CN114593089A - V-shaped meridian flow passage diffuser of micro turbojet engine - Google Patents
V-shaped meridian flow passage diffuser of micro turbojet engine Download PDFInfo
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- CN114593089A CN114593089A CN202210095799.1A CN202210095799A CN114593089A CN 114593089 A CN114593089 A CN 114593089A CN 202210095799 A CN202210095799 A CN 202210095799A CN 114593089 A CN114593089 A CN 114593089A
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- axial
- arc turning
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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
- F04D29/40—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
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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
- F04D29/40—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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
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- 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
Abstract
The invention discloses a V-shaped meridian flow passage diffuser of a micro turbojet engine, which comprises a wheel disc, a top cover and an outer casing, wherein a meridian flow passage is formed among the top cover, the wheel disc and the outer casing, the meridian flow passage consists of a radial expansion area, an arc turning expansion area and an axial expansion area which are sequentially connected, the radial expansion area is outwards reduced by taking the joint of the radial expansion area and the arc turning expansion area as a starting point, and the axial expansion area is outwards expanded by taking the joint of the axial expansion area and the arc turning expansion area as a starting point. Effectively reduce diffuser overall dimension, reduce boundary layer separation degree or emergence probability. The turning degree of the incoming flow from the radial direction to the axial direction is greatly reduced. Under the prerequisite that does not increase the processing degree of difficulty and guarantee diffuser efficiency, use the full passageway extension type meridian runner of diffuser, reduced the design requirement to the blade to a certain extent, especially because the influence of blade angular distribution, under the stronger condition of blade distortion, but the maximum width of moderate degree increase blade conveniently realizes the cooperation installation and dismantles repeatedly.
Description
Technical Field
The invention relates to the field of engine diffusers, in particular to a V-shaped meridian flow passage diffuser of a microminiature turbojet engine.
Background
The diffuser is the most main part of the centrifugal compressor of the microminiature turbojet engine except for the impeller, the pressure rise amount of the centrifugal compressor in the diffuser accounts for about thirty percent of the total pressure rise amount, and the direction of the airflow is converted from the radial direction to the axial direction while the airflow is subjected to speed reduction and pressure boost in the diffuser. The change of the shape of the meridian flow passage directly influences the change rule of the passage area of the diffuser, the change of the passage area is one of key parameters for determining the performance of the diffuser, when the expansion is too fast, a counter pressure gradient is generated, the separation of boundary layers is caused, the energy loss is caused, the expansion is too slow, the air flow speed is high, the friction loss is increased, the energy loss is also caused, meanwhile, the length of the air compressor is increased, the overall efficiency is reduced, the stable working range is narrowed, and the difficulty and the challenge are brought to the overall design of the micro turbojet engine.
In the prior art, the flow area of a meridian flow passage is controlled only by aiming at the radial diffuser passage section or the axial diffuser passage section variable-vane-height meridian flow passage design, or the equivalent vane height design is matched with proper vane angle change, so that the flow coming from an impeller outlet with different relative speeds in the vane height direction is met. Under the influence of the air flow at the outlet of the impeller, the distribution difference of the blade angle between the blade root and the blade top is larger no matter the blade height design or the blade height changing design, meanwhile, the thickness of the blade is limited by the size of the casing, the blade angle and other factors, the maximum thickness is narrower in some cases, the matching with other parts is difficult, and if the limitation of constraint conditions is not considered, the diffuser of the air compressor is overlong or the size of the outer casing is overlarge.
Disclosure of Invention
In order to overcome the defects that the distribution difference of the blade root and the blade top of the blade is large and the blade root and the blade top of the blade are difficult to match with other parts in the prior art, the invention provides the V-shaped meridian flow passage diffuser of the micro turbojet engine, which reduces the outer diameter of the diffuser, reduces the overall outline size of the gas compressor, increases the thickness of the blade, facilitates the matching of the gas compressor and other parts, does not increase the processing difficulty and the material cost, and reasonably ensures the pneumatic characteristic and the working performance of the gas compressor diffuser.
