Gas thermal corrosion detection device for metal material protective coating

Abstract

The utility model discloses a fuel gas hot corrosion detection device for a metal material protective coating. The fuel gas hot corrosion detection device comprises an oil path unit, a gas path unit, a liquid path unit, a combustion mechanism, a heating mechanism and a data acquisition and control unit, the oil path unit is connected with the kerosene channel, the gas path unit comprises an air unit and an oxygen unit, and the air unit is connected with the cooling channel; the oxygen unit is connected with the oxygen channel; the liquid path unit is connected with the carrier gas channel; and the data acquisition and control unit is connected with the oil path unit, the gas path unit, the liquid path unit, the ignition needle and the tubular thermal shock furnace, and is used for realizing on-off control and flow control of the oil path unit, the gas path unit and the liquid path unit, action control of the ignition needle and temperature control of the heating mechanism, and acquiring data. According to the utility model, the gas thermal environment can be more accurately simulated, the corrosion process can be monitored in real time, the corrosion rate can be quantified, and the corrosion resistance of different protective coatings under the complex gas thermal condition can be effectively evaluated.

Description

Technical Field

[0001] The utility model relates to a gas thermal corrosion detection device for a metal material protective coating. Background Art

[0002] Gas thermal corrosion is a complex corrosion phenomenon suffered by metal materials in high-temperature gas environments, especially in fields such as engine blades, gas turbines, internal combustion engines, and petrochemical equipment. This type of corrosion usually involves the interaction of active components such as oxygen, sulfides, and nitrides with metal materials and their protective coatings, resulting in the degradation of material structure, greatly shortening the service life of equipment components, and affecting the reliability and economy of the system.

[0003] Most of the existing gas thermal corrosion detection technologies and devices focus on simulating actual working conditions under laboratory conditions. However, in practical applications, these methods are often difficult to accurately reproduce the complexity and dynamic change characteristics of the actual service environment, such as temperature fluctuations, changes in gas composition, stress corrosion effects, etc. In addition, some existing detection devices may have problems such as low detection accuracy, long experimental cycle, and insufficient automation of data collection and analysis.

[0004] Therefore, there is an urgent need to develop a new gas thermal corrosion detection device and method for metal material protective coatings to more accurately simulate the gas thermal environment, monitor the corrosion process in real time, quantify the corrosion rate, and effectively evaluate the corrosion resistance of different protective coatings under complex gas thermal conditions, providing a scientific basis for improving material design and optimizing protection strategies. Utility Model Content

[0005] In order to solve the above technical problems, the utility model provides a gas thermal corrosion detection device for metal material protective coatings which can monitor the corrosion process in real time, quantify the corrosion rate, and effectively evaluate the corrosion resistance of different protective coatings under complex gas thermal conditions.

[0006] The technical solution of the utility model to solve the above technical problems is: a gas thermal corrosion detection device for metal material protective coating, comprising an oil circuit unit, a gas circuit unit, a liquid circuit unit, a combustion mechanism, a heating mechanism and a data acquisition and control unit;

[0007] The combustion mechanism comprises a front shell, an inner core, a rear shell and an ignition needle; the rear end of the front shell and the front end of the rear shell are connected to form a shell, an inner core installation cavity is provided in the shell, and an inner core is installed in the inner core installation cavity; a seawater hole is provided at the center of the end surface of the inner core, and the seawater hole penetrates the inner core, and an oxygen hole is also provided on the inner core, and the oxygen hole is connected to the ignition chamber of the front shell, and a fuel hole connected to the oxygen hole is provided on the side wall of the inner core;

[0008] A carrier gas channel is provided at the rear end center of the rear shell; an oxygen channel connected to the oxygen hole of the inner core, a kerosene channel connected to the fuel hole and a cooling channel are also provided on the rear shell; the cooling channel is connected to the cavity between the front of the rear shell and the inner core; three sets of sealing rings are provided between the inner core and the inner core installation cavity, one set of sealing rings is provided on both sides of the outlet of the oxygen channel, and one set of sealing rings is provided on both sides of the outlet of the kerosene channel; an ignition needle is installed on the front shell, and the ignition needle is located in the combustion chamber;

