CN114735194A - Aircraft cabin exhaust flow guide structure and method - Google Patents

Aircraft cabin exhaust flow guide structure and method Download PDF

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Publication number
CN114735194A
CN114735194A CN202210209309.6A CN202210209309A CN114735194A CN 114735194 A CN114735194 A CN 114735194A CN 202210209309 A CN202210209309 A CN 202210209309A CN 114735194 A CN114735194 A CN 114735194A
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CN
China
Prior art keywords
aircraft cabin
air
air guide
air inlet
exhaust
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
Application number
CN202210209309.6A
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Chinese (zh)
Inventor
李志杰
谭友德
王辉
盛世龙
石江波
朱璇
王源杰
卢迪
杨攀
李智
高旭
曹丽芳
王博哲
范开春
涂正光
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.)
General Designing Institute of Hubei Space Technology Academy
Original Assignee
General Designing Institute of Hubei Space Technology Academy
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by General Designing Institute of Hubei Space Technology Academy filed Critical General Designing Institute of Hubei Space Technology Academy
Priority to CN202210209309.6A priority Critical patent/CN114735194A/en
Publication of CN114735194A publication Critical patent/CN114735194A/en
Pending legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/40—Sound or heat insulation, e.g. using insulation blankets
    • 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
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Exhaust Silencers (AREA)

Abstract

The invention provides an exhaust and flow guide structure and method for an aircraft cabin, belonging to the technical field of an internal flow channel of an aircraft. An air guide pipeline with one end communicated with the air inlet is arranged in the aircraft cabin body, and the other end of the air guide pipeline is communicated with the outside of the aircraft cabin body. The air entering from the air inlet opening is transmitted to the outside of the aircraft cabin body through the air inlet hole and the air guide pipeline in sequence. The structure of the invention is isolated from the interior of the cabin body, so that high-temperature airflow entering the front structure can be led out when the aircraft flies, and the temperature in the cabin is prevented from rising.

