Annular tube combustion chamber temperature measurement system and working method thereof

Abstract

The present invention relates to the technical field of gas turbines, and in particular to a temperature measurement system for an annular tube combustion chamber and a working method thereof. The annular tube combustion chamber temperature measurement system comprises: a combustion chamber shell, wherein the inner and outer walls of the combustion chamber shell enclose an inner cavity of the combustion chamber; a plurality of flame tubes are arranged in the inner cavity of the combustion chamber, and the plurality of flame tubes are evenly spaced along the circumferential direction in the inner cavity of the combustion chamber; a cross-flame tube is arranged between two adjacent flame tubes for flame transmission; a viewing window is arranged on both radial sides of the cross-flame tube, suitable for providing an optical path for the laser; a TDLAS temperature measurement assembly comprises a laser transmitter and a laser receiver, wherein the laser transmitter and the laser receiver are respectively arranged on both radial sides of the cross-flame tube and arranged opposite to the viewing window; the annular tube combustion chamber temperature measurement system provided by the present invention can improve the accuracy and timeliness of combustion monitoring and diagnosis of the annular tube combustion chamber of a gas turbine.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a temperature measurement system for an annular tube combustion chamber and a working method thereof. Background Art

[0002] Because gas turbine combustors remain at high temperatures for extended periods, there is currently no reliable engineering technology capable of directly measuring their temperature. Existing methods for measuring the temperature of gas turbine annular duct combustors typically utilize temperature sensors (such as thermocouples) to monitor the turbine blade passage temperature and exhaust gas temperature, and then inversely calculate the combustor temperature, i.e., indirect measurement. However, this indirect measurement method cannot reveal the actual combustion conditions within the gas turbine combustor, resulting in low accuracy for combustion monitoring and diagnosis in the gas turbine combustor. Furthermore, its temperature measurement results are often accompanied by a "time lag" (thermocouple temperature measurement is based on the principle of heat conduction, and heat transfer requires a certain amount of time), which is detrimental to combustion diagnosis and results in poor timeliness for combustion monitoring and diagnosis in the gas turbine combustor. Therefore, existing methods for measuring the temperature of gas turbine combustors lack accuracy and timeliness for combustion monitoring and diagnosis in gas turbine annular duct combustors. Summary of the Invention

[0003] Therefore, the technical problem to be solved by the present invention is to overcome the defects of the existing gas turbine combustion chamber temperature measurement method in the prior art in the low accuracy and timeliness of combustion monitoring and diagnosis of the gas turbine annular tube combustion chamber, thereby providing an annular tube combustion chamber temperature measurement system that can improve the accuracy and timeliness of combustion monitoring and diagnosis of the gas turbine annular tube combustion chamber.

[0004] Another technical problem to be solved by the present invention is to overcome the defects of the existing gas turbine combustion chamber temperature measurement method in the prior art in terms of low accuracy and timeliness of combustion monitoring and diagnosis of the gas turbine annular tube combustion chamber, thereby providing a working method of an annular tube combustion chamber temperature measurement system that can improve the accuracy and timeliness of combustion monitoring and diagnosis of the gas turbine annular tube combustion chamber.

[0005] In order to solve the above technical problems, the present invention provides an annular tube combustion chamber temperature measurement system, comprising:

[0006] A combustion chamber housing, wherein the inner and outer walls of the combustion chamber housing enclose an inner chamber of the combustion chamber; a plurality of flame tubes are arranged in the inner chamber of the combustion chamber, and the plurality of flame tubes are evenly spaced along the circumferential direction of the inner chamber of the combustion chamber; a cross-flame tube is provided between two adjacent flame tubes for flame transmission;

[0007] Windows are provided on both radial sides of the cross-fire tube and are suitable for providing an optical path for the laser;

[0008] A TDLAS temperature measurement assembly includes a laser transmitter and a laser receiver, wherein the laser transmitter and the laser receiver are respectively arranged on both radial sides of the cross-fire tube and opposite to the viewing window;

[0009] In the measuring state, laser light is emitted from the laser emitter, passes through one of the windows on the cross-fire tube radially through the flow field to be measured in the cross-fire tube, then passes through another window on the cross-fire tube and is received by the laser receiver to measure the combustion temperature in the flame tube.

[0010] Optionally, a laser path between the laser transmitter and the laser receiver is perpendicular to the central axis of the cross-fire tube.

[0011] Optionally, the combustion chamber housing includes a first side circumferential wall and a second side circumferential wall, wherein the first side circumferential wall and the second side circumferential wall are radially spaced apart to form the combustion chamber cavity;

[0012] The laser transmitter is arranged on a side of the first side circumferential wall close to the cross-fire tube, and the laser receiver is arranged on a side of the second side circumferential wall close to the cross-fire tube.

[0013] Optionally, the distances from the viewing window on each cross-fire tube to both ends of the cross-fire tube are equal.

[0014] Optionally, the number of the TDLAS temperature measurement components is P, P satisfies P=2M+C, wherein M satisfies 3M+C=N, N is the number of the flame tubes, M is a positive integer, C is an integer, and 0≤C<3.

[0015] Optionally, among the N flame tubes, except for the first flame tube and the Nth flame tube which are not connected to each other, every other two adjacent flame tubes are connected to each other through the cross-flame tube.