In order to achieve the purpose, the invention adopts the following technical scheme:
the invention provides a V-shaped meridian flow passage diffuser of a micro turbojet engine, which comprises a wheel disc, a top cover and an outer casing, wherein the wheel disc is arranged on the inner side of the outer casing, the top cover is arranged on one side of the wheel disc and is connected with the outer casing, a meridian flow passage is formed among the top cover, the wheel disc and the outer casing and consists of a radial expansion area, an arc turning expansion area and an axial expansion area which are sequentially connected, the radial expansion area is outwards reduced by taking the joint of the radial expansion area and the arc turning expansion area as a starting point, and the axial expansion area is outwards expanded by taking the joint of the axial expansion area and the arc turning expansion area as a starting point.
In a preferred technical scheme of the invention, the wheel disc comprises a radial expansion section, an inner arc turning section and an axial expansion section, wherein the radial expansion section is one surface of the wheel disc close to the top cover, the axial expansion section is one surface of the wheel disc close to the outer casing, and the radial expansion section is connected with the axial expansion section through the inner arc turning section; the radial expansion section, the inner arc turning section and the axial expansion section form a meridian flow channel hub surface; the top cover comprises a radial straight line section and an outer circular arc turning section, the outer casing comprises an axial straight line section, and the radial straight line section, the outer circular arc turning section and the axial straight line section form a meridian flow channel rim surface; a radial expansion area is arranged between the radial expansion section and the radial straight line section, an arc turning expansion area is arranged between the inner arc turning section and the outer arc turning section, and an axial expansion area is arranged between the axial expansion section and the axial straight line section.
In a preferred technical scheme of the invention, a plurality of radial blades are uniformly arranged on the radial expansion section (42) of the wheel disc along the circumferential direction of the radial expansion section, and a plurality of axial blades are uniformly arranged on the axial expansion section of the wheel disc along the circumferential direction of the axial expansion section.
In a preferred technical scheme of the invention, a plurality of integral blades are arranged on the side edge of the wheel disc.
In a preferred technical scheme of the invention, the number of the radial blades and the number of the axial blades are respectively 19-39.
In a better technical scheme of the invention, the radial expansion section and the radial straight line section are arranged at an angle of 2-5 degrees.
In a preferred technical scheme of the invention, the axial expansion section and the axial straight-line section are arranged at an angle of 2-5 degrees.
In a preferred technical solution of the present invention, the starting point of the outer arc turning section is an intersection point of a radius extension line at the starting point of the inner arc turning section and the extension line of the radial straight line segment, the ending point of the outer arc turning section and the ending point of the inner arc turning section are located on the same vertical line, the starting point of the outer arc turning section is tangent to the ending point of the radial straight line segment, the ending point of the outer arc turning section is tangent to the starting point of the axial straight line segment, the starting point of the inner arc turning section is tangent to the ending point of the radial expansion segment, and the ending point of the inner arc turning section is tangent to the starting point of the axial expansion segment.
In a preferred embodiment of the present invention, the radial blade is located in the radial expansion region, and the axial blade is located in the axial expansion region.
In a preferred technical scheme of the present invention, the center of the outer arc turning section is higher than the center of the inner arc turning section in the radial direction.
The beneficial effects of the invention are as follows:
the V-shaped meridian flow passage diffuser of the microminiature turbojet engine provided by the invention is beneficial to effectively reducing the overall size of the diffuser and reducing the separation degree or occurrence probability of the boundary layer under the condition of reasonably controlling the expansion angle. Through the configuration mode of radial expansion section, inner arc turning section and axial expansion section of the hub surface of the meridian flow channel, the turning degree of incoming flow from the radial direction to the axial direction is greatly reduced. Under the prerequisite that does not increase the processing degree of difficulty and guarantee diffuser efficiency, use the full passageway extension type meridian runner of diffuser, reduced the design requirement to the blade to a certain extent, especially because the influence of blade angular distribution, under the stronger condition of blade distortion, but the blade maximum width of moderate degree increase, convenient cooperation installation and dismantlement repeatedly.
