CN115788965A - Adjustable stator blade adjusting mechanism of aero-engine - Google Patents
Adjustable stator blade adjusting mechanism of aero-engine Download PDFInfo
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- CN115788965A CN115788965A CN202211550472.5A CN202211550472A CN115788965A CN 115788965 A CN115788965 A CN 115788965A CN 202211550472 A CN202211550472 A CN 202211550472A CN 115788965 A CN115788965 A CN 115788965A
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- adjustable stator
- rocker arm
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Abstract
The application belongs to the technical field of adjustable stator blade of aeroengine and adjusts design, concretely relates to adjustable stator blade adjustment mechanism of aeroengine includes: each rocker arm is correspondingly connected with an upper journal of an adjustable stator blade extending out of the stator casing mounting hole; the linkage ring is sleeved on the stator casing, is hinged with the other end of each rocker arm and is formed by butt joint of two halves; each first bracket is correspondingly connected to a butt joint part of the two half linkage rings; the two second brackets are connected to the stator casing; each actuating cylinder is correspondingly hinged between the first support and the second support so as to drive the linkage ring to axially move and circumferentially rotate along the stator box, and each adjustable stator blade is driven to synchronously rotate through each rocker arm, so that the rotating angle of each stator blade is synchronously adjusted.
Description
Technical Field
The application belongs to the technical field of adjustable stator blade adjusting design of aero-engines, and particularly relates to an adjustable stator blade adjusting mechanism of an aero-engine.
Background
In order to ensure that the aero-engine can work efficiently under various working conditions, the air flow entering the aero-engine needs to be adjusted according to actual conditions, and therefore, part of the stator blades in the air compression are adjustable stator blades with adjustable angles.
The adjustable stator blade adjusting mechanism mainly comprises a plurality of rocker arms, a linkage ring, a pull rod, a support, an L-shaped rod and an actuating cylinder, wherein one end of each rocker arm is correspondingly connected with an upper journal of one adjustable stator blade extending out of the stator casing; the linkage ring is sleeved on the stator casing and is hinged with the other end of each rocker arm; one end of the pull rod is hinged on the linkage ring; the bracket is connected to the stator casing; the bent angle part of the L-shaped rod is hinged on the bracket, and one end of the L-shaped rod is connected with the other end of the pull rod and is hinged with the other end of the pull rod; the cylinder body of the actuating cylinder is hinged on the support, the piston rod is hinged with the other end of the L-shaped rod, therefore, the linkage ring is driven by the L-shaped rod and the pull rod to move along the axial direction and rotate along the circumferential direction of the stator box through the extension of the piston rod, each rocker arm is driven to swing synchronously, each adjustable stator blade is driven to rotate synchronously, and the synchronous adjustment of the rotating angle of each stator blade is realized, as shown in figure 1, in order to ensure the stable driving of the linkage ring, the actuating cylinder and the related part structures thereof are generally two and are symmetrically distributed along the circumferential direction of the stator box, and the technical scheme has the following defects:
1) The actuating cylinder is hinged with the linkage ring through the L-shaped rod, so that the number of kinematic pairs of the whole mechanism is increased, friction resistance factors are increased in the working process of the mechanism, tolerance accumulation of the mechanism can be increased, the clamping stagnation phenomenon in the working process of the mechanism is easy to cause, and the adjusting precision of the adjustable stator blade is reduced;
2) The linkage ring is of a whole-ring structure, is directly sleeved on the mirror stator casing along the axial direction, is designed to have a larger radial size for avoiding the external protruding part of the stator casing, is easy to deform in the working process of the mechanism, is difficult to ensure the adjusting precision of the adjustable stator blade, can increase the size of the whole mechanism, leads to the increase of the whole mass of the aero-engine, and is inconsistent with the weight reduction requirement of the current aero-engine.
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 adjustable stator vane adjustment mechanism for an aircraft engine that overcomes or mitigates at least one of the technical disadvantages of the known prior art.
The technical scheme of the application is as follows:
an adjustable stator blade adjustment mechanism for an aircraft engine, comprising:
each rocker arm is correspondingly connected with an upper journal of an adjustable stator blade extending out of the stator casing mounting hole;
the linkage ring is sleeved on the stator casing, is hinged with the other end of each rocker arm and is formed by butt joint of two halves;
each first bracket is correspondingly connected to a butt joint part of the two half linkage rings;
the two second brackets are connected to the stator casing;
each actuating cylinder is correspondingly hinged between the first support and the second support so as to drive the linkage ring to axially move and circumferentially rotate along the stator box, and each adjustable stator blade is driven to synchronously rotate through each rocker arm, so that the rotating angle of each stator blade is synchronously adjusted.
