CN117685434A - Quick connector device for blowing and turning start of aero-engine and aircraft - Google Patents

Abstract

The utility model relates to a quick connector device for blowing and starting an aeroengine and an aeroengine, wherein the quick connector device comprises a plug main body, a plug body and a plug body, wherein the end part of the plug main body is provided with a plug part; the connector is provided with an inserting channel and a valve port; the check valve assembly comprises a valve core and an elastic piece; the outer peripheral wall of the plug head of the plug main body is provided with a convex block protruding outwards along the radial direction, the inner wall of the insertion channel is provided with a limit slideway recessed outwards along the radial direction, and the convex block of the plug main body can be axially arranged in the limit slideway and axially limit with the limit slideway after rotating for a certain angle; in the state that the lug of the plug main body and the limiting slide rail are limited in the axial direction, the plug main body abuts against the valve core, and the valve core is far away from the valve port relative to the valve port to open the valve port. The quick connector has a compact structure, can realize quick plug of the engine and the high-pressure air pipeline under the condition of meeting the air starting flow requirement of the engine, and has a better self-sealing function.

Description

Quick connector device for blowing and turning start of aero-engine and aircraft

Technical Field

The utility model relates to the technical field of aeroengines, in particular to a quick connector and an aircraft, wherein the quick connector can be used for realizing quick connection and disconnection between a high-pressure gas pipeline and the engine when the aeroengine is started by high-pressure air blowing.

Background

The aeroengine provides power for the flight of the aircraft, and is more of a self-evident "bright bead on industrial crown" as the aircraft heart. It directly affects the performance of the aircraft and is also an important embodiment of national industry and national defense. The starting mode of the aeroengine mainly comprises high-pressure air blowing and rotating starting, gunpowder impact starting, motor belt rotating starting and the like. The high-pressure air starting mode is common. In order to improve the connection and disconnection efficiency of the engine and the high-pressure air pipeline, a quick connection mode is adopted for a connection mechanism between the engine and the high-pressure air pipeline, so that an operator can conveniently plug the high-pressure air pipeline.

The quick connector structure in the prior art is provided with a steel ball buckle quick connector and a spanner type quick connector. The Chinese patent application with the application number of CN201921651398.X discloses a quick-release copper joint, which comprises a first joint, wherein the output end of the first joint is connected with the input end of a fluid pipeline, and the input end of the first joint is provided with a first valve core component which axially slides along the central axis of the first joint; the output end of the second joint is provided with a second valve core assembly matched with the first valve core assembly, the second valve core assembly axially slides along the central shaft of the second joint, the input end of the second joint is connected with the output end of the other fluid pipeline, and the second joint is provided with a self-locking assembly; the first valve core component and the second valve core component form a valve core, and in the valve core opening state, the first valve core component and the second valve core component are mutually extruded. The self-locking assembly comprises a movable sleeve sliding along the outer side of the first connector and a steel ball arranged close to the output end of the second connector, a self-locking spring is arranged between the movable sleeve and the second connector, one end of the self-locking spring is connected with the movable sleeve, the other end of the self-locking spring is connected with the second connector, a plurality of clamping holes are uniformly formed in the side wall, close to the output end, of the second connector along the circumferential direction, the steel ball is clamped in the clamping holes, the steel ball can only be taken out from the outer side of the clamping holes, one end, close to the output end of the second connector, of the movable sleeve is pressed on the outer side of the steel ball, so that the inner side of the steel ball stretches into the clamping holes and extends into the second connector. The steel ball buckle quick connector in the patent application is convenient to use, but because the steel ball is required to have a certain radial movable space, the size of the steel ball buckle quick connector is often overlarge, the number of parts is too large, and the steel ball buckle quick connector is not well suitable for quick plug connection between a high-pressure gas pipeline and an engine due to the self-sealing structure. And as the Chinese patent application with the application number of CN201720103071.3 discloses a quick connector and a quick connector assembly comprising the same, the plate handle type quick connector is a quick connector made of casting materials, cannot resist high pressure, is structurally buckled by taking two ears as supporting points, is similar to a pair of pliers for two-point fixation, has uneven stress on sealing surfaces, and is easy to increase the leakage risk of a sealing part and excessively large in structural space occupation when a connecting pipe is laterally moved by external force and is subjected to shaking and deflection by stress, so that the plate handle type quick connector is not suitable for the application condition of high-pressure air blowing and rotating of an aeroengine.