[0016] The working method of the annular tube combustion chamber temperature measurement system provided by the present invention includes:

[0017] S1. Number N flame tubes from 1 to N in clockwise direction;

[0018] S2. Divide the units from the first flame tube in a clockwise direction and from the Nth flame tube in a counterclockwise direction simultaneously, and sequentially divide three adjacent flame tubes into one unit. When the number of flame tubes cannot be divided by 3, divide the remaining one or two flame tubes into the last unit;

[0019] S3. Setting windows on both cross-fire tubes in each unit and setting TDLAS temperature measuring components corresponding to the windows;

[0020] S4. Locate any flame tube with abnormal temperature in each unit using the first set of the TDLAS temperature measuring components and the second set of the TDLAS temperature measuring components in the unit.

[0021] Optionally, in step S4, when the first set of the TDLAS temperature measuring components in a certain unit detects a temperature abnormality, detection is performed using the second set of TDLAS temperature measuring components in the unit;

[0022] When the temperature measured by the second set of TDLAS temperature measuring components in the unit is normal, the temperature of the flame tube far away from the second set of TDLAS temperature measuring components is abnormal;

[0023] When the temperature measured by the second set of TDLAS temperature measuring components is also abnormal, the temperature of the flame tube between the first set of TDLAS temperature measuring components and the second set of TDLAS temperature measuring components is abnormal.

[0024] Optionally, in step S3, when the last unit has only one flame tube, the window and the TDLAS temperature measurement component corresponding to the window are set on any one of the cross-fire tubes on both sides of the flame tube.

[0025] Optionally, in step S3, when the last unit has only two of the flame tubes, the window and the TDLAS temperature measuring component corresponding to the window are set on the cross-flame tube between the two flame tubes, and the window and the TDLAS temperature measuring component corresponding to the window are set on any one of the cross-flame tubes on both sides of the two flame tubes.

[0026] The technical solution of the present invention has the following advantages:

[0027] 1. The annular tube combustion chamber temperature measurement system provided by the present invention provides a cross-flame tube between two adjacent flame tubes, thereby connecting the two adjacent flame tubes through the cross-flame tube for flame transmission; by providing windows on both radial sides of the cross-flame tube to provide an optical path for the laser, it is avoided to open holes in the flame tube, thereby avoiding adverse effects on the combustion flow field; and the temperature of the high-temperature combustion gas in the cross-flame tube is almost the same as the high-temperature combustion gas in the flame tubes on both sides, which can represent the real combustion temperature in the flame tubes. Compared with the currently commonly used method of inverting the combustion temperature based on the exhaust temperature measured by thermocouples and the turbine blade channel temperature, the annular tube combustion chamber temperature measurement system of the present invention can obtain the real combustion temperature in real time without affecting the flow field and combustion state in the original flame tube, and has a rapid response, without the "time lag" phenomenon in thermocouple temperature measurement, which is beneficial to combustion diagnosis and temperature measurement, and improves the accuracy and timeliness of combustion monitoring and diagnosis of gas turbine combustion chambers.

[0028] 2. The annular tube combustion chamber temperature measurement system provided by the present invention comprises the following: the laser transmitter is fixedly arranged on a side of the first side circumferential wall close to the cross-flame tube, and the laser receiver is fixedly arranged on a side of the second side circumferential wall close to the cross-flame tube; by fixing the TDLAS temperature measurement component on the wall surface of the combustion chamber rather than on the cross-flame tube, on the one hand, the influence of the vibration generated by the combustion pressure pulsation and the rotor rotation on the TDLAS temperature measurement component can be significantly reduced, which is beneficial to ensuring the measurement accuracy; on the other hand, due to the presence of high-temperature combustion gas in the cross-flame tube, directly fixing the temperature measurement system on the cross-flame tube is not conducive to the normal operation of the TDLAS temperature measurement component; while the wall surface of the combustion chamber is not in direct contact with the flame and the high-temperature combustion gas, which provides favorable conditions for the normal operation of the TDLAS temperature measurement component.

[0029] 3. The annular tube combustion chamber temperature measurement system provided by the present invention has a number of TDLAS temperature measurement components P, P satisfies P=2M+C, wherein M satisfies 3M+C=N, N is the number of the flame tubes, M is a positive integer, C is an integer, and 0≤C<3. By dividing every three adjacent N flame tubes in the annular tube combustion chamber into a unit, the TDLAS temperature measurement components are reasonably arranged in the annular tube combustion chamber. Under the premise of using a minimum number of TDLAS temperature measurement components, combustion monitoring can be performed on each of the flame tubes. This can not only accurately determine whether the combustion temperature in the flame tube is abnormal and precisely locate the faulty flame tube, which is beneficial to combustion diagnosis and normal operation of the gas turbine, but also significantly reduce manufacturing and operation and maintenance costs.

[0030] 4. The working method of the annular tube combustion chamber temperature measurement system provided by the present invention is to divide the units from the first flame tube in a clockwise direction and from the Nth flame tube in a counterclockwise direction at the same time, and successively divide the three adjacent flame tubes into one unit. When the number of flame tubes cannot be divided by 3, the remaining one or two flame tubes are divided into the last unit to ensure that both unconnected flame tubes can be monitored. While improving the accuracy and timeliness of combustion monitoring and diagnosis of the gas turbine combustion chamber, the function of the flame detector can be realized, thereby eliminating the flame detector, thereby simplifying the system structure, improving the operating efficiency of the gas turbine, and reducing costs.

