Combustion chamber outlet gas component mass spectrum in-situ sampling device, system and method

Abstract

The invention belongs to the technical field of mass spectrometer sample introduction analysis, provides a combustion chamber outlet fuel gas component mass spectrum in-situ sample introduction device, system and method, solves the sample introduction problem of aero-engine combustion chamber outlet fuel gas online mass spectrum analysis, and adopts the technical scheme that the device comprises a fuel gas sampling device and a fuel gas differential device; the fuel gas sampling device comprises a fuel gas sampling rake, an electric gate valve and a two-position three-way electromagnetic valve, one end of the fuel gas sampling rake is directly connected with an outlet cavity of an engine combustion chamber, the other end of the fuel gas sampling rake is connected with one side of the electric gate valve, and the other side of the electric gate valve is directly connected with the fuel gas differential device; the two-position three-way electromagnetic valve is communicated with a cavity of the electric gate valve; and the electric gate valve is combined with the two-position three-way electromagnetic valve, so that the flow of back flushing and sampling in gas sampling analysis can be completed. The stability of the amount of fuel gas entering the on-line mass spectrum is guaranteed, and in-situ on-line mass spectrum analysis of the fuel gas at the outlet of the combustion chamber of the aero-engine can be

Description

Technical Field

[0001] The invention belongs to the technical field of mass spectrometer sampling analysis, and in particular relates to a mass spectrometer in-situ sampling device, system and method for combustion chamber outlet gas components. Background Art

[0002] The statements in this section merely provide background information related to the present invention and do not necessarily constitute prior art.

[0003] Online mass spectrometry is an analytical instrument used for chemical composition identification and plays an irreplaceable role in the field of gas detection.

[0004] The existing sampling methods for online mass spectrometry analysis of aircraft engine combustion chamber outlet gas mainly include capillary sampling and molecular beam sampling.

[0005] Capillary injection is the most widely used injection method for online mass spectrometry. Its advantage is that the structure is relatively simple, but the narrow capillary will enhance the collision between the product and the wall, so only relatively stable components can be detected. The outlet pressure of the aircraft engine combustion chamber can reach up to 3MPa, and the temperature is above 2300K. Under high temperature and high pressure, the combustion of aviation kerosene not only produces stable components such as O2, CO2, CO, NOX, H2O, but also various highly active free radical components. The traditional gas analysis technology used for the diagnosis of the outlet of the aircraft engine combustion chamber has a reduced accuracy in the inverse calculation of the outlet gas temperature of the aircraft engine combustion chamber because it cannot detect the free radical components produced at high temperatures. These free radical components are highly active, have large wall loss, and have a short lifespan. Their detection requires direct, in-situ analysis.

[0006] Molecular beam sampling is to pass the sample into the vacuum through a small hole, and the pressure drops rapidly to form a molecular beam. The molecular beam sampling technology can complete the detection of active products and stable products. Therefore, molecular beam sampling technology is widely used in the combustion diagnosis of complex combustion fields. At present, molecular beam mass spectrometry is mainly used for the detection of laminar combustion flame gas under low pressure or normal pressure. This combustion environment is mostly assisted by commercialized laminar flame burners, which is very different from the actual engine combustion chamber working conditions. The interior of the real aircraft engine combustion chamber is a high-pressure system, and the gas exists in the form of high temperature and high pressure. The interior of the online mass spectrometer is a high vacuum environment. Excessive high-pressure gas will destroy the vacuum system and cause damage to the online mass spectrometer. In addition, during the aircraft engine ignition test, there is a moment of fuel injection. In order to avoid contaminating the detection instrument, it is required to use back-blowing gas with a pressure higher than the internal pressure of the combustion chamber for backblowing. High-pressure backblowing gas is also not conducive to maintaining the vacuum system of the online mass spectrometer. Summary of the invention

[0007] In order to solve at least one technical problem existing in the above-mentioned background technology, the first aspect of the present invention provides an in-situ sampling device for mass spectrometry of combustion chamber outlet gas composition, which uses an electric gate valve and a two-position three-way solenoid valve to jointly control the backflush process before ignition of the aircraft engine combustion chamber and the sampling process after combustion; by means of the electric gate valve chamber being connected to the atmosphere, the excess gas is discharged into the atmosphere, thereby ensuring the stability of the amount of gas entering the online mass spectrometer, and realizing the in-situ online mass spectrometry analysis of the gas at the outlet of the aircraft engine combustion chamber.