Drawings
FIG. 1 is a schematic view of a radial flow passage structure of a V-shaped radial flow passage diffuser of a micro turbojet engine according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a top cover and an outer casing of a V-shaped radial flow passage diffuser of a micro turbojet engine according to an embodiment of the present invention;
FIG. 3 is an enlarged schematic view of B in FIG. 2;
FIG. 4 is a schematic structural diagram of a wheel disc when a V-shaped meridian flow passage diffuser of a micro turbojet engine provided by the embodiment of the invention adopts split blades;
figure 5 is an enlarged schematic view of a in figure 4,
FIG. 6 is a partial sectional side view of a V-shaped meridian flow passage diffuser of a micro turbojet engine, provided by an embodiment of the invention, with split blades;
FIG. 7 is a schematic structural diagram of a wheel disc when a V-shaped meridian flow passage diffuser of a micro turbojet engine provided by the embodiment of the invention adopts integral blades;
FIG. 8 is an enlarged schematic view of C in FIG. 7;
fig. 9 is a partial sectional side view of a V-shaped radial flow passage diffuser of a micro turbojet engine, which is provided by an embodiment of the invention and adopts integral blades.
In the figure:
1-wheel disk, 11-radial blade, 12-axial blade, 13-integral blade, 2-top cover, 3-outer casing, 4-radial expansion area, 41-radial straight line section, 42-radial expansion section, 5-arc turning expansion area, 51-outer arc turning section, 52-inner arc turning section, 6-axial expansion area, 61-axial straight line section and 62-axial expansion section.
Detailed Description
The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings.
As shown in fig. 1 to 6, in an embodiment, a V-shaped radial flow channel diffuser of a micro turbojet engine is provided, which includes a wheel disc 1, a top cover 2 and an outer casing 3, the wheel disc 1 is disposed on an inner side of the outer casing 3, the top cover 2 is disposed on one side of the wheel disc 1, the top cover 2 is connected to the outer casing 3, a radial flow channel is formed between the top cover 2, the wheel disc 1 and the outer casing 3, the radial flow channel is composed of a radial expansion area 4, an arc turning expansion area 5 and an axial expansion area 6 which are sequentially connected, the radial expansion area 4 is outwardly contracted with a connection point of the radial expansion area 4 and the arc turning expansion area 5 as a starting point, and the axial expansion area 6 is outwardly expanded with a connection point of the axial expansion area 6 and the arc turning expansion area 5 as a starting point.
Due to the arrangement of the radial expansion area 4, the arc turning expansion area 5 and the axial expansion area 6, the meridian flow channel is of a V-shaped structure on the whole, the expansion of the flow channel is mainly realized by adjusting the sizes of the radial expansion area 4 and the axial expansion area 6, and on the other hand, the expansion of the flow channel is also realized by adjusting the size of the arc turning expansion area 5. The gas flow makes a transition from radial to axial from the circular arc turning expansion zone 5.
Further, the wheel disc 1 comprises a radial expansion section 42, an inner arc turning section 52 and an axial expansion section 62, wherein the radial expansion section 42 is one surface of the wheel disc 1 close to the top cover 2, the axial expansion section 62 is one surface of the wheel disc 1 close to the outer casing 3, and the radial expansion section 42 is connected with the axial expansion section 62 through the inner arc turning section 52; the radial expansion section 42, the inner arc turning section 52 and the axial expansion section 62 form a hub surface of the meridian flow passage; the top cover 2 comprises a radial straight line section 41 and an outer circular arc turning section 51, the outer casing 3 comprises an axial straight line section 61, and the radial straight line section 41, the outer circular arc turning section 51 and the axial straight line section 61 form a meridian flow channel rim surface; a radial expansion area 4 is arranged between the radial expansion section 42 and the radial straight line section 41, a circular arc turning expansion area 5 is arranged between the inner circular arc turning section 52 and the outer circular arc turning section 51, and an axial expansion area 6 is arranged between the axial expansion section 62 and the axial straight line section 61. The expansion of the flow channel is achieved by controlling the expansion angles of the radial expansion section 42 and the axial expansion section 62, and the other is determined by the arc radii of the inner arc turning section 52 and the outer arc turning section 51, the starting point of the arc and the position of the center of the circle, so that the expansion degree of the flow channel can be flexibly adjusted by adjusting the parameters.
