CN113833695A - Stator blade angle adjusting mechanism of compressor in engine - Google Patents
Stator blade angle adjusting mechanism of compressor in engine Download PDFInfo
- Publication number
- CN113833695A CN113833695A CN202111272363.7A CN202111272363A CN113833695A CN 113833695 A CN113833695 A CN 113833695A CN 202111272363 A CN202111272363 A CN 202111272363A CN 113833695 A CN113833695 A CN 113833695A
- Authority
- CN
- China
- Prior art keywords
- rocker arm
- stator
- compressor
- section rocker
- adjusting mechanism
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 53
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Images
Classifications
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/002—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by varying geometry within the pumps, e.g. by adjusting vanes
Abstract
The application belongs to the technical field of stator blade angle adjustment design of a compressor in an engine, and particularly relates to a stator blade angle adjusting mechanism of a compressor in an engine, which comprises: each rear-section rocker arm is correspondingly connected with an upper journal of a stator blade extending out of the stator casing mounting hole; one end of each front-section rocker arm is correspondingly hinged with the other end of one rear-section rocker arm; and the linkage ring is sleeved on the stator casing, is hinged with the other end of each front-section rocker arm, and can rotate along the circumferential direction of the stator casing to drive each front-section rocker arm and each rear-section rocker arm to synchronously swing in the circumferential direction of the stator casing so as to synchronously rotate each stator blade.
Description
Technical Field
The application belongs to the technical field of stator blade angle adjusting design of a compressor in an engine, and particularly relates to a stator blade angle adjusting mechanism of a compressor in an 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 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 stator blade angle adjusting mechanism of the compressor in the existing 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 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 of adjusting the angle of the stator blade by the linkage ring driven by the actuating cylinder, the linkage ring moves 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) the link ring needs to move axially along the stator casing, if an interference structure exists in the axial movement range of the link ring, such as a pipeline, a connecting edge and various bolts outside the stator casing, the link ring needs to be designed to have larger radial size, so that the rigidity of the link ring is weakened, the link ring is easy to deform greatly, the accurate adjustment of the rotation angle of the stator blade is further influenced, the rocker arms need to move outwards in the direction away from the stator casing in an overall adaptive manner, the height of the journal on each stator blade extending out of the mounting hole is correspondingly increased, the strength of the journal on each stator blade is required to be higher, and the overall dimension of the engine is increased;
3) 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
The present application is directed to a stator vane angle adjustment mechanism for a compressor in an engine that overcomes or mitigates at least one aspect of the technical disadvantages known to exist.
The technical scheme of the application is as follows:
a stator blade angle adjusting mechanism of a compressor in an engine comprises:
each rear-section rocker arm is correspondingly connected with an upper journal of a stator blade extending out of the stator casing mounting hole;
one end of each front-section rocker arm is correspondingly hinged with the other end of one rear-section rocker arm;
and the linkage ring is sleeved on the stator casing, is hinged with the other end of each front-section rocker arm, and can rotate along the circumferential direction of the stator casing to drive each front-section rocker arm and each rear-section rocker arm to synchronously swing in the circumferential direction of the stator casing so as to synchronously rotate each stator blade.
According to at least one embodiment of the application, in the stator blade angle adjusting mechanism of the compressor in the engine, one end, away from the corresponding upper shaft neck, of each rear-section rocker arm is hinged to one end, away from the linkage ring, of the corresponding front-section rocker arm through a single-lug and double-lug structure in a matched mode.
According to at least one embodiment of the application, in the stator blade angle adjusting mechanism of the compressor in the engine, the linkage ring is provided with a plurality of slots;
one end of each front-section rocker arm, which is back to the corresponding rear-section rocker arm, is correspondingly inserted into one slot;
compressor stator blade angle adjustment mechanism in engine still includes:
and each pin correspondingly enables one front-section rocker arm to be back to one end of the corresponding rear-section rocker arm and is hinged in the corresponding slot.
According to at least one embodiment of the present application, in the stator blade angle adjusting mechanism of a compressor in an engine, the mechanism further includes:
and each joint bearing is correspondingly sleeved on one pin, and the outer ring of the joint bearing is connected with one end of the corresponding front-section rocker arm back to the corresponding rear-section rocker arm.
According to at least one embodiment of the application, in the stator blade angle adjusting mechanism of the compressor in the engine, one end, back to the corresponding rear section rocker arm, of each front section rocker arm is provided with a connecting hole;
each connecting hole is sleeved on the outer ring of the corresponding joint bearing.
