Civil aero-engine reverse thrust outer duct sealing test tool and test system

Abstract

The invention provides a civil aero-engine reverse thrust outer duct sealing test tool and test system, the civil aero-engine reverse thrust outer duct sealing test tool comprises a sealing device and a balancing device, the sealing device comprises a sealing plate and an inflation sealing structure, the shape of the sealing plate is matched with the shape of a sealing working section, and the inflation sealing structure is arranged at the peripheral edge of the sealing plate in a surrounding manner; the balance device comprises a working rod, a balance weight, a linkage mechanism and a device carrier, the first end of the working rod is connected with the sealing device, the second end of the working rod is connected to the linkage mechanism, the linkage mechanism is installed on the device carrier, and the balance weight is connected with the linkage mechanism. The invention also provides a sealing test system. The defect that in the prior art, in a sealing test of a nacelle in a sealing rubber strip pressing mode before leaving a factory, the nacelle is subjected to extra stress and extrusion under the condition that sealing is achieved, and consequently abrasion between the nacelle and a pressing sealing piece is caused is overcome.

Description

Technical Field

[0001] The invention relates to the field of ground test bench testing of aircraft engines, and in particular to a reverse thrust outer duct sealing test tool and a test system for civil aircraft engines. Background Art

[0002] Leakage has long plagued various industries, especially aircraft engines. The sealing of the nacelle of civil aircraft engines is particularly important, which directly affects the thrust provided by the engine to the aircraft. However, leakage occurs from time to time in actual work. The reasons are mostly due to improper use of sealing methods or sealing materials, or aging and failure of sealing devices. Especially for dynamic seals and parts with irregular surfaces, the sealing device and even the equipment itself will be worn after use, and its sealing performance will be greatly reduced or even fail.

[0003] The nacelle is the core equipment of the aircraft, the protective cover of the engine, and the key technology for aircraft flight. It is wrapped around the outside of the aircraft engine and provides the required working environment for the normal operation of the engine. It can also play important functions such as noise reduction, ventilation and cooling, drainage and pressure relief, fire detection, and lightning protection. The nacelle mainly includes the air inlet, fan cover, reverse thrust and tail nozzle.

[0004] The civil aviation engine power unit for route operation consists of two parts: the aircraft engine and the product nacelle. As an important component of the power unit, the sealing of the product nacelle is very important. For this reason, a sealing inspection must be carried out before the nacelle leaves the factory. The produced nacelles are usually inspected for sealing by plugging and pressurizing to confirm whether the nacelle meets the airtight use requirements and meets the technical conditions of the supporting power unit.

[0005] The sealing test of the nacelle before leaving the factory usually adopts the form of compression of sealing strips. The nacelle is subjected to additional stress when the sealing is achieved, and the extrusion causes wear between the nacelle and the compression seal.

[0006] In the reverse thrust duct sealing test, the cross section of the reverse thrust duct needs to be sealed.

[0007] This type of seal generally has a larger circumference and the periphery is mostly irregular, resulting in inconsistent or variable gaps that need to be sealed. The range of variation is generally 3-5mm or even larger. It is difficult to achieve an ideal sealing effect using ordinary sealing strips.

[0008] The use of high-quality elastic sealing rubber rings or other high-efficiency sealing devices in sealing tests is difficult to promote and popularize due to their complex structure, high requirements for the use environment and high manufacturing costs.

[0009] In view of this, the inventor has designed a civil aviation engine thrust reverse duct sealing test tool and test system in order to solve the above technical problems. Summary of the invention

[0010] The technical problem to be solved by the present invention is to overcome the defect that in the prior art, the nacelle sealing test before delivery which adopts the form of compression with sealing strips will be subjected to additional stress when the sealing is achieved, and the extrusion will cause wear between the nacelle and the compression seal, and a civil aviation engine reverse thrust outer duct sealing test tool and test system are provided.

[0011] The present invention solves the above technical problems through the following technical solutions:

[0012] The present invention provides a civil aviation engine thrust reverser outer duct sealing test tool, which is characterized in that the test tool comprises a sealing device and a balancing device.

