A real-time status monitoring system for gas turbines based on wireless signal transmission

Abstract

The present invention relates to the technical field of gas turbine operation monitoring, and specifically discloses a gas turbine real-time status monitoring system based on wireless signal transmission, comprising a turbine casing assembled to the outside of the gas turbine; the turbine casing comprises a first casing and a second casing connected to one side of the first casing, the first casing away from the second casing at one end thereof being connected to an arc-shaped sleeve which can be matched with a gas turbine fan cover; a monitoring box connected to the inner wall of the first casing is provided on the side of the arc-shaped sleeve close to the second casing; the present invention is used in conjunction with a gas turbine, the turbine casing is placed outside the gas turbine to replace the existing casing, the components laid inside the turbine casing do not affect the operation of the gas turbine, a fan duct can be provided between the turbine casing and the turbine, and existing monitoring components such as vibration sensors and pressure sensors on the turbine casing can also be connected to a monitoring main control module in the monitoring box, so that the monitoring main control module can receive and process data and then send them to an aircraft terminal control in a unified wireless manner.

Description

Technical Field

[0001] The invention relates to the technical field of gas turbine operation monitoring, in particular to a gas turbine real-time state monitoring system based on wireless signal transmission. Background Art

[0002] An aircraft engine includes core components such as a compressor, a combustion chamber, and a turbine. A turbofan engine is a type of aircraft engine. The area of ​​its first-stage fan blades is much larger than that of a turbojet engine. The core engine flow path through which part of the air passes is called the inner duct, and the outer part through which the air passes through the first-stage booster blades driven by the internal turbine is called the outer duct. The booster blades also have the function of compressing the air, and can eject part of the inhaled air through the engine's outer duct nozzle to provide direct thrust, or mix it with the inner high-temperature combustion gas to generate thrust together.

[0003] Fault diagnosis technology for aviation gas turbines is an important guarantee for the safe and economical operation of aviation engines, and is also one of the important indicators for measuring their advancement. Due to the complex structure of aviation engines, high system integration, harsh service environment, and variable working conditions, as well as the constraints of limited online testing conditions and difficulty in ensuring the amount of diagnostic information, fault diagnosis faces many challenges. Existing monitoring methods will deploy vibration sensors in the engine to monitor the rotation state of the gas turbine, but the monitoring of gas flow input and output still needs to be improved.

[0004] In view of the above problems, a gas turbine real-time status monitoring system based on wireless signal transmission is proposed. Summary of the invention

[0005] The object of the present invention is to provide a gas turbine real-time status monitoring system based on wireless signal transmission to solve the problems raised in the above background technology.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] A gas turbine real-time condition monitoring system based on wireless signal transmission includes a turbine casing mounted to the outside of the gas turbine;

[0008] The turbine housing comprises a first housing and a second housing connected to one side of the first housing, wherein one end of the first housing away from the second housing is connected to an arc-shaped sleeve that can cooperate with the gas turbine fan cover;

[0009] A monitoring box connected to the inner wall of the first shell is provided on one side of the arc sleeve close to the second shell, a monitoring main control module and a wireless communication module are provided in the monitoring box, a detachable arc sealing plate is connected to one side of the monitoring box, and a plurality of air flow monitoring mechanisms for monitoring the uniformity of the intake air are installed on the annular inner wall of the arc sleeve;

[0010] The inner wall of the first shell is connected to a protective cover for leading the temperature sensor and vibration sensor on the gas turbine to the monitoring box;

[0011] A heat monitoring mechanism for monitoring the heat at the tail nozzle of the gas turbine is disposed on a side of the second shell away from the first shell.

[0012] In an optional scheme: the air flow monitoring mechanism includes at least six groups of air guides, the air guides are fixedly connected to the annular inner wall of the arc sleeve, the air guide is provided with a slope at one end away from the second shell, an air guide pipe is installed in the air guide, both ends of the air guide pipe are connected to the outside, the axis of the air guide pipe is parallel to the axis of the first shell, and the air guide is provided with an audio probe installed on the arc sleeve on the side of the air guide close to the second shell, and the monitoring end of the audio probe corresponds to the air outlet end of the air guide pipe.

