CN117345418A - Precooling type axisymmetric air inlet channel - Google Patents
Precooling type axisymmetric air inlet channel Download PDFInfo
- Publication number
- CN117345418A CN117345418A CN202311427403.XA CN202311427403A CN117345418A CN 117345418 A CN117345418 A CN 117345418A CN 202311427403 A CN202311427403 A CN 202311427403A CN 117345418 A CN117345418 A CN 117345418A
- Authority
- CN
- China
- Prior art keywords
- flow path
- bypass flow
- rear end
- axisymmetric
- air inlet
- 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
- 238000005192 partition Methods 0.000 claims abstract description 13
- 230000008602 contraction Effects 0.000 claims abstract description 11
- 230000007704 transition Effects 0.000 claims description 8
- 230000000694 effects Effects 0.000 abstract description 3
- 238000001816 cooling Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000011084 recovery Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
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- 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
-
- 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
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention discloses a precooling axisymmetric air inlet channel. The precooling axisymmetric air inlet channel comprises a lip cover, an expansion section, a central body, a contraction section, a precooler resistance piece, a bypass flow path partition board and a slot; the double-twisted-line type face lip cover is adopted, so that the air flow is ensured to uniformly enter the air inlet channel; the central body is supported by four support plates, so that the central body is ensured to be positioned on the central axis, and eccentric movement is avoided; the precooling type resistance piece adopts a ladder type, so that the effect of simulating the resistance of an actual precooler is realized. Compared with the prior art, the invention effectively solves the problem of overlarge flow resistance when the precooler is not in working state under the low Mach number condition, can adapt to wider flight envelope and completes more complex flight tasks.
Description
Technical Field
The invention relates to the technical field of supersonic air inlets, in particular to a precooling type axisymmetric air inlet.
Background
For a wide-range high-speed aircraft power system with Mach numbers of 0-6+, the traditional propulsion system cannot adapt to a wider flight envelope and a more complex flight task, and meanwhile, in order to reduce the air inlet stagnation temperature at a high Mach number, the air inflow is greatly reduced so as to cause great influence on an engine, and the precooling engine is produced as a novel power system. The precooling engine reduces the air inlet temperature by installing a precooler in an air inlet passage or an air inlet passage diffusion section, so that an engine power system is better matched, wide-speed-range flight is realized, the air inlet passage is used as a key component of a wide-speed-range aircraft power system, the function of the precooling engine is to provide high-quality air flow for the engine, and the performance of the engine is directly determined by the performance of the air inlet passage. The special installation of the precooler position tends to influence the compression performance and airflow quality of the air inlet channel and cause distortion of the outlet of the air inlet channel, and even when the blockage is too large, the engine is not started, so that the performance of the engine is seriously influenced. To improve inlet performance, a bypass flow path may be used to facilitate airflow downstream bypassing the high-resistance precooler, reducing flow losses caused by the precooler. Therefore, there is a need to develop new forms of air intake.
Disclosure of Invention
The invention aims to: in order to solve the problems, the invention provides the pre-cooling axisymmetric air inlet channel, which can effectively solve the problem of overlarge flow resistance when a pre-cooler is not in an operating state under the condition of low Mach number, is suitable for wider flight envelope and completes more complex flight tasks.
The technical scheme is as follows: in order to achieve the above purpose, the pre-cooling axisymmetric air inlet channel adopts the following technical scheme: the precooling axisymmetric air inlet channel comprises a lip cover, an expansion section coaxially connected with the rear end of the lip cover, a bypass flow path baffle plate fixed in the expansion section and surrounding a precooler resistance piece, a contraction section coaxially connected with the rear end of the expansion section, a central body positioned in the lip cover and the precooler resistance piece positioned in the expansion section; the bypass flow path partition plate is provided with a plurality of grooves extending along the axial direction; an annular inlet channel inlet is formed between the central body and the lip cover, a transition channel communicated with the inlet is formed between the rear end of the central body and the expansion section, a main flow channel communicated with the transition channel is formed in the hollow interior of the bypass flow channel partition plate, and an annular bypass flow channel is formed between the bypass flow channel partition plate and the expansion section; and the rear end of the main flow passage and the rear end of the bypass flow passage are communicated with the inside of the contraction section.
