CN111502784A - Air inlet volute structure - Google Patents
Air inlet volute structure Download PDFInfo
- Publication number
- CN111502784A CN111502784A CN202010350103.6A CN202010350103A CN111502784A CN 111502784 A CN111502784 A CN 111502784A CN 202010350103 A CN202010350103 A CN 202010350103A CN 111502784 A CN111502784 A CN 111502784A
- Authority
- CN
- China
- Prior art keywords
- channel section
- air channel
- baffle
- volute structure
- guide plate
- 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
- 230000007704 transition Effects 0.000 claims abstract description 27
- 238000000926 separation method Methods 0.000 abstract description 14
- 230000009471 action Effects 0.000 abstract description 2
- 238000012360 testing method Methods 0.000 description 10
- 238000010586 diagram Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000011056 performance test Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model relates to the technical field of aeroengines, and provides an air inlet volute structure, which comprises a body and a guide plate, wherein the body comprises a radial air channel section, an axial air channel section and a transition air channel section, and the transition air channel section is communicated with the radial air channel section and the axial air channel section; the guide plate is arranged in the body, and at least part of the guide plate is positioned in the transition air channel section to separate the transition air channel section, so that air flow flowing in through the radial air channel section enters the axial air channel section from two sides of the guide plate. The guide plate is arranged in the body, so that the flow separation of the air flow in the transition air channel section is greatly inhibited under the forced guide action of the guide plate, the internal flow field performance is greatly improved, the flow field uniformity in the axial air channel section is improved, and the problem of uneven axial air outlet of the air inlet volute structure in the prior art is solved.
Description
Technical Field
The disclosure relates to the technical field of aircraft engines, in particular to an air inlet volute structure.
Background
At present, a great deal of turbine performance tests are involved in the design process of the turbine of the aircraft engine, and the accuracy and reliability of the related tests have great influence on the design of the turbine. The existing stage of air inlet mode of the turbine performance test generally adopts an air inlet volute form. The volute air inlet mode is adopted to convert the air flow from radial to axial air inlet (namely, the air inlet volute structure can realize radial air inlet and axial air outlet), then the volute air inlet structure is connected with a test piece to finish the test, and finally the air is discharged from the exhaust volute.
The structure of the air flow flowing through the air inlet volute is in a contraction-expansion mode, air flow separation is easy to occur, the flow field at the inlet of a test is uneven, and the accuracy of a turbine performance test is influenced.
Disclosure of Invention
The present disclosure provides an air inlet volute structure to solve the problem of uneven axial air outlet of the air inlet volute structure in the prior art.
The invention provides an air inlet volute structure, which comprises:
the body comprises a radial air duct section, an axial air duct section and a transition air duct section, wherein the transition air duct section is communicated with the radial air duct section and the axial air duct section;
the guide plate is arranged in the body, and at least part of the guide plate is positioned in the transition air channel section to separate the transition air channel section, so that air flow flowing in through the radial air channel section enters the axial air channel section from two sides of the guide plate.
In one embodiment of the invention, the guide plate is of a cylindrical structure, the guide plate is positioned in the middle of the transition air duct section, and the guide plate and the body are arranged at intervals.
In an embodiment of the present invention, the shape of the baffle is composed of at least one arc surface, at least one curved surface, at least one plane, at least one inclined surface, or any combination thereof.
In one embodiment of the invention, the number of the guide plates is multiple, the guide plates are arranged at intervals, and one guide plate of two adjacent guide plates penetrates through the other guide plate.
In one embodiment of the invention, the body includes a fairing with a support plate disposed thereon, a portion of the support plate being located within the body for connection with the baffle.
In one embodiment of the invention, the support plate is connected to a plurality of baffles.
In one embodiment of the invention, the supporting plate is a plurality of supporting plates, and the plurality of supporting plates are arranged at intervals along the circumferential direction of the flow guide plate.
In one embodiment of the invention, the baffle includes a first end face and a second end face, the first end face and the second end face being located within the radial air channel section and the axial air channel section, respectively.
In one embodiment of the present invention, the intake volute structure further comprises:
the grating part is arranged in the body and is positioned in the axial air duct section.
