Aero-engine composite material repairing device

Abstract

The utility model relates to an aero-engine composite material repairing device. The aero-engine composite material repairing device comprises an inflation assembly which is arranged in a repairing area of a composite material and used for forming positive pressure on the composite material; the inflation pump is connected with the inflation assembly, and the inflation pump is used for providing an air source for the inflation assembly; and the pressure controller is used for controlling the inflation pump to supply air to the inflation assembly. The utility model provides an aero-engine composite material repairing device which can provide positive pressure for a composite material and improve repairing efficiency.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engines, in particular to an aviation engine composite material repair device. Background Art

[0002] In the field of aircraft engines, composite materials are used extensively in aircraft engines based on their excellent performance. For the repair of composite material components, if the space around the component is relatively large, it is convenient to be covered by sealing materials and form negative pressure through vacuuming to meet the requirement that the component can be repaired in situ; if the space around the component is relatively small and cannot be covered by sealing materials, the component must be removed for repair, but the cycle required for component disassembly and installation is relatively long, affecting the efficiency of aircraft use. Utility Model Content

[0003] In view of the above problems in the prior art, the utility model proposes an aircraft engine composite material repair device, which can provide positive pressure on the composite material and improve the repair efficiency.

[0004] Specifically, the utility model proposes an aircraft engine composite material repair device, comprising:

[0005] An inflatable component is disposed in a repair area of ​​the composite material, and the inflatable component is used to form a positive pressure on the composite material;

[0006] An air pump connected to the inflatable component, and used to provide an air source to the inflatable component;

[0007] A pressure controller is used to control the air pump to supply air to the inflatable component.

[0008] According to an embodiment of the utility model, the composite material repair device further comprises a pressure sensor for detecting a pressure signal of the positive pressure and feeding back the pressure signal to the pressure controller, and the pressure controller controls the operation of the air pump based on the pressure signal.

[0009] According to an embodiment of the present invention, the pressure sensor is arranged on the inflatable component and is located on the bonding surface between the inflatable component and the composite material.

[0010] According to an embodiment of the present invention, the composite material repair device further comprises a temperature controller and a heating component, wherein the heating component is used to heat the temperature of the repair area, and the temperature controller is used to control the operation of the heating component.

[0011] According to an embodiment of the utility model, the aircraft engine composite material repair device also includes a temperature sensor, which is arranged in the repair area. The temperature sensor obtains a temperature signal and feeds it back to the temperature controller. The temperature controller controls the operation of the heating component based on the temperature signal.

[0012] According to an embodiment of the utility model, the composite material repair device further comprises a central controller for controlling the operation of the pressure controller and the temperature controller, and the central controller records the positive pressure change and temperature change data of the repair area.

[0013] According to one embodiment of the utility model, the central controller includes a printing module, and the printing module is connected to an external printer. The central controller prints the positive pressure change and temperature change data of the repair area through the printing module and the printer.

[0014] According to an embodiment of the utility model, the central controller includes a display module, and the display module is connected to an external display. The central controller displays the positive pressure change and temperature change data of the repair area through the display module and the display.

[0015] According to an embodiment of the present invention, the composite material repairing device further comprises an input device connected to the central controller, and the central controller receives external control instructions through the input device.

[0016] The utility model provides an aircraft engine composite material repair device, which adopts an inflatable component to provide positive pressure to the composite material at the installation position, thereby improving the repair efficiency.

[0017] It should be understood that the above general description and the following detailed description of the present invention are exemplary and explanatory and are intended to provide further explanation of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings are included to provide a further understanding of the present invention, and they are included and constitute a part of this application. The accompanying drawings illustrate embodiments of the present invention and together with this specification serve to explain the principles of the present invention. In the accompanying drawings:

[0019] Figure 1 The structure diagram of a composite material repair device according to an embodiment of the utility model is shown. Figure 1 .

[0020] Figure 2 The structure diagram of a composite material repair device according to an embodiment of the utility model is shown. Figure 2 .

[0021] The above drawings include the following reference numerals:

[0022] Composite material repair device 100

[0023] Inflatable Components 101

[0024] Air pump 102

[0025] Pressure controller 103

[0026] Pressure sensor 104

[0027] Temperature controller 105

[0028] Heating element 106

[0029] Temperature sensor 107

[0030] Central controller 108

[0031] Print module 109

[0032] Printer 110

[0033] Display module 111

[0034] Display 112

[0035] Input Devices 113 DETAILED DESCRIPTION

[0036] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application may be combined with each other.