[0031] 5. The working method of the annular tube combustion chamber temperature measurement system provided by the present invention is as follows: N flame tubes are numbered in sequence from 1 to N in a clockwise direction; units are simultaneously divided from the first flame tube in a clockwise direction and from the Nth flame tube in a counterclockwise direction, and three adjacent flame tubes are divided into one unit in sequence; windows are set on the two cross-flame tubes in each unit, and TDLAS temperature measurement components corresponding to the windows are set; any flame tube with abnormal temperature in the unit is located by the first set of the TDLAS temperature measurement components and the second set of the TDLAS temperature measurement components in each unit. On the one hand, while improving the accuracy and timeliness of combustion monitoring and diagnosis of the gas turbine combustion chamber, the function of the flame detector can be realized, the flame detector is omitted, and the system structure is simplified. On the other hand, the faulty flame tube can be accurately located, and the real-time monitoring function of all flame tubes can be realized while using a minimum amount of monitoring equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0033] Figure 1 Schematic diagram of the radial cross-sectional structure of the annular tube combustion chamber temperature measurement system of the present invention;

[0034] Figure 2 for Figure 1 A partial enlarged view of the three flame tubes in the middle combustion chamber shell divided into individual units;

[0035] Figure 3 This is a schematic diagram of the monitoring principle of an annular tube combustion chamber in Example 2 of the working method of the annular tube combustion chamber temperature measurement system of the present invention;

[0036] Figure 4 This is a schematic diagram of the monitoring principle of an annular tube combustion chamber in Example 3 of the working method of the annular tube combustion chamber temperature measurement system of the present invention;

[0037] Figure 5 This is a schematic diagram of the monitoring principle of an annular tube combustion chamber in the fourth embodiment of the working method of the annular tube combustion chamber temperature measurement system of the present invention.

[0038] Description of reference numerals:

[0039] 10. Combustion chamber housing; 100. Combustion chamber inner cavity; 11. First side peripheral wall; 12. Second side peripheral wall;

[0040] 20. Flame tube;

[0041] 30. Cross-flame tube;

[0042] 40. Window;

[0043] 50. TDLAS temperature measurement component; 51. Laser transmitter; 52. Laser receiver. DETAILED DESCRIPTION

[0044] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0045] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0046] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0047] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0048] Example 1

[0049] Combine Figure 1-Figure 5 As shown, the annular tube combustion chamber temperature measurement system provided in this embodiment includes:

[0050] A combustion chamber housing 10, wherein the inner and outer walls of the combustion chamber housing 10 enclose a combustion chamber inner cavity 100; a plurality of flame tubes 20 are disposed in the combustion chamber inner cavity 100, and the plurality of flame tubes 20 are evenly spaced along the circumferential direction within the combustion chamber inner cavity 100; a cross-fire tube 30 is disposed between two adjacent flame tubes 20 for flame transmission;

[0051] Windows 40 are provided on both radial sides of the cross-fire tube 30 and are suitable for providing an optical path for the laser;

[0052] The TDLAS temperature measurement assembly 50 includes a laser emitter 51 and a laser receiver 52 . The laser emitter 51 and the laser receiver 52 are respectively disposed on radial sides of the cross-fire tube 30 and opposite to the viewing window 40 .

[0053] In the measuring state, laser light is emitted from the laser emitter 51 , passes through one of the windows 40 on the cross-flame tube 30 radially through the flow field to be measured in the cross-flame tube 30 , then passes through another window 40 on the cross-flame tube 30 and is received by the laser receiver 52 to measure the combustion temperature in the flame tube 20 .

[0054] It should be noted that the working principle of the TDLAS temperature measurement component 50 is based on the principle of tunable semiconductor laser absorption spectroscopy (TDLAS for short). The Beer-Lambert law is the basis of TDLAS temperature measurement technology, which can express the relationship between the strength of a substance's absorption of a certain monochromatic light and the absorbing substance. The Beer-Lambert law is specifically expressed as follows: when the incident light intensity I0 passes through a temperature measurement area with a certain absorption optical path L, when the laser output wavelength is the same as the central wavelength of a certain absorption spectrum line of the gas, the gas molecules will absorb the photon energy and change their energy levels, transitioning from a low energy level to a high energy level. At this time, the laser energy will also attenuate, and the light intensity will become I1. The attenuation degree of the laser intensity is related to the temperature, pressure, etc. of the gas molecules, which can be expressed by the Beer-Lambert law. Therefore, the information of the gas molecules being measured can be obtained by measuring the attenuation of the laser light intensity, and then the information of the environment in which the molecules are located can be obtained. The TDLAS principle is simple, easy to operate, and easy to miniaturize. As a non-contact measurement technology, it will not be affected by the flow field to be measured, and it has high precision and accurate and reliable measurement results.

[0055] It should be noted that, since the TDLAS temperature measurement component 50 requires an optical path for laser transmission, if a window is drilled on the flame tube, the drilling position is difficult to determine, and the size, shape and position of the hole are likely to affect the stability of the flow field in the flame tube. In severe cases, it may also cause thermoacoustic oscillation under the existing flame tube structure, making the combustion unstable. In addition, drilling holes on the flame tube wall will also disrupt the arrangement of the flame tube cooling air film holes, thereby reducing the cooling effect of the flame tube wall, causing uneven distribution of heat load on the flame tube wall, and reducing its service life. If the arrangement of the air film holes is redesigned, additional costs will be added. Based on this, in order to give full play to the advantages of TDLAS temperature measurement technology, improve the accuracy and timeliness of combustion monitoring and diagnosis, obtain the actual combustion situation in real time, and reduce manufacturing and operation and maintenance costs, this embodiment describes the annular tube combustion chamber temperature measurement system of the present invention based on the gas turbine annular tube combustion chamber.

