CN118148775A - Unidirectional pneumatic tab flow path with adaptive flow regulation function - Google Patents
Unidirectional pneumatic tab flow path with adaptive flow regulation function Download PDFInfo
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- CN118148775A CN118148775A CN202410212091.9A CN202410212091A CN118148775A CN 118148775 A CN118148775 A CN 118148775A CN 202410212091 A CN202410212091 A CN 202410212091A CN 118148775 A CN118148775 A CN 118148775A
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- 230000003044 adaptive effect Effects 0.000 title claims description 13
- 230000001105 regulatory effect Effects 0.000 claims description 7
- 239000007921 spray Substances 0.000 claims description 6
- 238000002156 mixing Methods 0.000 abstract description 11
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 2
- 239000000446 fuel Substances 0.000 description 4
- 238000004088 simulation Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000005283 ground state Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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Abstract
The invention provides a unidirectional pneumatic tab runner with a self-adaptive flow regulation function, which is based on the characteristics of common working condition parameters of a multi-duct aeroengine and the like, is provided with a unidirectional pneumatic tab runner represented by a special annular channel and a water drop type central body, and has the advantages of low altitude and high altitude high efficiency propulsion and high altitude reinforced mixing, no movable mechanical structure is needed, no valve is needed to be opened or closed, no runner structure is needed to be changed, and the unidirectional pneumatic tab runner has the characteristics of simple structure, good reliability and light weight.
Description
Technical Field
The invention relates to a unidirectional pneumatic tab runner with a self-adaptive flow regulation function, belonging to the technical field of reinforced blending and flow regulation of multi-duct aeroengines.
Background
With the development of science and technology and urgent demands in practical application, new generation aeroengines have made tremendous innovations in terms of overall layout, structure, fuel, etc., so as to meet more omnibearing demands. Taking future multi-duct aeroengines as an example, the layout of the multi-duct brings the characteristics of high altitude, high thrust, low altitude and low oil consumption, so that stronger mixing capability and limited jet pipe flow adjustment capability are expected to be obtained by a simpler structure. Some novel fuel aeroengines (such as hydrogen fuel aeroengines) not only have a multi-duct structure, but also have better environmental protection, simultaneously require flow regulation, and have better infrared stealth performance. The aerodynamic parameters of a plurality of ducts of the multi-duct aero-engine under different working conditions are greatly changed, and great requirements are set for the adjustment of the spray pipes. And the relation between the inlet pressure of the inner duct nozzle and the inlet pressure of the outer duct nozzle of the multiple duct aero-engine changes along with the flying height, namely, the inlet pressure of the outer duct nozzle is higher than the inlet pressure of the inner duct nozzle at low altitude and low speed, and the inlet pressure of the outer duct nozzle is lower than the inlet pressure of the inner duct nozzle at high altitude and high speed. Such conditions present greater difficulties in nozzle intensive blending and flow regulation. Therefore, there is a strong need to develop a flow control means for a multi-duct aircraft engine nozzle with enhanced blending and flow regulation capabilities.
At present, the pneumatic protruding sheet gradually becomes a research focus and a research hot spot of various countries by the characteristics of simple structure, light weight and high mixing efficiency, and is going to engineering application in the near future. In particular, the aerodynamic tabs are such that a small amount of airflow (secondary flow) is injected into the main flow to be blended at a specific angle to achieve efficient blending. The air injection flow, angle and time can be divided into a steady pneumatic protruding piece and an unsteady pneumatic protruding piece. Compared with the unsteady pneumatic protruding piece, the unsteady pneumatic protruding piece has slightly larger secondary flow, but has small unsteady influence on front end components (such as fans, compressors and the like) of the aero-engine, and has important application value. Therefore, the method is oriented to the actual demands in the future, and has urgent engineering practical value when the pneumatic protruding sheets are used for strengthening blending and the air flow control is further used for realizing the adjustment and control of the flow of the spray pipe.
Disclosure of Invention
The invention aims to: in order to overcome the defects in the prior art, the unidirectional pneumatic tab runner with the self-adaptive flow regulating function is based on the common working condition parameter characteristics of a multi-duct aeroengine and the like, is provided with a unidirectional pneumatic tab runner represented by a special annular channel and a water drop type central body, and has the advantages of taking the goals of low-altitude and high-altitude high-efficiency propulsion and high-altitude reinforced mixing into consideration, completely needing no movable mechanical structure, needing no valve opening and closing or changing any runner structure, and having the characteristics of simple structure, good reliability and light weight.