[0008] In order to achieve the above object, the present invention adopts the following technical solution:

[0009] A mass spectrometer in-situ sampling device for gas components at a combustion chamber outlet, comprising a gas sampling device and a gas differential device;

[0010] The gas sampling device comprises a gas sampling rake, an electric gate valve and a two-position three-way solenoid valve, one end of the gas sampling rake is directly connected to the engine combustion chamber outlet chamber, and the other end is connected to one side of the electric gate valve, the other side of the electric gate valve is directly connected to the gas differential device, and the two-position three-way solenoid valve is connected to the chamber of the electric gate valve;

[0011] The two-position three-way solenoid valve comprises a first control unit, a second control unit, a first gas channel, a second gas channel and a third gas channel;

[0012] When the first control unit is powered, the third gas channel is connected to the first gas channel, and the first gas channel to the second gas channel is closed. When the second control unit is powered, the first gas channel is connected to the second gas channel, and the third gas channel to the first gas channel is closed.

[0013] Furthermore, a gas sampling tube is arranged at the center of the gas sampling rake, and a water cooling channel is designed on the outer layer, one end of the gas sampling tube is placed in the combustion chamber of the aircraft engine, and the other end is connected to one side of the electric gate valve, and the other side of the electric gate valve is directly connected to the gas differential device. Furthermore, the electric gate valve adopts an electric ball valve, and the ball diameter is 3-5mm.

[0014] Furthermore, the gas sampling device also includes a gas flow channel and a back-blowing gas bottle, one end of the gas flow channel is connected to the chamber of the electric gate valve, and the other end is connected to one end of a two-position three-way solenoid valve, and the other end of the two-position three-way solenoid valve is connected to the back-blowing gas bottle.

[0015] Furthermore, before the combustion chamber of the aircraft engine is ignited, the gas flow channel is a back-blowing air channel; after the combustion chamber of the aircraft engine is ignited, the gas flow channel is a fuel gas channel.

[0016] Furthermore, the back-blowing gas in the back-blowing gas bottle back-blows the gaseous or liquid fuel before the combustion chamber of the aircraft engine is ignited, and the back-blowing gas uses nitrogen or zero air.

[0017] Furthermore, the gas differential device is a closed hollow chamber, including a flat electrode, a conical electrode and an oil pump, the flat electrode and the conical electrode are coaxially installed, the vacuum inside the chamber is maintained by the oil pump, and the gas differential area is the area between the flat electrode and the conical electrode.

[0018] Furthermore, the conical hole electrode is a plate-type electrode with a conical protrusion at the center, and a through hole for gas transmission is processed in the transverse direction at the tip of the cone.

[0019] In order to solve the above-mentioned problems, the second aspect of the present invention provides an in-situ sampling system for mass spectrometry of combustion chamber outlet gas composition, which utilizes an electric gate valve and a two-position three-way solenoid valve to jointly control the backflush process before ignition of the aircraft engine combustion chamber and the sampling process after combustion; by means of the electric gate valve chamber being connected to the atmosphere, excess gas is discharged into the atmosphere, thereby ensuring the stability of the amount of gas entering the online mass spectrometer, and realizing in-situ online mass spectrometry analysis of the gas at the outlet of the aircraft engine combustion chamber.

[0020] In order to achieve the above object, the present invention adopts the following technical solution:

[0021] A mass spectrometry in-situ sampling system for combustion chamber outlet gas components comprises a mass spectrometer and the device described in the first aspect, wherein the mass spectrometer is connected to the device.