[0056] Please note that, see Figure 1 As shown, the inner and outer walls of the combustion chamber shell 10 enclose a combustion chamber inner cavity 100, and a plurality of flame tubes 20 are provided in the combustion chamber inner cavity 100, and the plurality of flame tubes 20 are evenly spaced along the circumferential direction in the combustion chamber inner cavity 100; by arranging a cross-flame tube 30 between two adjacent flame tubes 20, the two adjacent flame tubes 20 are connected through the cross-flame tube 30 for flame transmission; when the gas turbine is operating normally, the high-temperature combustion gas in the cross-flame tube 30 comes from the two flame tubes 20 connected thereto, and the temperature of the high-temperature combustion gas in the cross-flame tube 30 is almost the same as that in the flame tubes 20 on both sides, which can represent the actual combustion temperature in the flame tube 20, so real-time temperature measurement of the cross-flame tube 30 based on TDLAS technology is equivalent to real-time monitoring of the actual combustion temperature in the flame tube 20 in the combustion chamber inner cavity 100. During the combustion process, the working environment and flow field parameters between adjacent flame tubes 20 are almost the same, so the high-temperature combustion gas in the cross-flame tube 30 between the two flame tubes 20 is in dynamic equilibrium, and the temperature in the cross-flame tube 30 measured by the TDLAS temperature measuring component 50 is the average combustion temperature of the two flame tubes 20.

[0057] In this embodiment, a cross-flame tube 30 is provided between two adjacent flame tubes 20, so that the two adjacent flame tubes 20 are connected through the cross-flame tube 30 for flame transmission; windows 40 are provided on both radial sides of the cross-flame tube 30 to provide an optical path for the laser, thereby avoiding opening holes in the flame tube 20, thereby avoiding adverse effects on the combustion flow field, and the temperature of the high-temperature combustion gas in the cross-flame tube 30 is almost the same as the temperature of the high-temperature combustion gas in the flame tubes 20 on both sides, which can represent the actual combustion temperature in the flame tube 20. Compared with the currently commonly used method of inverting the combustion temperature based on the exhaust temperature and turbine blade channel temperature measured by thermocouples, the annular tube combustion chamber temperature measurement system of the present invention can obtain the actual combustion temperature in real time without affecting the flow field and combustion state in the original flame tube, and has a rapid response. There is no "time lag" phenomenon in thermocouple temperature measurement, which is beneficial to combustion diagnosis and temperature measurement, and improves the accuracy and timeliness of combustion monitoring and diagnosis of gas turbine combustion chambers.

[0058] Specifically, the laser path between the laser emitter 51 and the laser receiver 52 is perpendicular to the central axis of the cross-fire tube 30 .

[0059] Please note that, see Figure 2 As shown, the laser path between the laser transmitter 51 and the laser receiver 52 is Figure 2 The center line "L" refers to the straight line; the central axis of the cross-fire tube 30 refers to Figure 2 The center lead "W" indicates the axis; the laser path L between the laser emitter 51 and the laser receiver 52 is perpendicular to the central axis W of the cross-flame tube 30 and intersects at one point, so that the laser can vertically penetrate one of the windows 40 on the cross-flame tube 30 and radially pass through the flow field to be measured in the cross-flame tube 30, and then vertically exit from the other window 40 on the cross-flame tube 30 and be received by the laser receiver 52, which is beneficial to improving the accuracy of measuring the flow field to be measured in the cross-flame tube 30.

[0060] Specifically, the combustion chamber housing 10 includes a first side circumferential wall 11 and a second side circumferential wall 12 , wherein the first side circumferential wall 11 and the second side circumferential wall 12 are radially spaced apart to form the combustion chamber cavity 100 ;

[0061] The laser emitter 51 is disposed on a side of the first side circumferential wall 11 close to the cross-fire tube 30 , and the laser receiver 52 is disposed on a side of the second side circumferential wall 12 close to the cross-fire tube 30 .

[0062] Please note that, see Figure 1As shown, the combustion chamber in this embodiment is an annular combustion chamber structure, and the combustion chamber housing 10 includes a first side circumferential wall 11 and a second side circumferential wall 12, and the first side circumferential wall 11 and the second side circumferential wall 12 are radially spaced apart to form the combustion chamber cavity 100; see Figure 2 As shown, the laser emitter 51 is fixedly arranged on a side of the first side circumferential wall 11 close to the cross-flame tube 30, and the laser receiver 52 is fixedly arranged on a side of the second side circumferential wall 12 close to the cross-flame tube 30; by fixing the TDLAS temperature measuring component 50 on the wall surface of the combustion chamber instead of fixing it on the cross-flame tube 30, on the one hand, the influence of the vibration generated by the combustion pressure pulsation and the rotor rotation on the TDLAS temperature measuring component 50 can be significantly reduced, which is conducive to ensuring the measurement accuracy; on the other hand, due to the presence of high-temperature combustion gas in the cross-flame tube 30, directly arranging the TDLAS temperature measuring component 50 on the cross-flame tube 30 is not conducive to its normal operation, while the wall surface of the combustion chamber is not in direct contact with the flame and the high-temperature combustion gas, which provides favorable conditions for the normal operation of the TDLAS temperature measuring component 50.

[0063] Specifically, the distances between the viewing window 40 on each cross-fire tube 30 and the two ends of the cross-fire tube 30 are equal.

[0064] Optionally, the viewing window 40 on each cross-fire tube 30 is equidistant from both ends of the cross-fire tube 30 , so that the viewing window 40 is located in the middle of the cross-fire tube 30 , which is beneficial to improving the accuracy of measuring the flow field to be measured in the cross-fire tube 30 .

