CN114017217B - Horn-shaped step type air inlet channel for back air inlet of helicopter - Google Patents
Horn-shaped step type air inlet channel for back air inlet of helicopter Download PDFInfo
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- CN114017217B CN114017217B CN202111381960.3A CN202111381960A CN114017217B CN 114017217 B CN114017217 B CN 114017217B CN 202111381960 A CN202111381960 A CN 202111381960A CN 114017217 B CN114017217 B CN 114017217B
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- section
- air inlet
- arc
- helicopter
- inlet channel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
- F02M35/10—Air intakes; Induction systems
- F02M35/10091—Air intakes; Induction systems characterised by details of intake ducts: shapes; connections; arrangements
- F02M35/10118—Air intakes; Induction systems characterised by details of intake ducts: shapes; connections; arrangements with variable cross-sections of intake ducts along their length; Venturis; Diffusers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
- F02M35/10—Air intakes; Induction systems
- F02M35/10091—Air intakes; Induction systems characterised by details of intake ducts: shapes; connections; arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
- F02M35/10—Air intakes; Induction systems
- F02M35/10091—Air intakes; Induction systems characterised by details of intake ducts: shapes; connections; arrangements
- F02M35/10124—Ducts with special cross-sections, e.g. non-circular cross-section
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
- F02M35/10—Air intakes; Induction systems
- F02M35/10242—Devices or means connected to or integrated into air intakes; Air intakes combined with other engine or vehicle parts
- F02M35/10295—Damping means, e.g. tranquillising chamber to dampen air oscillations
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention provides a horn-shaped step difference type air inlet channel for back air inlet of a helicopter, which comprises the following components: an arc section and a cone section; the first end of the arc-shaped section is used as an inlet of the air inlet channel to be arranged at the back of the helicopter, the second end of the arc-shaped section is connected with the large-mouth end of the conical section, and the small-mouth end of the conical section is connected with the engine; the shape of the arc-shaped section is in a horn radial shape from the second end to the first end; the inner diameter of the second end of the arc-shaped section is smaller than that of the large opening end of the conical section, and a step difference is formed at the joint. The total pressure recovery coefficient is effectively ensured, the pressure distortion is reduced, and the maintainability of the air inlet channel is improved.
Description
Technical Field
The invention belongs to the field of helicopter engine air inlet channel design, and particularly relates to a horn-shaped stepped air inlet channel for back air inlet of a helicopter.
Background
The air inlet channel is a channel for sucking air into the engine, and is specially used for providing air flow with certain quality for the engine, and the quality of the design directly influences the operation of the engine.
The air inlet channel of the air inlet channel is usually an integral smooth flow channel, but for the condition that the opening of the air inlet channel of the existing part of helicopter is arranged at the back of the helicopter body, the air flow entering the air inlet channel is uneven due to the influence of the helicopter hub and the front end part of the helicopter body, so that the total pressure recovery coefficient in the air inlet channel is smaller, the pressure distortion is larger, and the performance of an engine is seriously influenced.
Disclosure of Invention
The horn-shaped step difference type air inlet channel for back air inlet of the helicopter effectively ensures the total pressure recovery coefficient, reduces the pressure distortion and improves the maintainability of the air inlet channel.
The invention provides a horn-shaped step difference type air inlet channel for back air inlet of a helicopter, which comprises the following components: an arc section and a cone section;
the first end of the arc-shaped section is used as an inlet of the air inlet channel to be arranged at the back of the helicopter, the second end of the arc-shaped section is connected with the large-mouth end of the conical section, and the small-mouth end of the conical section is connected with the engine;
the shape of the arc-shaped section is in a horn radial shape from the second end to the first end;
the inner diameter of the second end of the arc-shaped section is smaller than that of the large opening end of the conical section, and a step difference is formed at the joint.
Optionally, the small opening end of the conical section is consistent with the size of the air inlet installation edge of the engine.
Optionally, the aerodynamic profile of the end face of the first end of the arcuate segment is consistent with the aerodynamic profile of the back of the helicopter.
Optionally, the second end of the arcuate segment has an inner diameter greater than the inner diameter of the small mouth end of the tapered segment.
Optionally, the radius of the second end of the arcuate segment differs from the radius of the large mouth end of the tapered segment by no more than 3% of the inner diameter of the small mouth end of the tapered segment.
Optionally, the lowest point of the arcuate segment is lower than the lowest point of the large mouth end of the tapered segment.
Optionally, the curved section has a bending angle of less than 90 °.
Optionally, a sealing strip is arranged at the joint of the arc section and the conical section.
The invention provides a horn-shaped step difference type air inlet channel for back air inlet of a helicopter, which comprises the following components: an arc section and a cone section; the first end of the arc-shaped section is used as an inlet of the air inlet channel to be arranged at the back of the helicopter, the second end of the arc-shaped section is connected with the large-mouth end of the conical section, and the small-mouth end of the conical section is connected with the engine; the shape of the arc-shaped section is in a horn radial shape from the second end to the first end; the inner diameter of the second end of the arc-shaped section is smaller than that of the large opening end of the conical section, a step difference is formed at the joint, and the proper step difference structure can effectively reduce the pressure difference, so that the pressure distribution at the small opening of the conical section is more uniform, and the pressure distortion is small.
