CN114962342B - Compressor end region vibration structure - Google Patents
Compressor end region vibration structure Download PDFInfo
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- CN114962342B CN114962342B CN202210585364.5A CN202210585364A CN114962342B CN 114962342 B CN114962342 B CN 114962342B CN 202210585364 A CN202210585364 A CN 202210585364A CN 114962342 B CN114962342 B CN 114962342B
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- compressor
- shell
- end region
- rotating shaft
- vibration structure
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- 235000001968 nicotinic acid Nutrition 0.000 claims abstract description 5
- 238000005457 optimization Methods 0.000 claims abstract description 3
- 238000000926 separation method Methods 0.000 claims description 13
- 241001505049 Balantiocheilos melanopterus Species 0.000 abstract description 3
- 230000003068 static effect Effects 0.000 description 8
- 238000010586 diagram Methods 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 239000011664 nicotinic acid Substances 0.000 description 2
- 230000001629 suppression Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000005684 electric field Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
Classifications
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
-
- 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
- F04D29/403—Casings; Connections of working fluid especially 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
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- 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
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a vibration structure of an end region of a gas compressor, which relates to the technical field of flow control of the gas compressor and comprises the following components: the device comprises a shell, a rotor, an eccentric block, a rotating shaft, a bearing and a motor; the number of the rotors is multiple; the rotors are sequentially sleeved on the rotating shaft; the rotating shaft is connected with the motor, and a bearing is arranged at the joint; the eccentric block is arranged on the rotating shaft; the shape of the shell is obtained by combining the shape of the silver shark dorsal fin based on the bionics principle and performing pneumatic optimization; the invention adopts the shape of the shell based on aerodynamic design to influence the flow of the fixed blade angular region of the compressor, and simultaneously, the eccentric block is provided with the frequency equivalent to the frequency of the non-fixed angular region, thereby eliminating the angular region separating structure of the fixed blade of the compressor, and playing the roles of improving the secondary flow and reducing the loss of the fixed blade of the compressor.
Description
Technical Field
The invention relates to the technical field of compressor flow control, in particular to a compressor end region vibration structure.
Background
With the continuous improvement of industrial technology, under the background of the rapid development of manufacturing technology and the gradual improvement of scientific research capability, the gas turbine with high power characteristics and high mobility advantages can be initially popularized and even widely applied to power systems of various ships and aviation airplanes. The compressor is used as a core component of the gas turbine, the internal flow of the compressor is extremely complex, and the pneumatic design also occupies the dominant position in the field of fluid mechanical design and has a larger specific gravity. The design difficulty of the compressor is significantly increased by the complexity of the internal flow of the compressor, and by the reverse pressure gradient in the channel, the severe boundary of the inlet stage and the high operating condition design of the preceding stage, and the complex flow in the corner region. Meanwhile, the problems of complicated change of a vortex structure, difficulty in capturing vortex geometry, interstage transmission of rotational instability and the like also cause the research and development of variable working conditions of the compressor to be hindered.
The secondary flow in the static blade end region of the compressor has larger influence on the disturbance and performance of the flow field. The occurrence of the wide-range separation phenomenon of the corner region significantly increases the total pressure loss of the compressor and deteriorates the downstream flow. There are some application means for controlling the secondary flow of the end region, such as endwall wing blades, asymmetric endwalls, cantilever arrangement of vanes, electromagnetic excitation, etc. The end wall vane blocks secondary flow, but the disturbance of the convection field is stronger, and meanwhile, the pressure difference between the vane and the suction surface is unavoidable. The asymmetric end wall is disposed about its entire perimeter She Huanna to inhibit radial flow but is relatively expensive to machine and dispose. The through flow of the root can be enhanced by the cantilever arrangement of the stator blade, but the blade is easy to deform under the stress, so that the service life of the blade is influenced. In addition, the electromagnetic excitation circuit is complex, and the application of an electric field in the actual engine is not easy to realize, so that the searching of a flow control means of the stator blade end region of the compressor, which is simple in arrangement and small in influence on the flow field, is a problem to be solved by a person skilled in the art.
