CN112197970A - Speed generator design method - Google Patents
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- CN112197970A CN112197970A CN202010994802.4A CN202010994802A CN112197970A CN 112197970 A CN112197970 A CN 112197970A CN 202010994802 A CN202010994802 A CN 202010994802A CN 112197970 A CN112197970 A CN 112197970A
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- 238000013461 design Methods 0.000 title abstract description 13
- 238000002485 combustion reaction Methods 0.000 claims abstract description 34
- 238000012360 testing method Methods 0.000 claims abstract description 33
- 238000007493 shaping process Methods 0.000 claims abstract description 6
- 238000012938 design process Methods 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 2
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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Abstract
The application belongs to the field of aero-engine combustion tests, and particularly relates to a speed generator design method. The design process of the speed generator comprises the following steps: the method comprises the following steps: manufacturing a test piece, S101, obtaining an annular plate, and dividing the annular plate into n concentric ring segments along the radial direction; s102, uniformly forming a plurality of flow-shaping holes along the circumferential direction of each circular ring section; step two: mounting a test piece at an inlet of an engine combustion chamber for testing to obtain radial velocity distribution of airflow at the inlet of the engine combustion chamber; step three: and (4) finely adjusting the opening area of the rectifying holes on the n circular ring sections, and repeating the second step and the third step until a test piece which enables the radial velocity distribution of the inlet airflow of the engine combustion chamber to be most uniform is found out. The design method of the speed generator can obtain the speed generator which enables the air inlet condition of the combustion chamber test to be more real, so that a more accurate test result is obtained, and especially for a pre-researched combustion test, the influence of an airflow boundary layer can be greatly reduced.
Description
Technical Field
The application belongs to the field of aero-engine combustion tests, and particularly relates to a speed generator design method.
Background
After the development of more annular combustors, the inlet flow field problem has led to a general emphasis on those working with combustors. By combustor inlet flow field is meant the velocity or total pressure of the combustor inlet flow and the distribution of the air mass flow (flow per unit area) in the circumferential and radial directions. For scheme selection, a pre-developed combustion test is usually required to be performed under a uniform inlet flow field, however, in the air inlet steady flow section of the combustion chamber, due to the influence of the airflow boundary layer, a local low-speed area appears in a near-wall area, and a peak shape is formed. The radial nonuniformity of the speed is easy to cause the nonuniformity of the air flow, the combustion organization and the temperature distribution of the outlet of the combustion chamber in the circumferential direction, and is also easy to cause the increase of the total pressure loss of the sudden-expansion diffuser, so that the optimal geometric dimension of the diffuser is changed, and the radial nonuniformity of the speed is also seriously inconsistent with the actual working condition of the combustion chamber of the engine.
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
It is an object of the present application to provide a method of designing a velocity generator to address at least one of the problems of the prior art.
The technical scheme of the application is as follows:
a method of designing a velocity generator, the velocity generator design process comprising the steps of:
the method comprises the following steps: making a test piece, specifically comprising:
s101, a ring-shaped plate is obtained, the ring-shaped plate is divided into n concentric ring segments along the radial direction, wherein the areas of the 1 st ring segment at the innermost side and the n th ring segment at the outermost side along the radial direction are equal to 1/(2(n-1)) of the total area of the ring-shaped plate, the areas of the n-2 ring segments between the 1 st ring segment and the n th ring segment are equal to 1/(n-1) of the total area of the ring-shaped plate, and n is more than or equal to 3;
s102, uniformly forming a plurality of flow adjusting holes along the circumferential direction of each circular ring segment, wherein the flow adjusting holes in the 1 st circular ring segment and the nth circular ring segment are semicircular holes, and the flow adjusting holes in the middle n-2 circular ring segments are circular holes;
step two: the test piece is arranged at the inlet of the combustion chamber of the engine for testing, and the radial velocity distribution of the airflow at the inlet of the combustion chamber of the engine is obtained;
step three: and (4) finely adjusting the opening area of the rectifying holes on the n circular ring sections, and repeating the second step and the third step until a test piece which enables the radial velocity distribution of the inlet airflow of the engine combustion chamber to be most uniform is found out.
