Quick connector device for aeroengine run-up and aircraft

Abstract

The application relates to a quick plug connector device for aero-engine rotation starting and an aircraft, and the quick plug connector device comprises a plug main body with a plug part at the end, a connector with a plug channel and a valve port, a check valve assembly comprising a valve core and an elastic member, a convex block protruding radially outward on the outer peripheral wall of the plug part of the plug main body, a limiting sliding channel recessed radially outward on the inner wall of the plug channel, the convex block of the plug main body being capable of being axially assembled into the limiting sliding channel and being limited in the axial direction after rotating by a certain angle, and the plug main body being abutted with the valve core in the state that the convex block of the plug main body is limited in the axial direction with the limiting sliding channel, and the valve core is separated from the valve port to open the valve port. The quick plug connector is small and compact, can realize quick plug-in and plug-out of the engine and the high-pressure air pipeline under the condition of meeting the engine air starting flow requirement, and has a good self-sealing function.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular to a quick-connect fitting and an aircraft that enables rapid connection and disconnection between a high-pressure gas pipeline and the engine when the aero-engine is started by blowing with high-pressure air. Background Technology

[0002] Aero engines provide power for aircraft flight, and as the heart of an aircraft, they are often referred to as the "jewel in the crown of industry." They directly affect aircraft performance and are a crucial indicator of a nation's industrial and defense strength. Aero engine starting methods mainly include high-pressure air start, propellant impact start, and electric motor start. Among these, high-pressure air start is the most common. To improve the efficiency of connecting and disconnecting the engine from the high-pressure air pipeline, the connection mechanism between the engine and the high-pressure air pipeline needs to adopt a quick-connect type, facilitating the operator's insertion and removal of the high-pressure air pipeline.

[0003] Existing quick-connect coupling structures include ball-bearing snap-fit ​​quick-connect couplings and lever-type quick-connect couplings. For example, Chinese utility model patent application CN201921651398.X discloses "A Quick-Connect Copper Coupling," which includes a first connector, the output end of which is connected to the input end of a fluid pipeline, and the input end of the first connector is provided with a first valve core assembly that slides axially along the central axis of the first connector; a second connector, the output end of which is provided with a second valve core assembly that cooperates with the first valve core assembly, the second valve core assembly sliding axially along the central axis of the second connector, the input end of the second connector being connected to the output end of another fluid pipeline, and the second connector being provided with a self-locking component; the first valve core assembly and the second valve core assembly constitute a valve core, and in the open state, the first valve core assembly and the second valve core assembly press against each other. The self-locking assembly includes a movable sleeve that slides along the outer side of the first connector and a steel ball positioned near the output end of the second connector. A self-locking spring is provided between the movable sleeve and the second connector, with one end connected to the movable sleeve and the other end connected to the second connector. The side wall of the second connector near the output end has several evenly spaced locking holes along its circumference, allowing the steel ball to be inserted. The steel ball can only be removed from the outside of the locking holes. The end of the movable sleeve near the output end of the second connector presses against the outside of the steel ball, causing the inner side of the steel ball to penetrate into the locking holes and extend into the second connector. While the steel ball snap-fit ​​quick connector in the aforementioned patent application is convenient to use, its size is often too large and the number of parts is excessive due to the need for a certain radial movement space for the steel ball. Furthermore, the self-sealing structure makes it unsuitable for quick-connect connections between high-pressure gas pipelines and engines. For example, Chinese invention patent application CN201720103071.3 discloses a "quick-connector and quick-connect assembly containing the same". This plate-handle quick connector is a quick connector made of cast material, which cannot withstand high pressure. Structurally, the two ears act as fulcrums for snapping, similar to "pliers" for two-point fixation. The sealing surface is subjected to uneven force. When the connecting pipe is subjected to external force, it moves to the side or shakes under force, which can easily increase the risk of leakage of the sealing part. The structure also occupies too much space and does not meet the application requirements of high-pressure air blowing in aero engines.