According to at least one embodiment of the application, in the stator blade angle adjusting mechanism of the compressor in the engine, the stator casing is provided with an axial stop groove;
the linkage ring is provided with an axial stop edge; the axial stop edge is clamped into the axial stop groove and can slide along the axial stop groove in the circumferential direction.
According to at least one embodiment of the application, in the stator blade angle adjusting mechanism of the compressor in the engine, the stator casing is provided with a plurality of bosses distributed along the circumferential direction;
the axial stop edge is provided with a plurality of through openings, and the bosses are distributed in a staggered mode in the circumferential direction of the stator casing.
According to at least one embodiment of the application, in the stator blade angle adjusting mechanism of the compressor in the engine, the stator casing is provided with an annular runway;
the linkage ring is provided with a plurality of through holes;
compressor stator blade angle adjustment mechanism still includes in the engine:
and each radial positioning pin is correspondingly arranged in one through hole, extends into the annular runway and can slide along the annular runway in the circumferential direction of the stator casing.
According to at least one embodiment of the present application, in the stator blade angle adjusting mechanism of a compressor in an engine, the mechanism further includes:
the actuating cylinder is connected between the stator casing and the linkage ring (5) and can drive the linkage ring (5) to rotate along the circumferential direction of the stator casing (3).
Drawings
FIG. 1 is a schematic diagram of a stator vane angle adjustment mechanism of a compressor in a prior art engine;
FIG. 2 is a schematic diagram of a stator vane angle adjustment mechanism of a compressor in an engine according to an embodiment of the present disclosure;
FIG. 3 is a schematic illustration of a rear rocker arm provided by an embodiment of the present application;
FIG. 4 is a schematic illustration of a forward swing arm provided by an embodiment of the present application;
wherein:
1-rear section rocker arm; 2-stator blades; 3-a stator case; 4-front segment rocker arm; 5-a linkage ring; 6-pin; 7-knuckle bearing; 8-an axial stop edge; 9-boss.
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.
A stator blade angle adjusting mechanism of a compressor in an engine comprises:
each rear-section rocker arm 1 is correspondingly connected with an upper journal of a stator blade 2 extending out of a mounting hole of a stator casing 3;
one end of each front-section rocker arm 4 is correspondingly hinged with the other end of one rear-section rocker arm 1;
and the linkage ring 5 is sleeved on the stator casing 3, is hinged with the other end of each front-section rocker arm 4, and can rotate along the circumferential direction of the stator casing 3 to drive each front-section rocker arm 4 and each rear-section rocker arm 1 to synchronously swing in the circumferential direction of the stator casing 3, so that each stator blade 2 synchronously rotates.
To the stator blade angle adjustment mechanism of the engine compressor disclosed in the above embodiment, as can be understood by those skilled in the art, the link ring 5 drives each front-section rocker arm 4, and the rear-section rocker arm 1 swings synchronously in the circumferential direction of the stator casing 3, each front-section rocker arm 4 can swing axially along the stator casing 3 relative to the corresponding rear-section rocker arm 1, an included angle between each front-section rocker arm 4 and the corresponding rear-section rocker arm 1 changes, and the effective length between the front-section rocker arms and the rear-section rocker arms changes adaptively, so as to reduce the axial force along the stator casing 3 borne by the link ring 5, thereby avoiding the link ring 5 from deforming greatly, and ensuring the accurate adjustment of the rotation angle of the stator blade 2.
For the stator blade angle adjusting mechanism of the compressor in the engine disclosed in the above embodiment, it can be understood by those skilled in the art that, in the process of adjusting the rotation angle of each stator blade 2, only the linkage ring 5 needs to rotate along the circumferential direction of the stator casing 3, and the problem of interference between the axial movement of the linkage ring 5 along the stator casing 3 and the external structure of the stator casing does not need to be considered, and the linkage ring 5 can be designed to have a relatively small radial dimension to maintain sufficient rigidity, avoid serious deformation, influence on the accuracy of adjusting the rotation angle of the stator blade 2, and do not need to additionally increase the height of the journal of each stator blade 2 extending out of the mounting hole, and do not additionally increase the overall dimension of the engine.
In some alternative embodiments, in the stator blade angle adjusting mechanism of the compressor in the engine, an end of each rear rocker arm 1 away from the corresponding upper journal is hinged to an end of the corresponding front rocker arm 4 away from the linkage ring 5 by a single-lug structure.
