CN114715417A - Aircraft air inlet device, system and non-supercharged cabin - Google Patents

Aircraft air inlet device, system and non-supercharged cabin Download PDF

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Publication number
CN114715417A
CN114715417A CN202210406202.0A CN202210406202A CN114715417A CN 114715417 A CN114715417 A CN 114715417A CN 202210406202 A CN202210406202 A CN 202210406202A CN 114715417 A CN114715417 A CN 114715417A
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CN
China
Prior art keywords
air
air inlet
panel
aircraft
holes
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Pending
Application number
CN202210406202.0A
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Chinese (zh)
Inventor
张烨
石越
黄辰
齐山贺
张驰
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Commercial Aircraft Corp of China Ltd
Beijing Aeronautic Science and Technology Research Institute of COMAC
Original Assignee
Commercial Aircraft Corp of China Ltd
Beijing Aeronautic Science and Technology Research Institute of COMAC
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Publication date
Application filed by Commercial Aircraft Corp of China Ltd, Beijing Aeronautic Science and Technology Research Institute of COMAC filed Critical Commercial Aircraft Corp of China Ltd
Priority to CN202210406202.0A priority Critical patent/CN114715417A/en
Publication of CN114715417A publication Critical patent/CN114715417A/en
Pending legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • 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
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fuel Cell (AREA)

Abstract

The invention relates to an aircraft air inlet device, an aircraft air inlet system and a non-supercharged cabin, wherein the aircraft air inlet device comprises an air inlet panel, a through hole and an air guide pipe, wherein the through hole is formed in the air inlet panel; the air duct is connected on the through-hole, the size of through-hole, the length and the diameter of air duct all can be adjusted according to the air input. The invention can effectively control the air inflow and the air inflow direction of the airplane, can meet the air inflow requirements of different fuel cell airplanes, and ensures that sufficient power supply voltage is provided for the airplane.