[0037] The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The following description of at least one exemplary embodiment is actually merely illustrative and is by no means intended to limit the present application and its application or use. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0038] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0039] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps set forth in these embodiments do not limit the scope of the present application. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to those of ordinary skill in the relevant field may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be considered as a part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so that once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0040] In the description of the present application, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction, and therefore cannot be understood as limiting the scope of protection of the present application; the directional words "inside and outside" refer to the inside and outside relative to the contours of each component itself.

[0041] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used herein to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" may include both "above" and "below". The device may also be positioned in other different ways, rotated 90 degrees or in other orientations, and the spatially relative descriptions used herein are interpreted accordingly.

[0042] In addition, it should be noted that the use of words such as "first" and "second" to define components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above words have no special meaning and cannot be understood as limiting the scope of protection of this application. In addition, although the terms used in this application are selected from well-known and commonly used terms, some terms mentioned in the specification of this application 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 article. In addition, it is required to understand this application not only by the actual terms used, but also by the meaning implied by each term.

[0043] Figure 1 The structure diagram of a composite material repair device according to an embodiment of the utility model is shown. Figure 1 As shown in the figure, an aircraft engine composite material repair device 100 mainly includes an inflation component 101 , an inflation pump 102 and a pressure controller 103 .

[0044] The inflatable component 101 is arranged in the repairing area of ​​the composite material and is used to form a positive pressure on the composite material.

[0045] The air pump 102 is connected to the air-filling component 101. The air pump 102 is used to provide an air source to the air-filling component 101, and the air-filling component 101 provides positive pressure to the composite material through the received air source.

[0046] The pressure controller 103 is used to control the air pump 102 to supply air to the inflatable component 101. According to the characteristics of the composite material and the repair operation requirements, the pressure controller 103 adjusts the positive pressure of the inflatable component 101 on the composite material to meet the repair requirements.

[0047] The utility model provides an aircraft engine composite material repair device 100 that is suitable for situations where the space around the composite material is small. After the composite material component is repaired, an inflatable component 101 that meets the material repair device is placed above the composite material component in the repair area, and the inflatable component 101 is pre-inflated by an air pump 102. A certain positive pressure is formed on the surface of the composite material with the help of the surrounding space, so as to facilitate subsequent repair steps such as shaping of the composite material component.

[0048] Figure 2 The structure diagram of a composite material repair device according to an embodiment of the utility model is shown. Figure 2Preferably, the composite material repair device 100 further includes a pressure sensor 104. The pressure sensor 104 is used to detect a pressure signal of a positive pressure and feed the pressure signal back to the pressure controller 103. The pressure controller 103 controls the operation of the air pump 102 based on the pressure signal. According to the characteristics of the composite material and the requirements of the repair operation, the pressure controller 103 controls the air filling component 101 to provide a positive pressure suitable for the composite material.

[0049] Preferably, the pressure sensor 104 is disposed on the inflatable component 101 and is located on the bonding surface between the inflatable component 101 and the composite material, and the pressure sensor 104 obtains pressure information on the surface of the composite material.

[0050] Preferably, the composite material repair device 100 further includes a temperature controller 105 and a heating assembly 106. The heating assembly 106 is used to heat the temperature of the repair area, and the temperature controller 105 is used to control the operation of the heating assembly 106. According to the characteristics of the composite material and the requirements of the repair operation, the temperature controller 105 heats the repair area to a set temperature through the heating assembly 106.

[0051] Preferably, the composite material repair device 100 further includes a temperature sensor 107. The temperature sensor 107 is disposed in the repair area, and the temperature sensor 107 obtains a temperature signal and feeds it back to the temperature controller 105. The temperature controller 105 controls the heating assembly 106 based on the temperature signal to heat the repair area to a set temperature that meets the repair requirements.

[0052] Preferably, the composite material repair device 100 further includes a central controller 108. The central controller 108 is used to control the pressure controller 103 and the temperature controller 105 to coordinate the pressure and temperature of the composite material in the entire repair area and meet the repair operation requirements. The central controller 108 is also used to record the positive pressure change and temperature change data of the repair area.

[0053] Preferably, the central controller 108 includes a printing module 109, and the printing module 109 is connected to an external printer 110. The central controller 108 prints the positive pressure change and temperature change data of the repair area through the printing module 109 and the printer 110.