[0013] In an optional solution: a reinforcing rib and a positioning ring are connected between the first shell and the arc sleeve, an installation cavity is provided between the reinforcing rib and the positioning ring, one end of the audio probe extends into the installation cavity to be connected to an installation box, a main control board connected to the audio probe is provided in the installation box, and the mounting seat is fixedly connected to the annular wall of the arc sleeve on one side close to the first shell.

[0014] In an optional solution: a lead-in groove for leading out the lines on the installation box is provided on one side of the arc-shaped sleeve, and wire threading holes are provided on the arc-shaped walls on both sides of the monitoring box.

[0015] In an optional scheme: the inner wall of the monitoring box is provided with a guide groove that cooperates with the arc-shaped sealing plate, one end of the guide groove is provided with an installation port for connecting the guide groove with the outside, the monitoring box is provided with a positioning platform at one end close to the installation port, the arc-shaped sealing plate is connected to a side away from the inner cavity of the monitoring box with a number of evenly arranged heat conducting plates, the positioning platform is provided with a positioning hole, and the end of the arc-shaped sealing plate is provided with a fixing hole corresponding to the positioning hole.

[0016] In an optional solution: a plurality of connecting plates connected to the inner wall of the first shell are provided on the side of the monitoring box away from the arc-shaped sleeve, the plurality of connecting plates are arranged in a circular array, and air flow channels are provided between the connecting plates.

[0017] In an optional scheme: the protective cover includes a cover body and a side sealing plate, the cover body is fixedly connected to the inner wall of the first shell, the inner cavity of the cover body is provided with a circuit cavity, the cover body is provided with a limit strip connected to the inner wall of the first shell on the side close to the second shell, the side sealing plate is connected to the cover body and the limit strip, and the side sealing plate can be welded or connected to the limit strip by fasteners.

[0018] In an optional solution: both the side sealing plate and the arc-shaped plate of the cover body may be provided with mounting grooves for fixing the pressure sensor and the vibration sensor.

[0019] In an optional solution: the inner wall of the second shell is connected to a plurality of tail nozzle support plates, the plurality of tail nozzle support plates are arranged in a circular array, and the heat monitoring mechanism is installed on the tail nozzle support plates.

[0020] In an optional scheme: the temperature monitoring mechanism includes a tail nozzle holder, a thermocouple measuring end and a positioning frame connected to one side of the tail nozzle holder, the positioning frame is fixedly connected to the tail nozzle support plate, a thermocouple is installed in a chamber connected to the tail nozzle holder and the positioning frame, one end of the thermocouple is the thermocouple measuring end, and the thermocouple measuring end extends to the outside of the tail nozzle holder.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] The present invention is used in conjunction with a gas turbine and can be specifically configured according to the size of the gas turbine. The turbine casing is placed outside the gas turbine to replace the existing casing, and the components laid inside the casing do not affect the operation of the gas turbine. The turbine casing and the turbine can be connected to the fan outlet duct. The existing monitoring components such as vibration sensors and pressure sensors in the turbine can also be connected to the monitoring main control module in the monitoring box, so that the monitoring main control module can receive and process the data and then wirelessly send it to the aircraft terminal control.

[0023] The air volume monitoring mechanism arranged at the turbine air inlet end of the present invention can monitor the uniformity of the turbine air intake, and the temperature monitoring mechanism arranged at the turbine outlet end can monitor the heat uniformity of the gas at the turbine tail nozzle, so as to monitor whether the outlet high-temperature gas is uniform and monitor the stable operation of the turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the structure of the present invention.

[0025] Figure 2 It is a schematic structural diagram of the second shell in the present invention, which is away from one end of the first shell.