In one embodiment of the invention, the grid elements are multiple, and the multiple grid elements are arranged at intervals along the extension direction of the axial air duct section;
wherein, the grid part and the guide plate are arranged at intervals.
According to the air inlet volute structure, the guide plate is arranged in the body, so that the flow separation of airflow in the transition air channel section is greatly inhibited under the forced guide effect of the guide plate on the airflow flowing in through the radial air channel section, the internal flow field performance is greatly improved, the flow field uniformity in the axial air channel section is improved, and the problem of uneven axial air outlet of the air inlet volute structure in the prior art is solved.
Drawings
Various objects, features and advantages of the present disclosure will become more apparent from the following detailed description of preferred embodiments thereof, when considered in conjunction with the accompanying drawings. The drawings are merely exemplary illustrations of the disclosure and are not necessarily drawn to scale. In the drawings, like reference characters designate the same or similar parts throughout the different views. Wherein:
FIG. 1 is a schematic illustration of an internal partial structure of an intake volute structure according to an exemplary embodiment;
FIG. 2 is a schematic illustration of a grill member configuration of an intake volute configuration, according to an exemplary embodiment;
FIG. 3 is a two-dimensional flow diagram of the original inlet volute structure profile;
FIG. 4 is a first two-dimensional flow diagram of a cross-section of the inlet volute configuration of the present invention;
figure 5 is a second two-dimensional flow diagram of a cross-section of the inlet volute configuration of the present invention.
The reference numerals are explained below:
10. a body; 11. a radial air duct section; 12. an axial air duct section; 13. a transition duct section; 14. a first wall surface; 15. a second wall surface; 20. a baffle; 21. a first end face; 22. a second end face; 30. a grid member.
Detailed Description
Exemplary embodiments that embody features and advantages of the present disclosure are described in detail below in the specification. It is to be understood that the disclosure is capable of various modifications in various embodiments without departing from the scope of the disclosure, and that the description and drawings are to be regarded as illustrative in nature, and not as restrictive.
In the following description of various exemplary embodiments of the disclosure, reference is made to the accompanying drawings, which form a part hereof, and in which are shown by way of illustration various exemplary structures, systems, and steps in which aspects of the disclosure may be practiced. It is to be understood that other specific arrangements of parts, structures, example devices, systems, and steps may be utilized and structural and functional modifications may be made without departing from the scope of the present disclosure. Moreover, although the terms "over," "between," "within," and the like may be used in this specification to describe various example features and elements of the disclosure, these terms are used herein for convenience only, e.g., in accordance with the orientation of the examples in the figures. Nothing in this specification should be construed as requiring a specific three dimensional orientation of structures in order to fall within the scope of this disclosure.
An embodiment of the present invention provides an air inlet volute structure, referring to fig. 1 and 2, the air inlet volute structure includes: the air duct comprises a body 10, wherein the body 10 comprises a radial air duct section 11, an axial air duct section 12 and a transition air duct section 13, and the transition air duct section 13 is communicated with the radial air duct section 11 and the axial air duct section 12; the guide plate 20, the guide plate 20 sets up in the body 10, and at least part of guide plate 20 is located transition wind channel section 13 to separate transition wind channel section 13, make the air current that flows in through radial wind channel section 11 get into axial wind channel section 12 from the both sides of guide plate 20.
According to the air inlet volute structure provided by the embodiment of the invention, the guide plate 20 is arranged in the body 10, so that the flow separation of the airflow in the transition air channel section 13 can be greatly inhibited under the forced guide action of the guide plate 20, the internal flow field performance is greatly improved, the flow field uniformity in the axial air channel section 12 is improved, and the problem of uneven axial air outlet of the air inlet volute structure in the prior art is solved.
In one embodiment, the baffle 20 is a cylindrical structure, the baffle 20 is located in the middle of the transition duct section 13, and the baffle 20 is spaced apart from the body 10. In order to adapt to the shape of the transition duct section 13 and enhance the flow guiding effect, a cylindrical flow guiding plate 20 may integrally divide the transition duct section 13 into two parts, so that the airflow flows into the axial duct section 12 along two sides of the flow guiding plate 20.
