CN113863992A - Stator blade rotation angle adjustment mechanism among aeroengine - Google Patents
Stator blade rotation angle adjustment mechanism among aeroengine Download PDFInfo
- Publication number
- CN113863992A CN113863992A CN202111250267.2A CN202111250267A CN113863992A CN 113863992 A CN113863992 A CN 113863992A CN 202111250267 A CN202111250267 A CN 202111250267A CN 113863992 A CN113863992 A CN 113863992A
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- stator
- stator casing
- stator blade
- rocker arm
- casing
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- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D7/00—Rotors with blades adjustable in operation; Control thereof
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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 stator blade turned angle regulation design among the aeroengine, concretely relates to stator blade turned angle adjustment mechanism among aeroengine includes: the plurality of rocker arms are distributed along the circumferential direction of the stator casing; one end of each rocker arm is correspondingly connected with an upper journal of a stator blade extending out of a stator casing mounting hole; the linkage ring is sleeved on the periphery of the stator casing, is hinged with the other end of each rocker arm, and is provided with an outward folded edge at one side back to each upper shaft neck; and the actuating cylinder is connected between the stator casing and the linkage ring so as to drive the linkage ring to axially move along the stator casing and circumferentially rotate along the stator casing, so that each rocker arm is driven to circumferentially swing along the stator casing, and each stator blade is further synchronously rotated.
Description
Technical Field
The application belongs to the technical field of stator blade rotation angle adjusting design in aircraft engines, and particularly relates to a stator blade rotation angle adjusting mechanism in an aircraft engine.
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 stator blades are adjusted to rotate synchronously through a rotating angle adjusting mechanism so as to change the angle of each stator blade synchronously, so that the gas flow flowing through the compressor is adjusted.
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 stator blade rotation angle adjusting mechanism in the existing aircraft 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 a stator blade extending out of a stator casing mounting hole; the linkage ring is sleeved on the stator casing and is hinged with the other end of each rocker arm; the actuating cylinder is connected between the stator casing and the linkage ring to drive the linkage ring to move and drive each rocker arm to synchronously swing in the circumferential direction of the stator casing, so that each stator blade synchronously rotates, and the synchronous adjustment of the rotating angle of each stator blade is realized, and the technical scheme has the following defects:
under the condition that the number of stator blades is large, corresponding rocker arms are arranged densely, the linkage ring does not have enough space for the actuating cylinder to be connected, the condition that the actuating cylinder interferes with the rocker arms is easy to occur, and the accurate adjustment of the rotating angle of each stator blade is difficult to guarantee.
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
The object of the present application is to provide a stator vane turning angle adjustment mechanism in an aircraft engine that overcomes or alleviates at least one of the technical disadvantages of the known prior art.
The technical scheme of the application is as follows:
a stator blade turning angle adjustment mechanism in an aircraft engine, comprising:
the plurality of rocker arms are distributed along the circumferential direction of the stator casing; one end of each rocker arm is correspondingly connected with an upper journal of a stator blade extending out of a stator casing mounting hole;
the linkage ring is sleeved on the periphery of the stator casing, is hinged with the other end of each rocker arm, and is provided with an outward folded edge at one side back to each upper shaft neck;
and the actuating cylinder is connected between the stator casing and the linkage ring so as to drive the linkage ring to axially move along the stator casing and circumferentially rotate along the stator casing, so that each rocker arm is driven to circumferentially swing along the stator casing, and each stator blade is further synchronously rotated.
According to at least one embodiment of the application, in the stator blade angle adjusting mechanism in the aircraft engine, the connecting bracket is connected between the flange and the actuator cylinder.
According to at least one embodiment of the application, in the stator blade angle adjusting mechanism in the aircraft engine, the actuating cylinders and the corresponding folding edges and connecting supports are multiple.
According to at least one embodiment of the application, in the stator blade angle adjusting mechanism in the aircraft engine, the outer wall of the stator casing is provided with an annular protruding portion, and the annular protruding portion abuts against the inner side of the linkage ring.
According to at least one embodiment of the present application, the stator blade angle adjusting mechanism in an aircraft engine further includes:
and each pin correspondingly hinges one end of one rocker arm back to the corresponding upper journal on the periphery of the linkage ring.
According to at least one embodiment of the present application, the stator blade angle adjusting mechanism in an aircraft engine further includes:
and each joint bearing is correspondingly connected with one end of one pin and the corresponding rocker arm, which is opposite to the corresponding upper shaft neck.
Drawings
FIG. 1 is a schematic view of a stator vane angle adjustment mechanism in an aircraft engine provided by an embodiment of the present application;
FIG. 2 is a partial view taken from the direction A of FIG. 1;
wherein:
1-a rocker arm; 2-a stator case; 3-stator blades; 4-a linkage ring; 5-folding edges; 6-actuating cylinder; 7-connecting the bracket; 8-an annular projection; 9-pins; 10-knuckle bearing.
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.