Disclosure of Invention
In view of the above, the present invention provides a vibrating structure of a compressor end region, which overcomes the above-mentioned drawbacks.
In order to achieve the above object, the present invention provides the following technical solutions:
a compressor end region vibration structure comprising: the device comprises a shell, a rotor, an eccentric block, a rotating shaft, a bearing and a motor; the number of the rotors is multiple; the rotors are sequentially sleeved on the rotating shaft; the rotating shaft is connected with the motor, and the bearing is arranged at the joint; the eccentric block is arranged on the rotating shaft; the shape of the shell is obtained by pneumatic optimization based on a bionics principle.
Optionally, the height of the shell is 5% -10% of the height of a given blade; the thickness of the shell is between 0.5mm and 1 mm.
Optionally, the placing position of the vibration structure is:
in the axial direction, at 80% to 100% of the chord length of a given blade;
in the tangential direction, the tangential distance from the center point of the vibration structure to the surface of the given blade is 10% -15% of the chord length of the given blade.
In the radial direction, is placed on the lower end wall of a given blade.
Optionally, the vibration frequency of the eccentric mass is set according to the dimension of the angular separation.
Alternatively, when the small-scale angular regions are separated, the vibration frequency of the eccentric mass is zero.
Alternatively, when the mesoscale angular regions are separated, the vibration frequency of the eccentric mass is 3000Hz.
Alternatively, when the large-scale angular regions are separated, the vibration frequency of the eccentric mass is 6000Hz.
Optionally, the plurality of rotors are different in size.
Compared with the prior art, the invention discloses a vibration structure of a compressor end region, which adopts a shell shape based on aerodynamic design to influence the flow of a static blade angle region of the compressor, and meanwhile, the frequency equivalent to the frequency separated from an unsteady angle region is set through an eccentric block, so that the angle separation structure of the static blade of the compressor is eliminated, and the effects of improving secondary flow and reducing the loss of the static blade of the compressor are achieved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present invention, and that other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a three-dimensional model of a vibrating structure of a compressor end region according to the present invention;
FIG. 2 is a schematic diagram of the portion A in FIG. 1;
FIG. 3 is a radial schematic view of a vibrating structure in the end region of a compressor according to the present invention;
FIG. 4 is a schematic view of the outer shape and inner structure of the casing of the compressor end region vibration structure of the present invention;
FIG. 5 is a schematic diagram showing the frequency selection of the vibration structure of the compressor end region according to the present invention;
FIG. 6 is a graph comparing vane loss with original vane loss with a compressor tip region vibrating structure;
wherein 1 is a vibration structure of an end region of the air compressor; 2 is a static blade of the compressor; 3 is a hub; a is a stationary blade pressure surface; b is the suction surface of the stator blade; c is the incoming flow direction;
1-1 is a first rotor; 1-2 is a second rotor; 1-3 is a third rotor; 1-4 is a fourth rotor; 1-5 is a shell; 1-6 are eccentric blocks; 1-7 are rotation axes; 1-8 are bearings;
2-1 is the tail edge of the static blade of the compressor; 2-2 is the molded line at the blade root of the static blade of the compressor.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The embodiment of the invention discloses a vibration structure of an end region of a gas compressor, which is shown in fig. 4 and comprises the following components: 1-5 parts of a shell, 1-6 parts of a rotor, 1-7 parts of a rotating shaft, 1-8 parts of a bearing and a motor; the rotor is sleeved on the rotating shafts 1-7; the rotating shaft 1-7 is connected with a motor, and a bearing 1-8 is arranged at the joint; the eccentric block 1-6 is arranged on the rotating shaft 1-7; wherein the rotating shafts 1-7 are of a typical eccentric vibration structural design; the number of the rotors is more than one, in the embodiment, four rotors are respectively a first rotor 1-1, a second rotor 1-2, a third rotor 1-3, a fourth rotor 1-4, the maximum rotor (third rotor 1-3) diameter is 10% -15% of the chord length of a given blade according to actual flowing, and the other rotor diameters are determined by the shape of a shell 1-5; the shells 1-5 are designed based on bionics principles, in combination with silver shark dorsal fin shape, and aerodynamic principles of flow field analysis.