[0022] In order to solve the above-mentioned problems, the third aspect of the present invention provides an in-situ sampling method for mass spectrometry of combustion chamber outlet gas components, which utilizes an electric gate valve and a two-position three-way solenoid valve to jointly control the backflush process before ignition of the aircraft engine combustion chamber and the sampling process after combustion; by connecting the chamber of the electric gate valve to the atmosphere, excess gas is discharged into the atmosphere, thereby ensuring the stability of the amount of gas entering the online mass spectrometer, and realizing in-situ online mass spectrometry analysis of the aircraft engine combustion chamber outlet gas.

[0023] In order to achieve the above object, the present invention adopts the following technical solution:

[0024] A method for in-situ mass spectrometry sampling of combustion chamber outlet gas components, comprising:

[0025] Before the combustion chamber of the aircraft engine is ignited, the first control unit is powered, the third gas channel is connected to the first gas channel, the electric gate valve is closed, and the back-blowing gas is blown into the combustion chamber of the aircraft engine through the third gas channel, the first gas channel, the electric gate valve chamber, and the gas sampling rake;

[0026] After the aircraft engine combustion chamber is ignited, the first control unit is powered off, backblowing is stopped, power is supplied to the second control unit, the first gas channel and the second gas channel are connected, the electric gate valve is opened, and the aircraft engine combustion chamber outlet gas enters the gas differential device through the gas sampling rake, and the excess gas is discharged into the environment through the first gas channel and the second gas channel.

[0027] The beneficial effects of the present invention are:

[0028] 1. The present invention adopts a high-temperature gas sampling rake to complete the sampling of high-temperature gas, and uses an electric gate valve and a two-position three-way solenoid valve to jointly control the backflush process before ignition of the aircraft engine combustion chamber and the sampling process after combustion, so as to realize the in-situ online sampling of the outlet gas of the real aircraft engine combustion chamber;

[0029] 2. The present invention uses an electric gate valve to isolate the high vacuum environment of the mass spectrometer from the high pressure environment of the combustion chamber, so that the mass spectrometer can be closely connected to the outlet of the combustion chamber of the aircraft engine, reducing the problem of slow response time caused by the long gas transmission pipeline;

[0030] 3. The present invention reserves a chamber inside the electric gate valve, and the chamber of the electric gate valve is connected to the atmosphere to buffer the high-pressure gas in the combustion chamber, and at the same time, the excess gas is discharged into the atmosphere, thereby ensuring the stability of the amount of gas entering the online mass spectrometer, and realizing the in-situ online mass spectrometry analysis of the gas at the outlet of the combustion chamber of the aircraft engine;

[0031] 4. The gas differential device in the present invention can allow high-temperature gas to be sampled in the form of a molecular beam, preventing active components in the gas from further reacting. It can not only achieve the transmission of highly active species in the gas, but also reduce the temperature and pressure of the gas.

[0032] Advantages of additional aspects of the present invention will be given in part in the following description, and in part will become obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The accompanying drawings in the specification, which constitute a part of the present invention, are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0034] Figure 1 It is a schematic structural diagram of a mass spectrometry in-situ sampling device for combustion chamber outlet gas components provided by an embodiment of the present invention;

[0035] Figure 2 The back-blowing route diagram of the back-blowing gas before ignition of the combustion chamber of an aircraft engine provided by an embodiment of the present invention;

[0036] Figure 3It is a gas sampling route map after ignition of the combustion chamber of an aircraft engine provided by an embodiment of the present invention;

[0037] Among them, 1. aircraft engine combustion chamber; 2. aircraft engine combustion chamber outlet chamber; 3. gas sampling rake; 4. water cooling channel; 5. two-position three-way solenoid valve; 501. first control unit; 502. second control unit; 503. first gas channel; 504. second gas channel; 505. third gas channel; 6. gas sampling tube; 7. electric plug valve; 8. flat electrode; 9. conical hole electrode; 10. oil pump; 11. gas flow channel; 12. back-blowing gas cylinder. DETAILED DESCRIPTION

[0038] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0039] It should be noted that the following detailed descriptions are all illustrative and intended to provide further explanation of the present invention. Unless otherwise specified, all technical and scientific terms used herein have the same meanings as those commonly understood by those skilled in the art to which the present invention belongs.