[0004] In summary, due to the extremely limited installation space between the engine and the aircraft, both conventional ball-bearing quick-connect couplings and lever-type quick-connect couplings far exceed the space dimensions specified in the design. In particular, the air-blown start-up of aero engines requires high air pressure and flow rate, and the aforementioned quick-connect structures are unable to meet the air flow requirements, or their structural volume is too large to be installed in the limited space between the engine and the aircraft even if the air flow requirements are met. Summary of the Invention

[0005] The first technical problem to be solved by the present invention is to provide a quick-connect coupling device for blow-starting an aero-engine, which is based on the current state of the prior art. The quick-connect coupling has a small and compact structure, can realize the quick insertion and removal of the engine and the high-pressure air pipeline while meeting the engine air start-up flow requirements, and has a good self-sealing function.

[0006] The second technical problem to be solved by the present invention is to provide an aircraft that uses the above-mentioned quick-connect device, in view of the current state of the prior art.

[0007] The technical solution adopted by the present invention to solve the first technical problem mentioned above is: a quick-connect coupling device for blow-starting an aircraft engine, comprising:

[0008] The plug body has a plug portion at its end;

[0009] The connector has a receiving chamber and an insertion channel communicating with the receiving chamber and into which the plug portion of the plug body is inserted, wherein a valve port is formed at the position where the receiving chamber and the insertion channel communicate.

[0010] A check valve assembly is disposed in the receiving chamber of the connector, including a valve core and an elastic element. The valve core is movably disposed in the receiving chamber in a manner that allows it to move closer to and further away from the valve port, and can correspondingly close and open the valve port. The elastic element acts on the valve core, and causes the valve core to always have a tendency to move toward the valve port and close the valve port.

[0011] The outer peripheral wall of the plug part of the plug body has a protrusion that protrudes radially outward, and the inner wall of the insertion channel has a limiting slide that is recessed radially outward. The protrusion of the plug body can be inserted into the limiting slide along the axial direction, and after rotating a certain angle, it is axially limited with the limiting slide.

[0012] When the protrusion of the plug body and the limiting slide are axially limited, the plug body abuts against the valve core, and the valve core moves away from the valve port to open the valve port.

[0013] Because the limiting slide that engages with the protrusion on the plug body is located on the inner wall of the insertion channel of the connector, it utilizes the wall thickness of the insertion channel on the plug. This allows the connector component to be made smaller, enabling installation within the limited space between the engine and the aircraft without reducing the airflow for engine start-up. Furthermore, when the plug body is detached from the connector, the check valve assembly inside the connector automatically closes the valve port, achieving a self-sealing function and effectively preventing foreign matter from entering the engine.

[0014] To facilitate smooth installation into the limiting slide and ensure secure axial positioning after installation, the limiting slide includes an axial section extending from the opening edge of the insertion channel toward the location of the receiving chamber, and a circumferential section extending circumferentially from the end of the axial section. The protrusion of the plug body can slide into the axial section of the limiting slide and, after rotating a certain angle, achieve axial positioning with the circumferential section of the limiting slide.

[0015] As an improvement, the end of the circumferential section of the limiting slide that connects to the axial section is designated as the first end, and the end away from the axial section is designated as the second end. The second end of the circumferential section has a limiting recess on its side wall near the insertion channel, which is used to limit the protrusion on the plug body. Due to the elasticity of the check valve assembly, the plug body also tends to disengage from the connector. The aforementioned limiting recess allows the protrusion on the plug body to be limited within it, thus achieving circumferential limiting and preventing the protrusion from easily moving in the opposite direction along the circumferential section of the limiting slide and disengaging.

[0016] For ease of processing, the limiting slide extends from the inner wall of the insertion channel to the outer wall of the insertion channel.

