Aero-engine component heating device

Abstract

The utility model discloses an aero-engine component heating device which comprises a heating control system which comprises a main control module and a heating module. The main control module comprises a controller, a relay, a temperature setting element and a display module, and the relay, the temperature setting element and the display module are respectively connected with the controller; the heating module comprises a heating element, a first temperature sensor, a temperature control element and a second temperature sensor, the heating element is connected with the relay, the first temperature sensor is connected with the controller, the temperature control element is connected with the controller, and the second temperature sensor is connected with the controller. And the second temperature sensor is arranged in the heating element. According to the embodiment of the utility model, manpower and material resources are saved, the reliability of heating work is improved, and the damage risk of a heated part is reduced, so that the aviation safety is further guaranteed.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engine installation, in particular to an aviation engine component heating device. Background Art

[0002] During the installation of aircraft engines (such as CFM56-5B), components such as the rear air intake cone need to be installed. This requires that the front flange edge of the rear air intake cone be heated to 80 degrees Celsius and the rear flange edge be heated to 60 degrees Celsius before installation to prevent surface wear and improper installation.

[0003] The existing heating method is to manually use a hot air gun in combination with a thermometer to measure the temperature. One person needs to hold the hot air gun to heat, and another person needs to hold the thermometer to measure the temperature. One person also needs to control the heated component when the component is out of position. The cooperation of multiple people is required, which is inefficient. The diameter of the air outlet of the hot air gun is only 1.5 cm. Uneven heating will occur during the operation, and the heated part will quickly return to normal temperature, resulting in the final heating effect being seriously substandard. At the same time, errors will occur in the thermometer measurement, making it difficult to effectively verify the work results due to lack of basis. In addition, human factors have a serious impact. When workers have a large workload, they will inevitably mix in human factors, resulting in a decline in work standards and low work reliability. There is a greater risk of component damage and even endangering aviation safety. Utility Model Content

[0004] The technical problem to be solved by the utility model is to provide an aircraft engine component heating device, which can operate the heating process by one person, improve work efficiency, shorten the heating time, improve the accuracy of the heating temperature, and reduce the impact of human factors on the work.

[0005] In order to solve the above technical problems, the utility model provides an aircraft engine component heating device, including a heating control system, wherein the heating control system includes a main control module and a heating module;

[0006] The main control module includes a controller, a relay, a temperature setting element and a display module, and the relay, the temperature setting element and the display module are respectively connected to the controller;

[0007] The heating module includes a heating element, a first temperature sensor, a temperature control element and a second temperature sensor. The heating element is connected to the relay, the first temperature sensor is connected to the controller, the temperature control element is connected to the controller, the second temperature sensor is connected to the controller, and the second temperature sensor is built into the heating element.

[0008] Optionally, the aircraft engine component heating device includes three independent heating control systems.

[0009] Optionally, each heating element of the heating control system is connected in a ring shape.

[0010] Optionally, each of the heating elements is a silica gel heating plate, and a heating wire is arranged in the silica gel heating plate.

[0011] Optionally, the temperature control element includes a variable resistance temperature knob.

[0012] Optionally, the controller includes an MCS-51 series single chip microcomputer;

[0013] Optionally, the MCS-51 series single chip microcomputer adopts STC89C52 chip.

[0014] Optionally, both the first temperature sensor and the second temperature sensor are DS18B20 temperature sensors.

[0015] Optionally, the display module includes an LCD1602 liquid crystal screen.

[0016] Optionally, the temperature setting element includes a temperature button.

[0017] Compared to the prior art, the present invention provides an aircraft engine component heating device, comprising a heating control system comprising a main control module and a heating module. The main control module comprises a controller, a relay, a temperature setting element, and a display module, the relay, temperature setting element, and display module being respectively connected to the controller. The heating module comprises a heating element, a first temperature sensor, a temperature control element, and a second temperature sensor, the heating element being connected to the relay, the first temperature sensor being connected to the controller, the temperature control element being connected to the controller, and the second temperature sensor being connected to the controller, the second temperature sensor being built into the heating element. The present invention can be applied to heating the flange edge of an aircraft engine's rear intake straightener. It utilizes a single-chip microcomputer control system, can preset a temperature value, and automatically stops when the actual temperature reaches the target temperature. It utilizes a silicone heating plate designed to suit the heated component, effectively achieving uniform heating. It utilizes a DS18B20 temperature sensor for multi-position temperature measurement, resulting in more accurate results. The integrated heating and monitoring system facilitates operation, saving manpower and material resources while improving work efficiency, enhancing heating reliability, and reducing the risk of damage to the heated component, thereby further ensuring aviation safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic diagram of the structural connection of an aircraft engine component heating device provided by an embodiment of the present utility model;