In summary, since the installation space between the engine and the aircraft is very limited, the installation space is far beyond the space size given by the design of the conventional steel ball buckle quick connector or the spanner type quick connector, and especially, the air pressure and the air flow are required to be higher by the air blowing rotation starting of the aeroengine, the air flow requirement is difficult to be met by the quick connection structure, or the structural volume is too large under the condition of meeting the air flow requirement, and the quick connection structure cannot be installed in the limited space between the engine and the aircraft.

Disclosure of Invention

The first technical problem to be solved by the utility model is to provide a quick connector device for blowing and turning start of an aeroengine aiming at the current state of the art, the quick connector device has small and compact structure, can realize quick plug-in and plug-out of the engine and a high-pressure air pipeline under the condition of meeting the requirement of the air starting flow of the engine, and has a better self-sealing function.

A second technical problem to be solved by the present utility model is to provide an aircraft employing the quick connector device according to the present utility model.

The technical scheme adopted by the utility model for solving the first technical problem is as follows: a quick connector device for a blow-down start of an aircraft engine, comprising:

a plug main body having a plug portion at an end portion thereof;

the connector is provided with an accommodating cavity and an inserting channel which is communicated with the accommodating cavity and is used for inserting the plug part of the plug main body into the accommodating cavity, and a valve port is formed at the position of the accommodating cavity, which is communicated with the inserting channel;

the check valve assembly is arranged in the accommodating chamber of the connector and comprises a valve core and an elastic piece, the valve core is movably arranged in the accommodating chamber in a mode of approaching and separating relative to the valve port and can correspondingly close and open the valve port, and the elastic piece acts on the valve core and enables the valve core to always have a trend of moving towards the valve port to close the valve port;

the outer peripheral wall of the plug head of the plug main body is provided with a protruding block protruding outwards in the radial direction, the inner wall of the insertion channel is provided with a limiting slideway recessed outwards in the radial direction, and the protruding block of the plug main body can be axially arranged in the limiting slideway and axially limited with the limiting slideway after rotating for a certain angle;

and in the state that the protruding block of the plug main body and the limiting slide rail are limited in the axial direction, the plug main body is propped against the valve core, and the valve core is far away from the valve port relatively to open the valve port.

Because the limiting slide way used for being in limit fit with the convex block on the plug main body is formed on the inner wall of the inserting channel of the connector, the wall thickness space of the part where the inserting channel is formed on the plug is utilized, thus the connector part is not required to be made very large, the whole body is smaller, the installation can be carried out in the limited space between the engine and the airplane, and the air starting and blowing flow of the aeroengine can not be reduced. In addition, when the plug main body is separated from the connector, the check valve assembly in the connector can automatically close the valve port, so that the self-sealing function is realized, and foreign matters outside the engine are effectively prevented from entering the engine.

In order to conveniently and smoothly install in the spacing slide and realize firm spacing in axial after the installation is put in place, spacing slide includes from the opening border of inserting the passageway towards the axial section that holds the position extension of cavity place and from the terminal circumference section that extends along circumference of axial section, the lug of plug main part can follow the axial section of spacing slide is gone into, and after rotatory certain angle with the circumference section of spacing slide realizes spacing in the axial.

As an improvement, one end, which is connected with the axial section, of the circumferential section of the limiting slide rail is marked as a first end, one end, which is far away from the axial section, of the limiting slide rail is marked as a second end, and a limiting concave part used for limiting the protruding block on the plug main body is arranged on the side wall, which is close to the inserting channel, of the second end of the circumferential section. Under the action of the elastic piece of the check valve assembly, the plug main body also has a tendency of outwards separating from the connector, and the arrangement of the limiting concave part can just limit the protruding block on the plug main body, namely realize the limitation in the circumferential direction, so that the protruding block is prevented from easily separating from the connector along the circumferential section of the limiting slideway in a reverse movement.

For the convenience of processing, the limit slide way penetrates from the inner wall of the inserting channel to the outer wall surface of the inserting channel.