As shown in fig. 1 and 2, the vibration structure 1 of the compressor end region is arranged at the end wall of the hub 3 of the compressor stator blade ring, the arrangement position is in a stator blade corner region close to the tail edge 2-1 of the compressor stator blade, and the position of the vibration structure 1 of the compressor end region can be visually seen through the molded line 2-2 at the tail edge 2-1 of the compressor stator blade and the molded line 2-2 at the root of the compressor stator blade, wherein the shell 1-5 of the vibration structure is based on the principle of bionics, and the silver shark fin is combined for aerodynamic design, so that the vibration structure can have a suppression effect on small-scale corner separation.
Wherein, for the compressor end region vibration structure 1, its arrangement position specifically is:
(1) In the axial direction, the axial flow direction is arranged at the position of 80 to 100 percent of the chord length of the static blade 2 of the compressor, namely, the chord length is in the range of 20 percent of the chord length close to the tail edge;
(2) In the tangential direction, the tangential distance between the central point of the blade and the surface of the blade is 10% -15% of the chord length of the blade;
(3) In the radial direction, the structure is placed on the lower endwall of the compressor vane 2 (i.e., the hub 3).
Wherein, for the compressor end region vibrating structure 1, its dimensions are given:
(1) Taking the maximum rotor as a reference, the diameter range of the rotor is 10% -15% of the chord length of a given blade according to actual flow;
(2) The thickness of the shell 1-5 is given between 0.5mm and 1mm based on the maximum rotor;
(3) The height range of the shell 1-5 of the vibration structure is 5% -10% of the height of a given blade according to actual flowing conditions.
The arrangement mode has the following advantages:
(1) The structural arrangement position is positioned in the corner region in the typical flow of the compressor, and the separated flow can be directly and effectively controlled.
(2) The setting of the structural parameters refers to the dimension of angular separation flow in an actual compressor, and the size of the angular separation flow can ensure that the separation flow can be well restrained without causing extra loss.
It can be seen from fig. 3 that the vibration structure of the compressor end region includes two surfaces, namely a stator blade pressure surface a and a stator blade suction surface b, which are arranged on the stator blade suction surface b side near the trailing edge, and the diameter range of the vibration structure is 10% -15% of the chord length of a given blade according to actual flow based on the maximum rotor. The height range of the shell 1-5 of the compressor end region vibration structure 1 is 5% -10% of the height of a given blade according to actual flow. Taking a certain type of compressor stator blade as an example, if the chord length of a certain type of compressor stator blade 2 is 72.7mm, the maximum rotor diameter in the vibration structure is 11% of the chord length, namely 8mm, and the outer diameter of the shell 1-5 corresponding to the maximum rotor is 13% of the chord length, namely 9.45mm. The height of the stator blade 2 of a compressor of a certain model is 120mm, and the height of the bionic shell 1-5 of the vibrating structure is 7.5% of the chord length and is 9mm. The axial position is arranged at 86% of the chord length of the stator blade of the compressor, the axial distance from the front edge point is 52.18mm, and the tangential position is arranged at the tangential position, the tangential distance from the vibration structure to the surface of the blade is 11% of the chord length and 8mm. In which c is indicated as the direction of incoming flow in fig. 3.