[0026] Figure 3 It is a structural schematic diagram of the heat monitoring mechanism in the present invention.

[0027] Figure 4 It is a schematic diagram of the structure inside the first shell in the present invention.

[0028] Figure 5 For the present invention Figure 4 Schematic diagram of the local split structure.

[0029] In the figure: 10, turbine casing; 11, first casing; 12, second casing; 13, arc sleeve; 14, tail nozzle holder; 15, thermocouple measuring end; 16, positioning frame; 17, tail nozzle support plate; 18, air guide; 19, air guide pipe; 20, acoustic probe; 21, reinforcing rib; 22, positioning ring; 23, lead groove; 24, monitoring box; 25, arc sealing plate; 26, connecting plate; 27, protective cover; 28, heat conducting plate; 29, guide groove; 30, cover body; 31, side sealing plate; 32, limit strip. DETAILED DESCRIPTION

[0030] See also Figure 1-Figure 5 , In this embodiment, a gas turbine real-time status monitoring system based on wireless signal transmission includes a turbine casing 10 assembled to the outside of the gas turbine;

[0031] The turbine casing 10 can be specifically configured according to the size of the gas turbine. The turbine casing is placed outside the gas turbine to replace the existing casing. The components laid inside the turbine casing do not affect the operation of the gas turbine. An external duct connected to the fan outlet can be provided between the turbine casing 10 and the turbine.

[0032] like Figure 1 As shown, the turbine housing 10 includes a first housing 11 and a second housing 12 connected to one side of the first housing 11, and an end of the first housing 11 away from the second housing 12 is connected to an arc-shaped sleeve 13 that can cooperate with a gas turbine fan cover;

[0033] like Figure 4 As shown, a monitoring box 24 connected to the inner wall of the first shell 11 is provided on the side of the arc sleeve 13 close to the second shell 12, and a monitoring main control module and a wireless communication module are provided in the monitoring box 24. A detachable arc-shaped sealing plate 25 is connected to one side of the monitoring box 24, and a plurality of air flow monitoring mechanisms for monitoring the uniformity of the intake air are installed on the annular inner wall of the arc sleeve 13;

[0034] The monitoring box 24 may also be provided with a power module, etc. The monitoring main control module may convert the received signal into digital form and process and package the received signal for transmission to the wireless communication module, and then wirelessly transmit the received signal to the aircraft terminal control.

[0035] like Figure 4 As shown, a protective cover 27 for connecting the pressure sensor and the vibration sensor on the gas turbine to the monitoring box 24 is connected to the inner wall of the first shell 11 .

[0036] A temperature monitoring mechanism for monitoring the temperature at the tail nozzle of the gas turbine is provided on the side of the second shell 12 away from the first shell 11; the temperature monitoring mechanism arranged at the turbine air outlet can monitor the uniformity of the gas temperature at the turbine tail nozzle to monitor whether the air outlet is uniform and monitor the stable operation of the turbine.

[0037] In this embodiment, the turbine casing 10 can be specifically set according to the size of the gas turbine, the arc sleeve 13 can be docked with the gas turbine fan cover, the fan is working, and the air flows in from one side of the arc sleeve 13. The wind volume monitoring mechanism monitors the uniformity of the intake air volume, and the temperature monitoring mechanism can monitor the uniformity of the heat of the gas at the turbine tail nozzle. The signals of the wind volume monitoring mechanism, the temperature monitoring mechanism, the pressure sensor, the vibration sensor and other components are transmitted to the monitoring main control module. The monitoring main control module can convert the received signals into digital signals, process them, and package them for transmission to the wireless communication module, and then send them to the aircraft terminal control in a unified wireless manner.