According to at least one embodiment of the application, in the adjustable stator vane adjusting mechanism of the aircraft engine, one end of each rocker arm, which faces away from the linkage ring, is connected to the end of the journal on the corresponding adjustable stator vane through a screw.
According to at least one embodiment of the application, in the adjustable stator vane adjusting mechanism of the aircraft engine, each rocker arm is hinged to the linkage ring through a pin joint bearing, and the end, facing away from the journal, of the corresponding adjustable stator vane is hinged to the linkage ring through a pin joint bearing.
According to at least one embodiment of the application, in the adjustable stator blade adjusting mechanism of the aircraft engine, the stator casing is provided with an annular protrusion;
the annular protrusion is located on the inner side of the linkage ring, and a small gap is formed between the annular protrusion and the linkage ring.
According to at least one embodiment of the application, in the adjustable stator blade adjusting mechanism of the aircraft engine, the two actuating cylinders are hinged between the corresponding first bracket and the corresponding second bracket through pin-fit joint bearings.
According to at least one embodiment of the application, in the adjustable stator vane adjusting mechanism of the aircraft engine, when each rocker arm is in the axial direction of the stator casing, the two actuating cylinders are in the vertical direction in the axial direction of the stator casing.
Drawings
FIG. 1 is a schematic view of a prior art adjustable stator vane adjustment mechanism for an aircraft engine;
FIG. 2 is a schematic view of an adjustable stator vane adjustment mechanism of an aircraft engine provided by an embodiment of the present application;
FIG. 3 is a view from the direction A of FIG. 2;
wherein:
1, a rocker arm; 2-adjustable stator blades; 3-a stator case; 4-a linkage ring; 5-a first support; 6-a second bracket; 7-an actuating cylinder.
For a better understanding of the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced, and do not represent actual product dimensions, and the drawings are for illustrative purposes only and are not to be construed as limiting the present 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 description of the application should not be construed as an absolute limitation of quantity, 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 should be noted that, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and the like as used in the description of the present application are to be construed broadly, e.g., the connection may be a fixed connection, a detachable connection, or an integral connection; 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 adjustable stator blade adjustment mechanism for an aircraft engine, comprising:
each rocker arm 1 is correspondingly connected with an upper journal of an adjustable stator blade 2 extending out of a mounting hole of a stator casing 3;
the linkage ring 4 is sleeved on the stator casing 3, is hinged with the other end of each rocker arm 4 and is formed by butt joint of two halves;
two first brackets 5, wherein each first bracket 5 is correspondingly connected to one butt joint part of the two half linkage rings 4;
two second brackets 6 connected to the stator case 3;
two actuating cylinders 7, each actuating cylinder 7 is correspondingly hinged between a first bracket 5 and a second bracket 6 so as to drive the linkage ring 4 to axially move and circumferentially rotate along the stator box 3, and each adjustable stator blade 2 is driven to synchronously rotate through each rocker arm 1, so that the rotating angle of each stator blade 2 is synchronously adjusted.
For the adjustable stator blade adjusting mechanism of the aero-engine disclosed in the above embodiment, as can be understood by those skilled in the art, two actuating cylinders 7 are designed to be directly connected to the link ring 4 through a bracket to directly drive the link ring 4, so that the number of kinematic pairs of the whole mechanism can be reduced, the frictional resistance of the mechanism in the working process can be reduced, the possibility of tolerance accumulation of the mechanism can be reduced, the clamping stagnation phenomenon in the working process of the mechanism can be avoided, and the reduction of the adjusting precision of the adjustable stator blade 2 can be ensured.
For the adjustable stator blade adjusting mechanism of the aero-engine disclosed by the embodiment, as can be further understood by those skilled in the art, the coupling ring 4 is formed by two half portions in butt joint, and during assembly, the two half portions can be directly in butt joint at corresponding positions on the stator casing 3, so that interference of an external protruding portion of the whole ring structure on the stator casing 3 in an axially sleeved mode can be avoided, the adjustable stator blade adjusting mechanism can be designed to have a smaller radial size, the possibility of deformation is reduced in the working process of the mechanism, the adjusting accuracy of the adjustable stator blade 2 is guaranteed, the two half portions of the coupling ring 4 are connected through the two first supports 5, specifically, the two half portions of the coupling ring can be connected through bolts, the overall mass of the aero-engine cannot be additionally and greatly increased, and weight reduction of the aero-engine is facilitated.