Further, the radial expansion section 42 of the disk 1 is uniformly provided with a plurality of radial blades 11 along the circumferential direction thereof, and the axial expansion section 62 of the disk 1 is uniformly provided with a plurality of axial blades 12 along the circumferential direction. The radial blades 11 and the axial blades 12 are integrated on the wheel disc 1 and are integrally machined with the wheel disc 1. While the wheel disc 1 mills a V-shaped surface on a machine tool, a plurality of diffuser radial blades 11 are uniformly milled along the radial circumferential direction of the wheel disc 1, and a plurality of axial blades 12 are uniformly milled along the axial circumferential direction. Simultaneously, the two blades are all provided with upper threaded holes, so that the blades can be installed in a matching manner with other components, and the blade is simple in structure and convenient to detach.
Further, the radial blades 11 and the axial blades 12 are provided with 19-39.
Compared with the prior art, in the process of designing the flow channel of the diffuser, a controllable dimension is creatively added from the inlet to the outlet of the diffuser channel, so that the maximum width of the blade can be ensured even under the conditions that the angles of the two blades change greatly and the twisting performance of the blade is strong, and the follow-up matching installation with other components is convenient.
Further, the radial expansion section 42 and the radial straight line section 41 are arranged at an angle of 2-5 degrees. The corresponding top cover 2 adopts a straight-line design, and the design can leave enough space for the installation and integration of other components at the upstream of the diffuser. In addition, in order to ensure that the turning channel part formed by the wheel disc 1 and the top cover 2 also forms an expansion channel, the inner arc turning section 52 is designed to turn earlier than the outer arc turning section 51. The radius of the inner curved turn section 52 is 2mm, which is less than the radius of the outer curved turn section 51, which is 12 mm.
Further, the axial expanding section 62 and the axial straight line section 61 are arranged at an angle of 2-5 degrees. The inlet of the axial expansion section 62 expands towards the side of the back blade height at an expansion angle of 2-5 degrees with the axial direction along the length direction of the flow path, and the outer casing 3 adopts a straight-line section design from the angle that the assembly with the outer casing 3 is simple and the expansion of the flow channel is not too fast, so that the whole meridian flow path from the inlet to the outlet is V-shaped.
Further, the starting point of the outer arc turning section 51 is the intersection point of the radius extension line at the starting point of the inner arc turning section 52 and the extension line of the radial straight line section 41, the ending point of the outer arc turning section 51 and the ending point of the inner arc turning section 52 are located on the same vertical line, the starting point of the outer arc turning section 51 is tangent to the ending point of the radial straight line section 41, the ending point of the outer arc turning section 51 is tangent to the starting point of the axial straight line section 61, the starting point of the inner arc turning section 52 is tangent to the ending point of the radial expanding section 42, and the ending point of the inner arc turning section 52 is tangent to the starting point of the axial expanding section 62.
Further, radial blades 11 are located in the radially expanded region 4 and axial blades 12 are located in the axially expanded region 6.
Further, the center of the outer arc turning section 51 is higher than the center of the inner arc turning section 52 in the radial direction.
Further, as shown in fig. 7-9, in another embodiment, the side of the disk 1 is uniformly provided with a plurality of integral blades 13. The integral blades 13 extend from the radial direction of the diffuser wheel disc 1 to the axial direction of the diffuser wheel disc, the integral diffuser does not have a blade-free turning section, and the integral blades 13 extend from the diffuser inlet to the diffuser outlet and penetrate through the whole flow passage.