Fig. 5 is a schematic diagram showing the frequency selection basis of the vibration structure 1 of the compressor end region, wherein three different types of lines 1/2/3 are the research results of different blade models, and the left graph and the right graph are the research results under the condition of different mach numbers, and it can be found that the mesoscale separation is mainly around 3000Hz, and the large scale separation is mainly distributed around 6000Hz, so that the vibration frequency of the vibration structure 1 of the compressor end region is controlled by means of the bionic aerodynamic design of the shells 1-5 without vibration under the small scale separation, the vibration frequency of 3000Hz is given under the mesoscale separation, and the vibration frequency of 6000Hz is given for the large scale angular region close to stall, and the adjustment mode is simple and easy to realize.
Fig. 6 is a loss comparison of the stator blade with the compressor end region vibration structure 1 and the original stator blade, and the curve is a total pressure loss coefficient radial distribution curve. Compared with the original stator blade, the stator blade with the compressor end region vibration structure 1 has the advantage that the total pressure loss coefficient is reduced by 17.97%.
Therefore, the invention has small structure volume, small disturbance to the flow field and enhanced suppression of angular separation; the shell shape based on aerodynamic design is adopted to influence the flow of the fixed blade angular region of the compressor, and meanwhile, the frequency equivalent to the frequency of the non-constant angular region is set through the eccentric block, so that the angular region separating structure of the fixed blade of the compressor is eliminated, and the effects of improving the secondary flow and reducing the loss of the fixed blade of the compressor are achieved.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (4)
1. A compressor end region vibration structure comprising: the motor comprises a shell (1-5), a rotor, an eccentric block (1-6), a rotating shaft (1-7), a bearing (1-8) and a motor; the number of the rotors is multiple; the rotors are sequentially sleeved on the rotating shafts (1-7); the rotating shaft (1-7) is connected with the motor, and the bearing (1-8) is arranged at the connecting part; the eccentric block (1-6) is arranged on the rotating shaft (1-7); the shape of the shell (1-5) is obtained by pneumatic optimization based on a bionics principle;
the vibration frequency of the eccentric blocks (1-6) is set according to the scale of the angular separation;
when the small-scale angle areas are separated, the vibration frequency of the eccentric blocks (1-6) is zero;
when the middle-scale angle area is separated, the vibration frequency of the eccentric blocks (1-6) is 3000Hz;
when the large-scale angular regions are separated, the vibration frequency of the eccentric blocks (1-6) is 6000Hz.
2. A compressor end area vibrating structure according to claim 1, characterized in that the shell (1-5) height is 5% to 10% of a given blade height; the thickness of the shell (1-5) is between 0.5mm and 1 mm.
3. The compressor end region vibration structure of claim 1, wherein the vibration structure is placed at a position: in the axial direction, at 80% to 100% of the chord length of a given blade; in the tangential direction, the tangential distance between the center point of the vibration structure and the surface of the given blade is 10% -15% of the chord length of the given blade; in the radial direction, is placed on the lower end wall of a given blade.
4. A compressor end region vibration structure according to claim 1, wherein a plurality of said rotors are different in size.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210585364.5A CN114962342B (en) | 2022-05-27 | 2022-05-27 | Compressor end region vibration structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210585364.5A CN114962342B (en) | 2022-05-27 | 2022-05-27 | Compressor end region vibration structure |