[0013] The sealing device comprises a sealing plate and an inflatable sealing structure, the shape of the sealing plate matches the shape of the sealing working section, and the inflatable sealing structure is arranged around the outer peripheral edge of the sealing plate;

[0014] The balancing device comprises a working rod, a balancing weight, a linkage mechanism and a device carrier, wherein the first end of the working rod is connected to the sealing device, the second end of the working rod is connected to the linkage mechanism, the linkage mechanism is mounted on the device carrier, and the balancing weight is connected to the linkage mechanism;

[0015] When the first end of the working rod moves in the axial direction, the linkage mechanism is driven to move the balancing weight in the opposite direction, thereby maintaining the overall balance of the test fixture.

[0016] According to an embodiment of the present invention, a sealing plate supporting structure is provided on the sealing plate.

[0017] According to one embodiment of the present invention, the sealing plate is C-shaped.

[0018] According to an embodiment of the present invention, the edge of the sealing plate has a groove structure, and the inflatable sealing structure is installed in the groove structure.

[0019] According to one embodiment of the present invention, the inflatable sealing structure is an inflatable rubber tube, the interior of the rubber tube is hollow and is provided with at least one air nozzle.

[0020] According to one embodiment of the present invention, the linkage mechanism is a linkage gear and a linkage rod, the linkage rod is provided with teeth matching with the linkage gear; the working rod has teeth matching with the linkage gear, and the balancing weight is provided on the linkage rod.

[0021] According to one embodiment of the present invention, the device carrier is a balancing cart.

[0022] According to one embodiment of the present invention, the device carrier has a lifting and lowering adjustment mechanism to adjust the height of the test tool.

[0023] The present invention also provides a civil aviation engine thrust reverser outer duct sealing test system, which is characterized in that the test system includes a pressure monitoring device and at least two civil aviation engine thrust reverser outer duct sealing test fixtures as described above.

[0024] The positive and progressive effects of the present invention are:

[0025] The civil aviation engine thrust reverser outer duct sealing test fixture and test system of the present invention have the following advantages:

[0026] 1. The reverse duct sealing test tooling has a simple structure and is easy to operate, which can improve on-site work efficiency;

[0027] 2. The front and rear plugs with sealing plates are in a balanced state and will not cause damage to the nacelle casing during penetration;

[0028] 3. During the sealing process, there is no relative movement with the outer wall of the nacelle except for the positive pressure, and the nacelle wall will not be worn;

[0029] 4. The working status of the sealing process can be monitored at any time, and the sealing pressure can be monitored;

[0030] 5. The structural device provided by this method has a simple structure, low cost, and simple maintenance, and can be widely used in various environments;

[0031] 6. Reduce the wear and damage of the two combined parts, and effectively extend the service life of tooling parts and seals. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always represent the same features, wherein:

[0033] Figure 1 The present invention is a schematic diagram of the sealing working section position of the reverse thrust duct sealing test tool for a civil aviation engine.

[0034] Figure 2 It is a schematic cross-sectional view of the sealing working section AA of the reverse thrust duct sealing test tooling of a civil aviation engine of the present invention.

[0035] Figure 3The invention is a schematic diagram of the installation of the reverse thrust outer duct sealing test tooling of a civil aviation engine.

[0036] Figure 4 The present invention is a schematic diagram of the installation and use of a working rod and a sealing plate of a reverse thrust duct sealing test tool for a civil aviation engine.

[0037] Figure 5A The present invention is a three-dimensional schematic installation diagram of a sealing plate and an inflatable sealing structure of a reverse thrust duct sealing test tool for a civil aviation engine from one perspective.

[0038] Figure 5B The present invention is a three-dimensional schematic diagram of the installation of the sealing plate and the inflatable sealing structure of the reverse thrust duct sealing test tooling of the civil aviation engine of the present invention from another perspective.

[0039] Fig. 6A It is an enlarged schematic cross-sectional view of the sealing position state of the inflatable sealing structure of the reverse duct sealing test tooling of a civil aviation engine of the present invention in an uninflated state.

