator blade to synchronously rotate.
According to at least one embodiment of the application, in the aircraft engine stator blade angle adjusting mechanism, each dowel bar is integrally formed with the linkage ring.
According to at least one embodiment of the application, in the above-mentioned aircraft engine stator blade angle adjusting mechanism, the stator casing is provided with a plurality of guide grooves distributed along the circumferential direction; each guide groove extends along the axial direction of the stator casing;
the linkage ring is provided with a plurality of guide bulges; each guide protrusion is inserted into one corresponding guide groove and can slide in the corresponding guide groove along the axial direction of the stator casing.
According to at least one embodiment of the present application, the above-mentioned aircraft engine stator blade angle adjusting mechanism further includes:
and one end of each rocker arm is correspondingly connected with one upper journal, and the other end of each rocker arm is meshed with the corresponding inter-dowel-bar tooth pattern.
According to at least one embodiment of the application, in the above-mentioned aircraft engine stator blade angle adjusting mechanism, one end of each rocker arm, which faces away from the corresponding dowel bar, is provided with a special-shaped hole; each profiled hole is sleeved on the corresponding upper journal.
According to at least one embodiment of the present application, the above-mentioned aircraft engine stator blade angle adjusting mechanism further includes:
and the actuating cylinder is connected between the stator casing and the linkage ring and can drive the linkage ring to move along the axial direction of the stator casing.
Drawings
FIG. 1 is a schematic view of a prior art aero-engine stator blade angle adjustment mechanism;
FIG. 2 is a schematic view of an aircraft engine stator blade angle adjustment mechanism provided by an embodiment of the present application;
FIG. 3 is a partial schematic view of an aircraft engine stator blade angle adjustment mechanism provided by an embodiment of the present application;
wherein:
1-a dowel bar; 2-a stator case; 3-stator blade. 4-a linkage ring; 5-rocker arm.
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 3.
An aircraft engine stator blade angle adjustment mechanism comprising:
a plurality of dowel bars 1 are distributed along the circumferential direction of the stator casing 2; each force transmission rod 1 is correspondingly connected with the upper journal of one stator blade 3 extending out of the mounting hole of the stator casing 2 in a toothed engagement mode;
and the linkage ring 4 is sleeved on the stator casing 2, is connected with one end of each force transfer rod 1, and can move along the axial direction of the stator casing 2 so as to drive each force transfer rod 1 to move synchronously along the axial direction of the stator casing 2, so that each stator blade 3 rotates synchronously.
To the aero-engine stator blade angle adjustment mechanism disclosed in the above embodiment, a person skilled in the art can understand that, in the process of adjusting the rotation angle of each stator blade 2, only the linkage ring 4 needs to move axially along the stator casing 2, and the rotation along the circumferential direction of the stator casing 2 does not need to occur, so that the linkage ring 4 can be prevented from generating large deformation, and the accurate adjustment of the rotation angle of the stator blade 3 is ensured.
To the aero-engine stator blade angle adjustment mechanism disclosed in the above embodiment, a person skilled in the art can also understand that, in the process of adjusting the rotation angle of each stator blade 2, the transmission of force is performed between the link ring 4 and the upper journal of each stator blade 3 in the form of insection by means of the force transmission rod 1, only the axial movement of the stator casing 2 needs to be performed, the movement is simple, the force transmission is performed without designing corresponding structures such as bearings, and the clamping stagnation is not easy to occur.
For the aero-engine stator blade angle adjustment mechanism disclosed in the above embodiment, it can be further understood by those skilled in the art that one end of each dowel bar 1 is connected to the link ring 4 and distributed along the circumferential direction of the link ring 4, so that the rigidity of the link ring 4 can be enhanced, the link ring 4 is prevented from being deformed greatly, and the accurate adjustment of the rotation angle of the stator blade 3 is ensured.
In some optional embodiments, in the above-mentioned angle adjusting mechanism for the stator blade of the aircraft engine, each dowel bar 1 is integrally formed with the link ring 4, so as to reduce the number of connecting parts between each dowel bar 1 and the link ring 4 and ensure the strength enhancing effect on the link ring 4.
In some alternative embodiments, in the above-mentioned aircraft engine stator blade angle adjusting mechanism, the stator casing 2 has a plurality of guide grooves distributed along the circumferential direction; each guide groove extends along the axial direction of the stator casing 2;
the linkage ring 4 is provided with a plurality of guide bulges; every direction protrusion corresponds inserts a guide way in, can follow stator cartridge receiver 2's axial slip in the guide way that corresponds to restriction link ring 5 is along stator cartridge receiver 2's circumferential direction, makes link ring 5 only can take place along stator cartridge receiver 2 axial's removal, guarantees the accurate regulation to 3 turned angles of stator blade.
In some optional embodiments, in the above-mentioned aircraft engine stator blade angle adjusting mechanism, further includes:
and one end of each rocker arm 5 is correspondingly connected with one upper journal, and the other end of each rocker arm 5 is meshed and connected with the corresponding threads between the force transmission rods 1.
For the aero-engine stator blade angle adjusting mechanism disclosed in the above embodiment, as can be understood by those skilled in the art, force transmission is performed between each force transmission rod 1 and the upper journal of the corresponding stator blade 3 through the rocker arm 5, so that the force arm between each force transmission rod 1 and the upper journal of the corresponding stator blade 3 can be extended, and therefore, in the process of adjusting the rotation angle of each stator blade 2, the axial force along the stator casing 2 borne by the link ring 4 can be reduced, and the link ring 4 is prevented from being deformed greatly, which affects accurate adjustment of the rotation angle of the stator blade 3.