In some alternative embodiments, in the above-mentioned adjustable stator vane adjusting mechanism for an aircraft engine, one end of each rocker arm 1, which faces away from the link ring 4, is connected to the end of the journal on the corresponding adjustable stator vane 2 by a screw.
In some alternative embodiments, in the above-mentioned adjustable stator vane adjusting mechanism for an aircraft engine, each rocker arm 1 is hinged to the link ring 4 with a pin joint bearing at an end facing away from the journal of the corresponding adjustable stator vane 2.
In some alternative embodiments, in the above-mentioned adjustable stator vane adjusting mechanism for an aircraft engine, the stator casing 3 has an annular protrusion thereon;
the annular protrusion is located on the inner side of the linkage ring 4, a small gap exists between the annular protrusion and the linkage ring 4, and the annular protrusion can support the linkage ring 4 when the linkage ring 4 deforms, so that the linkage ring 4 is prevented from deforming greatly.
In some alternative embodiments, in the above-mentioned adjustable stator vane adjusting mechanism for an aircraft engine, two actuating cylinders 7 are hinged between the corresponding first bracket 5 and second bracket 6 by pin-fitting joint bearings.
In some optional embodiments, in the above adjustable stator vane adjusting mechanism for an aircraft engine, when each rocker arm 1 is along the axial direction of the stator case 3, the two actuating cylinders 7 are in the vertical direction of the axial direction of the stator case 3, that is, when each stator vane 2 is at the intermediate angle, the two actuating cylinders 7 are designed to be tangent to the link ring 4, so that the driving force of the two actuating cylinders 7 can be directly applied to the link ring 4 to the maximum extent, when the stator vane 2 needs to be driven by the intermediate angle, the actuating force is large, and the angle of each stator vane 2 can be flexibly adjusted.
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. An adjustable stator blade adjustment mechanism of an aircraft engine, comprising:
each rocker arm (1) is correspondingly connected with an upper journal of an adjustable stator blade (2) extending out of a mounting hole of a stator casing (3);
the linkage ring (4) is sleeved on the stator casing (3), is hinged with the other end of each rocker arm (4) and is formed by butt joint of two halves;
each first bracket (5) is correspondingly connected to one butt joint part of the two halves of the linkage ring (4);
two second brackets (6) connected to the stator case (3);
the two actuating cylinders (7) are correspondingly hinged between the first support (5) and the second support (6) so as to drive the linkage ring (4) to axially move and circumferentially rotate along the stator box (3), and the adjustable stator blades (2) are driven to synchronously rotate through the rocker arms (1), so that the rotating angles of the stator blades (2) are synchronously adjusted.
2. The aero-engine adjustable stator vane adjustment mechanism of claim 1,
one end of each rocker arm (1), which is back to the linkage ring (4), is connected with the end part of the upper shaft neck of the corresponding adjustable stator blade (2) through a screw.
3. The adjustable stator vane adjustment mechanism of an aircraft engine as defined in claim 1,
each rocker arm (1) is back to one end of the journal on the corresponding adjustable stator blade (2) and is hinged on the linkage ring (4) through a pin matched joint bearing.
4. The adjustable stator vane adjustment mechanism of an aircraft engine as defined in claim 1,
the stator casing (3) is provided with an annular bulge;
the annular protrusion is positioned on the inner side of the linkage ring (4), and a small gap is reserved between the annular protrusion and the linkage ring (4).
5. The adjustable stator vane adjustment mechanism of an aircraft engine as defined in claim 1,
the two actuating cylinders (7) are hinged between the corresponding first bracket (5) and the corresponding second bracket (6) through pin matching joint bearings.
6. The adjustable stator vane adjustment mechanism of an aircraft engine as defined in claim 1,
when each rocker arm (1) is along the axial direction of the stator casing (3), the two actuating cylinders (7) are in the axial vertical direction of the stator casing (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211550472.5A CN115788965A (en) | 2022-12-05 | 2022-12-05 | Adjustable stator blade adjusting mechanism of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211550472.5A CN115788965A (en) | 2022-12-05 | 2022-12-05 | Adjustable stator blade adjusting mechanism of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115788965A true CN115788965A (en) | 2023-03-14 |
Family
ID=85445700
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211550472.5A Pending CN115788965A (en) | 2022-12-05 | 2022-12-05 | Adjustable stator blade adjusting mechanism of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115788965A (en) |
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2022
- 2022-12-05 CN CN202211550472.5A patent/CN115788965A/en active Pending
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