[0054] Preferably, the central controller 108 includes a display module 111, which is connected to an external display 112. The central controller 108 displays the positive pressure change and temperature change data of the repair area through the display module 111 and the display 112, so that the staff can directly observe the entire repair operation process.

[0055] Preferably, the composite material repairing device 100 further includes an input device 113, which is connected to the central controller 108, and the central controller 108 receives external control instructions through the input device 113. By way of example and not limitation, the input device 113 may be a keyboard and a mouse, or may be an input device 113 such as a mobile phone or a PAD.

[0056] The aircraft engine composite material repair device 100 provided by the utility model can meet the maintenance needs of engine composite material parts with relatively small surrounding space to remain in place. Its working principle is:

[0057] After the composite material component is repaired, the inflatable component 101 of the composite material repair device 100 is placed above the composite material component in the repair area;

[0058] The pressure controller 103 controls the inflatable component 101 to pre-inflate through the inflatable pump 102. The inflatable component 101 forms a certain positive pressure on the composite material by contacting the surface of the composite material with the help of the small space around it;

[0059] Simultaneously or subsequently to this process, a heating assembly 106, a temperature sensor 107, and a pressure sensor 104 are placed between the inflatable assembly 101 and the composite material;

[0060] Then, the heating component 106 is controllably heated by the temperature controller 105, and a controllable positive pressure is formed on the composite material by the air pump 102 and the air component 101;

[0061] The temperature and positive pressure are adjusted by the central controller 108 as maintenance needs change over time;

[0062] Complete repair work on composite components.

[0063] The utility model provides an aircraft engine composite material repair device with the following advantages:

[0064] 1. Form positive pressure through the inflatable component, and form a positive pressure that can be continuously regulated and monitored in the composite material repair area to meet the different fitting requirements in composite material repair;

[0065] 2. Precisely controlled heating can be applied to the composite material repair area to ensure the repair effect and quality of the composite material;

[0066] 3. The repair process can be monitored through the display;

[0067] 4. The central controller can record real-time operating parameters to facilitate analysis of maintenance results;

[0068] 5. Repairing composite parts in situ can simplify the repair process and increase the speed of repair.

[0069] It will be apparent to those skilled in the art that various modifications and variations can be made to the above exemplary embodiments of the present invention without departing from the spirit and scope of the present invention. Therefore, it is intended that the present invention covers modifications and variations of the present invention that fall within the scope of the appended claims and their equivalent technical solutions.

Claims

1. An aircraft engine composite material repair device, characterized in that: include: An inflatable component is disposed in a repair area of ​​the composite material, and the inflatable component is used to form a positive pressure on the composite material; An air pump connected to the inflatable component, and used to provide an air source to the inflatable component; A pressure controller is used to control the air pump to supply air to the inflatable component.

2. The aircraft engine composite material repair device according to claim 1, characterized in that: It also includes a pressure sensor for detecting the pressure signal of the positive pressure and feeding back the pressure signal to the pressure controller, and the pressure controller controls the operation of the inflation pump based on the pressure signal.

3. The aircraft engine composite material repair device according to claim 2, characterized in that: The pressure sensor is arranged on the inflatable component and is located on the bonding surface between the inflatable component and the composite material.

4. The aircraft engine composite material repair device according to claim 1, characterized in that: It also includes a temperature controller and a heating component, wherein the heating component is used to heat the temperature of the repair area, and the temperature controller is used to control the operation of the heating component.

5. The aircraft engine composite material repair device according to claim 4, characterized in that: It also includes a temperature sensor, which is arranged in the repair area. The temperature sensor obtains a temperature signal and feeds it back to the temperature controller. The temperature controller controls the operation of the heating component based on the temperature signal.

6. The aircraft engine composite material repair device according to claim 4, characterized in that: It also includes a central controller for controlling the operation of the pressure controller and the temperature controller, and the central controller records the positive pressure change and temperature change data of the repair area.

7. The aircraft engine composite material repair device according to claim 6, characterized in that: The central controller comprises a printing module, and the printing module is connected to an external printer. The central controller prints the positive pressure change and temperature change data of the repair area through the printing module and the printer.

8. The aircraft engine composite material repair device according to claim 6, characterized in that: The central controller comprises a display module, and the display module is connected to an external display. The central controller displays the positive pressure change and temperature change data of the repair area through the display module and the display.

9. The aircraft engine composite material repair device according to claim 6, characterized in that: It also includes an input device connected to the central controller, and the central controller receives external control instructions through the input device.

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