In order to ensure the locking firmness between the plug main body and the connector, two protruding blocks on the plug head of the plug main body are symmetrically arranged relative to the axis of the plug main body, and two limiting sliding ways on the connector are correspondingly arranged. It is contemplated that three or more protrusions on the plug portion of the plug body may be provided to further increase the security of the locking between the plug body and the plug.

In order to avoid the influence on the gas flow caused by the direct abutment of the peripheral edge of the port of the plug part with the valve core, the peripheral edge of the port of the plug part is provided with support legs which are arranged at intervals along the peripheral direction and extend outwards along the axial direction, and when the protruding block of the plug main body and the limiting slide rail are in the state of limiting in the axial direction, the end parts of the support legs of the plug main body abut against the valve core, and the valve core is far away from the valve port to open the valve port.

In order to improve the stability of the axial movement of the valve core and further ensure the tightness of the valve core matched with the valve port, the side wall of the valve core facing the valve port is provided with guide rods which are arranged at intervals along the circumferential direction and extend into the insertion channel, and each guide rod extends into the plug part of the plug main body in the state that the plug main body is inserted into the insertion channel of the connector.

In order to realize firm sealing between the plug main body and the connector and avoid the leakage problem in the gas transmission process, a sealing ring used for being in sealing contact with the outer peripheral wall of the plug head of the plug main body is embedded on the inner wall of the insertion channel of the connector.

For the convenience of the installation of the check valve assembly in the accommodating chamber of the connector, the connector comprises a connector main body with an installation opening at the bottom and a bottom plate detachably connected to the installation opening of the connector main body, the bottom plate and the connector main body jointly define the accommodating chamber, and the inserting channel is positioned on the connector main body.

In order to facilitate the mounting of the joint to the body of the engine, the base plate is intended to be connected to the body of the engine, and is provided with a connection hole through which the connection piece passes.

The utility model solves the second technical problem by adopting the technical proposal that: the aircraft comprises an engine and a skin wrapped outside the engine, wherein the quick connector device for blowing and starting the aircraft engine is further arranged between the skin and the engine.

Compared with the prior art, the utility model has the advantages that: the limiting slide way used for limiting and matching with the convex blocks on the plug main body is formed on the inner wall of the inserting channel of the connector, and particularly, the wall thickness space of the part where the inserting channel is located on the plug is utilized for forming, so that the connector part does not need to be very large, the flow requirement of air starting and blowing rotation of the aeroengine can be met, and the whole device is smaller, so that the device can be installed in a limited space between the engine and an airplane. In addition, when the plug main body is separated from the connector, the check valve assembly in the connector can automatically close the valve port, so that the self-sealing function is realized, and foreign matters outside the engine are effectively prevented from entering the engine.

Drawings

Fig. 1 is a schematic perspective view of a quick connector according to an embodiment of the present utility model;

fig. 2 is a schematic perspective view showing a state that a plug main body of a quick connector is separated from a connector according to an embodiment of the present utility model;

FIG. 3 is a top view of a quick connector according to an embodiment of the present utility model;

FIG. 4 is an axial cross-sectional view of a quick connector according to an embodiment of the present utility model;

FIG. 5 is an axial cross-sectional view of a joint according to an embodiment of the present utility model;

FIG. 6 is an exploded view of a quick connector according to an embodiment of the present utility model;

FIG. 7 is a front view of an aircraft of the present utility model;

fig. 8 is a cross-sectional view of the aircraft of fig. 7 at C-C.

Detailed Description

The utility model is described in further detail below with reference to the embodiments of the drawings.

In the description and claims of the present utility model, terms indicating directions, such as "front", "rear", "upper", "lower", "left", "right", "side", "top", "bottom", etc., are used to describe various example structural parts and elements of the present utility model, but these terms are used herein for convenience of description only and are determined based on the example orientations shown in the drawings. Because the disclosed embodiments of the utility model may be arranged in a variety of orientations, the directional terminology is used for purposes of illustration and is in no way limiting, such as "upper" and "lower" are not necessarily limited to being in a direction opposite or coincident with the direction of gravity.

Fig. 1-8 show a preferred embodiment of a quick connector device for aircraft engine blow-down and aircraft according to the utility model. The quick connector 20 device for the blowing start of the aeroengine comprises a plug main body 10, a connector 20, a sealing ring 40 and a check valve assembly.