[0009] The heating mechanism comprises a tubular thermal shock furnace and a fixture, wherein a corundum tube and a fixture are arranged in the tubular thermal shock furnace, and the corundum tube is connected with the fixture and the combustion chamber;

[0010] The oil circuit unit is connected to the kerosene channel, the gas circuit unit includes an air unit and an oxygen unit, the air unit is connected to the cooling channel; the oxygen unit is connected to the oxygen channel; the liquid circuit unit is connected to the carrier gas channel;

[0011] The data acquisition and control unit is respectively connected to the oil circuit unit, the gas circuit unit, the liquid circuit unit, the ignition needle and the tubular thermal shock furnace, and is used to realize on-off control and flow control of the oil circuit unit, the gas circuit unit and the liquid circuit unit, as well as the action control of the ignition needle and the temperature control of the heating mechanism, and to collect data.

[0012] Furthermore, the oil circuit unit includes an aviation kerosene tank, a filter, an oil pump, a flow meter I and a pressure transmitter I, and the aviation kerosene tank, the filter, the oil pump, the flow meter I and the pressure transmitter I are connected in sequence through a kerosene pipe; the output end of the pressure transmitter I is connected to the kerosene inlet hole of the combustion mechanism through a pipeline; the flow meter and the pressure transmitter I are respectively connected to the data acquisition and control unit.

[0013] Furthermore, the fixture is connected to the transmission output shaft through a rotating shaft, and the transmission input shaft is connected to the motor; the motor is installed on the motor seat, and the motor seat is installed with the top of the piston rod of the longitudinal cylinder; the output shaft passes through the furnace door of the tubular thermal shock furnace, and a transverse cylinder is fixedly installed at the bottom of the tubular thermal shock furnace, and a door panel is installed on the piston rod of the transverse cylinder, and the door panel can seal the furnace door when pushed by the transverse cylinder; the motor is connected to the data acquisition and control unit.

[0014] Furthermore, the air unit includes a compressed air tank, a carrier gas circuit, a cooling circuit and a cylinder circuit, and the carrier gas circuit includes a solenoid valve I, a pressure regulating valve I and a flow meter II connected in sequence through a pipeline; the inlet of the solenoid valve I is connected to the compressed air tank, the outlet of the flow meter II is connected to the carrier gas main circuit, and the carrier gas main circuit is connected to the carrier gas channel; the solenoid valve I is connected to the data acquisition and control unit;

[0015] The cooling circuit includes an electric regulating valve, a solenoid valve II, a pressure regulating valve II, a flow meter III and a pressure transmitter II connected in sequence through pipelines. The inlet of the electric regulating valve is connected to the compressed air tank, and the outlet of the pressure transmitter II is connected to the cooling channel; the electric regulating valve, the solenoid valve II and the flow meter III are connected to the data acquisition and control unit;

[0016] The cylinder circuit includes a cylinder main circuit connected to a compressed air tank and a cylinder branch I and a cylinder branch II. The cylinder branch I and the cylinder branch II are connected to the cylinder main circuit; the cylinder branch I is connected to the P port of a two-position five-way solenoid valve I, and a pressure regulating valve III is provided on the cylinder branch I; the A port and the B port of the two-position five-way solenoid valve I are respectively connected to the two air ports of the horizontal cylinder; the cylinder branch II is connected to the P port of the two-position five-way solenoid valve II, and a pressure regulating valve IV is provided on the cylinder branch I; the A port and the B port of the two-position five-way solenoid valve II are respectively connected to the two air ports of the longitudinal cylinder; the two-position five-way solenoid valve I and the two-position five-way solenoid valve II are respectively connected to the data acquisition and control unit.

[0017] Furthermore, the oxygen unit includes a liquid oxygen tank, a solenoid valve III, a mass controller and a pressure transmitter III. The liquid oxygen tank, the solenoid valve III, the pressure transmitter III and the mass controller are connected in sequence through an oxygen pipe, and the outlet of the mass controller is connected to the oxygen channel; the solenoid valve III, the pressure transmitter III and the mass controller are respectively connected to the data acquisition and control unit.

[0018] Furthermore, the liquid circuit unit includes a magnetic stirring cup and a peristaltic pump. Artificial seawater is provided in the magnetic stirring cup and stirring is maintained during operation. The magnetic stirring cup is connected to the inlet of the peristaltic pump through a pipeline, and the outlet of the peristaltic pump is connected to the carrier gas main circuit through a liquid pipeline.