Drawings
FIG. 1 is a schematic view of inlet port position;
FIG. 2 is a side view of the profile of the inlet;
FIG. 3 is an exterior elevation view of an inlet;
FIG. 4 is an enlarged schematic view of FIG. 2 at A;
FIG. 5 is a schematic diagram of the total pressure distribution at the outlet of the air intake.
Detailed Description
The horn-shaped step-difference type air inlet channel for back air inlet of the helicopter provided by the invention is explained below with reference to the attached drawings.
Referring to fig. 1-5, the technical scheme of the invention specifically provides a horn-shaped stepped air inlet channel for back air intake of a helicopter. Wherein, the intake duct includes: arcuate segments and tapered segments.
The first end of arc section sets up in the helicopter back as the intake duct entry, and smooth connection with the fuselage guarantees that the air current flows into in the intake duct from the outside smooth of fuselage, and the second end is connected with the big mouth end of toper section, and the little mouth end size of toper section is unanimous with the inlet installation limit size of engine, the installation of being convenient for.
The appearance of arc section is loudspeaker radial from the second end to first end, reduces first end air current velocity of flow, suppresses the separation of air current, and the minimum of arc section is less than the minimum of the big mouth end of toper section, slows down the air current effectively and flows into the toper section.
The included angle between the normal direction of the first end surface of the arc-shaped section and the axial direction of the second end surface is smaller than 90 degrees, as shown by theta angle in figure 2, the overlarge bending is prevented, the pressure gradient of the air flow in the air inlet pipeline is increased, the larger air flow separation is caused, and the pneumatic performance is poor.
The inner diameter of the second end of the arc-shaped section is smaller than that of the large opening end of the conical section, a step difference is formed at the joint, and the proper step difference structure can effectively reduce the pressure difference, so that the pressure distribution at the small opening of the conical section is more uniform, and the pressure distortion is small.
For example, as shown in fig. 2, in order to ensure the air intake quality of the engine, a conical section is designed at the outlet of the air inlet channel, so that the pressure difference of the air flow entering the engine is reduced, the uniformity is enhanced, the junction of the conical section and the arc-shaped section is designed as a step difference, and as shown in fig. 2-4, the step difference ΔR is the difference between the radius R1 of the large opening end of the conical section and the radius R2 of the second end of the arc-shaped section.
Alternatively, the difference range does not exceed 3% of the inner diameter of the small opening end of the tapered section, and an excessive difference does not reduce the pressure difference, but rather increases the pressure difference, i.e., the pressure distortion.
Although the air inlet is designed as a step, the sealing treatment is needed to be carried out on the step, so that the sealing performance of the air inlet is ensured. For example, a sealing strip or boot seal may be provided at the step.
Further, whether the air inlet is qualified or not is evaluated, performance analysis is required to be carried out on the air inlet, and the total pressure recovery coefficient sigma and the pressure distortion D are mainly considered C60 The inlet outlet section is equally divided into n parts (for example, n=18), each part is in a 360/n-degree sector shape, and the center point of the inlet outlet section is the centroid of the inlet outlet section, and a specific formula is as follows.
Wherein:
total pressure, P, indicative of mass-weighted average of inlet duct outlet cross-section w Total pressure, P, indicative of mass-weighted average of inlet cross-section of inlet duct i Is the total pressure of the sector section i, m i Mass flow rate for sector section i. i is an integer from 1 to n. />
For the minimum value of the average total pressure per 60 DEG fan-shaped section on the outlet section of the air intake duct>
Is the average total pressure on the outlet section of the air inlet channel, Q t Average dynamic pressure on inlet channel outlet section, ρ is density, v isLocal velocity in the outlet section of the inlet channel.
Compared with the shape without step difference, the proper step difference treatment is beneficial to reducing the outlet of the air inlet channel
And->
I.e. the pressure distortion is reduced, the total pressure recovery factor is less affected. In the state of 220km/h before flying, the total pressure distribution of the outlet of the air inlet channel is shown in figure 5, the pressure distortion is reduced by 21%, the total pressure recovery coefficient is basically unchanged, the stability and uniformity of air flow in the air inlet channel are enhanced, and the air inlet quality of the engine is ensured.
The key points of the invention are as follows: the air inlet channel is in a horn-shaped step-difference shape, so that pressure distortion is effectively reduced, and the air inlet quality of the engine is ensured; the sectional shape is beneficial to structural design; the inlet size of the air inlet channel is large, and the maintainability of the air inlet channel is improved.
Claims (6)
1. A horn-shaped step-difference air inlet for helicopter back air intake, the air inlet comprising: an arc section and a cone section;
the first end of the arc-shaped section is used as an inlet of the air inlet channel to be arranged at the back of the helicopter, the second end of the arc-shaped section is connected with the large-mouth end of the conical section, and the small-mouth end of the conical section is connected with the engine;
the shape of the arc-shaped section is in a horn radial shape from the second end to the first end;
the inner diameter of the second end of the arc-shaped section is smaller than that of the large opening end of the conical section, and a step difference is formed at the joint;
the inner diameter of the second end of the arc-shaped section is larger than the inner diameter of the small opening end of the conical section;
the radius of the second end of the arcuate segment differs from the radius of the large mouth end of the tapered segment by no more than 3% of the inner diameter of the small mouth end of the tapered segment.