[0040] Figure 6B It is an enlarged schematic cross-sectional view of the sealing position state of the inflatable sealing structure of the reverse duct sealing test tooling of a civil aviation engine of the present invention in an inflated state.

[0041] Fig. 7A The present invention is a schematic structural diagram of a balancing device for a reverse thrust duct sealing test fixture for a civil aviation engine.

[0042] Figure 7B The present invention is a dynamic schematic diagram of the working state of the balancing device of the reverse thrust outer duct sealing test tooling of the civil aviation engine.

[0043] Figure 8 The present invention is a schematic diagram of the specific structure of the balancing device of the reverse thrust outer duct sealing test tooling of the civil aviation engine.

[0044] [Reference Signs]

[0045] Sealing device 100

[0046] Sealing plate 110

[0047] Groove structure 111

[0048] Inflatable sealing structure 120

[0049] Gas nozzle 121

[0050] Sealing plate support structure 130

[0051] Balancing device 200

[0052] Working rod 210

[0053] The first end portion 211

[0054] The second end portion 212

[0055] Tooth 213

[0056] Balance weight 220

[0057] Linkage mechanism 230

[0058] Linkage gear 231

[0059] Linkage rod 232

[0060] Tooth 233

[0061] Device carrier 240

[0062] Sealing test section 300

[0063] Sealing working section 310

[0064] Nacelle wall surface 320 DETAILED DESCRIPTION

[0065] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0066] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to preferred embodiments of the present invention, examples of which are shown in the accompanying drawings. Wherever possible, the same reference numerals will be used throughout the drawings to represent the same or similar parts.

[0067] Furthermore, although the terms used in the present invention are selected from well-known and commonly used terms, some terms mentioned in the present invention specification may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this document.

[0068] Furthermore, it is required that the present invention be understood not only by the actual terms used but also by the meanings connoted by each term.

[0069] like Figures 2 to 8 As shown, the present invention provides a civil aviation engine reverse thrust outer duct sealing test tool, and the test tool includes a sealing device 100 and a balancing device 200.

[0070] The sealing device 100 includes a sealing plate 110 and an inflatable sealing structure 120 . The shape of the sealing plate 110 matches the shape of the sealing working section 310 . The inflatable sealing structure 120 is arranged around the peripheral edge of the sealing plate 110 .

[0071] The balancing device 200 includes a working rod 210, a balancing weight 220, a linkage mechanism 230 and a device carrier 240. The first end 211 of the working rod 210 is connected to the sealing device 100, and the second end 212 of the working rod 210 is connected to the linkage mechanism 230. The linkage mechanism 230 is installed on the device carrier 240, and the balancing weight 220 is connected to the linkage mechanism 230.

[0072] When one end of the working rod 210 moves axially, it drives the linkage mechanism 230 to move the balancing weight 220 in the opposite direction, thereby maintaining the overall balance of the test fixture.

[0073] The structure of the sealing plate 110 is a spatial irregular structural profile along the actual structural boundary of the product, which is simplified as a sealing plate structure in the figure. In addition, the actual tooling structure is a plurality of connecting profiles, one of which is used as an example in the figure.

[0074] Figure 1 The figure shows the overall assembly state of the engine nacelle when it is working in conjunction with the engine, and the section symbol AA shows the position of the sealing working section 310.

[0075] Figure 2 It is a schematic diagram of the AA section at the engine nacelle sealing working section 310, illustrating the overall relative position and sealing structure of various components during the sealing inspection process.

[0076] When conducting the reverse thrust duct sealing test, first set the inflatable sealing structure 120 to an uninflated state, move the test fixture, and use the working rod 210 to push the sealing plate 110 from the engine nacelle air inlet into the sealing working section 310, that is, the inlet end of the reverse thrust duct.

[0077] When the inflatable sealing structure 120 is in an uninflated state, a distance of several millimeters is reserved between the sealing device 100 and the inner wall of the nacelle, and the sealing device 100 does not contact the wall.