[0040] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit exemplary embodiments according to the present invention. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprising" and / or "including" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0041] In the present invention, terms such as "connected" and "connection" should be understood in a broad sense, indicating that the connection can be fixed, integral or detachable; it can be directly connected or indirectly connected through an intermediate medium. Relevant scientific research or technical personnel in this field can determine the specific meaning of the above terms in the present invention according to specific circumstances, and they should not be understood as limiting the present invention.

[0042] As introduced in the background technology, there are two main sampling methods for online mass spectrometry analysis of combustion chamber outlet gas of aircraft engines: capillary sampling and molecular beam sampling. Capillary sampling will cause the active products in the test object to be quenched and cannot be detected. Molecular beam sampling can complete the detection of active products, but it is only used in low-pressure or normal-pressure environments. In addition, the interior of the combustion chamber of a real aircraft engine is a high-pressure system, and the gas exists in the form of high temperature and high pressure. After passing through the high-temperature gas sampling rake, it still has a certain pressure; the interior of the online mass spectrometer is a high-vacuum environment, and excessive high-pressure gas will destroy the vacuum system and cause damage to the online mass spectrometer. During the ignition test of the aircraft engine, there is a moment of fuel injection. In order to avoid contaminating the detection instrument, it is required to use a back-blowing gas with a pressure higher than the internal pressure of the combustion chamber for backblowing. High-pressure backblowing gas is also not conducive to maintaining the vacuum system of the online mass spectrometer.

[0043] In order to solve the above technical problems, the present invention proposes an online mass spectrometry in-situ sampling system and method for the composition of the gas at the outlet of an aircraft engine combustion chamber, wherein a high-temperature gas sampling rake is used to complete the sampling of the high-temperature gas, and an electric gate valve and a two-position three-way solenoid valve are used to jointly control the backflush process before ignition of the aircraft engine combustion chamber and the sampling process after combustion; the chamber of the electric gate valve is connected to the atmosphere, and the excess gas is discharged into the atmosphere, thereby ensuring the stability of the amount of gas entering the online mass spectrometer, and realizing the in-situ online mass spectrometry analysis of the gas at the outlet of the aircraft engine combustion chamber; the molecular beam injection method can not only realize the detection of active species in the gas, but also have the effect of cooling and reducing the pressure of the gas; the above-mentioned device is connected to a time-of-flight mass spectrometer, and the single detection time can reach microseconds, which expands the application range of the mass spectrometer.

[0044] Embodiment 1

[0045] like Figure 1 As shown, this embodiment provides a combustion chamber outlet gas composition mass spectrometry in-situ sampling system, including a gas sampling device and a gas differential device; the gas sampling device and the gas differential device are tightly connected, and can perform real-time in-situ online sampling of the aircraft engine combustion chamber outlet gas, and enter the online mass spectrometry ionization source by molecular beam differential.

[0046] The gas sampling device is mainly used to control the back-blowing of the back-blowing gas before ignition of the aircraft engine combustion chamber and the sampling of the gas after ignition. The gas sampling device includes a gas sampling rake 3, an electric gate valve 7, a two-position three-way solenoid valve 5, a gas flow channel 11 and a back-blowing gas bottle 12 arranged in the outlet chamber 2 of the aircraft engine combustion chamber;

[0047] A gas sampling tube 6 is arranged in the gas sampling rake 3, one end of the gas sampling tube 6 is placed in the combustion chamber of the aircraft engine, and the other end is connected to one side of the electric gate valve 7; the other side of the electric gate valve 7 is directly connected to the gas differential device.

[0048] The gas sampling rake 3 is mainly responsible for sampling the high-temperature gas and cooling the gas. In this embodiment, the gas sampling rake 3 is formed in one piece by 3D printing using GH3536 alloy material.

[0049] A gas sampling tube 6 is arranged at the center of the gas sampling rake 3, and a water cooling channel 4 is designed on the outer layer; the gas sampling rake 3 is directly connected to the outlet chamber 2 of the aircraft engine combustion chamber, and is sealed with a high temperature resistant graphite gasket.