The technical scheme is as follows: in order to achieve the above purpose, the invention adopts the following technical scheme:
The unidirectional pneumatic tab flow passage with the self-adaptive flow regulation function is characterized in that the unidirectional pneumatic tab flow passage 9 is arranged between different ducts of the multi-duct aeroengine spray pipe, and controls the flow directions of different duct airflows under specified working conditions under the action of different duct pressure differences.
Preferably, the multi-duct aeroengine nozzle comprises an outer duct channel casing 2, at least an inner duct channel and an outer duct channel are arranged in the outer duct channel casing 2, a split casing 8 is arranged between the inner duct channel and the outer duct channel, and the split casing 8 is provided with the unidirectional pneumatic tab flow channel 9.
Preferably, the unidirectional pneumatic tab flow channel 9 comprises a special-shaped annular channel 9.2 and a central body 9.3, the special-shaped annular channel 9.2 is arranged on the split casing 8, the special-shaped annular channel 9.2 is in a 9-like shape, an outer duct air outlet 9.4 is arranged above the special-shaped annular channel, and an inner duct air outlet 9.1 is arranged below the special-shaped annular channel.
Preferably, the right side of the shaped annular channel 9.2 is a tapered channel from top to bottom, and the left side is a divergent channel or an equal straight channel.
Preferably, the special-shaped annular channel 9.2 is near the tail end of the split casing 8: if the distance L from the center of the central body 9.3 to the tail end of the split-flow casing 8 is set, L is not more than 10% -15% of the radius of the outlet 10 of the inner channel.
Preferably, for the content channel outlet 9.1: the included angle alpha 2 between the central line and the inner molded surface of the split casing 8, the included angle alpha 1 between the central line and the left side of the special-shaped annular channel 9.2 and the included angle alpha 3 between the central line and the right side of the special-shaped annular channel 9.2 meet a certain relation, namely alpha 1＜α2≤α3.
Preferably, for the special-shaped annular channel 9.2, the included angle beta 1、β2 between the central lines of the left and right side channels and the outer profile meets beta 1＜β2 < 90 degrees.
Preferably, beta 2/β1 is not less than 1.25.
Preferably, the central body 9.3 is in the shape of a drop.
The beneficial effects are that: compared with the prior art, the unidirectional pneumatic tab flow passage with the self-adaptive flow regulation function has the following advantages:
(1) Compared with the traditional pneumatic protruding piece, the invention has the capability of pneumatic protruding piece and flow adjustment, and meets the use requirements of a new generation of multi-duct aeroengines, hydrogen fuel aeroengines and the like;
(2) The scheme fully utilizes the change of internal and external culvert parameters of the multi-duct aeroengine and the like under different working conditions, realizes flow regulation and reinforced blending under the condition of completely needing no mechanical structure to actuate and move, and has the advantages of simple structure, light weight and good reliability.
Drawings
FIG. 1 is a cross-sectional view along the flow direction of a unidirectional pneumatic vane flow path with adaptive flow regulation in accordance with the present invention;
FIG. 2 is a detail view of a unidirectional aerodynamic tab flow path with adaptive flow regulation in accordance with the present invention;
FIG. 3 is a schematic illustration of a unidirectional pneumatic tab flow path with adaptive flow regulation in accordance with the present invention;
FIG. 4 is a numerical simulation Mach number cloud of an exemplary operating mode of the present invention;
The drawings include: 1. the device comprises an outer duct channel inlet, an outer duct channel casing, an outer duct channel outlet, a spray pipe outlet, an inner duct channel inlet, a central symmetry axis, a central cone, a split casing, a unidirectional pneumatic protruding piece runner and an inner duct channel outlet, wherein the outer duct channel inlet, the outer duct channel casing, the outer duct channel outlet, the spray pipe outlet, the inner duct channel inlet, the central symmetry axis, the central cone, the split casing and the inner duct channel outlet are respectively arranged in sequence. The unidirectional pneumatic tab flow channel 9 can be divided into 9.1, an inner duct air outlet, 9.2, a special-shaped annular channel, 9.3, a central body, 9.4 and an outer duct air outlet.
Detailed Description
The invention will be further described with reference to the accompanying drawings and examples.
1-3, A unidirectional pneumatic tab runner with a self-adaptive flow regulating function is characterized in that a specially designed unidirectional pneumatic tab runner is arranged in a middle splitter plate (a partition plate) of different ducts, and the flow directions of different duct airflows under specified working conditions are controlled under the action of different duct differential pressures.
Taking an aeroengine nozzle with an inner duct and an outer duct as an example, the section of the aeroengine nozzle passing through a central shaft is selected for analysis. Generally, the radius of the outlet cross-section is smaller than the radius of the nozzle inlet cross-section. Other bypass compositions may be analyzed similarly. The aerodynamic tab flow path is provided as a part of an axisymmetric cross section in the intermediate flow dividing plate of the inner and outer ducts.
