Annular Combustion Chamber Temperature Measurement System and its Working Method

Abstract

This invention relates to the field of gas turbine technology, specifically to an annular combustor temperature measurement system and its operating method. The annular combustor temperature measurement system includes: a combustor shell, comprising a first and second side peripheral walls arranged radially at intervals; a flame tube, comprising a first and second tube wall arranged radially at intervals; a first viewing window on the first tube wall; a second viewing window on the second tube wall; a first support rail fixedly disposed on the first side peripheral wall; a second support rail fixedly disposed on the second side peripheral wall; and a TDLAS temperature measurement assembly, comprising a laser emitter and a laser receiver, wherein the laser emitter is movably disposed on the first support rail, and the laser receiver is disposed on the second support rail to always remain on the same laser path as the laser emitter. The annular combustor temperature measurement system provided by this invention can improve the accuracy and timeliness of combustion monitoring and diagnosis of the annular combustor of a gas turbine.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, and specifically to an annular combustion chamber temperature measurement system and its working method. Background Technology

[0002] Because gas turbine combustors operate at high temperatures for extended periods, there is currently no reliable engineering technology to directly measure their temperature. Existing methods for measuring the temperature of annular gas turbine combustors typically involve monitoring turbine blade passage temperatures and exhaust temperatures using temperature sensors (such as thermocouples) to calculate the combustor temperature – an indirect measurement. However, this indirect method fails to reveal the true combustion conditions inside the combustor, resulting in low accuracy for combustion monitoring and diagnosis. Furthermore, the temperature measurements often exhibit a time lag (thermocouple measurements rely on heat conduction, which requires time), hindering combustion diagnosis and reducing timeliness. Therefore, existing gas turbine combustor temperature measurement methods offer limited accuracy and timeliness for combustion monitoring and diagnosis in annular gas turbine combustors. Summary of the Invention

[0003] Therefore, the technical problem to be solved by the present invention is to overcome the shortcomings of existing gas turbine combustor temperature measurement methods in terms of low accuracy and timeliness of combustion monitoring and diagnosis of gas turbine annular combustors, thereby providing an annular combustor temperature measurement system that can improve the accuracy and timeliness of combustion monitoring and diagnosis of gas turbine annular combustors.

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

[0005] To solve the above-mentioned technical problems, the present invention provides an annular combustion chamber temperature measurement system, comprising:

[0006] The combustion chamber shell includes a first side peripheral wall and a second side peripheral wall that are arranged radially at intervals; the flame tube is disposed between the first side peripheral wall and the second side peripheral wall, and the flame tube includes a first tube wall and a second tube wall that are arranged radially at intervals.

[0007] A first viewing window is opened on the first cylindrical wall; a second viewing window is opened on the second cylindrical wall;

[0008] A first support rail is fixedly disposed on the side of the first side peripheral wall near the flame tube; a second support rail is fixedly disposed on the side of the second side peripheral wall near the flame tube.

[0009] The TDLAS temperature measurement component includes a laser emitter and a laser receiver. The laser emitter is movably mounted on the first support rail to move circumferentially around the flame tube, and the laser receiver is movably mounted on the second support rail to always remain on the same laser path as the laser emitter.

[0010] During the movement of the TDLAS temperature measurement component relative to the flame tube, a laser is emitted from the laser emitter, passes radially through the first viewing window through the flow field to be measured inside the flame tube, and then exits through the second viewing window and is received by the laser receiver to measure the combustion temperature inside the flame tube.

[0011] Optionally, both the first and second windows are annular structures, and the first and second windows are coaxially arranged with the combustion chamber housing.

[0012] Optionally, the annular combustion chamber temperature measurement system further includes:

[0013] The first support slide is slidably disposed on the first support track on one side along the radial direction, and the other side is connected to the laser emitter to drive the laser emitter to move around the flame tube;

[0014] The second support slide is slidably disposed on the second support track along one side in the radial direction, and the other side is connected to the laser receiver so that the laser receiver and the laser emitter always remain on the same laser path.

[0015] Optionally, the annular combustion chamber temperature measurement system further includes:

[0016] A first adjusting bracket is fixedly mounted on the first supporting slide. The side of the first adjusting bracket away from the first supporting slide is connected to the laser emitter. The first adjusting bracket is adapted to adjust the laser emission angle of the laser emitter.

[0017] The second adjustment bracket is fixedly mounted on the second support slide. The side of the second adjustment bracket away from the second support slide is connected to the laser receiver. The second adjustment bracket is adapted to adjust the laser receiving angle of the laser receiver.