[0065] Specifically, the number of the TDLAS temperature measurement components 50 is P, and P satisfies P=2M+C, wherein M satisfies 3M+C=N, N is the number of the flame tubes 20, M is a positive integer, C is an integer, and 0≤C<3.

[0066] It should be noted that when the annular tube combustion chamber of the gas turbine operates normally, the working environment and flow field parameters between adjacent flame tubes 20 are almost the same. Therefore, the high-temperature gas in the cross-flame tube 30 between the two flame tubes 20 is in dynamic equilibrium, and the temperature in the cross-flame tube 30 measured by the TDLAS temperature measuring component 50 is the average combustion temperature of the two flame tubes 20. The number of the TDLAS temperature measuring components 50 is P, and P satisfies P=2M+C, where M satisfies 3M+C=N, where N is the number of the flame tubes 20, M is a positive integer, C is an integer, and 0≤C<3. By dividing every three adjacent N flame tubes 20 in the annular tube combustion chamber into a unit, the TDLAS temperature measuring components 50 are reasonably arranged in the annular tube combustion chamber. Under the premise of using the minimum number of TDLAS temperature measuring components 50, combustion monitoring can be performed on each flame tube 20. This can not only accurately determine whether the combustion temperature in the flame tube 20 is abnormal and accurately locate the faulty flame tube, which is beneficial to combustion diagnosis and normal operation of the gas turbine, but also significantly reduce manufacturing and operation and maintenance costs.

[0067] Specifically, among the N flame tubes 20 , except for the first flame tube 20 and the Nth flame tube 20 which are not connected to each other, every other two adjacent flame tubes 20 are connected to each other through the cross-fire tube 30 .

[0068] Example 2

[0069] The working method of the annular tube combustion chamber temperature measurement system provided in this embodiment includes:

[0070] S1. Number N flame tubes 20 in sequence from 1 to N in a clockwise direction;

[0071] S2. Divide the flame tubes 20 from the first flame tube 20 in a clockwise direction and from the Nth flame tube 20 in a counterclockwise direction simultaneously into units, and sequentially divide three adjacent flame tubes 20 into one unit. When the number of flame tubes 20 cannot be divided by 3, divide the remaining one or two flame tubes 20 into the last unit.

[0072] S3. A window 40 is provided on each of the two cross-fire tubes 30 in each unit, and a TDLAS temperature measuring assembly 50 is provided corresponding to the window 40;

[0073] S4. Using the first set of the TDLAS temperature measuring components 50 and the second set of the TDLAS temperature measuring components 50 in each unit, locate any flame tube 20 with abnormal temperature in the unit.

[0074] Please note that, please refer to the attached Figure 1As shown, among the N flame tubes 20 of the annular tube combustion chamber, except for the 1st flame tube 20 and the Nth flame tube 20 which are not connected to each other, every other two adjacent flame tubes 20 are connected to each other through the cross-flame tube 30; the annular tube combustion chamber of the gas turbine before the improvement usually needs to arrange flame detectors near the 1st flame tube 20 and the Nth flame tube 20, that is, the two flame tubes 20 that are not connected by the cross-flame tube 30, and monitor whether the flame is transmitted to each flame tube 20 at all times based on the light emitted by the combustion, so as to monitor whether all the flame tubes 20 of the gas turbine are burning normally from the ignition start-up to the shutdown stage. The working method of the annular tube combustion chamber temperature measurement system of the present invention is as follows: in step 2, units are simultaneously divided from the first flame tube 20 in a clockwise direction and from the Nth flame tube 20 in a counterclockwise direction, and three adjacent flame tubes 20 are sequentially divided into one unit. When the number of flame tubes 20 cannot be divided by 3, the remaining one or two flame tubes 20 are divided into the last unit to ensure that both unconnected flame tubes 20 can be monitored. While improving the accuracy and timeliness of combustion monitoring and diagnosis of the gas turbine combustion chamber, the function of the flame detector can be realized, the flame detector is omitted, thereby simplifying the system structure, improving the operating efficiency of the gas turbine, and reducing costs.

[0075] Please note that, see Figure 3 As shown, Figure 3 The number of flame tubes 20 of the annular tube type combustion chamber shown in FIG is eighteen. Figure 3 The annular tube type combustion chamber shown in the figure describes in detail the working method of the annular tube combustion chamber temperature measurement system of the present invention.

[0076] S1. Starting from the flame tube 20 at the top of the combustion chamber 100, the eighteen flame tubes 20 are numbered in sequence from 201 to 218 in a clockwise direction, namely 201, 202, 203, ..., 217, 218;

[0077] S2. Divide the units from the first flame tube 20 in a clockwise direction and from the eighteenth flame tube 20 in a counterclockwise direction simultaneously, and sequentially divide three adjacent flame tubes 20 into one unit, which is exactly six units;

[0078] S3. Windows 40 are provided on the two cross-fire tubes 30 in each unit, and TDLAS temperature measurement assemblies 50 corresponding to the windows 40 are provided. Each set of the TDLAS temperature measurement assemblies 50 includes a laser emitter 51 and a laser receiver 52. The laser emitter 51 and the laser receiver 52 are respectively provided on radial sides of the cross-fire tube 30 and opposite to the windows 40. That is, each unit includes three flame tubes 20, two cross-fire tubes 30, and two sets of the TDLAS temperature measurement assemblies 50.

[0079] S4. Using the first set of the TDLAS temperature measuring components 50 and the second set of the TDLAS temperature measuring components 50 in each unit, locate any flame tube 20 with abnormal temperature in the unit.