[0019] Figure 2 This is another structural connection diagram of an aircraft engine component heating device provided by an embodiment of the present utility model. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0021] See also Figure 1 , Figure 1 This is a schematic diagram of the structural connection of an aircraft engine component heating device provided by an embodiment of the present utility model. The aircraft engine component heating device includes a heating control system, which includes a main control module 1 and a heating module 2;

[0022] The main control module 1 includes a controller 101, a relay 102, a temperature setting element 103 and a display module 104, and the relay 102, the temperature setting element 103 and the display module 104 are respectively connected to the controller 101;

[0023] The heating module 2 includes a heating element 201, a first temperature sensor 202, a temperature control element 203 and a second temperature sensor 204. The heating element 201 is connected to the relay 102, the first temperature sensor 202 is connected to the controller 101, the temperature control element 203 is connected to the controller 101, the second temperature sensor 204 is connected to the controller 101, and the second temperature sensor 204 is arranged in the heating element 201.

[0024] For example, when in use, the heating module 2 is first partially fixed to the flange edge surface of the engine fairing cone, and the heating element 201 is placed on the outside of the flange edge of the fairing cone, and the first temperature sensor 202 is placed on the inside of the flange edge of the fairing cone. The power is turned on (powered by a 220V power supply), and the flange edge of the fairing cone is heated to the target degree Celsius according to the working target temperature. Then, the temperature control element 203 is adjusted to the target degree Celsius indication range to ensure that the heating element works within this range, and the start temperature degree Celsius and the stop temperature degree Celsius are set by the temperature setting element 103. The heating device can automatically start working and automatically stop when the first temperature sensor 202 recognizes that the flange edge of the engine fairing cone reaches the target degree Celsius.

[0025] In an optional embodiment, the aircraft engine component heating device includes three independent heating control systems.

[0026] It is worth noting that it contains three independent heating control systems, each of which can independently control the temperature of a specific part. At the same time, when these systems are independent of each other, they can be selectively turned on or off according to different needs. This not only improves the reliability of the device, but also can be flexibly adjusted according to different environmental conditions and operating conditions, thereby achieving the best heating effect.

[0027] In an optional embodiment, the aircraft engine component heating device uses a single-chip microcomputer as a controller, and the single-chip microcomputer is used to collect, process, and convert temperature signals, and output relay control signals and temperature information of the display module. The temperature is set by a temperature setting element, and three sets (6) of temperature sensors are used to collect temperature signals of the heating elements and the heated components of the aircraft engine at multiple positions. The operation of the heating elements is controlled by relays, and finally the real-time temperature value is displayed by the display module.

[0028] In an optional embodiment, the controller includes an MCS-51 series single-chip microcomputer, and the MCS-51 series single-chip microcomputer uses an STC89C52 chip.

[0029] It's worth noting that the MCS-51 series microcontrollers were chosen for their high integration, compact size, high reliability, powerful control capabilities, low voltage, low power consumption, ease of production for portable products, and ease of expansion. The STC89C52 chip, used as the hardware core, boasts 8KB of internal ROM storage, 512 bytes of data storage, and 8KB of EEPROM storage, making it fully compatible with the MCS-51 series. The STC89C52 can also be downloaded via the serial port, making it simple, convenient, and inexpensive.

[0030] In an optional embodiment, each heating element of the heating control system is connected in a ring shape, and each heating element is a silicone heating plate, and a heating wire is arranged in the silicone heating plate.