In one embodiment, the shape of the baffle 20 is composed of at least one arc surface, at least one curved surface, at least one flat surface, at least one inclined surface, or any combination thereof.
In one embodiment, the baffle 20 comprises at least a conical section, the small end of which is adjacent to the radial air channel section 11 and the large end of which is adjacent to the axial air channel section 12.
In one embodiment, the number of the baffles 20 is multiple, the baffles 20 are arranged at intervals, and one baffle 20 of two adjacent baffles 20 is arranged in the other baffle 20. The guide plates 20 are in a sleeving state in a spatial relationship, but the guide plates 20 are arranged at intervals, so that the transition air duct section 13 is divided into a plurality of cavities, the flow guiding capacity is improved, and the uniformity of a flow field in the axial air duct section 12 is improved.
In one embodiment, the body 10 includes a cowling with a support plate disposed thereon, portions of the support plate being positioned within the body 10 to couple with the baffle 20. The support plate is used for fixing the guide plate 20 in the body 10, so as to ensure the stability of the guide plate 20, and the guide plate 20 and the body 10 are arranged at intervals.
In one embodiment, a support plate connects a plurality of baffles 20. A plurality of guide plates 20 are all connected with a backup pad to this reduces the quantity of backup pad, guarantees not to cause excessive influence to the air current.
In one embodiment, the support plate is plural, and the plural support plates are arranged at intervals in the circumferential direction of the baffle 20. The plurality of support plates stably dispose the plurality of baffles 20 within the body 10.
In one embodiment, as shown in fig. 1, the baffle 20 includes a first end surface 21 and a second end surface 22, the first end surface 21 and the second end surface 22 being located within the radial air channel section 11 and the axial air channel section 12, respectively. The baffle 20 guides the air flow in the radial air channel section 11 to the axial air channel section 12, so as to ensure the uniformity of the air flow.
In one embodiment, as shown in fig. 1 and 2, the intake volute structure further comprises: the grating element 30, the grating element 30 is arranged in the body 10, and the grating element 30 is located in the axial air duct section 12. The provision of the grating elements 30 may further break up very small separation vortices in the flow field, thereby providing uniformity of the air flow exiting the axial duct section 12.
In one embodiment, the grating elements 30 are plural, and the plural grating elements 30 are arranged at intervals along the extending direction of the axial air duct section 12; wherein, the grid element 30 and the baffle 20 are arranged at intervals.
In one embodiment, as shown in fig. 1, the body 10 further includes a first wall 14 and a second wall 15, one of the plurality of baffles 20 is adjacent to the first wall 14, and one of the plurality of baffles 20 is adjacent to the second wall 15.
In one embodiment, the number of the guide plates 20 is two, the number of the grating members 30 is three, the flow separation of the air flow of the existing air inlet volute mainly occurs near the rotation stage (the transition air duct section 13), the air flow is rapidly contracted and rapidly expanded, and from the fluid mechanics perspective, a larger separation must be caused, but the size of the flow passage of the existing volute relates to a test piece, an output shaft and a dynamometer and cannot be changed randomly, so that the double-layer guide plates 20 are added in the rotation stage for forced flow guiding on the premise of keeping the size of the flow passage of the existing volute. The upper baffle 20 controls the flow of the air flow mainly in the area close to the upper wall (first wall 14) so that the size of the air flow passage in the area does not change greatly, and similarly, the lower baffle 20 controls the flow of the air flow in the lower area (i.e. the area close to the second wall 15). The flow separation is greatly inhibited by the forced diversion effect of the double-layer diversion plate 20, in order to further break the extremely small separation vortex in the flow field, three rows of grids (grid parts 30) are added at the outlet section of the volute, the distance between every two rows of grids is 10cm, each grid consists of a plurality of rectangles, and the thickness of the grid net is 2 mm.
The air inlet volute structure greatly improves the flow field and improves the uniformity of the inlet flow field of a test piece through the combined design of the anti-separation double-layer guide plate 20 and the grid piece 30, thereby improving the accuracy and the reliability of the whole test.