[0019] Furthermore, the data acquisition and control unit includes a PLC unit and an industrial computer unit.

[0020] Furthermore, the number of sealing rings in each group of sealing rings is two.

[0021] Compared with the prior art, the beneficial effects of the present invention are: the present invention can more accurately simulate the gas thermal environment, monitor the corrosion process in real time, quantify the corrosion rate, and effectively evaluate the corrosion resistance of different protective coatings under complex gas thermal conditions, providing a scientific basis for improving material design and optimizing processes. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural diagram of the utility model.

[0023] Figure 2 It is a structural schematic diagram of the combustion mechanism of the utility model.

[0024] In the figure: 1- aviation kerosene tank, 2- filter, 3- oil pump, 4- flow meter I, 5- pressure transmitter I, 101- kerosene pipe, 6- oxygen tank, 7- solenoid valve III, 8- pressure transmitter III, 9- quality controller, 102- oxygen pipe, 10- compressed air tank, 11- electric regulating valve, 12- solenoid valve II, 13- pressure regulating valve II, 14- flow meter III, 15- pressure transmitter II, 103- cooling circuit, 16- solenoid valve I, 17- pressure regulating valve I, 18- flow meter II, 104- carrier gas circuit, 23- magnetic stirring cup, 24- peristaltic pump, 105- liquid pipeline, 106- carrier gas main circuit, 107- cylinder main circuit, 108- cylinder branch I, 109- cylinder branch II, 19- Pressure regulating valve III, 20-two-position five-way solenoid valve I, 21-pressure regulating valve IV, 22-two-position five-way solenoid valve II, 200-combustion mechanism, 300-tubular thermal shock furnace, 301-corundum tube, 302-clamp, 303-horizontal cylinder, 304-vertical cylinder, 305-motor, 201-rear shell, 202-ignition needle, 203-front shell, 204-inner core, 205-O-type sealing ring, 206-combustion chamber, 2011-kerosene channel, 2012-oxygen channel, 2013-carrier gas channel, 2014-cooling channel, 2041-fuel hole, 2042-oxygen hole, 2043-seawater hole, 2044-cooling channel II, 207-sealing ring, 400-data acquisition and control unit. DETAILED DESCRIPTION

[0025] The utility model is further described below in conjunction with the accompanying drawings.

[0026] like Figure 1 As shown, the utility model includes an oil circuit unit, a gas circuit unit, a liquid circuit unit, a combustion mechanism, a heating mechanism and a data acquisition and control unit.

[0027] like Figure 2 As shown, the combustion mechanism comprises a front shell 203, an inner core 204, a rear shell 201 and an ignition needle 202. The rear end of the front shell 203 and the front end of the rear shell 201 are connected to form a shell, and the front shell 203 and the rear shell 201 are fastened with bolts. An O-ring 205 is arranged between the rear end of the front shell 203 and the front end of the rear shell 201. An inner core installation cavity is arranged in the shell, and the inner core 204 is installed in the inner core installation cavity. A seawater hole 2043 is arranged at the center of the end face of the inner core 204, and the seawater hole 2043 penetrates the inner core 204. An oxygen hole 2042 is also arranged on the inner core 204, and the oxygen hole 2042 is connected to the ignition chamber of the front shell. A fuel hole 2041 connected to the oxygen hole is arranged on the side wall of the inner core 204; an annular gap is formed between the front part of the inner core 204 and the front part of the rear shell, and the annular gap is a cooling channel II 2044.

[0028] A carrier gas channel 2013 is provided at the rear center of the rear shell 201; an oxygen channel 2012 connected to the oxygen hole of the inner core, a kerosene channel 2011 connected to the fuel hole, and a cooling channel 2014 are also provided on the rear shell 201. The cooling channel 2014 is connected to the cooling channel II 2044. Three groups of sealing rings 207 are provided between the inner core 204 and the inner core installation cavity, and the number of sealing rings in each group of sealing rings is two. A group of sealing rings 207 is provided on both sides of the outlet of the oxygen channel 2012, and a group of sealing rings 207 is provided on both sides of the outlet of the kerosene channel 2011. An ignition needle 202 is installed on the front shell 203, and the ignition needle 202 is located in the combustion chamber 206.