[0017] To ensure a secure lock between the plug body and the connector, the plug body has two protrusions on the plug portion symmetrically arranged relative to the axis of the plug body, and the connector also has two corresponding limiting slides. It is conceivable that the plug body could also have three or more protrusions on the plug portion to further enhance the secure lock between the plug body and the plug.

[0018] To prevent the port periphery of the plug from directly abutting against the valve core and affecting the gas flow rate, the port periphery of the plug has legs arranged circumferentially and extending outward axially. When the protrusion of the plug body and the limiting slide are axially limited, the ends of each leg of the plug body abut against the valve core, causing the valve core to move away from the valve port and open the valve port.

[0019] To improve the stability of the axial movement of the valve core and thus ensure the sealing performance of the valve core at the valve port, the valve core has guide rods arranged circumferentially and extending into the insertion channel on its side wall facing the valve port. When the plug body is inserted into the insertion channel of the connector, each of the guide rods extends into the interior of the plug portion of the plug body.

[0020] In order to achieve a reliable seal between the plug body and the connector and avoid leakage during gas transmission, a sealing ring is also embedded on the inner wall of the insertion channel of the connector to seal against the outer peripheral wall of the plug part of the plug body.

[0021] To facilitate the installation of the check valve assembly within the receiving chamber of the connector, the connector includes a connector body with an installation port at the bottom and a base plate detachably connected to the installation port of the connector body. The base plate and the connector body together define the receiving chamber, and the insertion channel is located on the connector body.

[0022] To facilitate the installation of the connector onto the engine body, the base plate is used to connect to the engine body and has connection holes for the connector to pass through.

[0023] The technical solution adopted by the present invention to solve the second technical problem mentioned above is: an aircraft, including an engine and a skin covering the engine, wherein the skin and the engine are further provided with the aforementioned quick-connect coupling device for blow-starting the aircraft engine.

[0024] Compared with the prior art, the advantages of this invention are as follows: Since the limiting slide for limiting the engagement with the protrusion on the plug body is opened on the inner wall of the insertion channel of the connector, specifically utilizing the wall thickness of the insertion channel portion of the plug, the connector component does not need to be very large to meet the airflow requirements for starting and rotating the aircraft engine. Because it is more compact overall, it can be installed in the limited space between the engine and the aircraft. Furthermore, when the plug body is detached from the connector, the check valve assembly inside the connector automatically closes the valve port, achieving a self-sealing function and effectively preventing external debris from entering the engine. Attached Figure Description

[0025] Figure 1 This is a three-dimensional structural diagram of the quick-connect connector according to an embodiment of the present invention;

[0026] Figure 2 This is a three-dimensional structural diagram of the quick-connect connector in the state where the plug body and the connector are detached, according to an embodiment of the present invention.

[0027] Figure 3 This is a top view of the quick-connect connector according to an embodiment of the present invention;

[0028] Figure 4 This is an axial sectional view of the quick-connect connector according to an embodiment of the present invention;

[0029] Figure 5 This is an axial sectional view of the connector according to an embodiment of the present invention;

[0030] Figure 6 This is an exploded view of the quick-connect connector according to an embodiment of the present invention;

[0031] Figure 7 This is a front view of the aircraft according to the present invention;

[0032] Figure 8 for Figure 7 A cross-sectional view of the aircraft at CC. Detailed Implementation

[0033] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments.

[0034] The specification and claims of this invention use terms indicating direction, such as "front," "rear," "upper," "lower," "left," "right," "side," "top," and "bottom," to describe various exemplary structural parts and elements of the invention. However, these terms are used herein merely for ease of explanation and are determined based on the exemplary orientations shown in the accompanying drawings. Since the embodiments disclosed in this invention can be arranged in different orientations, these terms indicating direction are for illustrative purposes only and should not be considered as limitations. For example, "upper" and "lower" are not necessarily limited to directions opposite to or consistent with the direction of gravity.

