CN112759008A

CN112759008A - Aviation water-gas separation device

Info

Publication number: CN112759008A
Application number: CN202011536264.0A
Authority: CN
Inventors: 胡瑞阳
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-12-23
Filing date: 2020-12-23
Publication date: 2021-05-07

Abstract

The invention relates to the technical field of water-gas separation devices, and discloses an aviation water-gas separation device which comprises a shell, wherein a pressure sensor sensing piece of a machine body is arranged above the shell, a plurality of groups of mutually communicated gas source inlets are formed in the middle of the upper surface of the pressure sensor sensing piece of the machine body, the gas source inlets are communicated downwards with a gas inlet pipeline vertically extending downwards into the shell, the lower end of the gas inlet pipeline is communicated with a heating chamber, a heating block is fixedly arranged in the middle of the inner bottom surface of the heating chamber, an L-shaped detection pipeline extending towards the upper left side is communicated with the left side surface of the heating chamber, and a two-position valve. The invention has the beneficial effects that: the separation of aqueous vapor has been realized, and can provide the heat source to fuselage pressure sensor sensitive piece again, has avoided extravagant a large amount of heats, has increased the utilization efficiency of the energy, has reduced the influence that water caused in getting into the detection pipeline, has reduced the restriction of device use, is favorable to the use.

Description

Aviation water-gas separation device

Technical Field

The invention relates to the technical field of water-gas separation devices, in particular to an aviation water-gas separation device.

Background

The functional structure of the machine body pressure sensor is composed of a surface pressure measuring part and an atmospheric data resolving part, and as the machine body pressure sensor is exposed in air flow outside the machine body, rainwater in the atmosphere can enter the interior of a product to influence the pressure transmission precision of the product and cause pressure hysteresis. Therefore, the product is designed to have waterproof and water removal capabilities so as to ensure that the airplane normally works under the weather conditions, the existing water-gas separation device occupies a certain size space inside and outside the product, the water cup cleaning maintenance process is troublesome, and the air tightness of the product is not easy to ensure.

In order to solve the problems, the conventional aviation water-gas separation device comprises a water removal precipitator containing cavity and a water removal heater, wherein the water removal precipitator containing cavity is of a cavity structure and is provided with an inlet and an outlet of a gas source, the inlet of the gas source is arranged above the water removal precipitator containing cavity, the outlet of the gas source is higher than the bottom surface of the water removal precipitator containing cavity, the inlet of the gas source is communicated with a pressure measuring hole of a pressure sensor of a machine body pressure sensor, the outlet of the gas source is communicated with a pressure sensor inside the machine body pressure sensor, the water removal heater is arranged between the water removal precipitator containing cavity and the pressure sensor of the machine body, when the aviation water-gas separation device is used, atmospheric condensate water, rainwater and the like enter the water removal precipitator containing cavity and then stay at the bottom of the water removal precipitator containing cavity, the water removal heater is arranged above the water removal precipitator containing cavity, and when the, and can cause great loss among the heat transmission process, very big increase the loss of the energy, reduce the utilization ratio of the energy, and the device takes place to rock in the water that dewatering precipitator appearance chamber easily enters the pipeline that the air supply detected, and then leads to the atmospheric pressure testing result skew, is unfavorable for the use.

Disclosure of Invention

The invention aims to provide an aviation water-gas separation device to solve the problems in the background technology.

In order to achieve the purpose, the invention provides the following technical scheme:

the utility model provides an aviation aqueous vapor separator, includes the casing, the casing top is provided with fuselage pressure sensor and receives the sensing piece, and pressure sensor receives sensing piece fuselage upper surface middle part and sets up the air supply import of multiunit mutual intercommunication, and the air supply import communicates downwards has vertical inlet duct that stretches into in the casing downwards, and inlet duct lower extreme intercommunication has the heating chamber, and bottom middle part fixed mounting has the heating piece in the heating chamber, heating chamber left surface intercommunication has the L type detection pipeline that stretches out to the upper left, and detection pipeline lower extreme fixed mounting has two valves, and fixed mounting has the humidity transducer who is located two valve tops in the detection pipeline, two valve communicate downwards has the second branch pipe that L type and horizontal segment extend to the right, and second branch pipe right-hand member intercommunication has the air chamber, and bottom middle part fixed mounting has pressure sensor in the air chamber.