[0031] It is worth noting that, in specific implementation, a silicone heating plate can be designed according to the appearance of the heated parts of the aircraft engine to achieve a full-area fitting effect and uniform heating. For example, in order to make the heating element fit the flange edge of the aircraft engine straightening cone (such as the front and rear flange edges of the rear intake straightening cone of the CFM56-5B aircraft engine are both ring-shaped, with a maximum outer diameter of 46 cm and a minimum inner diameter of 28 cm), each heating element can be connected together to form a circular silicone heating plate. If the processing is difficult during implementation, it can also be connected by Velcro or other means. Other ways of connection may require leaving some elements without heating wire structures on the edge of each part of the heating element. Among them, the heating wires of the entire ring are divided into three equal parts, and the heating elements of each part are controlled by an independent circuit.

[0032] In an optional embodiment, the temperature control element includes a variable resistance temperature knob.

[0033] In an optional embodiment, the temperature setting element includes a temperature button.

[0034] It should be noted that the temperature control element in the heating module and the temperature setting element in the main control module are two independent temperature control facilities. The temperature control element, i.e., the variable resistance temperature knob, controls the operating temperature of the heating element, keeping it operating within a stable temperature range and preventing it from overheating. The temperature setting element, i.e., the temperature button sets the target temperature of the heated component and is used to automatically start and stop the relay. When the temperature is below the set value, the relay operates, and when the temperature reaches the set value, the relay stops. The target temperature can be achieved within a range of 0-100 degrees Celsius with an accuracy of 0.1. The specific temperature value can be freely set according to the heating requirements.

[0035] In an optional embodiment, the first temperature sensor and the second temperature sensor are DS18B20 temperature sensors.

[0036] It should be noted that the first temperature sensor in the heating module is used to monitor the temperature of the heated component, namely the flange edge of the aircraft engine rectifier cone, and can also transmit relay control signals back to the controller to manage the heating operation of the heated component. The heating module also has an independent temperature control element (variable resistor temperature knob) and a second temperature sensor (built into the silicone heating plate). The second temperature sensor monitors the temperature of the heating element, and the variable resistor temperature knob controls it to achieve constant temperature heating of the heating element. The entire heating device uses three sets (six) of DS18B20 temperature sensors: three first temperature sensors and three second temperature sensors.

[0037] It is worth noting that the temperature measurement in the heating device of the aircraft engine component provided by the utility model can also consider using devices such as thermistors to utilize their temperature sensing effect, collect the voltage or current that changes with the measured temperature, perform A / D conversion, and then process the data by the single-chip microcomputer and apply it to the display circuit. However, this design requires the use of an A / D conversion circuit, and the temperature sensing circuit is relatively cumbersome. Therefore, the embodiment of the utility model uses a DS18B20 sensor, which can more easily directly read the measured temperature value and perform conversion.

[0038] In an optional embodiment, the display module includes an LCD1602 liquid crystal screen.

[0039] It's worth noting that the LCD1602 screen is a display module specifically designed for displaying letters, numbers, and symbols. It consists of several 5x7 or 5x11 dot matrix character positions, each capable of displaying a single character. Each position is separated by a dot pitch, and each row also has a spacing between them, serving as both character and line spacing. Its advantages include low power consumption, a compact size, rich display content, and an ultra-thin and lightweight design. The aircraft engine component heating device of this embodiment can be composed of three LCD1602 screens, each used to display the set and real-time temperatures of three heating control systems, facilitating manual monitoring and data recording, ensuring traceable work results.

[0040] See also Figure 2 , Figure 2 This is another structural connection diagram of an aircraft engine component heating device provided by an embodiment of the present utility model. Figure 2 As shown, the aircraft engine component heating device includes at least three independent heating control systems (A, B, C), each heating control system includes a main control module 1 and a heating module 2; the main control module 1 includes a controller ( Figure 2 Not shown), relay ( Figure 2 Not shown), the temperature setting element 103 is a temperature button, the display module 104 is an LCD1602 liquid crystal screen, the relay, the temperature button and the LCD1602 liquid crystal screen are connected to the controller ( Figure 2 (not shown); in the heating module 2, the heating element 201 is a silicone heating plate, the first temperature sensor 202 is a DS18B20 temperature sensor, the temperature control element 203 is a variable resistance temperature knob, and the second temperature sensor 204 is a DS18B20 temperature sensor; wherein, the silicone heating plate is connected to the relay 102 via a wire, the first temperature sensor 202 is connected to the controller 101 via a wire, the temperature rotary button is connected to the controller 101, and the second temperature sensor 204 is connected to the controller 101 via a wire, and is arranged in the silicone heating plate.

