Infrared thermometer applied to surface temperature measurement of aero-engine turbine blade

Abstract

The utility model discloses an infrared thermometer for measuring the surface temperature of a turbine blade of an aero-engine, and belongs to the field of infrared radiation temperature measurement. The device comprises an optical scanning probe, a movable control cabinet and a connecting cable. The optical scanning probe is specially used for collecting radiation signals on the surface of a turbine blade of an aero-engine and comprises a protective shell, a transmission structure, a driving motor and a supporting bottom plate, the protective shell is fixed to the transmission structure, the transmission structure is installed on the supporting bottom plate, the driving motor is fixed to the supporting bottom plate, and the driving motor is installed on the supporting bottom plate. The movable control cabinet comprises a cabinet main body, a driving module, an optical modulation module, a data acquisition module and an operation table, a motor connecting cable is used for connecting a motor and a cable of the driving module, and an optical signal transmission cable is used for transmitting an optical signal acquired by the optical scanning probe to the optical modulation module. According to the utility model, the temperature information acquisition of the high-temperature rotating turbine blade is realized through the cooperative work of all the components.

Description

Technical Field

[0001] The utility model patent belongs to the field of infrared radiation temperature measurement technology and provides an infrared thermometer for measuring the surface temperature field of an aircraft engine turbine rotor blade. Background Art

[0002] The temperature distribution state and temperature resistance limit of the surface of the turbine blade of an aircraft engine are factors that must be considered in the design and manufacture of turbine blades. Therefore, accurately and quickly obtaining the surface temperature information of the turbine blade under working conditions is conducive to improving the manufacturing and research and development level of my country's aircraft engines. Common temperature measurement methods such as thermocouples and temperature-indicating paints are contact-type, which will destroy the temperature distribution on the surface of the blade itself; in addition, high-speed rotating dynamic targets are also one of the factors that restrict the application of contact temperature measurement technologies such as thermocouples in blade temperature measurement. In order to solve the above problems, non-contact infrared radiation temperature measurement technology came into being. However, the existing infrared thermometers have limitations such as large equipment size, complex wiring, high cost, long measurement time, and narrow measurement range. They cannot quickly and effectively obtain the radiation signal of the turbine blade when the aircraft engine is in working state, so as to accurately obtain the surface temperature distribution of the turbine blade, which brings difficulties to the design and development of aircraft engine turbine blades. Therefore, there is an urgent need for an infrared thermometer with high maturity, easy operation, easy mobility, and the ability to quickly and accurately obtain the temperature signal of the turbine blade when the aircraft engine is in working state, so as to provide support for the research and development of aircraft engine turbine blades. Summary of the invention

[0003] The purpose of this utility model patent is to provide an infrared thermometer used for measuring the surface temperature field of aircraft engine turbine blades, so as to solve the problems of large equipment size, complex wiring and high cost when measuring the surface temperature information of turbine blades in the prior art.

[0004] In order to solve the above problems, the technical solution adopted by the utility model patent is: an infrared thermometer used for measuring the surface temperature field of aircraft engine turbine blades, including: an optical scanning probe, a movable control cabinet and a cable; the optical scanning probe and the movable control cabinet exchange data through the cable;

[0005] The optical scanning probe is used to extend into the interior of the aircraft engine to collect spectral information on the surface of the turbine blades; the optical scanning probe comprises: a protective housing, a transmission structure, an optical component, a supporting base plate and a driving motor, the optical component is installed in the protective housing, the protective housing will extend into the aircraft engine when collecting optical information on the surface of the turbine blades, the protective housing and the transmission structure are installed on the supporting base plate, the driving motor is installed on the transmission structure, the driving motor is used to drive the transmission structure, and the transmission structure is used to control the optical component;

[0006] The movable control cabinet includes: a cabinet body, a drive module, an optical modulation module, a data acquisition module and an operating table; the lower bottom surface of the cabinet body is provided with rollers; the operating table is located on the top of the cabinet body, and the drive module, the optical modulation module and the data acquisition module are located inside the cabinet body; the operating table includes an industrial display, an industrial display bracket, an industrial keyboard and an industrial keyboard bracket; the drive module is used to control the drive motor, and the optical information acquired by the optical scanning probe is transmitted to the optical modulation module through optical fiber, and the modulated signal is transmitted to the data acquisition module; the operating bracket is used for human-computer interaction.

[0007] Furthermore, the transmission structure of the optical scanning probe includes telescopic transmission and rotational transmission, and the driving motor includes: a telescopic driving motor and a rotational driving motor.

[0008] Furthermore, one end of the cable connected to the motor is connected to the motor, and the other end is connected to the aviation socket on the chassis panel of the drive module in the form of an aviation plug.

[0009] The beneficial effects of this utility model patent are: the data acquisition component (optical scanning probe) of the infrared thermometer is separated from the console component (movable control cabinet), and the user can remotely operate the data acquisition component, keeping the user away from the dangerous environment of high temperature and high pressure, thereby ensuring the user's own safety; in addition, the console component adopts a modular design, allowing the user to replace, upgrade or maintain various chassis modules without changing the overall cabinet, providing flexibility and maintainability for the cabinet maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] The utility model patent is further described in detail below based on the drawings and embodiments.