[0029] The heating mechanism includes a tubular thermal shock furnace 300, a corundum tube 301 and a fixture 302. The corundum tube 301 and the fixture 302 are arranged in the tubular thermal shock furnace 300. The corundum tube 301 is connected to the combustion chamber 206 and the fixture 302. The fixture 302 is connected to the transmission output shaft through a rotating shaft, and the transmission input shaft is connected to the motor 305; the motor 305 is installed on the motor seat, and the motor seat is installed with the top of the piston rod of the longitudinal cylinder 304. The output shaft passes through the furnace door of the tubular thermal shock furnace 300, and a transverse cylinder 303 is fixedly installed at the bottom of the tubular thermal shock furnace 300. A door plate is installed on the piston rod of the transverse cylinder 303, and the door plate can seal the furnace door under the push of the transverse cylinder 303. The motor 305 is connected to the data acquisition and control unit 400.

[0030] The aviation kerosene tank 1, the filter 2, the oil pump 3, the flow meter 14 and the pressure transmitter 15 in the oil circuit unit are connected in sequence through the kerosene pipe 101 and then connected to the kerosene channel 2011. The oil pump 3 adopts a magnetic gear pump, and the flow meter 14 adopts a float flowmeter. The flow meter 14 and the pressure transmitter 15 are respectively connected to the data acquisition and control unit. After the aviation kerosene 1 in the aviation kerosene tank 1 is filtered through the filter 2, the oil pump 3 provides power for kerosene transportation, and the flow and pressure signals are transmitted to the data acquisition and control unit 400 through the flow meter 14 and the pressure transmitter 15. The kerosene 1 finally enters the kerosene channel 2011 of the combustion mechanism through the kerosene pipe 101.

[0031] The gas circuit unit includes an air unit and an oxygen unit. The oxygen unit includes an oxygen tank 6, a solenoid valve III7, a pressure transmitter III8 and a mass controller 9. The oxygen tank 6, the solenoid valve III7, the pressure transmitter III8 and the mass controller 9 are connected in sequence through an oxygen pipe 102, and then the outlet of the mass controller 9 is connected to the oxygen channel 2012. The solenoid valve III7, the pressure transmitter III8 and the mass controller 9 are respectively connected to the data acquisition and control unit 400. The solenoid valve III7 controls the on-off of oxygen, the pressure transmitter III8 transmits the oxygen pressure signal to the data acquisition and control unit 400, and the mass controller 9 controls the flow rate of oxygen through the data acquisition and control unit 400 and feeds back the flow rate value. The oxygen in the oxygen tank 6 is finally passed into the oxygen channel 2012 of the combustion mechanism through the oxygen pipe 102.

[0032] The air unit is divided into three paths, namely, cooling path 103, carrier gas path 104 and cylinder path. Carrier gas path 107 includes electromagnetic valve I 16, pressure regulating valve I 17 and flow meter II 18 connected in sequence through pipelines; the inlet of electromagnetic valve I 16 is connected to the compressed air tank, the outlet of flow meter II 18 is connected to carrier gas main path 106, and carrier gas main path 106 is connected to carrier gas channel 2013; the signal of electromagnetic valve I 16 is connected to the data acquisition and control unit to control the on and off of the carrier gas, the pressure regulating valve I 17 adjusts the pressure of the unit, and the flow meter II 18 adopts a rotor flowmeter to adjust the size of the carrier gas flow and display the flow.

[0033] The cooling circuit 103 includes an electric regulating valve 11, a solenoid valve II 12, a pressure regulating valve II 13, a flow meter III 14 and a pressure transmitter II 15 connected in sequence through pipelines. The inlet of the electric regulating valve 11 is connected to the compressed air tank, and the outlet of the pressure transmitter II 15 is connected to the cooling channel. The signals of the electric regulating valve 11, the solenoid valve 12 and the flow meter III 14 are connected to the data acquisition and control unit 400, respectively, to control the flow rate of the compressed air, control the on-off of the compressed air and feedback the flow value. The pressure regulating valve II 13 is used to adjust the unit pressure.