Description

Aircraft cabin exhaust flow guide structure and method
Technical Field
The invention relates to the technical field of an inner flow passage of an aircraft, in particular to an exhaust and flow guide structure and method of an aircraft cabin.
Background
When the aircraft flies, high-temperature airflow entering from the front structure easily enters the cabin body to cause the temperature of the cabin body to rise if certain measures are not taken, and the temperature exceeds the service temperature condition of single-machine equipment in the cabin body, so that the success or failure of a flight task is directly influenced.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides an air exhaust and flow guide structure and method for an aircraft cabin, which are isolated from the interior of the cabin, so that high-temperature air flow entering the front structure can be guided out when the aircraft flies, and the temperature in the cabin is prevented from rising.
In order to achieve the above purposes, the technical scheme is as follows:
an air exhaust and flow guide structure of an aircraft cabin is provided, wherein the front end of the aircraft cabin is provided with an air inlet opening; the aircraft cabin body exhaust diversion structure comprises:
the flow baffle is arranged in the aircraft cabin body and is positioned behind the air inlet opening, a sealing assembly is arranged between the flow baffle and the aircraft cabin body, and an air inlet is formed in the flow baffle;
the air guide pipeline is positioned in the aircraft cabin body and arranged along the flight direction of the aircraft cabin body, the front end of the air guide pipeline is communicated with the air inlet holes, and the tail end of the air guide pipeline is communicated with the outside of the aircraft cabin body.
Preferably, the front end of the air guide pipeline is connected with the air inlet hole through a first connecting assembly;
the first connection assembly includes:
one end of the first filler neck is communicated with the air inlet;
one end of the first spherical joint is sleeved at the front end of the air guide pipeline;
and the first outer sleeve nut is sleeved at the other end of the first filler neck and the other end of the first spherical joint and is used for connecting the first filler neck and the first spherical joint.
Preferably, an inclined exhaust hole is formed in the rear of the aircraft cabin;
the rear end of the air guide pipeline is communicated with the inclined exhaust hole.
Preferably, a preset angle is formed between the rear end of the air guide pipeline and the inclined exhaust hole.
Preferably, the aircraft cabin exhaust air guide structure further comprises:
and the gas collecting box is positioned in the aircraft cabin body and is communicated with the tail end of the gas guide pipeline and the inclined exhaust hole.
Preferably, the tail end of the air guide pipeline is connected with the air collecting box through a second connecting assembly;
the second connection assembly includes:
one end of the second pipe connecting nozzle is communicated with the gas collecting box;
one end of the second spherical joint is sleeved at the tail end of the air guide pipeline;
and the second outer sleeve nut is sleeved at the other end of the second filler neck and the other end of the second spherical joint and is used for connecting the second filler neck and the second spherical joint.
Preferably, the air inlet opening is a circular opening;
the sealing assembly is arranged on the flow baffle plate and is provided with a sealing groove matched with the shape of the air inlet opening, and a sealing ring is arranged in the sealing groove.
Preferably, the gas guide pipeline is fixed on the inner wall of the aircraft cabin body through a plurality of hoops.
An aircraft cabin exhaust and flow guide method, wherein the front end of the aircraft cabin is provided with an air inlet opening; the aircraft cabin exhaust diversion method comprises the following steps:
a flow baffle plate is arranged in the aircraft cabin body and behind the air inlet opening, a sealing assembly is arranged between the flow baffle plate and the aircraft cabin body, and an air inlet is formed in the flow baffle plate;
an air guide pipeline with one end communicated with the air inlet is arranged in the aircraft cabin body, and the other end of the air guide pipeline is communicated with the outside of the aircraft cabin body;
the air entering from the air inlet opening is transmitted to the outside of the aircraft cabin body through the air inlet hole and the air guide pipeline in sequence.
Preferably, the exhaust and flow guide method of the aircraft cabin further comprises the following steps:
and a gas collection box communicated with the gas guide pipeline is arranged at the rear part in the aircraft cabin body, and is communicated with an inclined exhaust hole at the rear part of the aircraft cabin body.
The invention has the beneficial effects that:
according to the exhaust flow guide structure, the flow baffle plate is arranged on the inner side of the front end frame of the cabin body, the sealing structure is designed, high-temperature airflow can be effectively prevented from flowing into the cabin body, meanwhile, the air inlet hole is designed, the flow baffle plate is prevented from being loaded by large air pressure, and the exhaust flow guide structure is safe and reliable.
The gas collecting box is arranged at the rear part and used for buffering to prevent the guided airflow from directly scouring the cabin body structure, and the load risk of the cabin body is reduced.
The interior of the gas collection box is communicated with the inclined exhaust holes designed on the cabin body, and the inclined exhaust holes on the cabin body are designed to be inclined backwards and against the direction of airflow, so that external airflow is prevented from flowing backwards into the cabin body.
The gas guide pipeline is respectively communicated with the flow baffle and the gas collecting box, the diameter of the pipeline is designed to be proper, an effective high-temperature gas flow diversion flow channel can be formed, the cabin body is isolated from the inside, and the high-temperature gas flow is guided out.
Drawings
FIG. 1 is a schematic diagram of an aircraft cabin exhaust air guiding structure and method according to an embodiment of the present invention.
Fig. 2 is a schematic cross-sectional view taken along line a-a in fig. 1.
Fig. 3 is a schematic cross-sectional view at B-B in fig. 1.
1-an aircraft cabin; 2-a flow baffle; 3-sealing ring; 4-a gas guide pipeline; 5-a first filler neck; 6-first outer sleeve nut; 7-a first spherical joint; 8-a gas collection box; 9-clamping a hoop; 10-a second filler neck; 11-a second housing nut; 12-a second ball joint; 13-inclined vent hole.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific examples described herein are intended to be illustrative only and are not intended to be limiting. Moreover, all other embodiments that can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort belong to the protection scope of the present invention.