As a further scheme of the invention: the casing with fuselage pressure sensor receives to be provided with the cavity between the piece, and fuselage pressure sensor receives to sense a lower surface and sets up to the structure that the inboard is high outside low, and the evaporation hole that is located directly over the heating chamber is seted up to the casing upper surface, and the evaporation hole sets up to big-end-up's bell mouth structure and evaporation hole lower extreme communicate on the heating chamber.

As a further scheme of the invention: fixed surface installs two sets of supports that lie in the cavity bilateral symmetry and distribute on the casing, and fixed mounting has the water receiving tank that the cross-section is the U type on the support, and water receiving tank internal side surface upper portion and lower part all set up to the high inboard low inclined plane structure in the outside, set up the recess that the multiunit distributes along water receiving tank length direction about in the water receiving tank on the vertical section side, and sliding connection has the drainage plate of fixed mounting at fuselage pressure sensor receiving sensing piece lower surface in the water receiving tank, vertical section side contact in side lower part and the water receiving tank about the drainage plate.

As a further scheme of the invention: the water receiving tank is communicated downwards with a water inlet pipe vertically extending into the shell, a one-way valve located in the cavity is fixedly mounted on the water inlet pipe, and the lower end of the water inlet pipe is communicated with collecting boxes fixedly mounted on two sides of the bottom in the shell.

As a further scheme of the invention: the upper part of the pipeline, extending leftwards and downwards, of the detection pipeline is fixedly provided with two groups of water baffles which are matched with each other, a backflow pipe communicated with the two ends of the detection pipeline is arranged on the upper side of the lower water baffle, and the backflow pipe inclines rightwards and downwards.

As a still further scheme of the invention: the two-position valve is communicated with a first branch pipe downwards, and the lower end of the first branch pipe is communicated to the left collecting box.

Compared with the prior art, the invention has the beneficial effects that: by arranging the cavity, the heating chamber and the heating block, atmospheric condensate water, rainwater and the like enter the heating chamber and then are heated by the heating block, moisture is evaporated and then enters the cavity to contact the machine body pressure sensor and be heated by the sensing piece, and then the heat is released by condensation to heat the machine body pressure sensor and the sensing piece, the condensate water flows along the lower surface of the machine body pressure sensor and is collected, so that the separation of water and air is realized, a heat source can be provided for the machine body pressure sensor and the sensing piece, the waste of a large amount of heat is avoided, and the utilization efficiency of energy is increased; through setting up detection pipeline, breakwater, back flow and two-position valve, in a small amount of water got into the detection pipeline can send water back once more to the heating chamber through breakwater and back flow, if in a large amount of water got into the detection pipeline send water into the collecting box through two-position valve, reduced the influence that causes in the water entering detection pipeline, reduced the restriction of device use, be favorable to using.

Drawings

Fig. 1 is a front view of an aviation water-gas separation device.

Fig. 2 is an enlarged view at a1 in fig. 1.

Fig. 3 is a schematic structural diagram of a water receiving tank in an aviation water-gas separation device.

Fig. 4 is an enlarged view at a2 in fig. 1.

Wherein: 1. the device comprises a shell, a pressure sensor sensing element, a gas source inlet, a gas inlet pipeline, a cavity, a heating chamber, a heating block, a detection pipeline, a water baffle, a return pipe, a two-position valve, a 12 air chamber, a 13 pressure sensor, a 14 first branch pipe, a 15 second branch pipe, a 16 support, a 17 drainage plate, a 18 water receiving tank, a 19 one-way valve, a 20 water inlet pipe, a 21 collecting tank, a 22 evaporation hole, a 23 humidity sensor and a 24 groove, wherein the shell is provided with a heat insulation layer, the heat insulation layer is arranged on the shell, and the heat insulation layer is arranged on the shell.