FIG. 3 is a two-dimensional flow diagram of a cross-section of an original inlet volute showing that there is a large separation of the flow near the wall as the flow turns from radial to axial, forming a large number of separation vortices. The separation vortex can cause uneven distribution of speed, pressure and the like, cause instability of the inlet condition of a test piece, greatly affect the precision of a test result, and is not beneficial to accurate extraction of the pneumatic parameters of the turbine test. Fig. 4 and 5 are flow field diagrams under other working conditions after the guide plate 20 and the grid member 30 are added, and show that the air inlet volute structure of the invention can well control the development of air flow, eliminates the separation in the flow field, and ensures that the air flow in the whole air inlet volute is uniform, thereby well explaining the adaptability and superiority of the structure.
Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This invention is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and exemplary embodiments be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.
It will be understood that the invention is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the invention is limited only by the appended claims.
Claims (10)
1. An intake volute structure, comprising:
the air duct comprises a body (10), wherein the body (10) comprises a radial air duct section (11), an axial air duct section (12) and a transition air duct section (13), and the transition air duct section (13) is communicated with the radial air duct section (11) and the axial air duct section (12);
the guide plate (20) is arranged in the body (10), at least part of the guide plate (20) is positioned in the transition air channel section (13) to separate the transition air channel section (13), so that air flow flowing in through the radial air channel section (11) enters the axial air channel section (12) from two sides of the guide plate (20).
2. The inlet volute structure of claim 1, wherein the baffle (20) is a cylindrical structure, the baffle (20) is located in the middle of the transition duct section (13), and the baffle (20) is spaced apart from the body (10).
3. The inlet volute structure of claim 2, wherein the baffle (20) has a profile comprising at least one arc, at least one curve, at least one flat surface, at least one inclined surface, or any combination thereof.
4. The inlet volute structure according to claim 2 or 3, wherein the number of the baffles (20) is multiple, the baffles (20) are arranged at intervals, and one baffle (20) of two adjacent baffles (20) is arranged in the other baffle (20).
5. The inlet volute structure of claim 4, wherein the body (10) includes a cowling with a support plate disposed thereon, portions of the support plate being positioned within the body (10) to connect with the baffle (20).
6. The inlet volute structure of claim 5, wherein the support plate connects a plurality of the baffles (20).
7. The inlet volute structure according to claim 5 or 6, wherein the support plate is plural, and the plural support plates are provided at intervals in a circumferential direction of the baffle plate (20).
8. The inlet volute structure of claim 1, wherein the baffle (20) comprises a first end face (21) and a second end face (22), the first end face (21) and the second end face (22) being located within the radial air channel section (11) and the axial air channel section (12), respectively.
9. The intake volute structure of claim 1 or 8, further comprising:
the grid part (30), grid part (30) set up in body (10), grid part (30) are located in axial wind channel section (12).