2. The air intake of claim 1, wherein the small mouth end of the tapered section is sized to conform to an intake mounting edge of an engine.
3. The air intake of claim 1, wherein the first end of the arcuate segment has an end face aerodynamic profile that conforms to a helicopter back aerodynamic profile.
4. The inlet duct of claim 1, wherein a lowest point of the arcuate segment is lower than a lowest point of a large mouth end of the tapered segment.
5. The inlet duct of claim 1, wherein the curved segment has a bend angle of less than 90 °.
6. The inlet duct of claim 1, wherein a seal is provided at the junction of the arcuate segment and the tapered segment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111381960.3A CN114017217B (en) | 2021-11-19 | 2021-11-19 | Horn-shaped step type air inlet channel for back air inlet of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111381960.3A CN114017217B (en) | 2021-11-19 | 2021-11-19 | Horn-shaped step type air inlet channel for back air inlet of helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114017217A CN114017217A (en) | 2022-02-08 |
| CN114017217B true CN114017217B (en) | 2023-04-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111381960.3A Active CN114017217B (en) | 2021-11-19 | 2021-11-19 | Horn-shaped step type air inlet channel for back air inlet of helicopter |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3245190A1 (en) * | 1982-12-07 | 1984-06-07 | Roland 6000 Frankfurt Kurtz | Device for reducing the fuel consumption in motor vehicles with spark-ignition engine |
| JP2001099024A (en) * | 1999-09-29 | 2001-04-10 | Inoac Corp | Intake duct |
| US6522306B1 (en) * | 2001-10-19 | 2003-02-18 | Space Systems/Loral, Inc. | Hybrid horn for dual Ka-band communications |
| RU2353550C1 (en) * | 2007-11-26 | 2009-04-27 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Air intake with variable geometry for supersonic aircraft (versions) |
| CN105156286A (en) * | 2015-09-15 | 2015-12-16 | 戚荣生 | Solar hot gas flow vertical axis power generation gas inlet channel |
| EP3012447A1 (en) * | 2014-10-21 | 2016-04-27 | Yamaha Hatsudoki Kabushiki Kaisha | Straddled vehicle and method for manufacturing intake member |
| CN206668436U (en) * | 2017-03-02 | 2017-11-24 | 无锡市贝尔机械股份有限公司 | Diesel engine gaseous mixture connecting tube |
| CN108397319A (en) * | 2018-02-28 | 2018-08-14 | 荆州市福星塑料科技开发有限公司 | A kind of inlet pipe connection and preparation method thereof |
| CN208073649U (en) * | 2018-04-03 | 2018-11-09 | 无锡市贝尔机械股份有限公司 | Engine aspirating system Venturi tube |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| FR2962487B1 (en) * | 2010-07-06 | 2017-10-27 | Turbomeca | HEAT EXCHANGE ARCHITECTURE INTEGRATED WITH THE EXHAUST OF A TURBOMACHINE |
| EP3623294B1 (en) * | 2018-09-11 | 2022-08-31 | Airbus Operations S.L. | Aircraft comprising an air intake |
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2021
- 2021-11-19 CN CN202111381960.3A patent/CN114017217B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3245190A1 (en) * | 1982-12-07 | 1984-06-07 | Roland 6000 Frankfurt Kurtz | Device for reducing the fuel consumption in motor vehicles with spark-ignition engine |
| JP2001099024A (en) * | 1999-09-29 | 2001-04-10 | Inoac Corp | Intake duct |
| US6522306B1 (en) * | 2001-10-19 | 2003-02-18 | Space Systems/Loral, Inc. | Hybrid horn for dual Ka-band communications |
| RU2353550C1 (en) * | 2007-11-26 | 2009-04-27 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Air intake with variable geometry for supersonic aircraft (versions) |
| EP3012447A1 (en) * | 2014-10-21 | 2016-04-27 | Yamaha Hatsudoki Kabushiki Kaisha | Straddled vehicle and method for manufacturing intake member |
| CN105156286A (en) * | 2015-09-15 | 2015-12-16 | 戚荣生 | Solar hot gas flow vertical axis power generation gas inlet channel |
| CN206668436U (en) * | 2017-03-02 | 2017-11-24 | 无锡市贝尔机械股份有限公司 | Diesel engine gaseous mixture connecting tube |
| CN108397319A (en) * | 2018-02-28 | 2018-08-14 | 荆州市福星塑料科技开发有限公司 | A kind of inlet pipe connection and preparation method thereof |
| CN208073649U (en) * | 2018-04-03 | 2018-11-09 | 无锡市贝尔机械股份有限公司 | Engine aspirating system Venturi tube |
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| CN114017217A (en) | 2022-02-08 |
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