In some alternative embodiments, in the above-mentioned aircraft engine stator blade angle adjusting mechanism, one end of each rocker arm 5, which faces away from the corresponding dowel bar 1, is provided with a profiled hole; each profiled hole is sleeved on the corresponding upper journal.
In some optional embodiments, in the above-mentioned aircraft engine stator blade angle adjusting mechanism, further includes:
and an actuator cylinder connected between the stator case 2 and the link ring 4 to drive the link ring 4 to move in the axial direction of the stator case 2.
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.
Claims (6)
1. The utility model provides an aeroengine stator blade angle adjustment mechanism which characterized in that includes:
the plurality of dowel bars (1) are distributed along the circumferential direction of the stator casing (2); each force transmission rod (1) is correspondingly meshed and connected with the upper journal of one stator blade (3) extending out of the mounting hole of the stator casing (2) through insections;
the linkage ring (4) is sleeved on the stator casing (2) and is connected with one end of the force transfer rod (1) and can move along the axial direction of the stator casing (2) to drive the force transfer rod (1) to move along the axial direction of the stator casing (2) synchronously, so that the stator blades (3) rotate synchronously.
2. The aircraft engine stator blade angle adjustment mechanism according to claim 1,
each dowel bar (1) and the linkage ring (4) are integrally formed.
3. The aircraft engine stator blade angle adjustment mechanism according to claim 1,
the stator casing (2) is provided with a plurality of guide grooves distributed along the circumferential direction; each guide groove extends along the axial direction of the stator casing (2);
the linkage ring (4) is provided with a plurality of guide bulges; each guide protrusion is correspondingly inserted into one guide groove and can slide in the corresponding guide groove along the axial direction of the stator casing (2).
4. The aircraft engine stator blade angle adjustment mechanism according to claim 1,
further comprising:
and one end of each rocker arm (5) is correspondingly connected with one upper journal, and the other end of each rocker arm (5) is meshed with the corresponding inter-dowel bar (1) in a tooth pattern manner.
5. The aircraft engine stator blade angle adjustment mechanism according to claim 4,
one end of each rocker arm (5) back to the corresponding dowel bar (1) is provided with a special-shaped hole; each of the profiled holes is sleeved on the corresponding upper journal.
6. The aircraft engine stator blade angle adjustment mechanism according to claim 1,
further comprising:
and the actuating cylinder is connected between the stator casing (2) and the linkage ring (4) so as to drive the linkage ring (4) to move along the axial direction of the stator casing (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111272338.9A CN113883089B (en) | 2021-10-29 | 2021-10-29 | Angle adjusting mechanism for stator blade of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111272338.9A CN113883089B (en) | 2021-10-29 | 2021-10-29 | Angle adjusting mechanism for stator blade of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113883089A true CN113883089A (en) | 2022-01-04 |
| CN113883089B CN113883089B (en) | 2023-04-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111272338.9A Active CN113883089B (en) | 2021-10-29 | 2021-10-29 | Angle adjusting mechanism for stator blade of aero-engine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114427547A (en) * | 2022-01-21 | 2022-05-03 | 中国航发沈阳发动机研究所 | Stator blade rotation angle adjusting mechanism of compressor in aircraft engine |
| CN114483656A (en) * | 2022-01-21 | 2022-05-13 | 中国航发沈阳发动机研究所 | Stator blade angle adjusting mechanism of compressor in engine |
| CN115030779A (en) * | 2022-07-26 | 2022-09-09 | 中国航发沈阳发动机研究所 | Method for determining geometric relationship between adjustable stator blade deflection angle and adjusting mechanism |
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| CN111911461A (en) * | 2020-08-28 | 2020-11-10 | 中国航发沈阳发动机研究所 | Stator blade angle adjusting mechanism and stator casing structure thereof |
| CN213176092U (en) * | 2020-06-24 | 2021-05-11 | 西安陕鼓动力股份有限公司 | Centrifugal compressor basic level testing arrangement that can make up formula and adjust |
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| CN103291383A (en) * | 2013-06-26 | 2013-09-11 | 上海交通大学 | Gas-compressor multistage stationary-blade regulating mechanism allowing gear transmission |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114427547A (en) * | 2022-01-21 | 2022-05-03 | 中国航发沈阳发动机研究所 | Stator blade rotation angle adjusting mechanism of compressor in aircraft engine |
| CN114483656A (en) * | 2022-01-21 | 2022-05-13 | 中国航发沈阳发动机研究所 | Stator blade angle adjusting mechanism of compressor in engine |
| CN115030779A (en) * | 2022-07-26 | 2022-09-09 | 中国航发沈阳发动机研究所 | Method for determining geometric relationship between adjustable stator blade deflection angle and adjusting mechanism |
| CN115030779B (en) * | 2022-07-26 | 2024-05-17 | 中国航发沈阳发动机研究所 | Method for determining geometrical relationship between deflection angle of adjustable stator blade and adjusting mechanism |
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| Publication number | Publication date |
|---|---|
| CN113883089B (en) | 2023-04-07 |
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