Further, the special-designed unidirectional pneumatic protruding piece runner is composed of an inner duct air outlet 9.1, a special-shaped annular channel 9.2, a central body 9.3, an outer duct air outlet 9.4 and the like. When the total pressure of the inner culvert channel inlet 5 and the static pressure of the inner culvert channel outlet 9.1 are higher than the total pressure of the outer culvert channel inlet 1 and the static pressure of the outer culvert outlet 9.4, partial air flow flows in from the inner culvert channel outlet 9.1 and is sprayed out from the outer culvert outlet 9.4; on the contrary, the air flow flowing in from the outer duct air outlet 9.4 and ejected from the inner duct air outlet 9.1 is small and can be ignored.
Further, the shaped annular channel 9.2 and the central body 9.3 are approximately 9-shaped, wherein the inner duct air outlet 9.1 corresponds to the tail part of 9, and the outer duct air outlet 9.4 corresponds to the head part of 9. When part of the air flow flows in from the inner duct air outlet 9.1, the part of the air flow flows in from the tail part of the 9 and flows out from the outer duct air outlet 9.4 along the right semi-ring channel of the 9; when a trace amount of air flows in from the outer duct air outlet 9.4, the air flows along the two circular rings at the upper part of the '9', the flow is restrained, and the effect of approximate sealing is realized, so that the flow rate of the air flow is negligible.
Preferably, the width of the shaped annular channel 9.2 is not generally equal, and generally, the average width of the right half ring of the shaped annular channel 9.2 should be more than 125% of the average width of the left half ring of the shaped annular channel 9.2; the average width W of the whole special-shaped annular channel 9.2 is not less than 5% of the diameter of the outlet 10 of the inner channel, so as to ensure good mixing and flow regulating effects; but generally no greater than 20% of the diameter of the inner channel outlet 10 to reduce the impact on the thrust coefficient of the nozzle.
Preferably, the right half ring channel of the special-shaped annular channel 9.2 is a tapered channel as much as possible, and the left half ring channel of the special-shaped annular channel 9.2 is a divergent channel or an equal straight channel as much as possible.
Further, the profiled annular channel 9.2 should be as close as possible to the trailing end of the splitter plate, typically calculated as the distance L from the location of the central body of the profiled annular channel 9.2 to the trailing end of the splitter plate, L should be no more than 10% -15% of the radius of the inner duct outlet 10.
Furthermore, the profile of the inner channel air outlet 9.1 of the 9-shaped annular flow channel needs to be specially designed, and the included angle alpha 2 between the central line and the inner surface of the flow dividing plate, and the included angles alpha 1 and alpha 3 between the two side wall surfaces of the inner channel air outlet 9.1 and the inner profile meet certain relation, namely alpha 1＜α2≤α3, so that the approximate tapered horn mouth of the channel of the inner channel air outlet 9.1 is realized.
Further, the profile of the outer duct outlet 9.4 of the shaped annular channel 9.2 needs to be specially designed, specifically, the annular channel top end of the shaped annular channel 9.2 should be communicated with the outer duct. Furthermore, the included angle beta 1、β2 between the center line of the left half ring and the center line of the right half ring and the outer molded surface meets a certain relation, and beta 1＜β2 is smaller than 90 degrees; preferably, beta 2/β1 is not less than 1.25.
Through the design, under the high-speed high-altitude condition, the unidirectional pneumatic tab flow passage plays a role, and the total flow of the inner and outer ducts of the aeroengine can be more than 2% smaller than that of a configuration without the pneumatic tab; and under the ground state, the total flow of the inner duct and the outer duct of the aeroengine is basically unchanged. Generally, at high altitude and high velocity, a total flow capacity of not less than 2% will be obtained per 1% of the total flow of the nozzle inlet. The upper limit of the flow regulating capacity is not more than 15% and is constrained by the thickness of the splitter plate.
In particular, the design schemes are designed by using the overall parameters of the aeroengine that the total pressure of the outer culvert is lower than the total pressure of the inner culvert under the high-altitude high-speed condition and the total pressure of the inner culvert is lower than the total pressure of the outer culvert under the ground condition. If the law of the total pressure of the inner duct and the outer duct of the aero-engine is opposite to the above, reference can be made to similar designs.
The foregoing is only a preferred embodiment of the invention, it being noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the present invention, and such modifications and adaptations are intended to be comprehended within the scope of the invention.
Examples
Calculations were performed for a typical configuration of unidirectional aerodynamic tab flow channels with adaptive flow regulation.