[0080] Specifically, in step S4, when the first set of the TDLAS temperature measuring components 50 in a certain unit detects a temperature abnormality, detection is performed through the second set of the TDLAS temperature measuring components 50 in the unit;

[0081] When the temperature measured by the second set of TDLAS temperature measuring components 50 in the unit is normal, the temperature of the flame tube 20 far away from the second set of TDLAS temperature measuring components 50 is abnormal;

[0082] When the temperature measured by the second set of TDLAS temperature measuring components 50 is also abnormal, the temperature of the flame tube 20 located between the first set of TDLAS temperature measuring components 50 and the second set of TDLAS temperature measuring components 50 is abnormal.

[0083] Please note that, see Figure 3As shown, the following describes step S4 by taking the first unit composed of flame tubes numbered 201, 202 and 203 as an example. If it is stipulated that the cross-flame tube 30 between flame tube No. 201 and flame tube No. 202 corresponds to the first set of said TDLAS temperature measuring components 50, and it is stipulated that the cross-flame tube 30 between flame tube No. 202 and flame tube No. 203 corresponds to the second set of said TDLAS temperature measuring components 50, then when the first set of said TDLAS temperature measuring components 50 detects a temperature anomaly, it can be determined that one of the flame tubes connected to the cross-flame tube 30 corresponding to the first set of said TDLAS temperature measuring components 50 has a temperature anomaly, that is, the flame tube No. 201 or the flame tube No. 202 has a temperature anomaly, and at this time, the flame tube with the temperature anomaly is accurately located by the second set of said TDLAS temperature measuring components 50; since the first set of said TDLAS temperature measuring components 50 and the second set of said TDLAS temperature measuring components 50 detect a temperature anomaly, it can be determined that one of the flame tubes connected to the cross-flame tube 30 corresponding to the first set of said TDLAS temperature measuring components 50 has a temperature anomaly, that is, the flame tube No. 201 or the flame tube No. 202 has a temperature anomaly. At this time, the flame tube with the temperature anomaly is accurately located by the second set of said TDLAS temperature measuring components 50; The AS temperature measuring components 50 monitor the flame tube No. 202 located in the middle in real time. Therefore, when the temperature measured by the second set of the TDLAS temperature measuring components 50 is normal, the temperatures of the two flame tubes at both ends of the flame tube 30 corresponding to the second set of the TDLAS temperature measuring components 50 are normal, that is, the temperatures of the flame tube No. 202 and the flame tube No. 203 are normal, while the temperature of the flame tube far away from the second set of the TDLAS temperature measuring components 50 is abnormal, that is, the temperature of the flame tube No. 201 is abnormal or there is a fault; when the temperature measured by the second set of the TDLAS temperature measuring components 50 is also abnormal, the temperature of the flame tube located between the first set of the TDLAS temperature measuring components 50 and the second set of the TDLAS temperature measuring components 50 is abnormal, that is, the temperature of the flame tube No. 202 is abnormal or there is a fault. The positioning principle of the flame tubes with abnormal temperatures of the remaining units is similar to the above principle and will not be repeated here. Through the working method of the annular tube combustion chamber temperature measurement system of the present invention, the real-time monitoring function of all flame tubes can be achieved while using a minimum amount of monitoring equipment.

[0084] Example 3

[0085] See Figure 4 As shown, Figure 4 The number of flame tubes 20 in the annular tube type combustion chamber shown in FIG is twenty-two. Figure 4 The annular tube type combustion chamber shown in the figure describes in detail the working method of the annular tube combustion chamber temperature measurement system of the present invention.

[0086] S1. Starting from the flame tube 20 at the top of the combustion chamber 100, number the twenty-two flame tubes 20 in sequence from 201 to 220 in a clockwise direction, namely 201, 202, 203, ..., 221, 222;

[0087] S2, dividing the units from the first flame tube 20 in a clockwise direction and from the twenty-second flame tube 20 in a counterclockwise direction simultaneously, successively dividing three adjacent flame tubes 20 into one unit, and finally dividing the remaining flame tube numbered 210 into one unit independently;

[0088] S3. Windows 40 are provided on the two cross-fire tubes 30 in each unit, and TDLAS temperature measurement assemblies 50 corresponding to the windows 40 are provided. Each set of the TDLAS temperature measurement assemblies 50 includes a laser emitter 51 and a laser receiver 52. The laser emitter 51 and the laser receiver 52 are respectively provided on radial sides of the cross-fire tube 30 and opposite to the windows 40. That is, except for the flame tube numbered 210 which is independently divided into a unit, each of the remaining units includes three flame tubes 20, two cross-fire tubes 30, and two sets of the TDLAS temperature measurement assemblies 50.

[0089] S4. Using the first set of the TDLAS temperature measuring components 50 and the second set of the TDLAS temperature measuring components 50 in each unit, locate any flame tube 20 with abnormal temperature in the unit.

[0090] Specifically, in step S3 , when the last unit has only one flame tube 20 , the viewing window 40 and the TDLAS temperature measurement component 50 corresponding to the viewing window 40 are provided on any one of the cross-fire tubes 30 on both sides of the flame tube 20 .