[0050] In this embodiment, the outer diameter of the gas sampling tube is 3 mm and the inner diameter is 1 mm; the cooling water flow rate of the water-cooling channel is 0.2 kg / s and the pressure is 0.6 MPa.

[0051] It should be noted that in this embodiment, the electric gate valve 7 is an electric ball valve, which is responsible for the sealing of the gas sampling device and the gas differential device and the gas sampling, and can withstand a gas pressure of 0.1-3MPa, and the preferred ball diameter is 3-5mm;

[0052] Further, one end of the gas flow channel 11 is connected to the chamber of the electric gate valve 7, and the other end is connected to one end of the two-position three-way solenoid valve 5, and the other end of the two-position three-way solenoid valve 5 is connected to the back-blowing gas bottle 12;

[0053] Before the aircraft engine combustion chamber 1 is ignited, the gas flow channel 11 is a back-blowing gas channel; after the aircraft engine combustion chamber 1 is ignited, the gas flow channel 11 is a fuel gas channel.

[0054] The electric gate valve 7 is directly connected to the gas differential device, and is sealed by a fluororubber O-ring; there is a chamber inside the electric gate valve for buffering high-pressure gas.

[0055] In this embodiment, the back-blowing gas in the back-blowing gas bottle 12 back-blows the gaseous or liquid fuel before the aircraft engine combustion chamber is ignited to prevent the fuel from entering the pipeline or detection instrument. Nitrogen or zero air is preferred, and the back-blowing pressure is greater than the internal pressure of the aircraft engine combustion chamber.

[0056] In this embodiment, the two-position three-way solenoid valve 5 includes a first control unit 501, a second control unit 502, a first gas channel 503, a second gas channel 504 and a third gas channel 505;

[0057] When the first control unit 501 is powered, the third gas channel 505 is connected to the first gas channel 503, the first gas channel 503 to the second gas channel 504 is closed, and the gas flows from the third gas channel 505 to the first gas channel 503;

[0058] When the second control unit 502 is powered, the first gas channel 503 and the second gas channel 504 are connected, the third gas channel 505 to the first gas channel 503 is closed, and the gas flows from the first gas channel 503 to the second gas channel 504;

[0059] In this embodiment, the two-position three-way solenoid valve preferably has a pressure resistance of 0-4 MPa.

[0060] Among them, the gas differential device is a closed hollow chamber, including a flat electrode 8, a conical hole electrode 9 and an oil pump 10. The flat electrode 8 and the conical hole electrode 9 are coaxially installed, and the vacuum inside the chamber is maintained by the oil pump 10. The gas differential area is the area between the flat electrode and the conical hole electrode.

[0061] In this embodiment, the flat plate electrode 8 is in the shape of a flat plate, which is convenient for connection with the electric gate valve, and the diameter of the injection port is preferably 0.3-0.5 mm.

[0062] The conical hole electrode 9 is a plate electrode with a conical protrusion at the center. A through hole for gas transmission is processed in the transverse direction at the tip of the cone. The preferred diameter of the conical hole is 0.5-2 mm, and the preferred angle of the conical hole is 50 degrees.

[0063] The oil pump is responsible for maintaining the vacuum degree in the gas differential region. Preferably, the pumping speed of the dry pump is 7.5L / s, and the vacuum degree in the molecular beam differential region is 200-800Pa.

[0064] In this embodiment, during online mass spectrometry, a time-of-flight mass spectrometer is used as a gas detection instrument. A single detection is at the microsecond level, which can capture the transient change process inside the combustion chamber of an aircraft engine.