[0038] In one embodiment, Figure 4 As shown, the air volume monitoring mechanism includes at least six groups of air guides 18, the air guides 18 are fixedly connected to the annular inner wall of the arc sleeve 13, the air guide 18 is provided with a slope at one end away from the second shell 12 to reduce wind resistance, an air guide pipe 19 is installed in the air guide 18, both ends of the air guide pipe 19 are connected to the outside, the axis of the air guide pipe 19 is parallel to the axis of the first shell 11, and the air guide 18 is provided with an audio probe 20 installed on the arc sleeve 13 on the side close to the second shell 12, and the monitoring end of the audio probe 20 corresponds to the air outlet end of the air guide pipe 19;

[0039] The air introduced by the fan enters through the arc sleeve 13, the airflow passes through the air guide 18, and part of the airflow passes through the air guide pipe 19 to contact the audio probe 20. The audio probe 20 monitors the sound of the airflow. The range of the values ​​measured by the six groups of audio probes 20 is within the set range, and the air intake is uniform. When it exceeds the range, it can be combined with other monitoring components to further judge the working status of the turbine.

[0040] In one embodiment, Figure 4 As shown, a reinforcing rib 21 and a positioning ring 22 are connected between the first shell 11 and the arc sleeve 13, and an installation cavity is provided between the reinforcing rib 21 and the positioning ring 22. One end of the acoustic probe 20 extends into the installation cavity to connect to an installation box. A main control board connected to the acoustic probe 20 is provided in the installation box. The mounting seat is fixedly connected to the annular wall of the arc sleeve 13 on one side close to the first shell 11.

[0041] In one embodiment, Figure 4 As shown, one side of the arc sleeve 13 is provided with a lead-in groove 23 for leading out the line on the installation box, and the arc walls on both sides of the monitoring box 24 are provided with threading holes; the monitoring data of the audio probe 20 can be transmitted to the monitoring main control module.

[0042] In one embodiment, Figure 5As shown, the inner wall of the monitoring box 24 is provided with a guide groove 29 that cooperates with the arc-shaped sealing plate 25, and one end of the guide groove 29 is provided with a mounting port for connecting the guide groove 29 with the outside, and the monitoring box 24 is provided with a positioning platform at one end close to the mounting port, and the arc-shaped sealing plate 25 is connected to a side away from the inner cavity of the monitoring box 24 with a plurality of evenly arranged heat conducting plates 28, and the positioning platform is provided with a positioning hole, and the end of the arc-shaped sealing plate 25 is provided with a fixing hole corresponding to the positioning hole;

[0043] The arc-shaped sealing plate 25 can rotate around the axis of the first shell 11 . The arc-shaped sealing plate 25 is installed along the guide groove 29 to complete the fixation on the monitoring box 24 , thereby protecting the internal components of the monitoring box 24 .

[0044] In one embodiment, Figure 4 As shown, the monitoring box 24 is provided with a plurality of connecting plates 26 connected to the inner wall of the first shell 11 on the side away from the arc sleeve 13, and the plurality of connecting plates 26 are arranged in a circular array, and air flow channels are provided between the connecting plates 26; the connecting plates 26 can be used for connecting the outer side of the turbine with the inner side of the first shell 11; the air flow channel corresponds to the outer duct.

[0045] In one embodiment, Figure 2 As shown, the protective cover 27 includes a cover body 30 and a side sealing plate 31. The cover body 30 is fixedly connected to the inner wall of the first shell 11. The inner cavity of the cover body 30 is provided with a circuit cavity. The cover body 30 is provided with a limit strip 32 connected to the inner wall of the first shell 11 on the side close to the second shell 12. The side sealing plate 31 is connected to the cover body 30 and the limit strip 32. The side sealing plate 31 can be welded or connected to the limit strip 32 by fasteners; after the side sealing plate 31 is connected to the cover body 30, it is fixed at the limit strip 32 to protect the components in the circuit cavity.

[0046] In one embodiment, the side sealing plate 31 and the arc plate of the cover body 30 may be provided with mounting grooves for fixing the temperature sensor and the vibration sensor; the specific size is set according to actual needs.