[0035] Figures 1-8 A preferred embodiment of the quick-connect fitting device for blow-starting an aircraft engine and an aircraft according to the present invention is shown. The quick-connect fitting device 20 for blow-starting an aircraft engine includes a plug body 10, a connector 20, a sealing ring 40, and a check valve assembly.

[0036] The plug body 10 is a tubular structure, with a plug portion 11 at one end for insertion into the insertion channel 202 of the connector 20, and the other end for connection to a high-pressure gas pipeline (high-pressure gas source). The plug portion 11 of the plug body 10 has a circular cross-section, and its outer peripheral wall has a protrusion 111 that protrudes radially outward. Specifically, in this embodiment, the protrusion 111 is a pin, wherein there are two pins, which are symmetrically arranged relative to the axis of the plug portion 11.

[0037] The connector 20 is used for installation on the engine body, specifically in the gap space between the engine and the aircraft skin. The connector 20 includes a connector body 21 and a base plate 22. The connector body 21 is hollow and has a mounting opening at its bottom. The base plate 22 connects to the mounting opening of the connector body 21, and together they define a receiving chamber 201 for housing a check valve assembly. The connector body 21 also has an insertion channel 202 communicating with the receiving chamber 201 and allowing the plug portion 11 of the plug body 10 to be inserted therein. A valve port 203 is formed on the inner wall of the receiving chamber 201 at a position communicating with the insertion channel 202. The valve port 203 and the insertion channel 202 on the connector body 21 are opposite to the mounting opening on the connector body 21. The base plate 22 of the connector 20 is used for connection to the engine body and has a connection hole 221. A connector (such as a bolt) passing through the connection hole 221 can fix the connector 20 to the engine body. Figure 3As shown, an air outlet 222 for airflow is also provided on the base plate 22 at a position opposite to the valve port 203.

[0038] See Figure 4 and Figure 5 The check valve assembly includes a valve core 31 and an elastic element 32. The valve core 31 is movably disposed in the receiving chamber 201 in a manner that allows it to move closer to and further away from the valve port 203. In this embodiment, the elastic element 32 is a spring. The first end of the spring abuts against the side of the valve core 31 away from the valve port 203, and the second end abuts against the inner wall of the wall plate. Under the elastic force of the elastic element 32, the valve core 31 always has a tendency to move toward the valve port 203 and close the valve port 203.

[0039] The valve core 31 has guide rods 311 arranged circumferentially at intervals on one side wall facing the valve port 203 and extending into the insertion channel 202. In this embodiment, there are three guide rods 311, all arranged near the outer peripheral edge of the valve core 31. When the plug body 10 is inserted into the insertion channel 202 of the connector 20, the three guide rods 311 extend into the interior of the plug portion 11 of the plug body 10 and are set close to the inner wall of the plug portion 11. In this way, the stability of the axial movement of the valve core 31 during axial movement (i.e., during the opening and closing of the valve port 203) can be improved, avoiding shaking or displacement problems, thereby ensuring the sealing performance of the valve core 31 at the valve port 203.

[0040] See Figure 6 The inner wall of the insertion channel 202 has a radially outwardly recessed limiting slide 210. In this embodiment, the limiting slide 210 is generally L-shaped, including an axial section 211 extending from the opening edge of the insertion channel 202 toward the location of the receiving chamber 201, and a circumferential section 212 extending circumferentially from the end of the axial section 211 (i.e., the end near the valve port 203). When the plug body 10 is inserted into the insertion channel 202 of the connector 20, the protrusion 111 can slide in along the axial section 211 of the limiting slide 210 and, after rotating a certain angle, achieve axial limitation with the circumferential section 212 of the limiting slide 210. The end of the circumferential section 212 of the limiting slide 210 that connects to the axial section 211 is designated as the first end, and the end away from the axial section 211 is designated as the second end. A limiting recess 2120 is provided on the side wall of the second end of the circumferential section 212 of the limiting slide 210 near the insertion channel 202, where the protrusion 111 on the plug body 10 is limited. Due to the action of the elastic element 32 of the check valve assembly, the plug body 10 also tends to disengage from the connector 20. The aforementioned limiting recess 2120 is designed to limit the protrusion 111 on the plug body 10, thus achieving circumferential limiting and preventing the protrusion 111 from easily moving in the opposite direction along the circumferential section 212 of the limiting slide 210 and disengaging.