Description

Aircraft air inlet device, system and non-supercharged cabin
Technical Field
The invention belongs to the field of aircraft air inlet treatment, and particularly relates to an aircraft air inlet device, an aircraft air inlet system and a non-supercharged cabin.
Background
The fuel cell is a high-efficiency and environment-friendly power generation device, has the remarkable advantages of zero pollution and long endurance, and is a research and development hotspot of new energy aircrafts at home and abroad. The air hydrogen fuel cell takes hydrogen as a fuel as a reducing agent and oxygen as an oxidizing agent, and chemical energy is converted into electric energy through fuel reaction. An air-to-hydrogen fuel cell provides only one reaction vessel, with both the reactants hydrogen and oxygen being provided outside the cell.
An airplane driven by a hydrogen-oxygen fuel cell is generally provided with an air inlet channel on the airplane body, and a natural air inlet mode is adopted. In flight, outside air enters the cabin interior through the air inlet duct and becomes a reactant of the fuel cell.
The traditional air inlet channel is simple in structural form, parameters such as air inflow and air inlet direction cannot be adjusted, and the complex air inlet requirement of the fuel cell cannot be met.
Disclosure of Invention
In order to overcome the problems in the prior art, the invention provides an aircraft air inlet device, an aircraft air inlet system and a non-supercharged cabin, which can effectively control the air inlet amount and the air inlet direction.
An aircraft air inlet device comprises an air inlet panel, a plurality of through holes and an air guide pipe, wherein
All the through holes are arranged on the air inlet panel;
the air inlet panel comprises an outer surface and an inner surface, and the outer surface is communicated with the atmosphere;
the inner surface is connected with the air guide tubes through holes, and each air guide tube is connected with each through hole, wherein the sizes of the through holes and the air guide tubes and the lengths of the air guide tubes can be changed.
In accordance with the above aspect and any possible implementation manner, there is further provided an implementation manner in which the through holes are circular, and are distributed on the panel in a staggered arrangement, a longitudinal arrangement, a transverse arrangement, or a random arrangement.
The above aspect and any possible implementation manner further provide an implementation manner, where the aircraft panel is rectangular, and a distance from a center of the through hole disposed at the edge of the air intake panel to the edge of the air intake panel is greater than or equal to 3 times a radius of the through hole.
The above aspect and any possible implementation further provide an implementation in which the air intake rate of the air intake device is adjustable, and the size of the air intake rate is related to the radius of the through holes, the transverse distance and the longitudinal distance between any two through holes.
In accordance with the above aspect and any possible implementation manner, there is further provided an implementation manner, in which each air duct is perpendicular to the air intake panel, that is, a central axis of the air duct is in a direction consistent with a normal direction of the air intake panel; or each air duct and the included angle of the air inlet duct panel is 0-45 degrees.
The above aspect and any possible implementation further provide an implementation in which all of the gas-guide tubes are equal in length and have a thin-walled tube structure.
The above aspect and any possible implementation manner further provide an implementation manner, wherein the air duct includes two ends, one end of the air duct is connected to the through hole, the cross section of the other end is a chamfered surface, and a chamfer angle of the chamfered surface is greater than 0 degree and less than or equal to 90 degrees.
The invention also provides a non-supercharged cabin comprising the aircraft air intake device of the invention.
The invention also provides an aircraft air inlet system, which comprises a fuel cell and the non-supercharged cabin, wherein the non-supercharged cabin provides external air for the fuel cell through an aircraft air inlet device.
The above aspect and any possible implementation further provide an implementation in which the length of the air duct is adjustable according to the distance between the air intake panel and the fuel cell.
The invention has the advantages of
Compared with the prior art, the invention has the following beneficial effects:
the aircraft air inlet device comprises an air inlet panel, a plurality of through holes and air guide pipes, wherein all the through holes are formed in the air inlet panel; the air inlet panel comprises an outer surface and an inner surface, and the outer surface is communicated with the atmosphere; the inner surface is connected with the air guide tubes through holes, and each air guide tube is connected with each through hole, wherein the sizes of the through holes and the air guide tubes and the lengths of the air guide tubes can be changed. The invention can meet the requirement of set air input by adjusting the parameters of the size of the through hole and the air duct on the air inlet device, the length direction of the air duct and the like, and can be used for small fuel cell airplanes of different types.
Drawings
FIG. 1 is a plan view of an air intake device in an embodiment of the invention;
FIG. 2 is a schematic diagram of the cross-sectional arrangement of circular through holes on an intake faceplate according to an embodiment of the present invention;
FIG. 3 is a schematic view of the radius and spacing of circular through holes on an intake faceplate in an embodiment of the invention;
FIG. 4 is a front view of an air intake device in an embodiment of the present invention;
fig. 5 is a perspective view of an air intake device in an embodiment of the invention;
FIG. 6 is a schematic view of the air flow through the intake faceplate and the air duct in an embodiment of the present invention;
fig. 7 is a schematic view of the operating principle of a hydrogen fuel cell stack in an embodiment of the present invention.
Detailed Description
In order to better understand the technical solution of the present invention, the present disclosure includes but is not limited to the following detailed description, and similar techniques and methods should be considered as within the scope of the present invention. In order to make the technical problems, technical solutions and advantages of the present invention more apparent, the following detailed description is given with reference to the accompanying drawings and specific embodiments.
It should be understood that the described embodiments of the invention are only some embodiments of the invention, and not all embodiments. 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 invention.
The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the examples of the present invention and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
As shown in fig. 1, which is an overall framework of the present invention, the method according to the present invention does not limit the specific operating hardware and programming language, and can be implemented by writing in any language, so that other working modes are not described again.