Detailed Description

It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.

Example one

Referring to fig. 1-4, an aviation water-gas separating device comprises a housing 1, a machine body pressure sensor sensed piece 2 is arranged above the housing 1, a plurality of groups of mutually communicated gas source inlets 3 are arranged in the middle of the upper surface of the machine body 2 of the pressure sensor sensed piece, the gas source inlets 3 are communicated downwards with a gas inlet pipeline 4 vertically extending downwards into the housing 1, the lower end of the gas inlet pipeline 4 is communicated with a heating chamber 6, a cavity 5 is arranged between the housing 1 and the machine body pressure sensor sensed piece 2, the lower surface of the machine body pressure sensor sensed piece 2 is arranged in a structure with a high inner side and a low outer side, an evaporation hole 22 arranged right above the heating chamber 6 is arranged on the upper surface of the housing 1, the evaporation hole 22 is arranged in a conical hole structure with a large upper part and a small lower part, the lower end of the evaporation hole 22 is communicated with the heating chamber 6, a water receiving groove 18 with a U-shaped section is fixedly arranged on the bracket 16, the upper part and the lower part of the inner side surface of the water receiving groove 18 are both provided with an inclined plane structure with a high outer side and a low inner side, a plurality of groups of grooves 24 distributed along the length direction of the water receiving groove 18 are arranged on the side surfaces of the left vertical section and the right vertical section in the water receiving groove 18, a drainage plate 17 fixedly arranged on the lower surface of a pressure sensor receiving piece 1 of the machine body is connected in the water receiving groove 18 in a sliding way, the lower parts of the left side surface and the right side surface of the drainage plate 17 are contacted with the side surfaces of the vertical sections in the water receiving groove 18, the water receiving groove 18 is downwards communicated with a water inlet pipe 20 vertically extending into the shell 1, a check valve 19 positioned in the cavity 5 is fixedly arranged on the water inlet pipe 20, the lower end of the water inlet pipe 20 is, two groups of water baffles 9 which are matched with each other are fixedly arranged on the upper part of the pipeline extending leftwards and downwards of the detection pipeline 8, a return pipe 10 communicated with two ends of the detection pipeline 8 is arranged on the upper side of the lower water baffle 9, and the return pipe 10 inclines rightwards and downwards.

Example two

On the basis of the first embodiment, the lower end of the detection pipeline 8 is fixedly provided with the two-position valve 11, the humidity sensor 23 positioned above the two-position valve 11 is fixedly arranged in the detection pipeline 8, the two-position valve 11 is downwards communicated with the second branch pipe 15 which is L-shaped and extends rightwards along the horizontal section, the right end of the second branch pipe 15 is communicated with the air chamber 12, the middle part of the inner bottom surface of the air chamber 12 is fixedly provided with the pressure sensor 13, the two-position valve 11 is downwards communicated with the first branch pipe 14, and the lower end of the first branch pipe 14 is communicated with the left collection box.

The working principle of the invention is as follows: atmospheric condensate water, rainwater etc. get into in the heating chamber 6 through air supply import 3, heat evaporation is carried out to the water that gets into in the heating chamber 6 through heating block 7, get into in cavity 5 through evaporation hole 22 after the moisture evaporation, vapor meets fuselage pressure sensor and receives the heat supply for fuselage pressure sensor receives sensing piece 2 after the condensation, the condensate water is followed fuselage pressure sensor and is received sensing piece 2 lower surface flow after through drainage plate 17, water receiving tank 18 and inlet tube 20 get into in the collecting box 21, the air current continues to get into in the air chamber 12 through detecting tube 8 and detects the humidity in the detecting tube 8, detect the humidity in the detecting tube 8 through humidity transducer 23, send moisture to in the collecting box 21 through two valves 11 when humidity is great.