[0011] Figure 1 This is a system connection diagram of an infrared radiation thermometer used in the present utility model patent to measure the surface temperature field of an aircraft engine turbine blade.

[0012] Description of the main component symbols in the figure:

[0013] 1. Movable control cabinet; 2. Optical scanning probe; 3. Motor connecting cable; 4. Protective shell; 5. Transmission structure 1; 6. Support base plate; 7. Telescopic drive motor; 8. Scanning drive motor; 9. Operating table. DETAILED DESCRIPTION

[0014] In order to make the purpose, technical solution and advantages of the utility model patent more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0015] like Figure 1As shown, this embodiment provides a schematic diagram of the overall working connection of an infrared radiation thermometer for measuring the surface temperature of an aircraft engine turbine blade.

[0016] It is characterized in that it comprises an optical scanning probe 2, a movable control cabinet 1 and a connecting cable 3. The optical scanning probe is specially used for collecting radiation signals on the surface of the turbine blades of an aircraft engine, and comprises a protective shell 4, a transmission structure 5, drive motors 7 and 8 and a supporting base plate 6. The protective shell 4 is connected to the transmission structure 5 in a fixed manner, and the transmission structure 5 is installed on the supporting base plate 6. The drive motor 7 is fixed on the supporting base plate 6; the movable control cabinet 1 comprises a cabinet body, a drive module, an optical modulation module, a data acquisition module and an operating table 9, and the operating table 9 comprises an industrial display, an industrial display bracket, an industrial keyboard and an industrial keyboard bracket. The connecting cable comprises a motor connecting cable 3 and an optical signal transmission cable 15. The motor connecting cable 3 is used to connect the cables of the motors 7 and 8 and the drive module, and the optical signal transmission cable is used to transmit the optical signal collected by the optical scanning probe 2 to the optical modulation module.

[0017] The optical scanning probe 2 is characterized in that it includes a protective shell 4, a transmission structure 5 and drive motors 7 and 8. The protective shell 4 effectively protects the transmission structure 5. The transmission structure 5 uses an indirect connection structure to achieve telescopic and scanning movements. The telescopic drive motor 7 provides power for the telescopic movement of the optical scanning probe 2, and the scanning drive motor 8 provides power for the scanning movement of the optical scanning probe 2.

[0018] The transmission structure is characterized in that it includes two telescopic slides. The first telescopic slide 5 converts the rotational motion of the telescopic drive motor 7 into linear telescopic motion through belt drive, and the second telescopic slide is connected to the scanning drive motor 8 through a coupling to realize the scanning motion of the optical scanning probe 2.

[0019] The movable control cabinet 1 is characterized by comprising a cabinet body, a drive module, an optical modulation module, a data acquisition module and an operating table 9.

[0020] The operating table 9 is characterized in that it includes an industrial display, an industrial display bracket, a keyboard and a keyboard bracket. The industrial display bracket and the keyboard bracket are connected to the upper part of the cabinet body 9 by threaded fixing, and then the display and the keyboard are connected to the corresponding brackets.

[0021] The connecting cable is characterized in that it includes a motor connecting cable 3 and an optical signal transmission cable. One end of the motor connecting cable 3 is connected to the motors 7 and 8, and the other end is connected to the aviation socket on the chassis panel of the drive module in the form of an aviation plug, which has higher reliability.

Claims

1. An infrared thermometer used for measuring the surface temperature of aircraft engine turbine blades, characterized in that: The infrared thermometer comprises: an optical scanning probe, a movable control cabinet and a cable; the optical scanning probe and the movable control cabinet exchange data via the cable; The optical scanning probe is used to extend into the interior of the aircraft engine to collect spectral information on the surface of the turbine blades; the optical scanning probe comprises: a protective housing, a transmission structure, an optical component, a supporting base plate and a driving motor, the optical component is installed in the protective housing, the protective housing will extend into the aircraft engine when collecting optical information on the surface of the turbine blades, the protective housing and the transmission structure are installed on the supporting base plate, the driving motor is installed on the transmission structure, the driving motor is used to drive the transmission structure, and the transmission structure is used to control the optical component; The movable control cabinet includes: a cabinet body, a drive module, an optical modulation module, a data acquisition module and an operating table; the lower bottom surface of the cabinet body is provided with rollers; the operating table is located on the top of the cabinet body, and the drive module, the optical modulation module and the data acquisition module are located inside the cabinet body; the operating table includes an industrial display, an industrial display bracket, an industrial keyboard and an industrial keyboard bracket; the drive module is used to control the drive motor, and the optical information acquired by the optical scanning probe is transmitted to the optical modulation module through optical fiber, and the modulated signal is transmitted to the data acquisition module; the operating bracket is used for human-computer interaction.

2. An infrared thermometer for measuring the surface temperature of an aircraft engine turbine blade according to claim 1, characterized in that: The transmission structure of the optical scanning probe includes telescopic transmission and rotational transmission, and the driving motor includes: a telescopic driving motor and a rotational driving motor.

3. The infrared thermometer for measuring the surface temperature of an aircraft engine turbine blade according to claim 1, characterized in that: One end of the cable connected to the motor is connected to the motor, and the other end is connected to the aviation socket on the chassis panel of the drive module in the form of an aviation plug.

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