[0047] In one embodiment, Figure 3 As shown, the inner wall of the second shell 12 is connected to a plurality of tail nozzle support plates 17, and the plurality of tail nozzle support plates 17 are arranged in a circular array, and the temperature monitoring mechanism is installed on the tail nozzle support plates 17; the tail nozzle support plates 17 are used to connect the outer wall of the tail nozzle and the inner wall of the second shell 12, and the space between the tail nozzle support plates 17 can be used for external duct airflow discharge.

[0048] In one embodiment, Figure 3As shown, the temperature monitoring mechanism includes a tail nozzle holder 14, a thermocouple measuring end 15 and a positioning frame 16 connected to one side of the tail nozzle holder 14, the positioning frame 16 is fixedly connected to the tail nozzle support plate 17, a thermocouple is installed in the chamber connected to the tail nozzle holder 14 and the positioning frame 16, one end of the thermocouple is the thermocouple measuring end 15, and the thermocouple measuring end 15 extends to the outside of the tail nozzle holder 14;

[0049] The positioning frame 16 is placed outside the tail nozzle, the tail nozzle holder 14 is placed at the jet end of the tail nozzle, and the thermocouple measuring end 15 measures the gas temperature and the uniformity of the temperature of each part to facilitate the subsequent acquisition of the uniformity of the exhaust gas.

[0050] The working principle of the present invention is: the turbine casing 10 can be specifically set according to the size of the gas turbine, the arc sleeve 13 can be matched with the gas turbine fan cover, the fan is working, the air flows in from one side of the arc sleeve 13, the air introduced by the fan enters through the arc sleeve 13, the airflow passes through the air guide 18, and part of the airflow passes through the air guide pipe 19 to contact the audio probe 20, the audio probe 20 monitors the sound of the airflow, the range of the values ​​measured by the six groups of audio probes 20 is within the set range, the thermocouple measuring end 15 measures the gas temperature, and measures the uniformity of the temperature of each part to facilitate the subsequent acquisition of the uniformity of the exhaust gas. When it exceeds the range, it can be combined with other monitoring components to further judge the working state of the turbine, and the signals of the flow monitoring mechanism, temperature monitoring mechanism, pressure sensor and vibration sensor and other components are transmitted to the monitoring main control module, the monitoring main control module can convert the received signal into analog-to-digital and process and package it and transmit it to the wireless communication module, and then send it to the aircraft terminal control in a unified wireless manner.

Claims

1. A gas turbine real-time status monitoring system based on wireless signal transmission, comprising a turbine casing (10) mounted to the outside of the gas turbine; Features: The turbine casing (10) comprises a first casing (11) and a second casing (12) connected to one side of the first casing (11); an end of the first casing (11) away from the second casing (12) is connected to an arc-shaped sleeve (13) that can cooperate with a gas turbine fan cover; A monitoring box (24) connected to the inner wall of the first shell (11) is provided on the side of the arc-shaped sleeve (13) close to the second shell (12), wherein a monitoring main control module and a wireless communication module are provided in the monitoring box (24), and a detachable arc-shaped sealing plate (25) is connected to one side of the monitoring box (24), and a plurality of air flow monitoring mechanisms for monitoring the uniformity of the intake air are installed on the annular inner wall of the arc-shaped sleeve (13); The inner wall of the first shell (11) is connected to a protective cover (27) for leading a pressure sensor and a vibration sensor on the gas turbine to a monitoring box (24); A temperature monitoring mechanism for monitoring the temperature at the tail nozzle of the gas turbine is provided on a side of the second shell (12) away from the first shell (11); The air flow monitoring mechanism comprises at least six groups of air guides (18), wherein the air guides (18) are fixedly connected to the annular inner wall of the arc sleeve (13), and a slope is provided at one end of the air guide (18) away from the second shell (12). An air guide pipe (19) is installed in the air guide (18), and both ends of the air guide pipe (19) are connected to the outside, and the axis of the air guide pipe (19) is parallel to the axis of the first shell (11). An audio probe (20) installed on the arc sleeve (13) is provided on the side of the air guide (18) close to the second shell (12), and the monitoring end of the audio probe (20) corresponds to the air outlet end of the air guide pipe (19).

