CN112197294B - Rectifying plate - Google Patents
Rectifying plate Download PDFInfo
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- CN112197294B CN112197294B CN202010994805.8A CN202010994805A CN112197294B CN 112197294 B CN112197294 B CN 112197294B CN 202010994805 A CN202010994805 A CN 202010994805A CN 112197294 B CN112197294 B CN 112197294B
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- fairing
- ring
- holes
- rectifying plate
- segment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The application belongs to the field of aero-engine combustion tests, and particularly relates to a rectifying plate. The rectifying plate (1) is annular and is installed at an inlet of a combustion chamber of an engine, the rectifying plate (1) is divided into n concentric ring sections along the radial direction, wherein the areas of the 1 st ring section at the innermost side and the n th ring section at the outermost side along the radial direction are all equal to 1/(2(n-1)) of the total area of the rectifying plate (1), the areas of the n-2 ring sections between the 1 st ring section and the n th ring section are all equal to 1/(n-1) of the total area of the rectifying plate (1), and n is more than or equal to 3; a plurality of flow-adjusting holes (11) are uniformly formed in the circumferential direction of each ring segment, wherein the flow-adjusting holes (11) in the 1 st ring segment and the nth ring segment are semicircular holes, and the flow-adjusting holes (11) in the middle n-2 ring segments are circular holes. The uniform flow field can be realized, the experimental air inlet condition of the combustion chamber is more real, the research and development efficiency and accuracy of the combustion chamber are favorably improved, and the time cost and the economic cost are saved.
Description
Technical Field
The application belongs to the field of aero-engine combustion tests, and particularly relates to a rectifying plate.
Background
With the development of aero-engine combustion chambers, annular combustion chambers have become the mainstream of development. For the selection of the annular combustion chamber scheme, a pre-ground combustion test is often required to be performed under a uniform inlet flow field, however, in the intake steady flow section of the combustion chamber, due to the influence of an airflow boundary layer, a local low-speed region appears in a near-wall region to form a peak shape, and the nonuniformity of the speed in the radial direction is very likely to cause the nonuniformity of the air flow, the combustion organization and the outlet temperature distribution of the combustion chamber in the circumferential direction, and is also likely to cause the increase of the total pressure loss of the sudden-expansion diffuser, so that the optimal diffuser geometric dimension is changed, and is also seriously inconsistent with the actual working condition of the engine combustion chamber.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The purpose of this application is to provide a cowling panel to solve at least one problem that prior art exists.
The technical scheme of the application is as follows:
a fairing, comprising:
the rectifying plate is annular and is arranged at the inlet of the combustion chamber of the engine, the rectifying plate is radially divided into n concentric ring segments, wherein,
the areas of the 1 st annular segment at the innermost side and the nth annular segment at the outermost side in the radial direction are equal to 1/(2(n-1)) of the total area of the rectifying plate, the areas of the n-2 annular segments between the 1 st annular segment and the nth annular segment are equal to 1/(n-1) of the total area of the rectifying plate, and n is more than or equal to 3;
a plurality of flow-adjusting holes are uniformly formed in the circumferential direction of each ring segment, wherein the flow-adjusting holes in the 1 st ring segment and the nth ring segment are semicircular holes, and the flow-adjusting holes in the middle n-2 ring segments are full circular holes.
Optionally, the thickness of the rectifier plate is 5mm-10 mm.
Optionally, the aperture of the rectifying hole ranges from 4mm to 6 mm.
Optionally, the total open area of the flow straightening holes is 60-70% of the flow straightening plate.
Optionally, the open area of the rectifying hole on the 1 st ring segment is 2% -3% more than the open area of the rectifying hole on the adjacent second ring segment.
Optionally, the open area of the rectifying hole in the nth ring segment is 6-8% more than the open area of the rectifying hole in the adjacent second ring segment.
Optionally, the arrangement of the rectifying holes on two adjacent circular ring segments is a cross arrangement.
Optionally, the fairing plate is divided into 5 concentric ring segments along the radial direction, wherein the area of the 1 st ring segment at the innermost side and the area of the 5 th ring segment at the outermost side in the radial direction are equal to 1/8 of the total area of the fairing plate, and the area of the 3 middle ring segments are equal to 1/4 of the total area of the fairing plate.