[0034] The cylinder circuit includes a cylinder main circuit 107 connected to a compressed air tank and a cylinder branch circuit I108 and a cylinder branch circuit II109. The cylinder branch circuits I108 and II109 are connected to the cylinder main circuit 107. The cylinder branch circuit I is connected to the P port of a two-position five-way solenoid valve I20, and a pressure regulating valve III19 is provided on the cylinder branch circuit I; the A port and the B port of the two-position five-way solenoid valve I20 are respectively connected to the two air ports of the horizontal cylinder 303. The cylinder branch circuit II is connected to the P port of a two-position five-way solenoid valve II22, and a pressure regulating valve IV21 is provided on the cylinder branch circuit I; the A port and the B port of the two-position five-way solenoid valve II22 are respectively connected to the two air ports of the longitudinal cylinder 304. The two-position five-way solenoid valve I20 and the two-position five-way solenoid valve II22 are respectively connected to the data acquisition and control unit 400.

[0035] The liquid circuit unit includes a magnetic stirring cup 23 and a peristaltic pump 24. Artificial seawater is provided in the magnetic stirring cup 23 and is kept in a stirring state. The magnetic stirring cup 23 and the peristaltic pump 24 are connected through a liquid pipeline 105 and then connected to a carrier gas main circuit 106. The carrier gas main circuit 106 is connected to a carrier gas channel 2013. The peristaltic pump 24 transports the artificial seawater to the carrier gas main circuit 106 through the liquid pipeline 105 and passes into the carrier gas channel 2013 of the combustion mechanism.

[0036] Aviation kerosene, oxygen and artificial seawater are mixed in the combustion chamber 206 through the channels of the rear shell and the inner core. After the ignition needle 202 is ignited, a burning flame is ejected. After the fuel combustion chamber 206 is fully burned, the corrosive atmosphere enters the fixture 302 in the test area through the corundum tube 301, and the sample is tested at a constant temperature in the tubular high-temperature furnace 300. In order to keep the corrosive atmosphere uniform, the motor 305 rotates the bottom fixture, and then the fixture 302 rotates with the sample. It is regularly taken out of the furnace for cooling through the vertical cylinder 304. After it is taken out of the furnace, the horizontal cylinder 303 drives the door panel to close the furnace door to avoid heat loss, thereby performing a hot and cold cycle.

Claims

1. A gas thermal corrosion detection device for a metal material protective coating, comprising an oil circuit unit, a gas circuit unit, a liquid circuit unit, a combustion mechanism, a heating mechanism, and a data acquisition and control unit; Its characteristics are: The combustion mechanism comprises a front shell, an inner core, a rear shell and an ignition needle; the rear end of the front shell and the front end of the rear shell are connected to form a shell, an inner core installation cavity is provided in the shell, and an inner core is installed in the inner core installation cavity; a seawater hole is provided at the center of the end surface of the inner core, and the seawater hole penetrates the inner core, and an oxygen hole is also provided on the inner core, and the oxygen hole is connected to the ignition chamber of the front shell, and a fuel hole connected to the oxygen hole is provided on the side wall of the inner core; A carrier gas channel is provided at the rear end center of the rear shell; an oxygen channel connected to the oxygen hole of the inner core, a kerosene channel connected to the fuel hole and a cooling channel are also provided on the rear shell; the cooling channel is connected to the cavity between the front of the rear shell and the inner core; three sets of sealing rings are provided between the inner core and the inner core installation cavity, one set of sealing rings is provided on both sides of the outlet of the oxygen channel, and one set of sealing rings is provided on both sides of the outlet of the kerosene channel; an ignition needle is installed on the front shell, and the ignition needle is located in the combustion chamber; The heating mechanism comprises a tubular thermal shock furnace and a fixture, wherein a corundum tube and a fixture are arranged in the tubular thermal shock furnace, and the corundum tube is connected with the fixture and the combustion chamber; The oil circuit unit is connected to the kerosene channel, the gas circuit unit includes an air unit and an oxygen unit, the air unit is connected to the cooling channel; the oxygen unit is connected to the oxygen channel; the liquid circuit unit is connected to the carrier gas channel; The data acquisition and control unit is respectively connected to the oil circuit unit, the gas circuit unit, the liquid circuit unit, the ignition needle and the tubular thermal shock furnace, and is used to realize on-off control and flow control of the oil circuit unit, the gas circuit unit and the liquid circuit unit, as well as the action control of the ignition needle and the temperature control of the heating mechanism, and to collect data.