Optionally, in step S102, the number of the rectifying holes and the opening area on each ring segment are set by:
a. setting the number of the flow-rectifying holes on each circular ring segment according to the size of a required speed factor, wherein the speed factor theta is the percentage of the difference between the average speed and the minimum speed to the average speed, and theta is (Vave-Vmin)/Vave;
b. the open area of the rectifying holes on each circular ring section is ensured to occupy 60% -70% of the area of the corresponding circular ring section.
Optionally, the speed factor θ is not greater than 3%.
Optionally, the arrangement of the rectifying holes on two adjacent circular ring segments is a cross arrangement.
Optionally, in step S101, the annular plate is radially divided into 5 concentric ring segments, the areas of the 1 st ring segment and the 5 th ring segment are equal to 1/8 of the total area of the annular plate, and the area of the middle 3 ring segments is equal to 1/4 of the total area of the annular plate.
Optionally, the aperture of the flow-shaping hole is in the range of 1/6-1/4 of the radial length of the annular plate.
The invention has at least the following beneficial technical effects:
the speed generator design method can obtain the speed generator which enables the air inlet condition of the combustion chamber test to be more real, so that more accurate test results are obtained, especially for the pre-researched combustion test, the influence of the airflow boundary layer can be greatly reduced, the phenomenon that the air flow, the combustion organization and the outlet temperature distribution of the combustion chamber are not uniform in the circumferential direction is avoided, the situation that the total pressure loss of the sudden-expansion diffuser is increased to cause the optimal geometric dimension of the diffuser is changed is also avoided, the research and development efficiency and the accuracy of the combustion chamber are favorably improved, and the time cost and the economic cost are saved.
Drawings
FIG. 1 is a schematic diagram of a velocity generator according to one embodiment of the present application;
FIG. 2 is a schematic diagram of a velocity generator according to a second arrangement of the present application;
FIG. 3 is a schematic diagram of a velocity generator according to a third arrangement of the present application;
FIG. 4 is a schematic diagram of a velocity generator according to a fourth configuration of the present application;
FIG. 5 is a schematic comparison of the radial velocity profile of the combustor inlet gas stream provided with a velocity generator according to one embodiment of the present application;
FIG. 6 is a schematic illustration of radial velocity profiles for satisfying different combustor inlet flows in accordance with an embodiment of the present application.
Wherein:
1-an annular plate; 11-a rectifying hole; 12-rectifying seam.
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 6.
The application provides a design method of a speed generator, which comprises the following steps:
the method comprises the following steps: making a test piece, specifically comprising:
s101, obtaining a ring-shaped plate 1, dividing the ring-shaped plate 1 into n concentric ring segments along the radial direction, wherein the areas of the 1 st ring segment at the innermost side and the n th ring segment at the outermost side along the radial direction are equal to 1/(2(n-1)) of the total area of the ring-shaped plate 1, the areas of the n-2 ring segments between the 1 st ring segment and the n th ring segment are equal to 1/(n-1) of the total area of the ring-shaped plate 1, and n is more than or equal to 3;
s102, uniformly arranging a plurality of flow adjusting holes 11 along the circumferential direction of each circular ring segment, wherein the flow adjusting holes 11 in the 1 st circular ring segment and the nth circular ring segment are semicircular holes, and the flow adjusting holes 11 in the middle n-2 circular ring segments are full circular holes; wherein,
the number of fairing holes 11 and the open area on each ring segment are set by:
a. ensuring that the radial velocity distribution of the initial layout of the rectifying holes 11 on the n concentric ring segments is uniform,the number of the rectifying holes 11 on each ring segment is set according to the size of the required speed factor, wherein the speed factor theta is the percentage of the difference between the average speed and the minimum speed to the average speed, and theta is (V)ave-Vmin)/VaveIn one embodiment of the present application, the speed factor θ may be set to not more than 3%;
b. secondly, the total area of the openings of all the rectifying holes 11 on each circular ring section is ensured to occupy 60 to 70 percent of the area of the corresponding circular ring section;
step two: after the preliminary manufacturing of the test piece is completed, the test piece is installed at the inlet of the engine combustion chamber for testing, and the radial velocity distribution of the airflow at the inlet of the engine combustion chamber is obtained;
step three: and (5) finely adjusting the opening area of the rectifying holes 11 on the n circular ring sections, and repeating the second step and the third step until a test piece which enables the radial velocity distribution of the inlet airflow of the engine combustion chamber to be most uniform is found out.