[0078] One end of the working rod 210 connected to the sealing device 100 is the first end 211 of the working rod 210, and the other end of the working rod 210 connected to the linkage mechanism 230 is the second end 212 of the working rod 210. When the first end 211 of the working rod 210 moves axially, the linkage mechanism 230 drives the balancing weight 220 to move in the opposite direction, so that the weight of the balancing weight 220 can balance the weight of the sealing device 100, thereby maintaining the overall balance of the test fixture.

[0079] Due to the irregular surface of the nacelle, when the sealing device 100 penetrates into the sealing working section 310, in order to adapt to the irregular surface, the front and rear positions of the sealing device 100 need to be adjusted frequently, so that the sealing device 100 can be penetrated into the sealing working section 310 without contacting the nacelle wall 320.

[0080] Therefore, in the process of adjusting the front and rear position of the sealing device 100, the first end 211 of the working rod 210 connected to the sealing device 100 also moves inward or outward along the axial direction. Figure 7B In the O direction, the balancing weight 220 moves in the opposite direction, that is, in the I direction. Similarly, when the first end 211 of the working rod 210 moves outward along the axial direction, that is, Figure 7B In the I direction, the balancing weight 220 moves in the opposite direction, that is, the O direction.

[0081] When the sealing device 100 reaches the sealing working cross section 310, the inflatable sealing structure 120 is inflated. The cross-sectional state of the inflatable sealing structure 120 in the uninflated state is as follows: Fig. 6A As shown in the figure, F represents the flow direction of the airflow, and the airflow on one side of the sealing device 100 can flow to the other side. When a certain amount of gas is filled inside the inflatable sealing structure 120, the cross-sectional state of the inflatable sealing structure 120 in the inflated state is as follows Figure 6B As shown in the figure, F represents the flow direction of the airflow, and at this time the airflow on one side of the sealing device 100 cannot flow to the other side.

[0082] When the sealing devices 100 of the two civil aviation engine reverse thrust outer duct sealing test fixtures are respectively arranged at the inlet and outlet of the reverse thrust outer duct, one after the other, and the inflatable sealing structures 120 on the two test fixtures are in an inflated state, the reverse thrust outer duct is blocked, and a certain amount of gas is injected into the blocked reverse thrust outer duct to generate pressure, thereby performing a sealing check on the reverse thrust outer duct.

[0083] like Figures 2 to 4 As shown, as a preferred embodiment, a sealing plate support structure 130 is provided on the sealing plate 110. The sealing plate support structure 130 may be a frame structure supporting the sealing plate 110, thereby enhancing the overall strength and rigidity of the sealing plate 110.

[0084] like Figure 3 , Figure 4 , Figure 5A and Figure 5B As shown, as a preferred embodiment, the sealing plate 110 is C-shaped.

[0085] Since the sealing working section 310 of the reverse duct sealing test is usually C-shaped, the sealing plate 110 is designed to be C-shaped to fit the shape of the sealing working section 310 .

[0086] like Figure 5A and Figure 5B As shown, as a preferred embodiment, the edge of the sealing plate 110 has a groove structure 111 , and the inflatable sealing structure 120 is installed in the groove structure 111 .

[0087] The groove structure 111 on the edge of the sealing plate 110 provides a space for setting the inflatable sealing structure 120, and the inflatable sealing structure 120 can be stuck in the groove structure 111. When inflated, the two side walls of the groove structure 111 limit the lateral movement of the inflatable sealing structure 120, and the inflatable sealing structure 120 is fully in contact with the nacelle wall surface 320 at the opening, thereby improving the sealing performance. At the same time, since the inflatable sealing structure 120 is stuck in the groove structure 111, it is also convenient to disassemble and replace the inflatable sealing structure 120.

[0088] like Figure 5A and Figure 5B As shown, as a preferred embodiment, the inflatable sealing structure 120 is an inflatable rubber tube, the interior of the rubber tube is hollow and has at least one air nozzle 121.

[0089] The rubber tube with the air nozzle 121 achieves the sealing of the reverse thrust duct by the sealing device 100 through the inflation and deflation of the air nozzle 121 .