The invention has at least the following beneficial technical effects:
the utility model provides a fairing, divide into a plurality of concentric ring segments with annular fairing, through the setting for to the area of each ring segment and the overall arrangement form of the rectifying hole of seting up, can realize the uniform flow field, make the experimental air intake condition of combustion chamber more true, obtain more accurate test result, especially to the combustion test of prestudy nature, can greatly reduce the influence on air current boundary layer, avoid arousing that combustion chamber air flows, the combustion organization, the nonuniformity of outlet temperature distribution in circumference, also avoid because of suddenly expanding diffuser total pressure loss increase, the best diffuser geometry who leads to has the condition that changes, be favorable to improving combustion chamber research and development efficiency and accuracy, save time cost and economic cost.
Drawings
FIG. 1 is a schematic view of an embodiment of a fairing of the present application;
FIG. 2 is a view A-A of FIG. 1;
FIG. 3 is a rectification hole schematic diagram of a semi-circular hole of a rectification plate according to an embodiment of the present application;
fig. 4 is a partial schematic view of a rectifying plate according to the present embodiment.
Wherein:
1-a rectifying plate; 11-flow straightening hole.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 4.
The application provides a cowling panel, refer to fig. 1 to 2, this cowling panel 1 is the annular, installs in engine combustion chamber import department, can carry out bolted connection through setting up inside and outside installation limit and combustion chamber test piece on cowling panel 1 to realize the installation.
Specifically, the rectifying plate 1 of the present application is radially divided into n concentric ring segments, wherein the areas of the 1 st ring segment at the innermost side and the nth ring segment at the outermost side in the radial direction are equal to 1/(2(n-1)) of the total area of the rectifying plate 1, the areas of the n-2 ring segments located between the 1 st ring segment and the nth ring segment are equal to 1/(n-1) of the total area of the rectifying plate 1, and n is greater than or equal to 3.
Further, as shown in fig. 3, a plurality of rectifying holes 11 are uniformly formed along the circumferential direction of each ring segment, wherein the rectifying holes 11 on the 1 st ring segment and the nth ring segment are semicircular holes, and the rectifying holes 11 on the middle n-2 ring segments are full circular holes.
The rectifying plate is set to be suitable for the geometric structure size of the air inlet rectifying section of the annular combustion chamber test piece of the domestic aero-engine, and the thickness of the rectifying plate is set to be 5-10 mm.
The rectifying plate is divided into n concentric circular ring sections along the radial direction in order to realize uniform radial velocity distribution before the inlet of a test piece of a combustion chamber, and the aperture range of a rectifying hole 11 formed in each circular ring section is set between 4mm and 6 mm.
In the flow regulating plate of the present application, the total opening area of the flow regulating holes 11 is preferably set to 60% to 70% of the flow regulating plate 1. In this embodiment, the ratio of the open area of the rectifying hole 11 in the 1 st ring segment of the rectifying plate 1 is 2% -3% more than that of the open area of the rectifying hole 11 in the adjacent ring segment outside. Furthermore, the opening area of the rectifying hole 11 on the nth ring section of the rectifying plate 1 accounts for 6-8% more than the opening area of the rectifying hole 11 on the adjacent ring section at the inner side. Wherein, the ratio of the open area is open area/area of the corresponding ring segment.
Advantageously, in the rectifying plate of the present application, the arrangement of the rectifying holes 11 on two adjacent circular ring sections is cross arrangement, and the cross arrangement of the holes has a better effect of reducing the thickness of the boundary layer than the parallel arrangement of the holes.
As shown in fig. 4, in an embodiment of the present application, the rectifying plate 1 is divided into 5 concentric ring segments along the radial direction, wherein the area of the 1 st ring segment at the innermost side and the area of the 5 th ring segment at the outermost side along the radial direction are equal to 1/8 of the total area of the rectifying plate 1, the area of the 3 ring segments located between the 1 st ring segment and the 5 th ring segment are equal to 1/4 of the total area of the rectifying plate 1, that is, the plurality of ring segments in the middle of the rectifying plate 1 are all equal ring surfaces, and the area of the ring segments at both sides along the radial direction is half of the area of the middle ring segment. In this embodiment, the external diameter of cowling panel 1 is 500mm, and the internal diameter is 450mm, and the semicircle orifice is seted up to 1 st ring section and the 5 th ring section from radial inboard to the 1 st ring section and the 5 th ring section alternately overall arrangement on two adjacent ring sections, and the trompil area of all cowling panels 11 is about 60% of cowling panel 1.