Preferably, the embodiment of the present invention provides an air inlet device, which comprises an air inlet panel 12, wherein the panel is a thin plate section and is provided with uniformly distributed circular through holes 13. Each through hole 13 is connected with an air duct 14, the air duct 14 is of a thin-wall tube type structure, the air inlet panel 12 comprises an outer surface and an inner surface, the outer surface faces the atmosphere, and the inner surface is connected with all the air ducts 14 through the through holes 13, namely all the air ducts 14 are arranged on one side of the air inlet device facing the cabin interior 11. Each air duct 14 comprises two ends, one end of each air duct is connected with the through hole 13, one end of each air duct 14, which is far away from the air inlet panel 12 and the cabin exterior 10, is provided with a chamfer 15, the angle between the chamfer 15 and the normal of the air inlet panel 12 is a chamfer angle, and the chamfer angle of the chamfer is between 0 degree and 90 degrees, namely, is greater than 0 degree and is less than or equal to 90 degrees. The air inlet panel 12 can be made of non-metallic materials such as nylon, so that the air inlet panel 12 has the advantages of light weight, good forming quality and high forming speed, is suitable for small-sized general airplanes, and the number of the through holes 13 arranged on the air inlet panel is the same as that of the air guide tubes 14.
Preferably, as shown in fig. 2, the through holes 13 of the air inlet device 12 in the embodiment of the present invention may be arranged in various ways, specifically, but not limited to, staggered arrangement, longitudinal and transverse arrangement, random arrangement, and the like. As shown in fig. 3, when the through holes 13 are circular, the air intake rate of the air intake device 12 is related to the radius of the circular through holes 13, the transverse distance and the longitudinal distance between any two circular through holes 13Specifically, the radius of each circular through hole 13 is set to r, and the lateral distance between two circular through holes 13 is set to d1Longitudinal spacing of d2Then, the estimation formula of the intake rate γ of the intake device is: gamma-pi r2/(d1×d2) According to different fuel cells, the air inlet rate of the air inlet device can be flexibly adjusted by changing the radius of the through holes and the transverse and longitudinal spacing between the through holes.
Preferably, in the embodiment of the present invention, the shape of the air intake panel is rectangular, and the four corners are rounded, and the distance from the center of the through hole 13 at the edge of the air intake panel 12 to the edge of the air intake panel 12 is greater than or equal to 3r, that is, 3 times of the radius of the through hole 13, so as to ensure that the air entering through the through hole 13 of the air intake panel 12 can be completely introduced into the fuel cell as much as possible.
Preferably, as shown in fig. 4 and 6, all the air ducts 14 in the embodiment of the present invention are perpendicular to the air intake panel, i.e. the central axis of the air duct is in line with the normal direction of the air intake panel, so as to ensure that the flow of the incoming air is perpendicular to the direction of the air intake panel 12; or, as shown in fig. 5, the air duct 14 may not be perpendicular to the air intake panel 12, and the included angle between the air duct 14 and the air intake panel 12 is set to be 0 to 45 degrees, so that the angle between the entering air flow and the air intake duct panel direction is 0 to 45 degrees, and the air flow direction of the air entering the body can be adjusted by changing the angle between the axis of the air duct 14 and the normal direction between the air intake duct panel 12, and all the air ducts 14 in the present invention have the same length, and the thickness or the radius can be adjusted according to the size of the through hole 13, thereby ensuring the sealing connection between the air duct 14 and the through hole 13.
Preferably, the air duct 14 and the air intake panel 12 are connected together in an embodiment of the present invention. The invention adopts advanced manufacturing technology to integrally form the air inlet panel 12, the circular through hole 13 and the air duct 14 at the upper part at one time, and the air inlet panel 12 and the air duct 14 do not need to be connected by other media through the integral forming, thereby saving time and improving product quality.
Preferably, the embodiment of the invention also provides a non-pressurized cabin, the non-pressurized cabin comprises the aircraft air inlet device, and the through hole in the air inlet device is in a normally open state, so that air can be allowed to freely flow through the air guide pipe, and the non-pressurized cabin is suitable for the non-pressurized cabin.
Preferably, an embodiment of the present invention further provides an aircraft air intake system comprising a fuel cell and the non-pressurized cabin of the present invention, the non-pressurized cabin providing external air to the fuel cell through an aircraft air intake device.
Preferably, in the embodiment of the present invention, in the flight of an airplane, air outside the cabin enters the air duct 14 through the circular through hole 13 on the air intake panel 12, the air flows along the air duct 14, enters the cabin interior, and then provides reactants for the fuel cell, and the present invention adopts a hydrogen fuel cell stack, and the hydrogen fuel cell stack burns under the condition of reacting with the air. The air outside the non-supercharging cabin can accurately flow to the hydrogen fuel cell stack through the air inlet panel 12 according to the length direction of the air guide pipe 14, so that the air inlet efficiency can be improved; meanwhile, unnecessary influence of the airflow on other equipment and the like can be avoided. Aiming at the air inlet requirements of different fuel cells, the air inlet amount can be adjusted by changing the air inlet rate of the air inlet device, or the air inlet direction can be adjusted by changing the length direction of the air guide pipe 14 and the angle of the oblique plane at the far end of the air guide pipe 14, namely the air inlet amount and the air inlet direction of the air inlet device can be changed.
Preferably, the length of the air duct 14 in the embodiment of the present invention is related to the distance between the air intake panel 12 and the hydrogen fuel cell stack, and when the air intake panel 12 is closer to the hydrogen fuel cell stack, the length of the air duct 14 is shorter, and conversely, when the distance is farther, the length of the air duct 14 is longer, so that the chamfered surface of the air duct 14 should be close to the hydrogen fuel cell stack as much as possible, so that the hydrogen fuel cell stack reacts with air as much as possible.
The operating principle of the hydrogen fuel cell stack is shown in fig. 7. During the use of the hydrogen fuel cell stack, hydrogen is supplied from the hydrogen storage tank. Reacting with hydrogen is oxygen, and the primary source of oxygen is air. Air at atmospheric pressure typically does not provide sufficient oxygen for the hydrogen fuel cell. The invention adopts the air inlet device without adopting an additional supercharging device, and when the aircraft flies, a narrow space is formed between the air guide pipes 14 on the air inlet panel 12, so that the air entering the interior of the aircraft body is accelerated to flow, the local air pressure is increased, and sufficient air input is provided for the hydrogen fuel battery pack, thereby providing sufficient oxygen input. The size and dimensions of the gas-guiding tube 14, such as the radius and length, can be changed according to the required oxygen input of the hydrogen fuel cell stack. The hydrogen fuel cell stack releases heat when a chemical reaction occurs, and the ambient temperature may rise to 85 degrees or more, so that the gas guide tube 14 has a thin-walled tube structure to ensure normal operation during the temperature rise.
The foregoing description shows and describes several preferred embodiments of the invention, but as aforementioned, it is to be understood that the invention is not limited to the forms disclosed herein, but is not to be construed as excluding other embodiments and is capable of use in various other combinations, modifications, and environments and is capable of changes within the scope of the inventive concept as expressed herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the invention as defined by the appended claims.