The present invention will be described in further detail with reference to the drawings and examples.
As shown in fig. 1, the invention discloses an exhaust and flow guide structure of an aircraft cabin, wherein the front end of the aircraft cabin 1 is provided with an air inlet opening, and the rear of the aircraft cabin 1 is provided with an oblique exhaust hole 13. The exhaust and flow guide structure of the aircraft cabin comprises a flow baffle plate 2 which is arranged inside the aircraft cabin 1 and is positioned behind an air inlet opening, a sealing assembly is arranged between the flow baffle plate 2 and the aircraft cabin 1, and the flow baffle plate 2 is provided with an air inlet. The air guide pipeline 4 is connected to the inlet port, and the air guide pipeline 4 is located the inside of the aircraft cabin body 1, and sets up along the aircraft cabin body 1 direction of flight, the front end of air guide pipeline 4 with the inlet port intercommunication, the end of air guide pipeline 4 with the outside intercommunication of the aircraft cabin body 1.
In this embodiment, the fender of aircraft cabin 1 preceding terminal surface area seal groove structure flows board 2 through the screw installation, guarantee the heat-seal of the preceding terminal surface of the cabin body behind the installation sealing washer 3, avoid high-temperature air current to get into the under-deck, the inlet port is designed simultaneously, avoid keeping off and flow board 2 and receive great atmospheric pressure load, safety and reliability, lay along cabin internal portion with the air duct way 4 of inlet port intercommunication, constitute the air discharge flow way and with cabin internal portion isolated, when the realization is when the aircraft flies, derive the high-temperature air current that anterior structure got into, avoid the function that the cabin internal temperature risees.
In a preferred embodiment, as shown in fig. 2, the front end of the air guide pipe 4 is connected to the air inlet hole through a first connecting assembly. The first connection assembly comprises a first filler neck 5 and a first ball joint 7 which are fixedly connected by a first outer nut 6. One end of the first filler neck 5 is communicated with the air inlet, one end of the first spherical joint 7 is sleeved at the front end of the air guide pipeline 4, and the other end of the first filler neck 5 and the other end of the first spherical joint 7 are sleeved with the first outer nut 6.
In this embodiment, the baffle 2 is provided with an air inlet, and the first filler neck 5 is welded to the air inlet to form a flow guiding structure at the front of the cabin.
In a preferred embodiment, as shown in fig. 3, the rear end of the air guide pipe 4 is communicated with the inclined exhaust hole 13. A preset angle is formed between the rear end of the air guide pipeline 4 and the inclined exhaust hole 13.
In this embodiment, the rear end of the air duct 4 is communicated with an oblique air vent hole designed on the cabin body, and the oblique air vent hole on the cabin body is designed to be backward oblique and against the air flow direction, so as to prevent external air flow from flowing backward into the cabin body.
In a preferred embodiment, the exhaust and flow guide structure of the aircraft cabin further includes a gas collecting box located inside the aircraft cabin 1 and communicated with the end of the gas guide pipeline 4 and the oblique exhaust hole 13.
The second connecting assembly comprises a second filler neck 10 and a second spherical joint 12 which are fixedly connected through a second casing nut 11, one end of the second filler neck 10 is communicated with the gas collecting box 8, one end of the second spherical joint 12 is sleeved at the tail end of the gas guide pipeline 4, and a second casing nut 11 is sleeved at the other end of the second filler neck 10 and the other end of the second spherical joint 12 and used for connecting the second filler neck 10 with the second spherical joint 12.
In the embodiment, the gas collecting box 8 is installed on the rear end surface of the aircraft cabin 1 through screws; the interior of the gas collection box 8 is communicated with a backward inclined exhaust hole 13 designed on the aircraft cabin body 1. The front end of the gas collecting box 8 is provided with an opening, a second filler pipe 10 is welded, and the second filler pipe is connected with the gas guide pipeline 4 through a second outer sleeve nut 11 and a second spherical joint 12 to form a high-temperature gas flow exhaust channel and be isolated from the interior of the cabin body, so that high-temperature gas flow entering the front structure is led out when the aircraft flies, and the temperature in the cabin is prevented from rising.
In a preferred embodiment, the air inlet opening is a circular opening.
The sealing assembly is arranged on the flow baffle plate 2 and is a sealing groove matched with the shape of the air inlet opening, and a sealing ring 3 is arranged in the sealing groove.
In the preferred embodiment, the air guide line 4 is fastened to the inner wall of the aircraft cabin 1 by means of a plurality of clips 9.
The invention also discloses an aircraft cabin exhaust and flow guide method, wherein the front end of the aircraft cabin 1 is provided with an air inlet opening, and the aircraft cabin exhaust and flow guide method comprises the following steps:
a flow baffle plate 2 is arranged in the aircraft cabin body 1 behind the air inlet opening, a sealing assembly is arranged between the flow baffle plate 2 and the aircraft cabin body 1, and an air inlet is formed in the flow baffle plate.
An air duct 4 with one end communicated with the air inlet is arranged inside the aircraft cabin 1, and the other end of the air duct 4 is communicated with the outside of the aircraft cabin 1.
The air entering from the air inlet opening is conveyed to the outside of the aircraft cabin 1 through the air inlet and the air duct 4 in that order.
Further, a gas collection box 8 communicated with the gas guide pipeline 4 is arranged at the rear part in the aircraft cabin body 1, and the gas collection box 8 is communicated with an inclined exhaust hole 13 at the rear part of the aircraft cabin body 1.
The present invention is not limited to the above-described embodiments, and it will be apparent to those skilled in the art that various modifications and improvements can be made without departing from the principle of the present invention, and such modifications and improvements are also considered to be within the scope of the present invention. Those not described in detail in this specification are within the skill of the art.