[0090] Fig. 6A and Figure 6B The inflation process of the inflatable sealing structure 120 is shown, the physical model is simplified, and the pressure difference between the inside and outside of the sealing material is used as the characteristic parameter. When the internal pressure is greater than the external pressure, the inflatable sealing ring is pressed against the nacelle wall 320 and at the same time pressed in the groove structure 111 of the sealing plate 110 to prevent air from flowing from the inside of the nacelle to the outside.

[0091] exist Figure 5A , Figure 5B , Fig. 6A and Figure 6B In the embodiment, an inflatable sealing ring is placed in the groove structure 111 on the edge of the sealing plate 110. The figure shows an inflatable rubber tube, which is hollow inside and has one or more air nozzles 121. Inflatable sealing rings are a common type of product. Generally, the types of inflatable sealing rings are divided by the specifications and cross-sectional shapes of the inflatable sealing rings. In terms of cross-sectional shapes, there are circular, rectangular, square, trapezoidal, D-shaped, C-shaped, V-shaped, M-shaped and other types of inflatable sealing rings. Fig. 6A and Figure 6BTaking the structure of the O-ring as an example, when the structure is not inflated, a distance of several millimeters is reserved to avoid contact with the interior of the nacelle and the wall surface. After inflation, the structure is tightly fitted with the side wall of the groove structure 111 at the edge of the sealing plate 110 and the nacelle wall surface 320 to prevent air circulation.

[0092] like Figure 8 As shown, as a preferred embodiment, the linkage mechanism 230 is preferably configured as a linkage gear 231 and a linkage rod 232, and the linkage rod 232 is provided with teeth 233 that cooperate with the linkage gear 231; the working rod 210 has teeth 213 that cooperate with the linkage gear 231, and the balancing weight 220 is arranged on the linkage rod 232.

[0093] The linkage mechanism 230 of the above structure enables the axial movement of the balance weight 220 and the working rod 210 to be synchronously anti-phase, and when the position of the sealing device 100 connected to the working rod 210 is adjusted, the balance and stability of the entire test fixture is achieved.

[0094] like Figure 3 , Fig. 7A and Figure 7B As shown, as a preferred embodiment, the device carrier 240 can preferably be a balancing cart.

[0095] After the balancing trolley as the device carrier 240 carries the working rod 210, the balancing weight 220 and the linkage mechanism 230, it is convenient for the civil aviation engine reverse thrust outer duct sealing test tooling to be positioned at the reverse thrust outer duct sealing test working point

[0096] like Fig. 7A , 7B As shown, when the balancing trolley pushes the sealing plate 110 deeper into the nacelle, the balancing weight 220 on the trolley is synchronously moved in the opposite direction through the action of the linkage gear 231 on the tooling. As the sealing plate 110 is extended, the structure is always in a balanced state and will not be deflected.

[0097] As a preferred embodiment, the device carrier 240 has a lifting and lowering adjustment mechanism to adjust the height of the test tooling.

[0098] Here, the lifting and adjusting mechanism can be an adjustable height mechanism such as a hydraulic lifting platform in the prior art. The upper part of the lifting and adjusting mechanism is provided with a device consisting of a working rod 210, a balancing weight 220 and a linkage mechanism 230, and the lower part of the lifting and adjusting mechanism is provided on the device carrier 240, thereby realizing the adjustable height of the test tooling.

[0099] Since the height of the test fixture is adjustable, it can adapt to sealing test environments at different heights.

[0100] The present invention also provides a civil aviation engine thrust reverse duct sealing test system, comprising a pressure monitoring device and the civil aviation engine thrust reverse duct sealing test tooling.

[0101] The pressure monitoring device is used to monitor the internal pressure changes of the inflatable sealing structure 120 and the pressure changes in the blocked reverse thrust duct during the reverse thrust duct sealing test of the civil aviation engine.