Specifically, in an embodiment of the present application, in step S101, the annular plate 1 may be radially divided into 5 concentric annular segments, the areas of the 1 st annular segment at the innermost side and the 5 th annular segment at the outermost side in the radial direction are equal to 1/8 of the total area of the annular plate 1, the area of the middle 3 annular segments is equal to 1/4 of the total area of the annular plate 1, that is, the annular segments at the middle of the annular plate 1 are all equal annular surfaces, and the areas of the annular segments at both sides in the radial direction are half of the area of the middle annular segment.
According to the design method of the speed generator, the preset number of rectifying holes 11 are uniformly distributed along the circumferential direction of each circular ring section, the rectifying holes 11 in the 1 st circular ring section and the nth circular ring section are semicircular holes, and the rectifying holes 11 in the middle n-2 circular ring sections are full circular holes. In the initial layout of the rectifying holes 11, the radial velocity distribution is firstly ensured to be a uniform flow field, and the number of the rectifying holes 11 in the corresponding arrangement is adjusted according to the required velocity distribution and the velocity factor. In one embodiment of the present application, the average speed in the speed factor θ is the average of the axial speeds of n circular ring segments, and currently, in the design of the generator for realizing the uniform flow field speed, the speed factor can reach 0.0225 at minimum.
In the design method of the speed generator, the aperture area of the rectifying hole 11 on each circular ring segment is set by firstly ensuring that the aperture area of each circular ring segment accounts for 60% -70% of the area of the corresponding circular ring segment. In this embodiment, the diameter of the rectifying holes 11 is in the range of 1/6-1/4 of the radial length of the annular plate 1. In order to realize uniform and smooth speed distribution, in the subsequent steps, the opening area of the rectifying holes 11 on each circular ring section is gradually increased to be adjusted on the basis of ensuring that the opening area occupation ratio is approximately equal, the opening is not too large until reasonable air distribution is found, and the best effect of reducing the thickness of the boundary layer is achieved. And finally, finding out a test piece which enables the radial velocity distribution of the airflow at the inlet of the engine combustion chamber to be most uniform through experimental verification.
Advantageously, in this embodiment, 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.
In the speed generator design method, the rectification effect of other forms of annular plate 1 structures is verified. One layout form is shown in fig. 2, a plurality of rows of flow regulating slits 12 are radially arranged on an annular plate 1, each row of flow regulating slits 12 comprises a plurality of sections which are circumferentially arranged at equal intervals, and different intervals can be set between two adjacent rows of flow regulating slits 12 according to requirements. In another layout form, the annular plate 1 is provided with a flow-adjusting hole 11 and a flow-adjusting slit 12 in turn along the radial direction. As shown in fig. 3, in the present embodiment, a row of semicircular holes, three rows of circular holes, and a row of flow-regulating slits 12 are sequentially formed from the inner side to the outer side in the radial direction of the annular plate 1. In the third layout form, the flow-straightening holes 11, the flow-straightening slits 12, and the flow-straightening holes 11 are opened in this order from the inside to the outside in the radial direction of the annular plate 1. As shown in fig. 4, in the present embodiment, the annular plate 1 includes, in order from the inside to the outside in the radial direction, a row of semicircular flow-straightening holes 11, a row of circular flow-straightening holes 11, a row of flow-straightening slits 12, a row of circular flow-straightening holes 11, and a row of semicircular flow-straightening holes 11.
According to the design method of the velocity generator, the annular plate 1 in four layout forms is tested, the layout that only a plurality of rows of rectifying holes 11 are arranged on the annular plate 1 is obviously better than the layout that only rectifying slits 12 are arranged and the rectifying holes 11 and the rectifying slits 12 are arranged, and the thickness of boundary layers can be reduced better. The layout of the rectifying holes 11 and the rectifying slits 12 is less sensitive to adjustment, the speeds on two sides are uniformly distributed, the effect of reducing the thickness of the boundary layer is poor, the peak-shaped distribution with high middle and low two ends is easy to occur, and the layout pressure loss of the slits is very high.