[0065] like Figure 2 and Figure 3 As shown, the working principle of this device is:

[0066] Before the combustion chamber of the aircraft engine is ignited, the first control unit 501 of the two-position three-way solenoid valve is powered, the third gas channel 505 is connected to the first gas channel 503, the electric gate valve 7 is closed, and the back-blowing gas is passed from the third gas channel 505 to the first gas channel 503, the chamber of the electric gate valve 7, and the gas sampling rake 3 back-blown into the combustion chamber 1 of the aircraft engine;

[0067] After the aircraft engine combustion chamber is ignited, the first control unit 501 is powered off, backblowing is stopped, power is supplied to the second control unit 502 of the two-position three-way solenoid valve, the first gas channel 503 and the second gas channel 504 are connected, the electric gate valve 7 is opened, and the gas at the outlet of the aircraft engine combustion chamber enters the gas differential device through the gas sampling rake 3 to be further depressurized, and then enters the online mass spectrometer, and the excess gas is discharged into the environment through the first gas channel 503 and the second gas channel 504 of the two-position three-way solenoid valve.

[0068] The advantage of the above scheme is that the present invention utilizes the electric gate valve and the two-position three-way solenoid valve to jointly control the backflush process before ignition of the aircraft engine combustion chamber and the sampling process after combustion; by means of the electric gate valve chamber being connected to the atmosphere, the excess gas is discharged into the atmosphere, thereby ensuring the stability of the amount of gas entering the online mass spectrometer, and realizing in-situ online mass spectrometry analysis of the gas at the outlet of the aircraft engine combustion chamber; the molecular beam form of the sampling method can not only realize the detection of active species in the gas, but also have the effect of cooling and reducing the pressure of the gas; the above device is connected to a time-of-flight mass spectrometer, and the single detection time can reach microseconds, which expands the application range of the mass spectrometer.

[0069] Embodiment 2

[0070] This embodiment provides a mass spectrometry in-situ sampling system for combustion chamber outlet gas components, comprising a mass spectrometer and the device described in Embodiment 1, wherein the mass spectrometer is connected to the device.

[0071] Embodiment 3

[0072] This embodiment provides a method for in-situ mass spectrometry sampling of combustion chamber outlet gas components, comprising:

[0073] Before the combustion chamber of the aircraft engine is ignited, the first control unit 501 of the two-position three-way solenoid valve is powered, the third gas channel 505 is connected to the first gas channel 503, the electric gate valve 7 is closed, and the back-blowing gas is passed from the third gas channel 505 to the first gas channel 503, the chamber of the electric gate valve 7, and the gas sampling rake 3 back-blown into the combustion chamber 1 of the aircraft engine;

[0074] After the aircraft engine combustion chamber is ignited, the first control unit 501 is powered off, backblowing is stopped, power is supplied to the second control unit 502 of the two-position three-way solenoid valve, the first gas channel 503 and the second gas channel 504 are connected, the electric gate valve 7 is opened, and the gas at the outlet of the aircraft engine combustion chamber enters the gas differential device through the gas sampling rake 3 to be further depressurized, and then enters the online mass spectrometer, and the excess gas is discharged into the environment through the first gas channel 503 and the second gas channel 504 of the two-position three-way solenoid valve.

[0075] The advantage of the above scheme is that the present invention utilizes the electric gate valve and the two-position three-way solenoid valve to jointly control the backflush process before ignition of the aircraft engine combustion chamber and the sampling process after combustion; by means of the electric gate valve chamber being connected to the atmosphere, the excess gas is discharged into the atmosphere, thereby ensuring the stability of the amount of gas entering the online mass spectrometer, and realizing in-situ online mass spectrometry analysis of the gas at the outlet of the aircraft engine combustion chamber; the molecular beam form of the sampling method can not only realize the detection of active species in the gas, but also have the effect of cooling and reducing the pressure of the gas; the above device is connected to a time-of-flight mass spectrometer, and the single detection time can reach microseconds, which expands the application range of the mass spectrometer.

[0076] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A mass spectrometer in-situ sampling device for combustion chamber outlet gas components, characterized in that: It includes a gas sampling device and a gas differential device; The gas sampling device comprises a gas sampling rake (3), an electric gate valve (7) and a two-position three-way solenoid valve (5); one end of the gas sampling rake (3) is directly connected to the engine combustion chamber outlet chamber (2), and the other end is connected to one side of the electric gate valve (7); the other side of the electric gate valve (7) is directly connected to the gas differential device; the two-position three-way solenoid valve (5) and the chamber of the electric gate valve (7) are in communication; The two-position three-way solenoid valve (5) comprises a first control unit (501), a second control unit (502), a first gas channel (503), a second gas channel (504) and a third gas channel (505); When the first control unit (501) is powered, the third gas channel (505) is connected to the first gas channel (503), and the first gas channel (503) to the second gas channel (504) is closed. When the second control unit (502) is powered, the first gas channel (503) is connected to the second gas channel (504), and the third gas channel (505) to the first gas channel (503) is closed.