[0102] The pressure monitoring device includes two sensor modules: one sensor module is arranged inside the nacelle to monitor the stable balance of the pressure inside the nacelle, thereby monitoring the pressure in the reverse thrust outer duct that is blocked during the sealing test; the other sensor module is arranged inside the inflatable sealing structure 120 to monitor the pressure stability of the inflatable sealing structure 120.

[0103] According to the above structural description, the specific implementation steps of the reverse thrust outer duct sealing test system of the civil aviation engine of the present invention are as follows:

[0104] Step S1: The sealing inspection work starts, and the engine installed on the nacelle integrated frame is placed in a specified position;

[0105] Step S2, connecting the balancing device 200 using the balancing vehicle as the device carrier 240 and the sealing plate supporting structure 130;

[0106] Step S3, putting an inflatable rubber tube on the edge of the reserved groove structure 111 of the sealing plate 110;

[0107] Step S4, connecting the screw positions of the sealing plate support structure 130 and the sealing plate 110, and after fixing, adjusting the balance of the overall tooling;

[0108] Step S5, move the balancing vehicle to a suitable position in front of the nacelle, and gradually push the sealing plate 110 deeper into the air inlet of the nacelle;

[0109] Step S6: Adjust the position of the trolley, observe and adjust the distance between the edge of the sealing plate 110 and the nacelle wall 320. At this time, the air before and after the sealing plate 110 can flow freely. Fig. 6A ;

[0110] Step S7, check the distance between the edge of the sealing plate 110 and the nacelle wall 320, and if it meets the requirements, determine the distance and fix the spatial position of the sealing plate 110;

[0111] Step S8, open the connected air supply pipeline and inflate the rubber tube until the sealing rubber tube is completely in contact with the nacelle wall surface 320;

[0112] Step S9: monitor and manage the pressure inside the rubber tube. When the pressure reaches the specified value, close the air supply valve. At this time, the air before and after the sealing plate 110 cannot circulate. Figure 6B ;

[0113] Step S 10 , conduct sealing tests, monitor the pressure changes of the outer duct at the sealing point in real time, and understand the sealing effect.

[0114] like Figure 3 As shown, when the test tooling is installed, the working rod 210, the balancing weight 220 and the linkage mechanism 230 are loaded from the far right, and the sealing plate support structure 130, the sealing plate 110 and the inflatable sealing structure 120 are installed in sequence according to the order of the arrows in the figure, and penetrate into the inner wall of the nacelle of the engine.

[0115] like Figure 4 As shown, when the test fixture is installed, the first end 211 of the working rod 210 is connected to the sealing plate 110 with the sealing plate support structure 130, and the structure of the second end 212 of the working rod 210 connected to other parts of the balancing device 200 is omitted in the figure, and the working rod 210 extends the sealing plate 110 into the sealing test section 300 of the reverse thrust duct of the engine nacelle for sealing test. As shown in the figure, the first end 211 of the working rod 210 has a portion axially bent inwardly toward the sealing test section 300, so that the sealing plate 110 is extended into the nacelle.

[0116] like Figure 5A , 5B As shown, when the test fixture is installed, the inflatable sealing structure 120 is sleeved on the edge of the sealing plate 110 and is stuck in the groove structure 111 on the edge of the sealing plate 110 .

[0117] The present invention provides a civil aviation engine reverse thrust duct sealing test tool and test system, which are used to perform sealing inspection on the reverse thrust duct of the civil aviation engine nacelle, solving the problem of sealing leakage during the inspection of the sealing of the reverse thrust duct of the civil aviation engine nacelle. This sealing structure is particularly effective when applied to irregular surface areas of large nacelles. It not only solves the leakage problem caused by irregular walls between two moving parts, but also greatly reduces the wear and damage of the two combined parts, effectively extending the service life of the tooling parts and seals. By using the sealing structure with front and rear sealing plates 110 of the present invention, it can ensure that the tooling used in work is balanced in force, and no additional force acts on the wall of the engine nacelle casing.

[0118] Since the sealing device 100 used for sealing is sealed in the form of active inflation, the internal pressure is monitored and can be adjusted at any time.