[0091] Please note that, see Figure 4 As shown, this embodiment Figure 4The number of flame tubes 20 in the annular tube combustion chamber shown is twenty-two. In step S3, the last unit has only one flame tube, which is numbered 210. Then, the window 40 and the TDLAS temperature measuring component 50 corresponding to the window 40 are set on any one of the cross-flame tubes 30 on both sides of the flame tube No. 210. In this embodiment, the window 40 and the TDLAS temperature measuring component 50 corresponding to the window 40 can be set on the cross-flame tube 30 between the flame tube No. 210 and the flame tube No. 211; if it is specified that the cross-flame tube 30 between the flame tube No. 210 and the flame tube No. 211 corresponds to the first set of the TDLAS temperature measuring components 50, and it is specified that the cross-flame tube 30 between the flame tube No. 211 and the flame tube No. 212 corresponds to the second set of the TDLAS temperature measuring components 50, then when the first set of the TDLAS temperature measuring components 50 detects a temperature abnormality, it can be determined that one of the flame tubes connected to the cross-flame tube 30 corresponding to the first set of the TDLAS temperature measuring components 50 has a temperature abnormality. , that is, there is a temperature abnormality in flame tube No. 210 or flame tube No. 211. At this time, the flame tube with abnormal temperature is accurately located by the second set of the TDLAS temperature measuring components 50; since the first set of the TDLAS temperature measuring components 50 and the second set of the TDLAS temperature measuring components 50 both monitor the flame tube No. 211 located in the middle in real time, therefore, when the temperature measured by the second set of the TDLAS temperature measuring components 50 is normal, the two flame tubes at both ends of the cross-flame tube 30 corresponding to the second set of the TDLAS temperature measuring components 50 are both normal in temperature, that is, the flame tube No. 211 and the flame tube No. 212 are both normal in temperature, while the temperature of the flame tube far away from the second set of the TDLAS temperature measuring components 50 is abnormal, that is, the temperature of the flame tube No. 210 is abnormal or there is a fault; when the temperature measured by the second set of the TDLAS temperature measuring components 50 is also abnormal, the temperature of the flame tube located between the first set of the TDLAS temperature measuring components 50 and the second set of the TDLAS temperature measuring components 50 is abnormal, that is, the temperature of the flame tube No. 211 is abnormal or there is a fault. The principle of locating the flame tubes with abnormal temperatures in the remaining units is similar to the above principle and will not be repeated here. The working method of the annular tube combustion chamber temperature measurement system of the present invention can achieve real-time monitoring of all flame tubes while using a minimum amount of monitoring equipment.

[0092] Example 4

[0093] See Figure 5 As shown, Figure 5 The number of the flame tubes 20 of the annular tube type combustion chamber shown in FIG is twenty. Figure 5 The annular tube type combustion chamber shown in the figure describes in detail the working method of the annular tube combustion chamber temperature measurement system of the present invention.

[0094] S1. Starting from the flame tube 20 at the top of the combustion chamber 100, number the twenty flame tubes 20 in sequence from 201 to 220 in a clockwise direction, namely 201, 202, 203, ..., 219, 220;

[0095] S2, dividing the units from the first flame tube 20 in a clockwise direction and from the twentieth flame tube 20 in a counterclockwise direction simultaneously, successively dividing three adjacent flame tubes 20 into one unit, and finally dividing the remaining two flame tubes numbered 210 and 211 into one unit independently;

[0096] S3. Windows 40 are provided on the two cross-fire tubes 30 in each unit, and TDLAS temperature measurement assemblies 50 corresponding to the windows 40 are provided. Each set of the TDLAS temperature measurement assemblies 50 includes a laser emitter 51 and a laser receiver 52. The laser emitter 51 and the laser receiver 52 are respectively provided on radial sides of the cross-fire tube 30 and opposite to the windows 40. That is, except for the flame tube numbered 210 which is independently divided into a unit, each of the remaining units includes three flame tubes 20, two cross-fire tubes 30, and two sets of the TDLAS temperature measurement assemblies 50.

[0097] S4. Using the first set of the TDLAS temperature measuring components 50 and the second set of the TDLAS temperature measuring components 50 in each unit, locate any flame tube 20 with abnormal temperature in the unit.

[0098] Specifically, in step S3, when the last unit has only two flame tubes 20, the window 40 and the TDLAS temperature measuring component 50 corresponding to the window 40 are set on the cross-flame tube 30 between the two flame tubes 20, and the window 40 and the TDLAS temperature measuring component 50 corresponding to the window 40 are set on any one of the cross-flame tubes 30 on both sides of the two flame tubes 20.

[0099] Please note that, see Figure 5 As shown, this embodiment Figure 5The number of flame tubes 20 in the annular tube combustion chamber shown is twenty. In step S3, the last unit has only two flame tubes, and the two flame tubes are numbered 210 and 211 respectively. In this embodiment, the window 40 and the TDLAS temperature measurement component 50 corresponding to the window 40 can be set on the cross-flame tube 30 between the flame tubes 210 and 211, and the window 40 and the TDLAS temperature measurement component 50 corresponding to the window 40 can be set on the cross-flame tube 30 between the flame tubes 211 and 212. The positioning principle of the flame tube with abnormal temperature in this embodiment is similar to that of the above-mentioned embodiment 3 and will not be repeated here. Through the working method of the annular tube combustion chamber temperature measurement system of the present invention, the real-time monitoring function of all flame tubes can be realized while using a minimum amount of monitoring equipment.

[0100] It should be noted that in actual production, the probability of two adjacent flame tubes in a gas turbine annular combustor failing simultaneously is extremely low. The operating method of the annular combustor temperature measurement system of the present invention is suitable for determining the combustion status of a specific flame tube in each unit and accurately locating the faulty flame tube. Currently, the annular combustors used in gas turbines have no more than thirty flame tubes. The operating method of the annular combustor temperature measurement system of the present invention enables real-time monitoring of all flame tubes while using a minimal amount of monitoring equipment.