2. The in-situ mass spectrometry sampling device for combustion chamber outlet gas components according to claim 1, characterized in that: A gas sampling tube (6) is arranged at the center of the gas sampling rake (3), and a water cooling channel (4) is designed on the outer layer. One end of the gas sampling tube (6) is placed in the combustion chamber of the aircraft engine, and the other end is connected to one side of the electric gate valve (7). The other side of the electric gate valve (7) is directly connected to the gas differential device.

3. The in-situ mass spectrometry sampling device for combustion chamber outlet gas components according to claim 1, characterized in that: The electric gate valve (7) is an electric ball valve, and the ball diameter is 3-5 mm.

4. The in-situ mass spectrometry sampling device for combustion chamber outlet gas components according to claim 1, characterized in that: The gas sampling device further comprises a gas circulation channel (11) and a back-blowing gas bottle (12); one end of the gas circulation channel (11) is connected to the chamber of the electric gate valve (7), and the other end is connected to one end of a two-position three-way solenoid valve (5); and the other end of the two-position three-way solenoid valve (5) is connected to the back-blowing gas bottle (12).

5. The in-situ mass spectrometry sampling device for combustion chamber outlet gas components according to claim 4, characterized in that: Before the combustion chamber of the aircraft engine is ignited, the gas flow channel (11) is a back-blowing gas channel; after the combustion chamber of the aircraft engine is ignited, the gas flow channel (11) is a fuel gas channel.

6. The in-situ mass spectrometry sampling device for combustion chamber outlet gas components according to claim 4, characterized in that: The back-blowing gas in the back-blowing gas bottle (12) back-blows the gaseous or liquid fuel before the combustion chamber of the aircraft engine is ignited, and the back-blowing gas uses nitrogen or zero air.

7. The in-situ mass spectrometry sampling device for combustion chamber outlet gas components according to claim 1, characterized in that: The gas differential device is a closed hollow chamber, comprising a flat plate electrode (8), a conical hole electrode (9) and an oil pump (12). The flat plate electrode (8) and the conical hole electrode (9) are coaxially installed, and the vacuum inside the chamber is maintained by the oil pump (10). The gas differential area is the area between the flat plate electrode (8) and the conical hole electrode (9).

8. The in-situ mass spectrometry sampling device for combustion chamber outlet gas components according to claim 7, characterized in that: The conical hole electrode (9) is a plate-type electrode with a conical protrusion at the center, and a through hole for gas transmission is processed in the transverse direction at the tip of the cone.

9. A mass spectrometry in-situ sampling system for combustion chamber outlet gas components, characterized in that: It comprises a mass spectrometer and the device according to any one of claims 1 to 8, wherein the mass spectrometer is connected to the device.

10. A method for in-situ mass spectrometry sampling of combustion chamber outlet gas components, characterized in that: include: Before the combustion chamber of the aircraft engine is ignited, the first control unit (501) is powered, the third gas channel (505) is connected to the first gas channel (503), the electric gate valve (7) is closed, and the back-blowing gas is blown into the combustion chamber (1) of the aircraft engine through the third gas channel (505), the first gas channel (503), the chamber of the electric gate valve (7), and the gas sampling rake (3); After the combustion chamber of the aircraft engine is ignited, the first control unit (501) is powered off, backblowing is stopped, power is supplied to the second control unit (502), the first gas channel (503) and the second gas channel (504) are connected, the electric gate valve is opened, and the fuel gas at the outlet of the combustion chamber of the aircraft engine enters the fuel gas differential device through the fuel gas sampling rake (3), and the excess fuel gas is discharged into the environment through the first gas channel (503) and the second gas channel (504).

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