In this embodiment, 5 ring segments are provided in the direction of twelve o' clock along the course
The rectifying holes 11 are formed by 246 rectifying holes 11 in the 1 st circular ring section from the inner side to the outer side, 240 rectifying holes 11 in the 2 nd circular ring section, 238 rectifying holes 11 in the 3 rd circular ring section, 244 rectifying holes 11 in the 4 th circular ring section and 260 rectifying holes 11 in the 5 th circular ring section.
The utility model provides a cowling panel divides into a plurality of concentric ring segments with annular cowling panel 1, through the setting to the overall arrangement form of the rectification hole 11 of the area of each ring segment and seting up, acquires the even import flow field of engine combustion chamber. Through test verification, a uniform flow field can be realized, the air inlet condition of the combustion chamber test is more real, a more accurate test result is obtained, especially for a pre-researched combustion test, the influence of an air flow boundary layer can be greatly reduced, the nonuniformity of the air flow, the combustion organization and the outlet temperature distribution of the combustion chamber in the circumferential direction is avoided, and the condition that the geometric size of the optimal diffuser is changed due to the increase of the total pressure loss of the sudden-expansion diffuser is also avoided. The method and the device are beneficial to improving the research and development efficiency and accuracy of the combustion chamber, and save time cost and economic cost.
The rectifying plate can be used for speed generating devices for subsequent tests of different head combustion chambers with different models, can be applied to tests and engineering practices requiring speed by civil pipelines, and has wide application prospect.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A fairing, comprising:
the rectifying plate (1) is annular and is arranged at the inlet of a combustion chamber of an engine, the rectifying plate (1) is radially divided into n concentric ring segments, wherein,
the areas of the 1 st annular segment at the innermost side and the nth annular segment at the outermost side in the radial direction are all equal to 1/(2(n-1)) of the total area of the rectifying plate (1), the areas of the n-2 annular segments between the 1 st annular segment and the nth annular segment are all equal to 1/(n-1) of the total area of the rectifying plate (1), and n is more than or equal to 3;
a plurality of flow-adjusting holes (11) are uniformly formed in the circumferential direction of each ring segment, wherein the flow-adjusting holes (11) in the 1 st ring segment and the nth ring segment are semicircular holes, and the flow-adjusting holes (11) in the middle n-2 ring segments are circular holes.
2. The fairing according to claim 1, characterized in that the thickness of the fairing (1) is 5mm-10 mm.
3. The fairing plate as claimed in claim 1, characterised in that the aperture of the fairing holes (11) is in the range of 4mm to 6 mm.
4. The fairing plate as claimed in claim 1, characterised in that the total open area of the fairing holes (11) is 60-70% of the fairing plate (1).
5. The fairing as recited in claim 4, characterized in that the open area of the fairing holes (11) in the 1 st ring segment is 2-3% more than the open area of the fairing holes (11) in the adjacent ring segment.
6. The fairing as recited in claim 5, characterized in that the open area of the fairing holes (11) in the nth ring segment is 6-8% more than the open area of the fairing holes (11) in the adjacent ring segment.
7. The fairing as claimed in claim 1, characterized in that the arrangement of the fairing holes (11) on two adjacent ring segments is a cross arrangement.
8. The fairing as claimed in claim 1, characterized in that the fairing (1) is divided radially into 5 concentric ring segments, wherein the area of the radially innermost 1 st ring segment and the area of the outermost 5 th ring segment are each equal to 1/8 of the total area of the fairing (1), and the area of the middle 3 ring segments are each equal to 1/4 of the total area of the fairing (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202010994805.8A CN112197294B (en) | 2020-09-21 | 2020-09-21 | Rectifying plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010994805.8A CN112197294B (en) | 2020-09-21 | 2020-09-21 | Rectifying plate |
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| CN112197294A CN112197294A (en) | 2021-01-08 |
| CN112197294B true CN112197294B (en) | 2022-04-01 |
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| CN202010994805.8A Active CN112197294B (en) | 2020-09-21 | 2020-09-21 | Rectifying plate |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113154445A (en) * | 2021-04-23 | 2021-07-23 | 浙江浙能技术研究院有限公司 | Combustor import rectification structure |
| CN114100943B (en) * | 2021-12-30 | 2022-12-02 | 北京科技大学 | Ultrasonic atomizing nozzle for forming fog cone |
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