In some alternative embodiments, in the stator vane angle adjusting mechanism of the compressor in the engine, the linkage ring 5 has a plurality of slots;
one end of each front-section rocker arm 4, which is back to the corresponding rear-section rocker arm 1, is correspondingly inserted into one slot;
compressor stator blade angle adjustment mechanism in engine still includes:
a plurality of pins 6, each pin 6 is corresponding with the one end that corresponds back section rocking arm 1 with a anterior segment rocking arm 4 dorsad, articulates in the slot that corresponds.
In some optional embodiments, in the stator blade angle adjusting mechanism of a compressor in an engine, the mechanism further includes:
a plurality of joint bearings 7, every joint bearing 7 corresponds to cup joint on a pin 6, and its outer lane is connected with the one end that corresponds back end rocking arm 1 dorsad corresponding anterior segment rocking arm 4.
In some optional embodiments, in the stator blade angle adjusting mechanism of a compressor in the engine, one end of each front-section rocker arm 4, which faces away from the corresponding rear-section rocker arm 1, is provided with a connecting hole;
each connecting hole is sleeved on the outer ring of the corresponding joint bearing 7.
To the stator blade angle adjusting mechanism of the engine compressor disclosed in the above embodiment, as can be understood by those skilled in the art, the link ring 5 drives each front-section rocker arm 4, and the rear-section rocker arm 1 synchronously swings in the circumferential direction of the stator casing 3, because each front-section rocker arm 4 can swing axially along the stator casing 3 relative to the corresponding rear-section rocker arm 1, the included angle between each front-section rocker arm 4 and the corresponding rear-section rocker arm 1 changes, and the effective length between the front-section rocker arms and the rear-section rocker arms changes adaptively, the size and position errors caused by the introduction of the processing and assembling processes can be eliminated to a certain extent, and the situation that each knuckle bearing 9 is blocked is avoided.
In some alternative embodiments, in the stator vane angle adjusting mechanism of the compressor in the engine, the stator casing 3 is provided with an axial stop groove;
the linkage ring 5 is provided with an axial stop edge 8; the axial stopping edge 8 is clamped into the axial stopping groove and can slide along the axial stopping groove in the circumferential direction, so that the linkage ring 5 can be limited to slide along the axial direction of the stator casing 3, and each front-section rocker arm 4 is prevented from being separated from the corresponding rear-section rocker arm 1.
In some optional embodiments, in the stator blade angle adjusting mechanism of the compressor in the engine, the stator casing 3 has a plurality of bosses 9 distributed along the circumferential direction;
the axial stop edge 8 has a plurality of openings, the projections 9 being distributed in a staggered manner in the circumferential direction of the stator casing 3.
For the stator blade angle adjusting mechanism of the engine compressor disclosed in the above embodiment, as can be understood by those skilled in the art, when the linking ring 5 is assembled to the stator casing 3, the angle of the linking ring may be adjusted, so that each through opening on the axial stopping edge 8 of the linking ring 5 is directly opposite to each boss 9 on the stator casing 3, the linking ring 5 is axially pushed along the stator casing 3, the axial stopping edge 8 of the linking ring 5 avoids each boss 9 and is clamped into the axial stopping groove, and then the linking ring 5 is circumferentially rotated along the stator casing 3, so that each through opening and each boss 9 are circumferentially staggered in the stator casing 3, so as to prevent the axial stopping edge 8 from coming out of the axial stopping groove.
In some alternative embodiments, in the stator blade angle adjusting mechanism of the compressor in the engine, the stator casing 3 has an annular runway thereon;
the linkage ring 5 is provided with a plurality of through holes;
compressor stator blade angle adjustment mechanism still includes in the engine:
and each radial positioning pin is correspondingly arranged in one through hole, extends into the annular runway and can slide along the annular runway in the circumferential direction of the stator casing 3.
To the stator blade angle adjusting mechanism of the compressor in the engine disclosed in the above embodiment, those skilled in the art can understand that the existence of each radial positioning pin can effectively ensure the roundness of the link ring 5, so that the link ring 5 and the stator casing 3 are kept concentric, thereby avoiding that a large deformation is radially launched on the stator casing 3 to affect the adjusting precision of the rotation angle of each stator blade 2, and in addition, the radial positioning pin can be matched with the annular runway to limit the axial sliding of the link ring 5 along the stator casing 3, so as to prevent each front-section rocker arm 4 from being separated from the corresponding rear-section rocker arm 1.
In some optional embodiments, in the stator blade angle adjusting mechanism of a compressor in an engine, the mechanism further includes:
and an actuator cylinder connected between the stator case 3 and the link ring 5 to drive the link ring 5 to rotate in the circumferential direction of the stator case 3.