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| CN114962342A CN114962342A (en) | 2022-08-30 |
| CN114962342B true CN114962342B (en) | 2024-04-02 |
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| CN202210585364.5A Active CN114962342B (en) | 2022-05-27 | 2022-05-27 | Compressor end region vibration structure |
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05222901A (en) * | 1992-02-10 | 1993-08-31 | Hitachi Ltd | Structure of stationary blade of turbine |
| EP2126367A1 (en) * | 2007-01-17 | 2009-12-02 | Ansaldo Energia S.P.A. | Turbogas system multistage compressor |
| CN103352414A (en) * | 2013-06-28 | 2013-10-16 | 洛阳北川重工机械有限公司 | Method for optimizing parameters of multi-frequency multi-amplitude vibratory roller |
| CN104153820A (en) * | 2014-07-22 | 2014-11-19 | 哈尔滨工程大学 | Large meridional expansion variable-geometry turbine with stepped spherical end wall |
| CN106481369A (en) * | 2016-11-01 | 2017-03-08 | 南京航空航天大学 | A kind of shunting leaflet structure controlling stators flow separation |
| JP2017050922A (en) * | 2015-08-31 | 2017-03-09 | 澤藤電機株式会社 | Vibration type compressor |
| CN107355426A (en) * | 2017-08-16 | 2017-11-17 | 江苏中联风能机械股份有限公司 | A kind of super low noise bumps biomimetic type subway tunnel propeller fan movable vane piece |
| JP2018028297A (en) * | 2016-08-18 | 2018-02-22 | 株式会社Ihi | Stationary blade structure of axial flow compressor |
| CN110701111A (en) * | 2019-10-25 | 2020-01-17 | 江汉大学 | Method for reducing total pressure loss of guide vane of axial flow fan by using splitter vane |
| CN110848153A (en) * | 2019-09-13 | 2020-02-28 | 浙江理工大学上虞工业技术研究院有限公司 | Axial flow fan with bionic blade tail edge and working method thereof |
| CN114109913A (en) * | 2021-11-26 | 2022-03-01 | 中国民航大学 | Compressor stator blade cascade with small oblique ribs at end wall of leading edge of blade root |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9764357B2 (en) * | 2005-06-27 | 2017-09-19 | General Vibration Corporation | Synchronized array of vibration actuators in an integrated module |
-
2022
- 2022-05-27 CN CN202210585364.5A patent/CN114962342B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05222901A (en) * | 1992-02-10 | 1993-08-31 | Hitachi Ltd | Structure of stationary blade of turbine |
| EP2126367A1 (en) * | 2007-01-17 | 2009-12-02 | Ansaldo Energia S.P.A. | Turbogas system multistage compressor |
| CN103352414A (en) * | 2013-06-28 | 2013-10-16 | 洛阳北川重工机械有限公司 | Method for optimizing parameters of multi-frequency multi-amplitude vibratory roller |
| CN104153820A (en) * | 2014-07-22 | 2014-11-19 | 哈尔滨工程大学 | Large meridional expansion variable-geometry turbine with stepped spherical end wall |
| JP2017050922A (en) * | 2015-08-31 | 2017-03-09 | 澤藤電機株式会社 | Vibration type compressor |
| JP2018028297A (en) * | 2016-08-18 | 2018-02-22 | 株式会社Ihi | Stationary blade structure of axial flow compressor |
| CN106481369A (en) * | 2016-11-01 | 2017-03-08 | 南京航空航天大学 | A kind of shunting leaflet structure controlling stators flow separation |
| CN107355426A (en) * | 2017-08-16 | 2017-11-17 | 江苏中联风能机械股份有限公司 | A kind of super low noise bumps biomimetic type subway tunnel propeller fan movable vane piece |
| CN110848153A (en) * | 2019-09-13 | 2020-02-28 | 浙江理工大学上虞工业技术研究院有限公司 | Axial flow fan with bionic blade tail edge and working method thereof |
| CN110701111A (en) * | 2019-10-25 | 2020-01-17 | 江汉大学 | Method for reducing total pressure loss of guide vane of axial flow fan by using splitter vane |
| CN114109913A (en) * | 2021-11-26 | 2022-03-01 | 中国民航大学 | Compressor stator blade cascade with small oblique ribs at end wall of leading edge of blade root |
Non-Patent Citations (2)
| Title |
|---|
| 仿生波浪前缘叶片在核电汽轮机中的应用;陈桐;谢诞梅;杨长柱;张恒良;熊扬恒;杜海芬;张敬;;中国电机工程学报(12);全文 * |
| 静叶轮毂间隙对压气机角区失速的控制;廖吉香;姜斌;吕从鹏;邱毅;王国强;郑群;;航空动力学报(07);全文 * |
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| CN114962342A (en) | 2022-08-30 |
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