[0119] Since the sealing plate part of the sealing tooling is fixed in space due to the deep thrust of the outer duct, there is no stress contact and relative movement at the edge of the structural part with the outer wall of the nacelle except for the positive pressure during the contact process.

[0120] Since the part of the sealing tooling that pushes the outer duct backwards uses a balance method to supplement the unbalanced torque generated by the depth, the tooling is always in a balanced state and no additional stress is generated on the test piece itself.

[0121] During the reverse thrust outer duct sealing test, an active inflatable sealing device 100 is used to seal the front and rear airflow passages of the nacelle, which can monitor the changes in the sealing pressure and ensure the work effect on site.

[0122] In summary, the reverse thrust outer duct sealing test system of the civil aviation engine of the present invention has the following advantages:

[0123] 1. Simple structure, easy operation, and improved on-site work efficiency;

[0124] Second, the front and rear plugs with sealing plates 110 are in a balanced state and will not cause damage to the nacelle casing during penetration;

[0125] 3. During the sealing process, there is no relative movement with the outer wall of the nacelle except for the positive pressure, and the nacelle wall surface will not be worn 320;

[0126] 4. The working status of the sealing process can be monitored at any time, and the sealing pressure can be monitored;

[0127] 5. The tooling has a simple structure, low cost, and simple maintenance, and can be widely used in various environments;

[0128] 6. Reduce the wear and damage of the two combined parts, and effectively extend the service life of tooling parts and seals.

[0129] Although the specific embodiments of the present invention are described above, it should be understood by those skilled in the art that these are only examples, and the protection scope of the present invention is defined by the appended claims. Those skilled in the art may make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. A civil aviation engine thrust reverse duct sealing test tool, characterized in that: The test fixture includes a sealing device and a balancing device. The sealing device comprises a sealing plate and an inflatable sealing structure, the shape of the sealing plate matches the shape of the sealing working section, and the inflatable sealing structure is arranged around the outer peripheral edge of the sealing plate; The balancing device comprises a working rod, a balancing weight, a linkage mechanism and a device carrier, wherein the first end of the working rod is connected to the sealing device, the second end of the working rod is connected to the linkage mechanism, the linkage mechanism is mounted on the device carrier, and the balancing weight is connected to the linkage mechanism; When the first end of the working rod moves in the axial direction, the linkage mechanism is driven to move the balancing weight in the opposite direction, thereby maintaining the overall balance of the test fixture.

2. The civil aviation engine thrust reverser outer duct sealing test tool as claimed in claim 1, characterized in that: A sealing plate supporting structure is arranged on the sealing plate.

3. The civil aviation engine thrust reverser outer duct sealing test tool as claimed in claim 1, characterized in that: The sealing plate is C-shaped.

4. The civil aviation engine thrust reverser outer duct sealing test tool as claimed in claim 1, characterized in that: The edge of the sealing plate is provided with a groove structure, and the inflatable sealing structure is installed in the groove structure.

5. The civil aviation engine thrust reverser outer duct sealing test tool as claimed in claim 1, characterized in that: The inflatable sealing structure is an inflatable rubber tube, the interior of the rubber tube is hollow and is provided with at least one air nozzle.

6. The civil aviation engine thrust reverser outer duct sealing test tool as claimed in claim 1, characterized in that: The linkage mechanism comprises a linkage gear and a linkage rod, the linkage rod is provided with teeth matching with the linkage gear; the working rod is provided with teeth matching with the linkage gear, and the balancing weight is provided on the linkage rod.

7. The civil aviation engine thrust reverser outer duct sealing test tool as claimed in claim 1, characterized in that: The device carrier is a balancing car.

8. The civil aviation engine thrust reverser outer duct sealing test tool as claimed in claim 1, characterized in that: The device carrier is provided with a lifting and lowering adjustment mechanism to adjust the height of the test tooling.

9. A civil aviation engine thrust reverse duct sealing test system, characterized in that: The test system comprises a pressure monitoring device and at least two civil aviation engine thrust reverse duct sealing test fixtures as described in any one of claims 1-8.

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