The plug body 10 has a tubular structure as a whole, and has a plug portion 11 at one end portion for plug-in fitting with the insertion passage 202 of the connector 20 and a high-pressure gas pipe (high-pressure gas supply) at the other end portion. The cross section of the plug portion 11 of the plug main body 10 is circular, and the outer peripheral wall thereof has a protruding block 111 protruding radially outward, specifically, the protruding block 111 of the present embodiment is a pin, wherein the pin has two pins symmetrically arranged with respect to the axis of the plug portion 11.

The joint 20 is intended to be mounted on the body of an engine, in particular in the interstitial space between the engine and the skin of an aircraft. The joint 20 includes a joint body 21, in which the interior of the joint body 21 is hollow and a mounting port is formed at the bottom, and a bottom plate 22, which is connected at the mounting port of the joint body 21, together defining a receiving chamber 201 for seating the check valve assembly. The connector body 21 is further provided with an insertion passage 202 which communicates with the accommodation chamber 201 and into which the plug portion 11 of the plug body 10 is inserted, and a valve port 203 is formed in the inner wall of the accommodation chamber 201 at a position communicating with the insertion passage 202. The valve port 203 and the insertion passage 202 of the joint body 21 are opposed to the mounting port of the joint body 21. The base plate 22 of the joint 20 is adapted to be coupled to a main body of an engine, and is provided with a coupling hole 221, and the joint 20 may be fixed to the main body of the engine by a coupling member (e.g., a bolt) passing through the coupling hole 221. As shown in fig. 3, the bottom plate 22 is further provided with an air outlet 222 at a position opposite to the valve port 203 for air flow.

Referring to fig. 4 and 5, the check valve assembly includes a valve body 31 and an elastic member 32. The valve element 31 is movably provided in the housing chamber 201 so as to be movable toward and away from the valve port 203. The elastic member 32 in this embodiment is a spring, the first end of the spring abuts against one side of the valve core 31 away from the valve port 203, the second end abuts against the inner wall of the wall plate, and under the elastic force of the elastic member 32, the valve core 31 always has a tendency to move toward the valve port 203 and close the valve port 203.

The side wall of the valve element 31 facing the valve port 203 has guide rods 311 arranged at intervals in the circumferential direction and extending into the insertion passage 202. In the present embodiment, the guide bars 311 have three, each disposed adjacent to the outer peripheral edge of the spool 31. In the state that the plug main body 10 is inserted into the insertion channel 202 of the connector 20, the three guide rods 311 extend into the plug portion 11 of the plug main body 10 and are arranged close to the inner wall of the plug portion 11, so that the stability of the axial movement of the valve core 31 can be improved when the valve core 31 moves axially (i.e. in the process of opening and closing the valve port 203), the shaking or shifting problem is avoided, and the sealing performance of the valve core 31 matched with the valve port 203 is further ensured.

Referring to fig. 6, the interior wall of the insertion channel 202 has a radially outwardly recessed stop ramp 210 thereon. The limiting slide 210 of the present embodiment is generally L-shaped, and includes an axial section 211 extending from the opening edge of the insertion channel 202 toward the position of the accommodating chamber 201, and a circumferential section 212 extending from the end of the axial section 211 (i.e., the end near the valve port 203) in the circumferential direction. When the plug body 10 is inserted into the insertion channel 202 of the connector 20, the projection 111 can slide in along the axial section 211 of the limit slide 210 and, after a certain angle of rotation, axially limit with the circumferential section 212 of the limit slide 210. One end of the circumferential section 212 of the limiting slide 210, which is connected with the axial section 211, is denoted as a first end, and one end of the circumferential section 212, which is far away from the axial section 211, is denoted as a second end, and a limiting concave portion 2120 in which the protruding block 111 of the plug main body 10 is limited is arranged on a side wall of the second end of the circumferential section 212 of the limiting slide 210, which is close to the inserting channel 202. Due to the elastic member 32 of the check valve assembly, the plug body 10 also has a tendency to move out of the connector 20, and the positioning of the positioning recess 2120 just allows the protrusion 111 on the plug body 10 to position therein, i.e. realize positioning in the circumferential direction, so as to avoid the protrusion 111 from easily moving in the opposite direction along the circumferential section 212 of the positioning slide 210 to move out.