[0101] The working method of the annular tube combustion chamber temperature measurement system of the present invention is as follows: N flame tubes 20 are numbered in sequence from 1 to N in a clockwise direction; units are simultaneously divided from the first flame tube 20 in a clockwise direction and from the Nth flame tube 20 in a counterclockwise direction, and three adjacent flame tubes 20 are divided into one unit in sequence; windows 40 are provided on the two cross-flame tubes 30 in each unit, and TDLAS temperature measurement components 50 corresponding to the windows 40 are provided; any flame tube with abnormal temperature in the unit is located by using the first set of the TDLAS temperature measurement components 50 and the second set of the TDLAS temperature measurement components 50 in each unit. On the one hand, while improving the accuracy and timeliness of combustion monitoring and diagnosis of the gas turbine combustion chamber, the function of the flame detector can be realized, the flame detector is omitted, and the system structure is simplified. On the other hand, the faulty flame tube can be accurately located, and the real-time monitoring function of all flame tubes can be realized while using a minimum amount of monitoring equipment.

[0102] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Those skilled in the art will readily appreciate that other variations or modifications based on the above descriptions are possible. It is not necessary and impossible to enumerate all implementation methods here. Obvious variations or modifications arising therefrom remain within the scope of protection of the present invention.

Claims

1. A temperature measurement system for an annular tube combustion chamber, characterized in that: include: A combustion chamber shell (10), wherein the inner and outer walls of the combustion chamber shell (10) enclose an inner combustion chamber cavity (100); a plurality of flame tubes (20) are arranged in the inner combustion chamber cavity (100), and the plurality of flame tubes (20) are evenly spaced along the circumferential direction in the inner combustion chamber cavity (100); and a cross-flame tube (30) is provided between two adjacent flame tubes (20) for flame transmission; Windows (40) are provided on both radial sides of the cross-flame tube (30) and are suitable for providing an optical path for the laser; A TDLAS temperature measurement assembly (50) comprises a laser emitter (51) and a laser receiver (52), wherein the laser emitter (51) and the laser receiver (52) are respectively arranged on both radial sides of the cross-fire tube (30) and are arranged opposite to the viewing window (40); a laser path between the laser emitter (51) and the laser receiver (52) is perpendicular to the central axis of the cross-fire tube (30); In the measuring state, laser light is emitted from the laser emitter (51), passes through one of the windows (40) on the cross-fire tube (30), radially passes through the flow field to be measured in the cross-fire tube (30), and then passes through another window (40) on the cross-fire tube (30) and is received by the laser receiver (52) to measure the combustion temperature in the flame tube (20).

2. The annular tube combustion chamber temperature measurement system according to claim 1, characterized in that: The combustion chamber housing (10) comprises a first side circumferential wall (11) and a second side circumferential wall (12), wherein the first side circumferential wall (11) and the second side circumferential wall (12) are radially spaced apart to form the combustion chamber inner cavity (100); The laser transmitter (51) is arranged on a side of the first side peripheral wall (11) close to the cross-flame tube (30), and the laser receiver (52) is arranged on a side of the second side peripheral wall (12) close to the cross-flame tube (30).

3. The annular tube combustion chamber temperature measurement system according to claim 1, characterized in that: The distances between the viewing window (40) on each cross-fire tube (30) and the two ends of the cross-fire tube (30) are equal.

4. A method for operating the annular tube combustion chamber temperature measurement system according to any one of claims 1 to 3, characterized in that: include: S1. Number N flame tubes (20) in sequence from 1 to N in a clockwise direction; S2, dividing the units from the first flame tube (20) in a clockwise direction and from the Nth flame tube (20) in a counterclockwise direction at the same time, and sequentially dividing three adjacent flame tubes (20) into one unit, and when the number of flame tubes (20) cannot be divided by 3, dividing the remaining one or two flame tubes (20) into the last unit; S3. arranging windows (40) on the two cross-flame tubes (30) in each unit, and arranging TDLAS temperature measurement components (50) corresponding to the windows (40); S4. Using the first set of the TDLAS temperature measurement components (50) and the second set of the TDLAS temperature measurement components (50) in each unit, any flame tube (20) with abnormal temperature in the unit is located.

5. The operating method of the annular tube combustion chamber temperature measurement system according to claim 4, characterized in that: In step S4, when the first set of the TDLAS temperature measuring components (50) in a unit detects a temperature abnormality, detection is performed through the second set of the TDLAS temperature measuring components (50) in the unit; When the temperature measured by the second set of TDLAS temperature measuring components (50) in the unit is normal, the temperature of the flame tube (20) away from the second set of TDLAS temperature measuring components (50) is abnormal; When the temperature measured by the second set of TDLAS temperature measuring components (50) is also abnormal, the temperature of the flame tube (20) located between the first set of TDLAS temperature measuring components (50) and the second set of TDLAS temperature measuring components (50) is abnormal.

6. The operating method of the annular tube combustion chamber temperature measurement system according to claim 4 or 5, characterized in that: In step S3, when the last unit has only one flame tube (20), the viewing window (40) and the TDLAS temperature measurement component (50) corresponding to the viewing window (40) are provided on any one of the cross-fire tubes (30) on both sides of the flame tube (20).

7. The operating method of the annular tube combustion chamber temperature measurement system according to claim 4 or 5, characterized in that: In step S3, when the last unit has only two flame tubes (20), the viewing window (40) and the TDLAS temperature measurement component (50) corresponding to the viewing window (40) are set on the cross-flame tube (30) between the two flame tubes (20), and the viewing window (40) and the TDLAS temperature measurement component (50) corresponding to the viewing window (40) are set on any one of the cross-flame tubes (30) on both sides of the two flame tubes (20).

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