The V-shaped meridian flow passage diffuser of the micro turbojet engine achieves speed reduction and pressurization of airflow through continuous expansion in the radial/turning/axial directions, can reduce the outer diameter of the diffuser, moderately increase the maximum width of blades, reduce the separation degree or occurrence probability of boundary layers, reduce the energy loss of the diffuser and improve the performance of an engine compressor under the same design requirement.
Other techniques of this embodiment employ existing techniques.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the spirit and scope of the invention. The present invention is not to be limited by the specific embodiments disclosed herein, and other embodiments that fall within the scope of the claims of the present application are intended to be within the scope of the present invention.
Claims (10)
1. The utility model provides a microminiature turbojet engine V type meridian runner diffuser, includes rim plate (1), top cap (2) and outer machine casket (3), and rim plate (1) sets up in the inboard of outer machine casket (3), and top cap (2) set up in one side of rim plate (1), and top cap (2) are connected its characterized in that with outer machine casket (3): a meridian flow passage is formed among the top cover (2), the wheel disc (1) and the outer casing (3), the meridian flow passage consists of a radial expansion area (4), an arc turning expansion area (5) and an axial expansion area (6) which are sequentially connected,
the radial expansion area (4) is outwards reduced by taking the joint of the radial expansion area and the arc turning expansion area (5) as a starting point, and the axial expansion area (6) is outwards expanded by taking the joint of the axial expansion area and the arc turning expansion area (5) as a starting point.
2. The V-shaped meridian flow channel diffuser of the micro turbojet engine as claimed in claim 1, wherein:
the wheel disc (1) comprises a radial expansion section (42), an inner arc turning section (52) and an axial expansion section (62),
the radial expansion section (42) is one surface of the wheel disc (1) close to the top cover (2), the axial expansion section (62) is one surface of the wheel disc (1) close to the outer casing (3), and the radial expansion section (42) is connected with the axial expansion section (62) through the inner arc turning section (52);
the radial expansion section (42), the inner arc turning section (52) and the axial expansion section (62) form a meridian flow channel hub surface;
the top cover (2) comprises a radial straight line section (41) and an outer circular arc turning section (51), the outer casing (3) comprises an axial straight line section (61), and the radial straight line section (41), the outer circular arc turning section (51) and the axial straight line section (61) form a meridian flow channel rim surface;
a radial expansion area (4) is arranged between the radial expansion section (42) and the radial straight line section (41), an arc turning expansion area (5) is arranged between the inner arc turning section (52) and the outer arc turning section (51), and an axial expansion area (6) is arranged between the axial expansion section (62) and the axial straight line section (61).
3. The V-shaped meridian flow channel diffuser of the micro turbojet engine as claimed in any one of claim 2, wherein:
the radial expansion section (42) of the wheel disc (1) is evenly provided with a plurality of radial blades (11) along the circumferential direction, and the axial expansion section (62) of the wheel disc (1) is evenly provided with a plurality of axial blades (12) along the circumferential direction.
4. The V-shaped meridian flow channel diffuser of the micro turbojet engine as claimed in any one of claim 2, wherein:
the side of the wheel disc (1) is provided with a plurality of integral blades (13).
5. The V-meridian flow passage diffuser of the micro-miniature turbojet engine as recited in claim 3, wherein:
the number of the radial blades (11) and the number of the axial blades (12) are respectively 19-39.
6. The V-shaped meridian flow passage diffuser of the micro turbojet engine as claimed in claim 2, wherein:
the radial expansion section (42) and the radial straight line section (41) are arranged in an angle of 2-5 degrees.
7. The V-meridian flow passage diffuser of the micro-miniature turbojet engine as recited in claim 2, wherein:
the axial expansion section (62) and the axial straight line section (61) are arranged at an angle of 2-5 degrees.