[0041] For example, during use, the entire annular silicone heating plate is first fixed to the flange surface of the aircraft engine's spur cone. The silicone heating plate is placed outside the spur cone flange, and three DS18B20 temperature sensors (first temperature sensor 202) are placed inside the spur cone flange. Power supply 3 (powered by a 220V power supply) is connected. The spur cone flange is heated to a specified temperature (e.g., 80 degrees Celsius) based on the target operating temperature. The variable resistor temperature knobs (A, B, and C) are then adjusted to the 80-degree Celsius indication range to ensure the silicone heating plate operates within this range. The start temperature is set to 79 degrees Celsius and the stop temperature is set to 80 degrees Celsius using the temperature buttons. The heating device automatically begins operating and stops when the three DS18B20 temperature sensors (first temperature sensor 202) detect that the temperature of the spur cone flange has reached 80 degrees Celsius. During this process, the three second temperature sensors 204 also monitor the temperature of the silicone heating plate to prevent it from overheating.

[0042] In summary, the present invention provides an aircraft engine component heating device, comprising a heating control system, the heating control system comprising a main control module and a heating module; the main control module comprising a controller, a relay, a temperature setting element, and a display module, the relay, temperature setting element, and display module respectively connected to the controller; the heating module comprising a heating element, a first temperature sensor, a temperature control element, and a second temperature sensor, the heating element being connected to the relay, the first temperature sensor being connected to the controller, the temperature control element being connected to the controller, and the second temperature sensor being connected to the controller, the second temperature sensor being built into the heating element. The present invention can be applied to the flange edge heating of aircraft engine intake straighteners. It utilizes a single-chip microcomputer control system, can preset a temperature value, and automatically stops when the actual temperature reaches the target temperature. It utilizes a silicone heating plate designed to suit the heated component, effectively achieving uniform heating. It utilizes a DS18B20 temperature sensor for multi-position temperature measurement, resulting in more accurate results. It integrates heating and monitoring functions into one unit, making operation simple, saving manpower and material resources, and improving work efficiency, enhancing the reliability of heating operations, and reducing the risk of damage to heated components, thereby further ensuring aviation safety.

[0043] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications are also considered to be within the scope of protection of the present invention.

Claims

1. An aircraft engine component heating device, characterized in that: A heating control system is included, wherein the heating control system includes a main control module and a heating module; The main control module includes a controller, a relay, a temperature setting element and a display module, and the relay, the temperature setting element and the display module are respectively connected to the controller; The heating module includes a heating element, a first temperature sensor, a temperature control element and a second temperature sensor. The heating element is connected to the relay, the first temperature sensor is connected to the controller, the temperature control element is connected to the controller, the second temperature sensor is connected to the controller, and the second temperature sensor is built into the heating element.

2. The aircraft engine component heating device according to claim 1, characterized in that: The aviation engine component heating device includes three independent heating control systems.

3. The aircraft engine component heating device according to claim 2, characterized in that: The heating elements of each heating control system are connected in a ring shape.

4. The aircraft engine component heating device according to claim 3, characterized in that: Each of the heating elements is a silica gel heating plate, and a heating wire is arranged in the silica gel heating plate.

5. The aircraft engine component heating device according to claim 2, wherein: The temperature control element includes a variable resistance temperature knob.

6. The aircraft engine component heating device according to claim 2, characterized in that: The controller includes an MCS-51 series single chip microcomputer.

7. The aircraft engine component heating device according to claim 6, characterized in that: The MCS-51 series single chip microcomputer adopts STC89C52 chip.

8. The aircraft engine component heating device according to claim 2, wherein: The first temperature sensor and the second temperature sensor both adopt DS18B20 temperature sensors.

9. The aircraft engine component heating device according to claim 2, wherein: The display module includes an LCD1602 liquid crystal screen.

10. The aircraft engine component heating device according to claim 2, wherein: The temperature setting element includes a temperature button.

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