Although the preferred embodiments of the present patent have been described in detail, the present patent is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present patent within the knowledge of those skilled in the art.

Claims

1. An aviation water-gas separation device comprises a shell (1) and is characterized in that a machine body pressure sensor sensing piece (2) is arranged above the shell (1), a plurality of groups of mutually communicated air source inlets (3) are formed in the middle of the upper surface of the machine body (2) of the pressure sensor sensing piece, the air source inlets (3) are communicated downwards with an air inlet pipeline (4) vertically extending downwards into the shell (1), the lower end of the air inlet pipeline (4) is communicated with a heating chamber (6), a heating block (7) is fixedly installed in the middle of the inner bottom surface of the heating chamber (6), the left side surface of the heating chamber (6) is communicated with an L-shaped detection pipeline (8) extending upwards leftwards, a two-position valve (11) is fixedly installed at the lower end of the detection pipeline (8), a humidity sensor (23) positioned above the two-position valve (11) is fixedly installed in the detection pipeline (8), the two-position valve (11) is communicated downwards with an L, the right end of the second branch pipe (15) is communicated with an air chamber (12), and the middle part of the inner bottom surface of the air chamber (12) is fixedly provided with a pressure sensor (13).

2. The aviation water-gas separation device is characterized in that a cavity (5) is formed between the shell (1) and the fuselage pressure sensor sensing piece (2), the lower surface of the fuselage pressure sensor sensing piece (2) is of a structure with a high inner side and a low outer side, an evaporation hole (22) located right above the heating chamber (6) is formed in the upper surface of the shell (1), the evaporation hole (22) is of a conical hole structure with a large upper part and a small lower part, and the lower end of the evaporation hole (22) is communicated to the heating chamber (6).

3. The aviation water-gas separation device according to claim 1 or 2, characterized in that two groups of brackets (16) which are symmetrically arranged in the cavity (5) from left to right are fixedly arranged on the upper surface of the housing (1), a water receiving tank (18) with a U-shaped section is fixedly arranged on each bracket (16), and the upper part and the lower part of the inner side surface of each water receiving tank (18) are both arranged to be of an inclined surface structure with a high outer side and a low inner side.

4. The aviation water-gas separation device according to claim 3, wherein a plurality of groups of grooves (24) distributed along the length direction of the water receiving groove (18) are formed in the left and right vertical section side surfaces in the water receiving groove (18), a drainage plate (17) fixedly installed on the lower surface of the pressure sensor receiving piece (1) of the aircraft body is connected in the water receiving groove (18) in a sliding manner, and the lower parts of the left and right side surfaces of the drainage plate (17) are in contact with the vertical section side surfaces in the water receiving groove (18).

5. The aviation water-gas separating device of claim 1, wherein the water receiving tank (18) is downwardly communicated with a water inlet pipe (20) vertically extending into the housing (1), a check valve (19) positioned in the cavity (5) is fixedly mounted on the water inlet pipe (20), and the lower end of the water inlet pipe (20) is communicated with collecting tanks (21) fixedly mounted on two sides of the bottom in the housing (1).

6. The aviation water-gas separating device as claimed in claim 1, wherein two sets of water baffles (9) which are matched with each other are fixedly installed on the upper portion of the pipeline, which extends to the left and downwards, of the detection pipeline (8), a return pipe (10) which is communicated with two ends of the detection pipeline (8) is arranged on the upper side of the lower water baffle (9), and the return pipe (10) is inclined to the right and downwards.

7. The aviation water-gas separation device is characterized in that the two-position valve (11) is communicated with a first branch pipe (14) downwards, and the lower end of the first branch pipe (14) is communicated with a left collecting box (21).