[0041] In this embodiment, the limiting slide 210 extends from the inner wall of the insertion channel 202 to the outer wall of the insertion channel 202. That is, the limiting slide 210 is an L-shaped opening that runs through both the inside and outside. This structural design allows users to more intuitively observe the position of the limiting slide 210 and slide the protrusion 111 on the plug body 10 into the set position on the limiting slide 210.

[0042] In this embodiment, a sealing ring 40 is also embedded on the inner wall of the insertion channel 202 of the connector 20. After the plug body 10 is inserted into the insertion channel 202 of the connector 20, the outer peripheral wall of the plug part 11 of the plug body 10 is in sealing contact with the sealing ring 40, thereby achieving a reliable seal between the outer peripheral wall of the plug body 10 and the inner peripheral wall of the insertion channel 202 of the connector 20, and avoiding leakage problems during gas transmission.

[0043] The plug portion 11 of this embodiment also has circumferentially spaced legs 112 that extend outward in the axial direction. When the protrusion 111 of the plug body 10 is axially limited by the limiting slide 210, the ends of each leg 112 of the plug body 10 can abut against the valve core 31, causing the valve core 31 to move away from the valve port 203 and open the valve port 203. The structural design of using legs 112 to drive the valve core 31 to move can avoid the circumference of the plug portion 11 directly abutting against the valve core 31 and affecting the gas flow rate.

[0044] join Figure 7 and Figure 8 This embodiment also relates to an aircraft, including an engine 51 and a skin 52 covering the engine 51. There is a gap between the skin 52 and the engine 51, and the quick-connect device 1 for blowing and starting the aircraft engine is disposed in the gap. The base plate 22 of the connector 20 of the quick-connect device is used to connect with the main body of the engine 51.

[0045] The quick-connector 20 in this embodiment is used as follows:

[0046] Align the plug portion 11 of the plug body 10 with the insertion channel 202 of the connector 20, ensuring that the protrusion 111 on the plug portion 11 aligns with the front end of the axial section 211 of the limiting slide 210 on the connector 20. Then, insert the plug body 10 into the insertion channel 202 of the connector 20, pushing the plug body 10 to the bottom and rotating it clockwise into place. At this point, the three support legs 112 on the plug body 10 open the check valve core 31, compressing the spring and opening a passage for the entire airflow. The cross-sectional area of ​​the flow channel meets the flow requirements, and the airflow flows through the check valve core 31 into the engine blow-through hole. Under the push of the check valve spring, the protrusion 111 on the plug body 10 engages with the limiting recess on the circumferential end of the limiting slide 210, preventing the plug body 10 from rotating in the opposite direction and falling off. The sealing ring 40 provides a radial seal to the outer peripheral wall of the plug body 10 and the inner peripheral wall of the insertion channel 202 of the connector 20, preventing airflow leakage. When the plug body 10 needs to be disengaged, push the plug body 10 to the bottom and rotate it counterclockwise. The protrusion 111 on the plug body 10 disengages from the limiting recess and comes out in the opposite direction along the limiting slide 210. The plug body 10 then separates from the connector 20. The spring of the check valve assembly pushes the check valve core 31 back to close the valve port 203, realizing the self-sealing function and preventing foreign objects from entering the engine.