Claims (10)

1. The aircraft air inlet device is characterized by comprising an air inlet panel, a plurality of through holes and an air guide pipe, wherein the air inlet panel is provided with a plurality of through holes
All the through holes are arranged on the air inlet panel;
the air inlet panel comprises an outer surface and an inner surface, and the outer surface is communicated with the atmosphere;
the inner surface is connected with the air guide tubes through holes, and each air guide tube is connected with each through hole, wherein the sizes of the through holes and the air guide tubes and the lengths of the air guide tubes can be changed.
2. An aircraft air induction device according to claim 1, wherein the through-holes are circular in shape and are distributed in a staggered, cross-wise or random arrangement on the panel.
3. An aircraft air induction device according to claim 2, wherein the aircraft panel is rectangular and the distance from the centre of the through hole at the edge of the air induction panel to the edge of the air induction panel is greater than or equal to 3 times the radius of the through hole and greater.
4. An aircraft air inlet device according to claim 3, wherein the air inlet rate of the air inlet device is adjustable and the magnitude of the air inlet rate is related to the radius of the through holes, the lateral spacing and the longitudinal spacing between any two of the through holes.
5. An aircraft air induction device according to claim 1, wherein each air duct is perpendicular to the air intake panel; or the included angle between each air guide pipe and the air inlet panel is 0-45 degrees.
6. An aircraft air induction device according to claim 3, wherein all of the air ducts are of equal length and are of thin-walled tubular construction.
7. An aircraft air inlet device according to claim 3, wherein the air duct comprises two ends, one end of the air duct is connected with the through hole, the end of the other end is provided with a chamfer, and the chamfer angle of the chamfer is greater than 0 degree and less than or equal to 90 degrees.
8. A non-pressurized cabin, characterized in that it comprises an aircraft air intake device according to any one of claims 1 to 7.
9. An aircraft air intake system comprising a fuel cell and a non-pressurized cabin as claimed in claim 8, the non-pressurized cabin providing external air to the fuel cell via an aircraft air intake.
10. An aircraft air intake system according to claim 9, wherein the length of the air duct is adjustable in dependence on the distance between the air intake panel and the fuel cell.
CN202210406202.0A 2022-04-18 2022-04-18 Aircraft air inlet device, system and non-supercharged cabin Pending CN114715417A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210406202.0A CN114715417A (en) 2022-04-18 2022-04-18 Aircraft air inlet device, system and non-supercharged cabin

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210406202.0A CN114715417A (en) 2022-04-18 2022-04-18 Aircraft air inlet device, system and non-supercharged cabin

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Publication Number Publication Date
CN114715417A true CN114715417A (en) 2022-07-08

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6138950A (en) * 1998-10-06 2000-10-31 Northrop Grumman Corporation Aircraft engine air intake system
US20130336781A1 (en) * 2011-11-24 2013-12-19 Rolls-Royce Plc Aircraft
CN110805495A (en) * 2019-12-05 2020-02-18 江西洪都航空工业集团有限责任公司 Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft
CN217416121U (en) * 2022-04-18 2022-09-13 中国商用飞机有限责任公司北京民用飞机技术研究中心 Air conveying device, cabin and system of airplane

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6138950A (en) * 1998-10-06 2000-10-31 Northrop Grumman Corporation Aircraft engine air intake system
US20130336781A1 (en) * 2011-11-24 2013-12-19 Rolls-Royce Plc Aircraft
CN110805495A (en) * 2019-12-05 2020-02-18 江西洪都航空工业集团有限责任公司 Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft
CN217416121U (en) * 2022-04-18 2022-09-13 中国商用飞机有限责任公司北京民用飞机技术研究中心 Air conveying device, cabin and system of airplane

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