2. A gas turbine real-time status monitoring system based on wireless signal transmission according to claim 1, characterized in that: A reinforcing rib (21) and a positioning ring (22) are connected between the first shell (11) and the arc-shaped sleeve (13); a mounting cavity is provided between the reinforcing rib (21) and the positioning ring (22); one end of the audio probe (20) extends into the mounting cavity to connect to a mounting box; a main control board connected to the audio probe (20) is provided in the mounting box; and a mounting seat is fixedly connected to an annular wall of the arc-shaped sleeve (13) on one side close to the first shell (11).

3. A gas turbine real-time status monitoring system based on wireless signal transmission according to claim 2, characterized in that: One side of the arc-shaped sleeve (13) is provided with a lead-in groove (23) for leading out the lines on the installation box, and the arc-shaped walls on both sides of the monitoring box (24) are provided with threading holes.

4. A gas turbine real-time status monitoring system based on wireless signal transmission according to claim 1, characterized in that: The inner wall of the monitoring box (24) is provided with a guide groove (29) that cooperates with the arc-shaped sealing plate (25); one end of the guide groove (29) is provided with an installation opening for connecting the guide groove (29) with the outside; the monitoring box (24) is provided with a positioning platform at one end close to the installation opening; the arc-shaped sealing plate (25) is connected to a side away from the inner cavity of the monitoring box (24) with a plurality of evenly arranged heat conducting plates (28); the positioning platform is provided with a positioning hole; and the end of the arc-shaped sealing plate (25) is provided with a fixing hole corresponding to the positioning hole.

5. A gas turbine real-time status monitoring system based on wireless signal transmission according to claim 1, characterized in that: A plurality of connecting plates (26) connected to the inner wall of the first shell (11) are provided on a side of the monitoring box (24) away from the arc-shaped sleeve (13); the connecting plates (26) are arranged in a circular array; and air flow channels are provided between the connecting plates (26).

6. A gas turbine real-time status monitoring system based on wireless signal transmission according to claim 1, characterized in that: The protective cover (27) comprises a cover body (30) and a side sealing plate (31); the cover body (30) is fixedly connected to the inner wall of the first shell (11); a circuit cavity is provided in the inner cavity of the cover body (30); a limit strip (32) connected to the inner wall of the first shell (11) is provided on the side of the cover body (30) close to the second shell (12); the side sealing plate (31) is connected to the cover body (30) and the limit strip (32); and the side sealing plate (31) can be welded or connected to the limit strip (32) by fasteners.

7. A gas turbine real-time status monitoring system based on wireless signal transmission according to claim 6, characterized in that: The side sealing plate (31) and the arc-shaped plate of the cover body (30) may be provided with mounting grooves for fixing the pressure sensor and the vibration sensor.

8. A gas turbine real-time status monitoring system based on wireless signal transmission according to claim 1, characterized in that: The inner wall of the second shell (12) is connected to a plurality of tail nozzle support plates (17), the plurality of tail nozzle support plates (17) are arranged in a circular array, and the temperature monitoring mechanism is mounted on the tail nozzle support plates (17).

9. A gas turbine real-time status monitoring system based on wireless signal transmission according to claim 8, characterized in that: The temperature monitoring mechanism comprises a tail nozzle holder (14), a thermocouple measuring end (15) and a positioning frame (16) connected to one side of the tail nozzle holder (14); the positioning frame (16) is fixedly connected to a tail nozzle support plate (17); a thermocouple is installed in a chamber connected to the tail nozzle holder (14) and the positioning frame (16); one end of the thermocouple is the thermocouple measuring end (15), and the thermocouple measuring end (15) extends to the outside of the tail nozzle holder (14).

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