Claims

1. A quick-connect coupling device for blow-starting an aircraft engine, comprising: The plug body (10) has a plug portion (11) at its end; The connector (20) has a receiving chamber (201) and an insertion channel (202) communicating with the receiving chamber (201) and allowing the plug portion (11) of the plug body (10) to be inserted therein, wherein a valve port (203) is formed at the position where the receiving chamber (201) and the insertion channel (202) communicate; A check valve assembly is disposed in the receiving chamber (201) of the connector (20), including a valve core (31) and an elastic element (32). The valve core (31) is movably disposed in the receiving chamber (201) in a manner that it can move closer to and further away from the valve port (203), and can correspondingly close and open the valve port (203). The elastic element (32) acts on the valve core (31) and makes the valve core (31) always have a tendency to move toward the valve port (203) to close the valve port (203). Its features are: The plug body (10) has a protrusion (111) on the outer peripheral wall of the plug portion (11) that protrudes radially outward, and the insertion channel (202) has a limiting slide (210) that is recessed radially outward on the inner wall. The protrusion (111) of the plug body (10) can be inserted into the limiting slide (210) axially, and after rotating a certain angle, it is axially limited with the limiting slide (210). When the protrusion (111) of the plug body (10) and the limiting slide (210) are axially limited, the plug body (10) abuts against the valve core (31) and moves the valve core (31) away from the valve port (203) to open the valve port (203); The port of the plug (11) has circumferentially spaced legs (112) that extend outward in the axial direction. When the protrusion (111) of the plug body (10) and the limiting slide (210) are axially limited, the ends of each leg (112) of the plug body (10) abut against the valve core (31) and make the valve core (31) move away from the valve port (203) to open the valve port (203). The valve core (31) has guide rods (311) arranged circumferentially and extending into the insertion channel (202) on its side wall facing the valve port (203). When the plug body (10) is inserted into the insertion channel (202) of the connector (20), each guide rod (311) extends into the interior of the plug portion (11) of the plug body (10) and is set close to the inner wall of the plug portion (11).

2. The quick-connect coupling device for blow-starting an aircraft engine according to claim 1, characterized in that: The limiting slide (210) includes an axial section (211) extending from the opening edge of the insertion channel (202) toward the location of the receiving chamber (201) and a circumferential section (212) extending circumferentially from the end of the axial section (211). The protrusion (111) of the plug body (10) can slide into the axial section (211) of the limiting slide (210) and, after rotating a certain angle, achieve axial limiting with the circumferential section (212) of the limiting slide (210).

3. The quick-connect coupling device for blow-starting an aircraft engine according to claim 2, characterized in that: The end of the circumferential section (212) of the limiting slide (210) that connects with the axial section (211) is called the first end, and the end away from the axial section (211) is called the second end. The second end of the circumferential section (212) has a limiting recess (2120) on the side wall near the insertion channel (202) for limiting the protrusion (111) on the plug body (10) to be positioned therein.

4. The quick-connect coupling device for blow-starting an aircraft engine according to claim 1, characterized in that: The limiting slide (210) extends from the inner wall of the insertion channel (202) to the outer wall of the insertion channel (202).

5. The quick-connect coupling device for blow-starting an aircraft engine according to any one of claims 1 to 4, characterized in that: The plug body (10) has two protrusions (111) on the plug portion (11) arranged symmetrically with respect to the axis of the plug body (10), and the connector (20) also has two corresponding limiting slides (210).

6. The quick-connect coupling device for blow-starting 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 provided with a sealing ring (40) for sealing contact with the outer peripheral wall of the plug part (11) of the plug body (10).

7. The quick-connect coupling device for blow-starting an aircraft engine according to any one of claims 1 to 4, characterized in that: The connector (20) includes a connector body (21) with an installation port at the bottom and a base plate (22) detachably connected to the installation port of the connector body (21). The base plate (22) and the connector body (21) together define the receiving chamber (201). The insertion channel (202) is located on the connector body (21). The base plate (22) is used to connect to the main body of the engine and has a connection hole (221) for the connector to pass through.

8. An aircraft comprising an engine (51) and a skin (52) covering the engine (51), characterized in that: A quick-connector device for blow-starting an aircraft engine as described in any one of claims 1 to 7 is also provided between the skin (52) and the engine (51).

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