8. The V-shaped meridian flow passage diffuser of the micro turbojet engine as claimed in claim 2, wherein:
the starting point of the outer arc turning section (51) is the intersection point of the radius extension line at the starting point of the inner arc turning section (52) and the extension line of the radial straight line section (41), the ending point of the outer arc turning section (51) and the ending point of the inner arc turning section (52) are positioned on the same vertical line, the starting point of the outer arc turning section (51) is tangent to the ending point of the radial straight line section (41), the ending point of the outer arc turning section (51) is tangent to the starting point of the axial straight line section (61), the starting point of the inner arc turning section (52) is tangent to the ending point of the radial expansion section (42), and the ending point of the inner arc turning section (52) is tangent to the starting point of the axial expansion section (62).
9. The V-shaped meridian flow passage diffuser of the micro turbojet engine as claimed in claim 3, wherein:
the radial blades (11) are located in the radial expansion zone (4), and the axial blades (12) are located in the axial expansion zone (6).
10. The V-shaped meridian flow passage diffuser of the micro turbojet engine as claimed in claim 2, wherein:
the circle center of the outer arc turning section (51) is higher than the position of the circle center of the inner arc turning section (52) in the radial direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210095799.1A CN114593089A (en) | 2022-01-26 | 2022-01-26 | V-shaped meridian flow passage diffuser of micro turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210095799.1A CN114593089A (en) | 2022-01-26 | 2022-01-26 | V-shaped meridian flow passage diffuser of micro turbojet engine |
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|---|---|
| CN114593089A true CN114593089A (en) | 2022-06-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210095799.1A Pending CN114593089A (en) | 2022-01-26 | 2022-01-26 | V-shaped meridian flow passage diffuser of micro turbojet engine |
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| CN108644152A (en) * | 2018-04-04 | 2018-10-12 | 中国航发湖南动力机械研究所 | Diffuser twisted blade and design method, diffuser and centrifugation/inclined flow air compressor |
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| CN210949272U (en) * | 2019-08-26 | 2020-07-07 | 中国人民解放军总参谋部第六十研究所 | Small blade independently designed wedge-shaped integral diffuser |
| CN111622985A (en) * | 2020-06-19 | 2020-09-04 | 上海尚实能源科技有限公司 | Diffuser integrating diffusion and rectification |
| CN113756951A (en) * | 2021-09-30 | 2021-12-07 | 大连理工大学 | Shape-preserving diffuser with radial diffuser and axial diffuser fused |
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2022
- 2022-01-26 CN CN202210095799.1A patent/CN114593089A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB609971A (en) * | 1945-03-31 | 1948-10-08 | British Thomson Houston Co Ltd | Improvements in and relating to centrifugal compressors |
| CN1384902A (en) * | 1999-09-07 | 2002-12-11 | 通用电气公司 | Dewwirler system for centrifugal compressor |
| CN102414452A (en) * | 2009-02-24 | 2012-04-11 | 戴森技术有限公司 | Centrifugal compressor |
| CN104074799A (en) * | 2013-11-17 | 2014-10-01 | 中国科学院工程热物理研究所 | Axial-flow compressor with expanding meridional channel and design method of axial-flow compressor |
| CN103742450A (en) * | 2013-12-22 | 2014-04-23 | 中国科学院工程热物理研究所 | Vane type diffuser with horseshoe-shaped diffuser channels |
| US20200011345A1 (en) * | 2017-02-10 | 2020-01-09 | Siemens Aktiengesellschaft | Return stage of a multi-staged compressor or expander with twisted guide vanes |
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| CN210949272U (en) * | 2019-08-26 | 2020-07-07 | 中国人民解放军总参谋部第六十研究所 | Small blade independently designed wedge-shaped integral diffuser |
| CN111622985A (en) * | 2020-06-19 | 2020-09-04 | 上海尚实能源科技有限公司 | Diffuser integrating diffusion and rectification |
| CN113756951A (en) * | 2021-09-30 | 2021-12-07 | 大连理工大学 | Shape-preserving diffuser with radial diffuser and axial diffuser fused |
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