The limiting slide way 210 of the present embodiment penetrates from the inner wall of the inserting channel 202 to the outer wall of the inserting channel 202, that is, the limiting slide way 210 is an L-shaped opening with inner and outer penetrating, which is convenient for a user to more intuitively observe the position of the limiting slide way 210 and slide the bump 111 on the plug main body 10 into the set position on the limiting slide way 210.

The inner wall of the insertion channel 202 of the connector 20 of the present embodiment is further embedded with a sealing ring 40, and after the plug main body 10 is inserted into the insertion channel 202 of the connector 20, the outer peripheral wall of the plug head 11 of the plug main body 10 is in sealing contact with the sealing ring 40, so that firm sealing is realized between the outer peripheral wall of the plug main body 10 and the inner peripheral wall of the insertion channel 202 of the connector 20, and the leakage problem in the gas transmission process is avoided.

The peripheral edge of the port of the plug portion 11 of the present embodiment also has the legs 112 arranged at intervals in the circumferential direction and extending outward in the axial direction. In the state that the protruding block 111 of the plug main body 10 and the limit slide 210 limit in the axial direction, the end portions of the supporting legs 112 of the plug main body 10 can abut against the valve core 31, the valve core 31 is separated from the valve port 203 to open the valve port 203, and the structural design that the supporting legs 112 drive the valve core 31 to move can avoid the influence on the gas transmission flow caused by the fact that the peripheral edge of the port of the plug 11 directly abuts against the valve core 31.

Referring to fig. 7 and 8, the present embodiment further relates to an aircraft, which includes an engine 51 and a skin 52 wrapped around the engine 51, wherein a gap is provided between the skin 52 and the engine 51, and the quick connector device 1 for blowing and turning of the aircraft engine is disposed in the gap, wherein the bottom plate 22 of the connector 20 of the quick connector is used for connecting with the main body of the engine 51.

The quick connector 20 of the present embodiment is used as follows:

the plug part 11 of the plug main body 10 is aligned with the inserting channel 202 of the connector 20, the protruding blocks 111 on the plug part 11 are opposite to the front end ports of the axial sections 211 of the limiting slide ways 210 on the connector 20, then the plug main body 10 is inserted into the inserting channel 202 of the connector 20 in a proper state, the plug main body 10 is pushed to the bottom, after rotating clockwise in place, at the moment, the three supporting legs 112 on the plug main body 10 prop up the check valve core 31, the check valve core 31 compresses the spring, a passage is opened for the whole air flow, the flow cross section meets the flow requirement, the air flow flows into the engine blowing holes through the periphery of the check valve core 31, and the protruding blocks 111 on the plug main body 10 are blocked into the limiting notches on the circumferential ends of the limiting slide ways 210 under the pushing of the check valve spring, so that the plug main body 10 is prevented from reversely rotating to fall off. The seal ring 40 radially seals the outer circumferential wall of the plug body 10 and the inner circumferential wall of the insertion passage 202 of the joint 20 to prevent leakage of air flow. When the plug main body 10 is required to be separated, the plug main body 10 is pushed to the bottom, the plug main body 10 rotates anticlockwise, the protruding block 111 on the plug main body 10 is separated from the limiting notch and reversely separated along the limiting slideway 210, the plug main body 10 is separated from the connector 20, the spring of the check valve assembly pushes the check valve core 31 to rebound to close the valve port 203, the self-sealing function is realized, and foreign matters outside the engine are prevented from entering the engine.

Claims (10)