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 (9)
1. The utility model provides a compressor stator blade angle adjustment mechanism in engine which characterized in that includes:
each rear-section rocker arm (1) is correspondingly connected with an upper journal of a stator blade (2) extending out of a mounting hole of the stator casing (3);
a plurality of front-section rocker arms (4), wherein one end of each front-section rocker arm (4) is correspondingly hinged with the other end of one rear-section rocker arm (1);
and the linkage ring (5) is sleeved on the stator casing (3) and is hinged with the other end of the front-section rocker arm (4) to drive the stator casing (3) to rotate in the circumferential direction so as to drive the front-section rocker arm (4) and the rear-section rocker arm (1) to synchronously swing in the circumferential direction of the stator casing (3) to enable the stator blades (2) to synchronously rotate.
2. The stator vane angle adjusting mechanism of a compressor in an engine according to claim 1,
and one end of each rear-section rocker arm (1) far away from the corresponding upper shaft neck and one end of the corresponding front-section rocker arm (4) far away from the linkage ring (5) are hinged in a matched manner through a single-lug and double-lug structure.
3. The stator vane angle adjusting mechanism of a compressor in an engine according to claim 1,
the linkage ring (5) is provided with a plurality of slots;
one end of each front-section rocker arm (4), which is back to the corresponding rear-section rocker arm (1), is correspondingly inserted into one slot;
compressor stator blade angle adjustment mechanism in engine still includes:
and each pin (6) correspondingly connects one end of the front-section rocker arm (4) back to the corresponding rear-section rocker arm (1) and is hinged in the corresponding slot.
4. The stator vane angle adjusting mechanism of a compressor in an engine according to claim 3,
further comprising:
and each joint bearing (7) is correspondingly sleeved on one pin (6), and the outer ring of each joint bearing (7) is connected with one end of the corresponding front-section rocker arm (4) back to the corresponding rear-section rocker arm (1).
5. The stator vane angle adjusting mechanism of a compressor in an engine according to claim 4,
one end of each front-section rocker arm (4) back to the corresponding rear-section rocker arm (1) is provided with a connecting hole;
each connecting hole is sleeved on the outer ring of the corresponding joint bearing (7).
6. The stator vane angle adjusting mechanism of a compressor in an engine according to claim 1,
the stator casing (3) is provided with an axial stop groove;
the linkage ring (5) is provided with an axial stop edge (8); the axial stop edge (8) is clamped into the axial stop groove and can slide along the axial stop groove in the circumferential direction.
7. The stator vane angle adjusting mechanism of a compressor in an engine according to claim 6,
the stator casing (3) is provided with a plurality of bosses (9) distributed along the circumferential direction;
the axial stop edge (8) is provided with a plurality of through openings, and the bosses (9) are distributed in a staggered mode in the circumferential direction of the stator casing (3).
8. The stator vane angle adjusting mechanism of a compressor in an engine according to claim 1,
the stator casing (3) is provided with an annular runway;
the linkage ring (5) is provided with a plurality of through holes;
compressor stator blade angle adjustment mechanism still includes in the engine:
and each radial positioning pin is correspondingly arranged in one through hole, extends into the annular runway and can slide along the annular runway in the circumferential direction of the stator casing (3).