Fig. 5 is a schematic diagram showing a comparison between a flow field obtained by using the velocity generator of the present application to rapidly realize a uniform flow field for an inlet of a combustion chamber and a flow field obtained without using the velocity generator, and it can be seen that after the velocity generator provided by the present application is used, the boundary layer is obviously eliminated, and the effect of the uniform flow field is realized. Fig. 6 shows that for different inlet speed distribution requirements, the speed generator provided by the present application obtains the speed distribution of the upper peak and the lower peak to meet the corresponding test use requirements.
The design method of the speed generator can obtain the speed generator which enables the air inlet condition of the combustion chamber test to be more real, so that 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 air flow, combustion organization and outlet temperature distribution of the combustion chamber in the circumferential direction is avoided, and the condition that the optimal diffuser geometric size is changed due to the increase of total pressure loss of the sudden-expansion diffuser is also avoided. The method and the device improve the research and development efficiency and accuracy of the combustion chamber, and save time cost and economic cost. The speed generating device can be used for speed generating devices for subsequent tests of different types and different head combustion chambers, can be applied to tests and engineering practices of civil pipelines with certain requirements on speed, 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 (6)
1. A method for designing a velocity generator, wherein the method for designing a velocity generator comprises the steps of:
the method comprises the following steps: making a test piece, specifically comprising:
s101, obtaining a ring-shaped plate (1), dividing the ring-shaped plate (1) into n concentric ring segments along the radial direction, wherein the areas of the 1 st ring segment at the innermost side and the n th ring segment at the outermost side along the radial direction are all equal to 1/(2(n-1)) of the total area of the ring-shaped plate (1), the areas of the n-2 ring segments between the 1 st ring segment and the n th ring segment are all equal to 1/(n-1) of the total area of the ring-shaped plate (1), and n is more than or equal to 3;
s102, uniformly arranging a plurality of flow-adjusting holes (11) along the circumferential direction of each ring segment, wherein the flow-adjusting holes (11) on the 1 st ring segment and the nth ring segment are semicircular holes, and the flow-adjusting holes (11) on the n-2 ring segments in the middle are full circular holes;
step two: the test piece is arranged at the inlet of the combustion chamber of the engine for testing, and the radial velocity distribution of the airflow at the inlet of the combustion chamber of the engine is obtained;
step three: and (3) finely adjusting the opening area of the rectifying holes (11) on the n circular ring sections, and repeating the second step and the third step until a test piece which enables the radial velocity distribution of the inlet airflow of the engine combustion chamber to be most uniform is found out.
2. The method of claim 1, wherein the number of flow-shaping holes (11) and the open area of the flow-shaping holes are set per ring segment in step S102 by:
a. setting the number of the flow-rectifying holes (11) on each circular ring section according to the size of a required speed factor, wherein the speed factor theta is the percentage of the difference between the average speed and the minimum speed to the average speed, and theta is (V)ave-Vmin)/Vave；
b. The open area of the rectifying holes (11) on each circular ring section is ensured to occupy 60% -70% of the area of the corresponding circular ring section.
3. A method of designing a velocity generator according to claim 2, characterised in that the velocity factor θ is not greater than 3%.
4. The method of designing a velocity generator according to claim 2, characterized in that the arrangement of the flow-shaping holes (11) on two adjacent ring segments is a cross arrangement.
5. The method of claim 2, wherein the annular plate (1) is divided into 5 concentric ring segments in the radial direction in step S101, the area of each of the 1 st and 5 th ring segments is equal to 1/8 of the total area of the annular plate (1), and the area of the middle 3 ring segments is equal to 1/4 of the total area of the annular plate (1).
6. The method of claim 5, wherein the aperture of the flow-shaping orifice (11) is in the range 1/6-1/4 of the radial length of the annular plate (1).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010994802.4A CN112197970B (en) | 2020-09-21 | 2020-09-21 | Design method of speed generator |
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| CN202010994802.4A CN112197970B (en) | 2020-09-21 | 2020-09-21 | Design method of speed generator |
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| CN112197970B CN112197970B (en) | 2022-08-26 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114216685A (en) * | 2021-10-20 | 2022-03-22 | 中国航发四川燃气涡轮研究院 | Main combustion chamber component test piece for simulating radial velocity field of outlet of gas compressor |
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| CN112197970B (en) | 2022-08-26 |
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