Further, the precooling type resistance piece comprises a central shaft, a fixed support and a plurality of coil groups, wherein the fixed support and the coil groups are arranged in a divergent mode from the central shaft to the periphery; all coils are coaxially arranged, the diameters of a plurality of outermost coils of the same group are the same, and simultaneously, the outermost diameters of the plurality of coil groups are sequentially increased from front to back along a central axis to form stepped arrangement; each coil sequentially passes through all the fixing brackets.
Furthermore, the lip cover adopts a twisted wire profile.
Furthermore, the center body is supported by four support plates.
Further, the bypass flow path separator is cylindrical.
Further, the rear end of the center body is connected with a bypass flow path partition plate.
Further, the rear end of the contraction section is connected with the measuring section.
Further, the inside of the bypass flow path partition plate is communicated with the bypass flow path through a slot.
Further, the center body and the bypass flow path separator are fitted and fixed from the rear end of the expansion section.
The beneficial effects are that: compared with the prior art, the invention has the following remarkable effects: the bypass flow path separator is fixed on the expansion section of the air inlet channel to form a bypass flow path, an additional flow path is added in the expansion section, airflow is caused to bypass the precooler with high resistance to flow downstream, flow loss caused by the precooler in the internal flow field is reduced, the total pressure recovery coefficient of the air inlet channel is effectively improved when the Mach number is low, namely, the precooler is in a non-working state, the flight envelope of the precooled air inlet channel is further widened, and the wide-speed-domain flight task is better completed.
Drawings
Fig. 1 is a three-dimensional view of a pre-cooled axisymmetric inlet channel.
Fig. 2 is a cross-sectional view of a pre-cooled axisymmetric inlet channel.
FIG. 3 is a three-dimensional view of a bypass flow path assembly of a pre-cooled axisymmetric inlet duct.
FIG. 4 is a three-dimensional view of a precooler resistance of a precooling axisymmetric air scoop.
Detailed Description
The invention discloses a precooling axisymmetric air inlet channel. Referring to fig. 1 to 4, the pre-cooling axisymmetric air inlet provided by the present invention is described in further detail below: the precooling axisymmetric air inlet channel comprises a lip cover 1, an expansion section 2, a bypass flow path baffle 3, a contraction section 4, a measuring section 5, a central body 6, a precooler resistance piece 7, a slot 8, a transition channel 9, a main flow channel 10, a bypass flow path 11, a central shaft 12, a fixed bracket 13 and a coil group 14; the lip cover 1 adopts a twisted pair type surface to ensure that air flow uniformly enters the air inlet channel, the rear end of the lip cover 1 is coaxially connected with the expansion section 2, the central body 6 is positioned in the lip cover 1, an annular air inlet channel inlet is formed between the central body 6 and the lip cover 1, the central body 6 is supported by four support plates to ensure that the central body 6 is positioned on the central axis to avoid eccentric movement, meanwhile, the rear end of the central body 6 is connected with the bypass flow path baffle 3, the rear end of the expansion section 2 is coaxially connected with the contraction section 4, the rear end of the contraction section 4 is connected with the measuring section 5, the bypass flow path baffle 3 is cylindrical, a plurality of slots 8 extending along the axial direction are formed on the bypass flow path baffle 3, an annular bypass flow path 11 is formed between the expansion section 2 and the bypass flow path baffle 3, the bypass flow path baffle 3 is internally communicated with the bypass flow path 11 through the slots 8, meanwhile, the bypass flow path baffle 3 is fixed on the expansion section 2 and surrounds the precooler resistance piece 7, a transition channel 9 is formed between the hollow interior of the bypass flow path 3, the main flow path 10 is communicated with the transition channel 9, the rear end of the bypass flow path 10 and the rear end of the bypass flow path 11 are both communicated with the interior of the contraction section 4, and the front end of the bypass flow path 11 is not communicated with the transition channel 9; the precooler resistance piece 7 is positioned in the expansion section 2, the precooler resistance piece 7 comprises a central shaft 12, fixed brackets 13 and a plurality of coil groups 14 which are arranged in a divergent mode from the central shaft 12 to the periphery, all coils are coaxially arranged, the diameters of a plurality of outermost coils of the same group are the same, meanwhile, the diameters of the plurality of coil groups 14 are sequentially increased from front to back along the central shaft 12 to form stepped arrangement, all coils sequentially pass through all the fixed brackets 13, and the integral configuration adopts a stepped mode to realize the effect of simulating the actual precooler resistance; the center body 6 and the bypass flow path separator 3 are fitted and fixed from the rear end of the expansion section 2. The precooling axisymmetric air inlet channel has the advantages of fixed geometric configuration, simple structure, accurate and efficient control, no need of mass output and the like.