Claims (10)

1. An aircraft cabin exhaust and flow guide structure is characterized in that the front end of an aircraft cabin (1) is provided with an air inlet opening; it is characterized in that the air exhaust and flow guide structure of the aircraft cabin comprises:
the flow baffle plate (2) is arranged inside the aircraft cabin body (1) and is positioned behind the air inlet opening, a sealing assembly is arranged between the flow baffle plate (2) and the aircraft cabin body (1), and an air inlet is formed in the flow baffle plate (2);
the air guide pipeline (4) is located inside the aircraft cabin body (1) and arranged along the flight direction of the aircraft cabin body (1), the front end of the air guide pipeline (4) is communicated with the air inlet holes, and the tail end of the air guide pipeline (4) is communicated with the outside of the aircraft cabin body (1).
2. An aircraft cabin exhaust air guide structure according to claim 1, wherein the front end of the air guide pipeline (4) is connected with the air inlet hole by a first connecting component;
the first connection assembly includes:
a first filler neck (5), one end of which is communicated with the air inlet;
a first spherical joint (7), one end of which is sleeved at the front end of the air guide pipeline (4);
and the first outer sleeve nut (6) is sleeved at the other end of the first filler neck (5) and the other end of the first spherical joint (7) and is used for connecting the first filler neck (5) and the first spherical joint (7).
3. The aircraft cabin exhaust air guide structure according to claim 1, wherein the aircraft cabin (1) has an oblique exhaust hole (13) at the rear;
the rear end of the air guide pipeline (4) is communicated with the inclined exhaust hole (13).
4. The exhaust and air guide structure of an aircraft cabin according to claim 3, wherein the rear end of the air guide pipeline (4) has a predetermined angle with the oblique exhaust hole (13).
5. The aircraft cabin exhaust air guide structure of claim 3, further comprising:
the gas collecting box (8) is located inside the aircraft cabin body (1) and is communicated with the tail end of the gas guide pipeline (4) and the inclined exhaust hole (13).
6. The aircraft cabin exhaust air guide structure of claim 5, wherein the end of the air guide pipeline (4) is connected to the air collection box (8) by a second connection assembly;
the second connection assembly includes:
a second filler neck (10), one end of which is communicated with the gas collecting box (8);
a second spherical joint (12), one end of which is sleeved at the tail end of the air guide pipeline (4);
and the second outer sleeve nut (11) is sleeved at the other end of the second filler neck (10) and the other end of the second spherical joint (12) and is used for connecting the second filler neck (10) and the second spherical joint (12).
7. The aircraft cabin exhaust air guide structure of claim 1 wherein the air inlet opening is a circular opening;
the sealing assembly is arranged on the flow blocking plate (2) and is provided with a sealing groove matched with the shape of the air inlet opening, and a sealing ring (3) is arranged in the sealing groove.
8. An aircraft cabin exhaust air guide arrangement according to claim 1, characterised in that the air guide line (4) is fastened to the inner wall of the aircraft cabin (1) by means of a plurality of clips (9).
9. An aircraft cabin exhaust and flow guide method, wherein the front end of an aircraft cabin (1) is provided with an air inlet opening; the method for exhausting and guiding the aircraft cabin is characterized by comprising the following steps:
a flow baffle plate (2) is arranged in the aircraft cabin body (1) and behind the air inlet opening, a sealing assembly is arranged between the flow baffle plate (2) and the aircraft cabin body (1), and an air inlet is formed in the flow baffle plate;
an air guide pipeline (4) with one end communicated with the air inlet is arranged in the aircraft cabin body (1), and the other end of the air guide pipeline (4) is communicated with the outside of the aircraft cabin body (1);
the air entering from the air inlet opening is transmitted to the outside of the aircraft cabin (1) through the air inlet hole and the air guide pipeline (4) in sequence.
10. The aircraft cabin exhaust air guiding method of claim 9, further comprising:
the rear part in the aircraft cabin body (1) is provided with a gas collection box (8) communicated with the gas guide pipeline (4), and the gas collection box (8) is communicated with an inclined exhaust hole (13) in the rear part of the aircraft cabin body (1).
CN202210209309.6A 2022-03-04 2022-03-04 Aircraft cabin exhaust flow guide structure and method Pending CN114735194A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210209309.6A CN114735194A (en) 2022-03-04 2022-03-04 Aircraft cabin exhaust flow guide structure and method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210209309.6A CN114735194A (en) 2022-03-04 2022-03-04 Aircraft cabin exhaust flow guide structure and method

Publications (1)

Publication Number Publication Date
CN114735194A true CN114735194A (en) 2022-07-12

Family

ID=82274682

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210209309.6A Pending CN114735194A (en) 2022-03-04 2022-03-04 Aircraft cabin exhaust flow guide structure and method

Country Status (1)

Country Link
CN (1) CN114735194A (en)

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