1. A quick connector device for a blow-down start of an aircraft engine, comprising:

a plug main body (10) having a plug portion (11) at an end portion thereof;

a joint (20) having an insertion passage (202) which communicates with the accommodation chamber (201) and into which the plug portion (11) of the plug main body (10) is inserted, wherein a valve port (203) is formed at a position where the accommodation chamber (201) and the insertion passage (202) communicate with each other;

the check valve assembly is arranged in the accommodating chamber (201) of the joint (20) and comprises a valve core (31) and an elastic piece (32), wherein the valve core (31) is movably arranged in the accommodating chamber (201) in a mode of approaching and separating relative to the valve port (203) and can correspondingly close and open the valve port (203), and the elastic piece (32) acts on the valve core (31) and enables the valve core (31) to always have a trend of moving towards the valve port (203) to close the valve port (203);

the method is characterized in that: the outer peripheral wall of the plug part (11) of the plug main body (10) is provided with a protruding block (111) protruding outwards along the radial direction, the inner wall of the insertion channel (202) is provided with a limiting slide way (210) recessed outwards along the radial direction, and the protruding block (111) of the plug main body (10) can be axially arranged in the limiting slide way (210) and can axially limit with the limiting slide way (210) after rotating for a certain angle;

when the protruding block (111) of the plug body (10) and the limit slide (210) are limited in the axial direction, the plug body (10) is abutted against the valve core (31), and the valve core (31) is separated from the valve port (203) to open the valve port (203).

2. The quick connector device for air engine blowing start of claim 1, wherein: the limiting slide way (210) comprises an axial section (211) extending from the opening edge of the inserting channel (202) towards the position where the accommodating chamber (201) is located and a circumferential section (212) extending from the tail end of the axial section (211) along the circumferential direction, and the protruding block (111) of the plug main body (10) can slide in along the axial section (211) of the limiting slide way (210) and axially limit with the circumferential section (212) of the limiting slide way (210) after rotating for a certain angle.

3. The quick connector device for air engine blowing start of claim 2, wherein: one end, connected with the axial section (211), of the circumferential section (212) of the limiting slide way (210) is marked as a first end, one end, far away from the axial section (211), of the limiting slide way (210) is marked as a second end, and a limiting concave part (2120) used for limiting the protruding block (111) on the plug main body (10) is arranged on the side wall, close to the inserting channel (202), of the second end of the circumferential section (212).

4. The quick connector device for air engine blowing start of claim 1, wherein: the limit slide way (210) penetrates from the inner wall of the inserting channel (202) to the outer wall surface of the inserting channel (202).

5. The quick connector device for the blowing start of an aircraft engine according to any one of claims 1 to 4, characterized in that: the protruding blocks (111) on the plug part (11) of the plug main body (10) are symmetrically arranged relative to the axis of the plug main body (10), and the limit sliding ways (210) on the connector (20) are correspondingly arranged.

6. The quick connector device for the blowing start of an aircraft engine according to any one of claims 1 to 4, characterized in that: the peripheral edge of the port of the plug part (11) is provided with support legs (112) which are arranged at intervals along the peripheral direction and extend outwards along the axial direction, and when the protruding block (111) of the plug main body (10) and the limiting slide way (210) are limited in the axial direction, the end part of each support leg (112) of the plug main body (10) is propped against the valve core (31) and the valve core (31) is separated from the valve port (203) to open the valve port (203).

7. The quick connector device for the blowing start of an aircraft engine according to any one of claims 1 to 4, characterized in that: the valve core (31) is provided with guide rods (311) which are arranged at intervals along the circumferential direction on the side wall facing the valve port (203) and extend into the insertion channel (202), and each guide rod (311) extends into the plug part (11) of the plug main body (10) in a state that the plug main body (10) is inserted into the insertion channel (202) of the connector (20).

8. The quick connector device for the blowing start of an aircraft engine according to any one of claims 1 to 4, characterized in that: the inner wall of the insertion channel (202) of the connector (20) is also embedded with a sealing ring (40) which is used for being in sealing contact with the outer peripheral wall of the plug part (11) of the plug main body (10).

9. The quick connector device for the blowing start of an aircraft engine according to any one of claims 1 to 4, characterized in that: the connector (20) comprises a connector main body (21) with a mounting opening at the bottom and a bottom plate (22) detachably connected to the mounting opening of the connector main body (21), the bottom plate (22) and the connector main body (21) jointly define a containing cavity (201), an inserting channel (202) is located on the connector main body (21), and the bottom plate (22) is used for being connected with a main body of an engine and is provided with a connecting hole (221) for a connecting piece to pass through.

10. An aircraft comprising an engine (51) and a skin (52) wrapped around the engine (51), characterized in that: a quick connector device for the blowing start of an aeroengine according to any one of claims 1 to 9 is also provided between the skin (52) and the engine (51).