2. The gas thermal corrosion detection device for metal material protective coating according to claim 1 is characterized in that: The oil circuit unit includes an aviation kerosene tank, a filter, an oil pump, a flow meter I and a pressure transmitter I, which are connected in sequence through a kerosene pipe; the output end of the pressure transmitter I is connected to the kerosene inlet hole of the combustion mechanism through a pipeline; the flow meter and the pressure transmitter I are respectively connected to the data acquisition and control unit.

3. The gas thermal corrosion detection device for metal material protective coating according to claim 1 is characterized in that: The fixture is connected to the transmission output shaft through a rotating shaft, and the transmission input shaft is connected to the motor; the motor is installed on the motor seat, and the motor seat is installed with the top of the piston rod of the longitudinal cylinder; the output shaft passes through the furnace door of the tubular thermal shock furnace, and a transverse cylinder is fixedly installed at the bottom of the tubular thermal shock furnace, and a door panel is installed on the piston rod of the transverse cylinder, and the door panel can seal the furnace door under the push of the transverse cylinder; the motor is connected to the data acquisition and control unit.

4. The gas thermal corrosion detection device for metal material protective coating according to claim 3 is characterized in that: The air unit comprises a compressed air tank, a carrier gas circuit, a cooling circuit and a cylinder circuit, and the carrier gas circuit comprises a solenoid valve I, a pressure regulating valve I and a flow meter II which are sequentially connected through pipelines; The inlet of the solenoid valve I is connected to the compressed air tank, the outlet of the flow meter II is connected to the carrier gas main line, the carrier gas main line is connected to the carrier gas channel; the solenoid valve I is connected to the data acquisition and control unit; The cooling circuit includes an electric regulating valve, a solenoid valve II, a pressure regulating valve II, a flow meter III and a pressure transmitter II connected in sequence through pipelines. The inlet of the electric regulating valve is connected to the compressed air tank, and the outlet of the pressure transmitter II is connected to the cooling channel; the electric regulating valve, the solenoid valve II and the flow meter III are connected to the data acquisition and control unit; The cylinder circuit includes a cylinder main circuit connected to a compressed air tank and a cylinder branch I and a cylinder branch II. The cylinder branch I and the cylinder branch II are connected to the cylinder main circuit; the cylinder branch I is connected to the P port of a two-position five-way solenoid valve I, and a pressure regulating valve III is provided on the cylinder branch I; the A port and the B port of the two-position five-way solenoid valve I are respectively connected to the two air ports of the horizontal cylinder; the cylinder branch II is connected to the P port of the two-position five-way solenoid valve II, and a pressure regulating valve IV is provided on the cylinder branch I; the A port and the B port of the two-position five-way solenoid valve II are respectively connected to the two air ports of the longitudinal cylinder; the two-position five-way solenoid valve I and the two-position five-way solenoid valve II are respectively connected to the data acquisition and control unit.

5. The gas thermal corrosion detection device for metal material protective coating according to claim 1 or 3, characterized in that: The oxygen unit comprises a liquid oxygen tank, a solenoid valve III, a mass controller and a pressure transmitter III. The liquid oxygen tank, the solenoid valve III, the pressure transmitter III and the mass controller are connected in sequence through an oxygen pipe, and the outlet of the mass controller is connected to the oxygen channel; the solenoid valve III, the pressure transmitter III and the mass controller are respectively connected to the data acquisition and control unit.

6. The gas thermal corrosion detection device for metal material protective coating according to claim 1 is characterized in that: The liquid circuit unit includes a magnetic stirring cup and a peristaltic pump. Artificial seawater is arranged in the magnetic stirring cup and stirring is kept during operation. The magnetic stirring cup is connected to the inlet of the peristaltic pump through a pipeline, and the outlet of the peristaltic pump is connected to the carrier gas main circuit through a liquid pipeline.

7. The gas thermal corrosion detection device for metal material protective coating according to claim 1 is characterized in that: The data acquisition and control unit includes a PLC unit and an industrial computer unit.

8. The gas thermal corrosion detection device for metal material protective coating according to claim 1 is characterized in that: The number of sealing rings in each set of sealing rings is two.

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