A stator blade turning angle adjustment mechanism in an aircraft engine, comprising:
a plurality of rocker arms 1 distributed along the circumferential direction of the stator case 2; one end of each rocker arm 1 is correspondingly connected with an upper journal of a stator blade 3 extending out of a mounting hole of the stator casing 2;
the linkage ring 4 is sleeved on the periphery of the stator casing 2, is hinged with the other end of each rocker arm 1, and is provided with an outward folded edge 5 at one side back to each upper shaft neck;
the actuating cylinder 6 is connected between the stator casing 2 and the linkage ring 4, so that the linkage ring 4 can be driven to axially move along the stator casing 2 and circumferentially rotate along the stator casing 2, and each rocker arm 1 is driven to circumferentially swing along the stator casing 2, and each stator blade 3 is enabled to synchronously rotate.
For the stator blade rotation angle adjusting mechanism in the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that the side of the link ring 4 facing away from each upper journal is provided with an outward folded edge 5 to provide a spatial position for the connection of the actuator cylinder 6 thereon, and the actuator cylinder 6 is connected to the folded edge 5, so that the interference with each rocker arm 1 can be avoided, and the accurate adjustment of the rotation angle of each stator blade can be ensured.
In some alternative embodiments, in the stator vane angle adjusting mechanism in the aircraft engine, the connecting bracket 7 is connected between the flange 5 and the actuator cylinder 6.
In some alternative embodiments, in the stator vane angle adjusting mechanism in the aircraft engine, the actuating cylinder 6 and the corresponding flange 5 and the connecting bracket 7 are provided in plurality.
In some alternative embodiments, in the above-mentioned stator vane angle adjusting mechanism for an aircraft engine, the outer wall of the stator casing 2 has an annular protruding portion 8, and the annular protruding portion 8 abuts against the inner side of the link ring 4.
For the stator blade rotation angle adjusting mechanism in the aircraft engine disclosed in the above embodiment, those skilled in the art can understand that the outer wall of the stator casing 2 is designed to have the annular protruding portion 8 abutting against the inner side of the link ring 4, so that the roundness of the link ring 4 can be effectively ensured, the link ring 4 is prevented from generating large radial deformation, and the precision of adjusting the rotation angle of each stator blade 3 is ensured.
In some optional embodiments, in the above stator blade angle adjusting mechanism in an aircraft engine, further comprising:
a plurality of pins 9, each pin 9 hinging one end of one rocker arm 1, facing away from the corresponding upper journal, to the periphery of the link ring 4.
In some optional embodiments, in the above stator blade angle adjusting mechanism in an aircraft engine, further comprising:
a plurality of spherical plain bearings 10, each spherical plain bearing 10 being connected to the end of a pin 9 facing away from the respective upper journal of the respective rocker arm 1.
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 a stator blade turned angle adjustment mechanism among aeroengine which characterized in that includes:
a plurality of rocker arms (1) distributed along the circumferential direction of the stator casing (2); one end of each rocker arm (1) is correspondingly connected with an upper journal of a stator blade (3) extending out of the mounting hole of the stator casing (2);
the linkage ring (4) is sleeved on the periphery of the stator casing (2), is hinged with the other end of each rocker arm (1), and is provided with an outward folded edge (5) at one side back to each upper shaft neck;
the actuating cylinder (6) is connected between the stator casing (2) and the linkage ring (4) and can drive the linkage ring (4) to axially move along the stator casing (2) and circumferentially rotate along the stator casing (2), so that the rocker arms (1) are driven to circumferentially swing along the stator casing (2), and the stator blades (3) are synchronously rotated.
2. The mechanism for adjusting the rotational angle of a stator blade in an aircraft engine according to claim 1,
and the connecting bracket (7) is connected between the folding edge (5) and the actuating cylinder (6).
3. The mechanism of adjusting the rotational angle of a stator blade in an aircraft engine according to claim 2,
the actuating cylinders (6) and the corresponding folding edges (5) and the connecting supports (7) are multiple.
4. The mechanism for adjusting the rotational angle of a stator blade in an aircraft engine according to claim 1,
the outer wall of the stator casing (2) is provided with an annular protruding part (8), and the annular protruding part (8) abuts against the inner side of the linkage ring (4).
5. The mechanism for adjusting the rotational angle of a stator blade in an aircraft engine according to claim 1,
further comprising:
a plurality of pins (9), wherein one end of one rocker arm (1) which is back to the corresponding upper journal is hinged to the periphery of the linkage ring (4) by each pin (9).
6. The mechanism of adjusting the angle of a stator vane in an aircraft engine according to claim 5,
and each joint bearing (10) is correspondingly connected to one end, back to the corresponding upper shaft neck, of the pin (9) and the corresponding rocker arm (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111250267.2A CN113863992A (en) | 2021-10-26 | 2021-10-26 | Stator blade rotation angle adjustment mechanism among aeroengine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111250267.2A CN113863992A (en) | 2021-10-26 | 2021-10-26 | Stator blade rotation angle adjustment mechanism among aeroengine |
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| CN113863992A true CN113863992A (en) | 2021-12-31 |
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| CN202111250267.2A Pending CN113863992A (en) | 2021-10-26 | 2021-10-26 | Stator blade rotation angle adjustment mechanism among aeroengine |
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