10. The inlet volute structure according to claim 9, wherein the grid element (30) is a plurality of grid elements (30), and the grid elements (30) are spaced apart along the extension direction of the axial air duct section (12);
wherein the grid element (30) and the baffle (20) are arranged at a distance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010350103.6A CN111502784A (en) | 2020-04-28 | 2020-04-28 | Air inlet volute structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010350103.6A CN111502784A (en) | 2020-04-28 | 2020-04-28 | Air inlet volute structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111502784A true CN111502784A (en) | 2020-08-07 |
Family
ID=71871497
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010350103.6A Pending CN111502784A (en) | 2020-04-28 | 2020-04-28 | Air inlet volute structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111502784A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112729751A (en) * | 2020-12-30 | 2021-04-30 | 哈尔滨工业大学 | Test bed |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11141452A (en) * | 1997-11-04 | 1999-05-25 | Naoyoshi Hosoda | Wind power generating device |
| CN1397634A (en) * | 2002-08-23 | 2003-02-19 | 清华大学 | Gas-lifting recirculating reactor with more concentric guide barrels |
| CN201582162U (en) * | 2010-01-06 | 2010-09-15 | 沈阳新松机器人自动化股份有限公司 | Modularized centrifugal speed-regulating flow-regulating fan for CO2 lasers |
| CN104566459A (en) * | 2014-12-08 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Grading air intake nozzle of combustor of gas turbine |
| CN107630725A (en) * | 2017-11-01 | 2018-01-26 | 中国航发湖南动力机械研究所 | Suitable for testing the air inlet volute of ride |
| CN207830214U (en) * | 2017-12-16 | 2018-09-07 | 大唐东北电力试验研究所有限公司 | A kind of fan outlet constant-current stabilizer |
-
2020
- 2020-04-28 CN CN202010350103.6A patent/CN111502784A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11141452A (en) * | 1997-11-04 | 1999-05-25 | Naoyoshi Hosoda | Wind power generating device |
| CN1397634A (en) * | 2002-08-23 | 2003-02-19 | 清华大学 | Gas-lifting recirculating reactor with more concentric guide barrels |
| CN201582162U (en) * | 2010-01-06 | 2010-09-15 | 沈阳新松机器人自动化股份有限公司 | Modularized centrifugal speed-regulating flow-regulating fan for CO2 lasers |
| CN104566459A (en) * | 2014-12-08 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Grading air intake nozzle of combustor of gas turbine |
| CN107630725A (en) * | 2017-11-01 | 2018-01-26 | 中国航发湖南动力机械研究所 | Suitable for testing the air inlet volute of ride |
| CN207830214U (en) * | 2017-12-16 | 2018-09-07 | 大唐东北电力试验研究所有限公司 | A kind of fan outlet constant-current stabilizer |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112729751A (en) * | 2020-12-30 | 2021-04-30 | 哈尔滨工业大学 | Test bed |
| CN112729751B (en) * | 2020-12-30 | 2023-10-27 | 哈尔滨工业大学 | Test bed |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8257036B2 (en) | Externally mounted vortex generators for flow duct passage | |
| US6261055B1 (en) | Exhaust flow diffuser for a steam turbine | |
| Hamstra et al. | Active inlet flow control technology demonstration | |
| JP5887049B2 (en) | Exhaust plenum for turbine engines | |
| GB2164098A (en) | Improvements in or relating to aerofoil section members for turbine engines | |
| CN107687948B (en) | Air inlet total pressure and vortex flow coupling distortion generator and distortion test method | |
| CN111175053B (en) | Air inlet distortion simulation device for aircraft engine | |
| CN107436219B (en) | Inlet and exhaust pipeline device in unconventional layout form | |
| CN101750204A (en) | Engine simulator for dynamic simulation test in high-speed wind tunnel | |
| CN106870201A (en) | For the exhaust nozzle of gas-turbine unit | |
| JP2011236897A (en) | Diffuser for gas turbine system | |
| CN111502784A (en) | Air inlet volute structure | |
| Adenubi | Performance and flow regime of annular diffusers with axial turbomachine discharge inlet conditions | |
| Henry et al. | Summary of subsonic-diffuser data | |
| CN112229639B (en) | Design method of aero-engine intake total pressure distortion generation device | |
| CN110566285A (en) | Compact centripetal turbine guider | |
| CN112197294B (en) | Rectifying plate | |
| Anabtawi et al. | An experimental study of vortex generators in boundary layer ingesting diffusers with a centerline offset | |
| CN115289499B (en) | Hollow support plate of gas inlet of combustion chamber of gas turbine | |
| CN114198324B (en) | Multi-element coupling centrifugal fan collector, centrifugal fan and preparation method of centrifugal fan collector | |
| Pramstrahler et al. | The Impact of Inlet Flow Angle on Turbine Vane Frame Aerodynamic Performance | |
| Saka et al. | Development of a framework for a circulation control-based unmanned aerial vehicle | |
| CN112049688B (en) | Over-prerotation blade type receiving hole for equal-radius prerotation air supply system | |
| CN115560988A (en) | Aeroengine low pressure turbine director flow detection test section structure | |
| Sonoda et al. | The effect of inlet boundary layer thickness on the flow within an annular S-shaped duct |
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: 20200807 |