Figure 4 shows an axisymmetric cross-section numerical simulation mach number cloud of the configuration of the present patent technology versus the reference configuration versus the specific example. The two cloud charts are numerical simulation Mach number cloud charts with a reference configuration, and the through flow rates of the two cloud charts are m a、mb respectively. The two lower cloud pictures are numerical simulation Mach number cloud pictures using the technology of the patent, and the through flow rates of the two cloud pictures are m a、0.98mb respectively; the flow through the aerodynamic tabs at high altitude and high velocity is no greater than 0.007m b.
Claims (10)
1. The unidirectional pneumatic protruding piece runner with the self-adaptive flow regulating function is characterized in that the unidirectional pneumatic protruding piece runner (9) is arranged between different ducts of the multi-duct aeroengine spray pipe, and controls the flow direction of different duct airflows under specified working conditions under the action of different duct pressure differences.
2. The unidirectional pneumatic tab runner with the self-adaptive flow regulating function as claimed in claim 1, wherein the multi-duct aeroengine nozzle comprises an outer duct channel case (2), at least an inner duct channel and an outer duct channel are arranged in the outer duct channel case (2), a split case (8) is arranged between the inner duct channel and the outer duct channel, and the unidirectional pneumatic tab runner (9) is arranged on the split case (8).
3. The unidirectional pneumatic tab runner with the self-adaptive flow regulating function as claimed in claim 1, wherein the unidirectional pneumatic tab runner (9) comprises a special-shaped annular channel (9.2) and a central body (9.3), the special-shaped annular channel (9.2) is arranged on the split-flow casing (8), the special-shaped annular channel (9.2) is in a 9-like shape, an outer duct air outlet (9.4) is arranged above the special-shaped annular channel, and an inner duct air outlet (9.1) is arranged below the special-shaped annular channel.
4. A unidirectional pneumatic tab flow passage with adaptive flow regulation as claimed in claim 3, characterized in that the channels on the left and right sides of the profiled annular channel (9.2) are not equally wide and satisfy: the average width of the right channel is more than 125% of the average width of the left channel; and the average width W of the whole special-shaped annular channel (9.2) is not less than 5% of the diameter of the outlet (10) of the inner channel and not more than 20% of the diameter of the outlet (10) of the inner channel.
5. A unidirectional pneumatic tab flow passage with adaptive flow regulation as claimed in claim 3 or 4, characterized in that the right side of the profiled annular channel (9.2) is a converging channel from top to bottom and the left side is a diverging channel or an equi-straight channel.
6. A unidirectional aerodynamic tab runner with adaptive flow regulation as claimed in claim 3, characterized in that the profiled annular channel (9.2) is near the tail end of the split casing (8): the distance L from the center of the central body (9.3) to the tail end of the diversion casing (8) is set, and L is not more than 10% -15% of the radius of the outlet (10) of the inner channel.
7. A unidirectional pneumatic tab flow passage with adaptive flow regulation function as claimed in claim 3, characterized in that for the content passage outlet (9.1): the included angle alpha 2 between the central line and the inner molded surface of the split casing (8), the included angle alpha 1 between the central line and the left side of the special-shaped annular channel (9.2) and the included angle alpha 3 between the central line and the right side of the special-shaped annular channel (9.2) meet a certain relation, namely alpha 1＜α2≤α3.
8. A unidirectional pneumatic tab flow passage with adaptive flow regulation as claimed in claim 3, characterized in that for said profiled annular passage (9.2) the angle β 1、β2 between the centre line of the left and right side passage and the outer profile satisfies β 1＜β2 < 90 °.
9. The unidirectional aerodynamic tab flow path with adaptive flow regulation of claim 8, wherein β 2/β1 is greater than or equal to 1.25.
10. A unidirectional aerodynamic tab flow path with adaptive flow regulation as claimed in claim 3, characterized in that said central body (9.3) is drop-shaped.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410212091.9A CN118148775A (en) | 2024-02-27 | 2024-02-27 | Unidirectional pneumatic tab flow path with adaptive flow regulation function |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202410212091.9A CN118148775A (en) | 2024-02-27 | 2024-02-27 | Unidirectional pneumatic tab flow path with adaptive flow regulation function |
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| CN118148775A true CN118148775A (en) | 2024-06-07 |
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| CN202410212091.9A Pending CN118148775A (en) | 2024-02-27 | 2024-02-27 | Unidirectional pneumatic tab flow path with adaptive flow regulation function |
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| CN (1) | CN118148775A (en) |
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- 2024-02-27 CN CN202410212091.9A patent/CN118148775A/en active Pending
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