9. The stator vane angle adjusting mechanism of a compressor in an engine according to claim 1,
further comprising:
and the actuating cylinder is connected between the stator casing (3) and the linkage ring (5) and can drive the linkage ring (5) to rotate along the circumferential direction of the stator casing (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111272363.7A CN113833695A (en) | 2021-10-29 | 2021-10-29 | Stator blade angle adjusting mechanism of compressor in engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111272363.7A CN113833695A (en) | 2021-10-29 | 2021-10-29 | Stator blade angle adjusting mechanism of compressor in engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113833695A true CN113833695A (en) | 2021-12-24 |
Family
ID=78966589
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111272363.7A Pending CN113833695A (en) | 2021-10-29 | 2021-10-29 | Stator blade angle adjusting mechanism of compressor in engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113833695A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114776634A (en) * | 2022-05-12 | 2022-07-22 | 中国空气动力研究与发展中心空天技术研究所 | Engine inlet guide vane angle adjusting mechanism |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103277339A (en) * | 2013-06-26 | 2013-09-04 | 上海交通大学 | Multistage stationary blade adjusting mechanism of gas compressor including universal-like pairs |
| CN106545524A (en) * | 2015-09-23 | 2017-03-29 | 中航商用航空发动机有限责任公司 | Compressor stator blade governor motion |
| JP2018178835A (en) * | 2017-04-11 | 2018-11-15 | 株式会社Ihi | Variable stator blade |
| US20190048738A1 (en) * | 2017-08-14 | 2019-02-14 | Safran Aero Boosters Sa | System of Variable Stator Vanes For A Turbine Engine |
| CN209483698U (en) * | 2019-01-24 | 2019-10-11 | 中国航发商用航空发动机有限责任公司 | Link ring supporting mechanism, stator blade regulating mechanism and compressor |
| 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 |
| CN214146025U (en) * | 2021-01-18 | 2021-09-07 | 中国航发商用航空发动机有限责任公司 | Fixed blade adjusting mechanism of gas compressor |
-
2021
- 2021-10-29 CN CN202111272363.7A patent/CN113833695A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103277339A (en) * | 2013-06-26 | 2013-09-04 | 上海交通大学 | Multistage stationary blade adjusting mechanism of gas compressor including universal-like pairs |
| CN106545524A (en) * | 2015-09-23 | 2017-03-29 | 中航商用航空发动机有限责任公司 | Compressor stator blade governor motion |
| JP2018178835A (en) * | 2017-04-11 | 2018-11-15 | 株式会社Ihi | Variable stator blade |
| US20190048738A1 (en) * | 2017-08-14 | 2019-02-14 | Safran Aero Boosters Sa | System of Variable Stator Vanes For A Turbine Engine |
| CN209483698U (en) * | 2019-01-24 | 2019-10-11 | 中国航发商用航空发动机有限责任公司 | Link ring supporting mechanism, stator blade regulating mechanism and compressor |
| 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 |
| CN214146025U (en) * | 2021-01-18 | 2021-09-07 | 中国航发商用航空发动机有限责任公司 | Fixed blade adjusting mechanism of gas compressor |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114776634A (en) * | 2022-05-12 | 2022-07-22 | 中国空气动力研究与发展中心空天技术研究所 | Engine inlet guide vane angle adjusting mechanism |
| CN114776634B (en) * | 2022-05-12 | 2023-11-03 | 中国空气动力研究与发展中心空天技术研究所 | Engine inlet guide vane angle adjusting mechanism |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8376692B2 (en) | Turbo compressor in an axial type of construction | |
| US10400622B2 (en) | Guide vane adjusting device and turbomachine | |
| CN111911461B (en) | Stator blade angle adjusting mechanism and stator casing structure thereof | |
| KR101146641B1 (en) | Variable capacity-type exhaust turbo supercharger equipped with variable nozzle mechanism | |
| CN111561471A (en) | Stator blade rotation angle adjusting mechanism | |
| JPS62282126A (en) | Variable nozzle structure for turbine | |
| CN113833695A (en) | Stator blade angle adjusting mechanism of compressor in engine | |
| CN214146025U (en) | Fixed blade adjusting mechanism of gas compressor | |
| CN104047812A (en) | Bearing with a supporting element and method of supporting a first ring of a bearing | |
| CN113202621B (en) | Stator blade rotation angle adjusting mechanism | |
| CN102713309A (en) | Device for adjusting variable guide vanes | |
| CN113864245A (en) | Engine stator blade angle adjusting mechanism | |
| CN111561474A (en) | Stator structure and assembling method thereof | |
| CN114151381A (en) | Stator blade angle adjusting mechanism in engine | |
| CN108757509B (en) | Low-pressure compressor structure of gas turbine | |
| CN115949623A (en) | Aero-engine compressor stator blade angle adjusting mechanism | |
| CN113883090B (en) | Aero-engine stator blade rotation angle adjusting mechanism | |
| CN115962156A (en) | Adjustable blade angle adjustment mechanism of compressor in aircraft engine | |
| CN106437878B (en) | Method for producing a variable-geometry turbine of an exhaust-gas turbocharger | |
| CN113863992A (en) | Stator blade rotation angle adjustment mechanism among aeroengine | |
| CN115788965A (en) | Adjustable stator blade adjusting mechanism of aero-engine | |
| CN114526126A (en) | Inlet variable-camber guide vane structure capable of eliminating rotary boss | |
| CN113863993A (en) | Stator blade angle adjusting mechanism in aircraft engine | |
| JP2018178835A (en) | Variable stator blade | |
| CN113883089B (en) | Angle adjusting mechanism for stator blade of aero-engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20211224 |