In the ground suction test, the bypass flow path control method is adopted for verification under the condition that the Mach number of the outlet of the air inlet channel is selected to be 0.1, 0.2 and 0.3. The bypass flow path control method and the conventional pre-cooling type air inlet test are respectively carried out under the condition of installing the precooler, and the total air inlet outlet pressure recovery coefficient sigma under three different outlet Mach under the two conditions is compared in table 1. It can be seen that by adopting the bypass flow path control method, the aerodynamic performance of the outlet of the air inlet channel is higher, and the control method effectively reduces aerodynamic loss caused by the precooler.
| Mach number | Inlet duct without bypass flow path | This embodiment |
| 0.1 | 0.969 | 0.985 |
| 0.2 | 0.9 | 0.943 |
| 0.3 | 0.79 | 0.873 |
Claims (10)
1. A precooling type axisymmetric air inlet channel is characterized in that: the precooler comprises a lip cover (1), an expansion section (2) coaxially connected with the rear end of the lip cover (1), a bypass flow path baffle plate (3) fixed in the expansion section (2) and surrounding a precooler resistance piece (7), a contraction section (4) coaxially connected with the rear end of the expansion section (2), a central body (6) positioned in the lip cover (1) and the precooler resistance piece (7) positioned in the expansion section (2); a plurality of slots (8) extending along the axial direction are arranged on the bypass flow path partition plate (3); an annular inlet channel inlet is formed between the central body (6) and the lip cover (1), a transition channel (9) communicated with the inlet is formed between the rear end of the central body (6) and the expansion section (2), a main channel (10) communicated with the transition channel (9) is formed in the hollow interior of the bypass channel partition plate (3), and an annular bypass channel (11) is formed between the bypass channel partition plate (3) and the expansion section (2); the rear end of the main flow passage (10) and the rear end of the bypass flow passage (11) are communicated with the inside of the contraction section (4).
2. The pre-cooled axisymmetric intake duct of claim 1, wherein: the precooling type resistance piece (7) comprises a central shaft (12), a fixed bracket (13) which is divergently arranged from the central shaft (12) to the periphery, and a plurality of coil groups (14); all coils are coaxially arranged, the diameters of a plurality of outermost coils of the same group are the same, and a plurality of coil groups (14) sequentially increase the outermost diameters from front to back along a central shaft (12) to form stepped arrangement; each coil sequentially passes through all the fixed brackets (13).
3. The pre-cooled axisymmetric intake duct of claim 1, wherein: the lip cover (1) adopts a twisted wire profile.
4. The pre-cooled axisymmetric intake duct of claim 1, wherein: the central body (6) is supported by four support plates.
5. The pre-cooled axisymmetric intake duct of claim 1, wherein: the bypass flow path separator (3) is cylindrical.
6. The pre-cooled axisymmetric intake duct of claim 1, wherein: the rear end of the center body (6) is connected with the bypass flow path partition plate (3).
7. The pre-cooled axisymmetric intake duct of claim 1, wherein: the rear end of the contraction section (4) is connected with the measuring section (5).
8. The pre-cooled axisymmetric intake duct of claim 1, wherein: the bypass flow path partition plate (3) is fixed with the bottom of the rear end of the expansion section (2) and the two sides of the rear end of the central body (6) to divide the inner flow path of the air inlet into a main flow path (10) and a bypass flow path (11).
9. The pre-cooled axisymmetric intake duct of claim 1, wherein: the inside of the bypass flow path partition plate 3 is communicated with a bypass flow path 11 through a slot 8.
10. The pre-cooled axisymmetric intake duct of claim 1, wherein: the central body (6) and the bypass flow path partition plate (3) are installed and fixed from the rear end of the expansion section (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311427403.XA CN117345418A (en) | 2023-10-31 | 2023-10-31 | Precooling type axisymmetric air inlet channel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311427403.XA CN117345418A (en) | 2023-10-31 | 2023-10-31 | Precooling type axisymmetric air inlet channel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117345418A true CN117345418A (en) | 2024-01-05 |
Family
ID=89362959
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311427403.XA Pending CN117345418A (en) | 2023-10-31 | 2023-10-31 | Precooling type axisymmetric air inlet channel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117345418A (en) |
-
2023
- 2023-10-31 CN CN202311427403.XA patent/CN117345418A/en active Pending
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