[0018] Optionally, a nozzle module is provided inside the flame tube; the laser path between the laser emitter and the laser receiver is always perpendicular to the spray axis of the nozzle module and intersects at a target intersection point, which is located in the downstream region of the nozzle module where combustion is sufficient and / or the region where the flame is fully developed.

[0019] Optionally, the annular combustion chamber temperature measurement system further includes a transition section, one axial end of which is connected to the flame tube, and the other end of which is adapted to be connected to the turbine inlet.

[0020] The transition section includes a first transition wall and a second transition wall arranged radially at intervals. A third viewing window is provided on the first transition wall, and a fourth viewing window is provided on the second transition wall.

[0021] During the movement of the TDLAS temperature measurement component relative to the transition section, a laser is emitted from the laser emitter, passes radially through the third window through the flow field to be measured within the transition section, and then exits through the fourth window and is received by the laser receiver to measure the combustion temperature within the transition section.

[0022] Optionally, the annular combustion chamber temperature measurement system further includes: a third bearing rail, fixedly disposed on the side of the first side peripheral wall near the transition section; and a fourth bearing rail, fixedly disposed on the side of the second side peripheral wall near the transition section.

[0023] The laser transmitter is movably mounted on the third support track to move circumferentially around the transition section, and the laser receiver is movably mounted on the fourth support track to always remain on the same laser path as the laser transmitter.

[0024] The working method of the annular combustion chamber temperature measurement system provided by the present invention includes:

[0025] S1. A TDLAS temperature measurement component is movably installed on the combustion chamber shell to monitor the temperature of the flame tube;

[0026] S2, drive the laser emitter and laser receiver to move synchronously and uniformly along the circumferential direction at the same angular velocity;

[0027] S3. Adjust the angle of the laser emitter and the laser receiver so that the laser path between the laser emitter and the laser receiver is always perpendicular to the direction of fluid movement inside the flame tube.

[0028] S4. The angular velocities of the laser emitter and laser receiver remain constant within a single monitoring cycle. One or more sampling times are set within a single monitoring cycle, and the flow field to be measured inside the flame tube is monitored at each sampling time.

[0029] Optionally, step S1 may further include:

[0030] At least two sets of TDLAS temperature measurement components are installed axially on the combustion chamber shell, and the flame tube temperature and transition section temperature are coupled and measured through the at least two sets of TDLAS temperature measurement components.

[0031] Optionally, in step S1, at least two sets of TDLAS temperature measuring components are circumferentially arranged on the combustion chamber shell, and the same area to be measured is monitored by the at least two sets of TDLAS temperature measuring components, and the TDLAS temperature measuring components are staggered along the axial direction.

[0032] The technical solution of this invention has the following advantages:

[0033] 1. The annular combustion chamber temperature measurement system provided by this invention provides a laser propagation path for the TDLAS temperature measurement component by opening a first viewing window on the first wall of the combustion chamber and a second viewing window on the second wall. By fixing the first and second support rails to the first and second side peripheral walls of the combustion chamber shell respectively, favorable conditions are provided for the normal operation of the TDLAS temperature measurement component. The laser receiver and the laser emitter move circumferentially along the first and second support rails respectively, thereby monitoring the actual temperature of the flow field to be measured inside the combustion chamber in real time, accurately and promptly identifying the specific location of the combustion fault, and determining whether the temperature distribution is uniform. Compared with the previous method of calculating the combustion temperature based on the exhaust temperature and turbine blade channel temperature measured by thermocouples, the annular combustion chamber temperature measurement system of this invention can directly monitor the temperature of the flow field to be measured inside the combustion chamber in real time, with a rapid response and no "time lag" phenomenon in thermocouple temperature measurement. This is beneficial for combustion diagnosis and temperature measurement, improving the accuracy and timeliness of combustion monitoring and diagnosis of the gas turbine combustion chamber.

[0034] 2. The annular combustion chamber temperature measurement system provided by the present invention comprises a first support slide connected to a first support rail, wherein the first support slide moves circumferentially along the first support rail, thereby driving the laser emitter to move around the flame tube; a second support slide is slidably connected to a second support rail, wherein the second support slide moves circumferentially along the second support rail, thereby driving the laser receiver to move circumferentially; the first support slide and the second support slide can be synchronously driven by a motor to move synchronously and uniformly at the same angular velocity in the circumferential direction, thereby ensuring that the laser receiver and the laser emitter always remain on the same laser path and that the laser path is perpendicular to the direction of motion of the flow field to be measured in the flame tube, thereby ensuring the accuracy of the TDLAS temperature measurement component in measuring the temperature of the flow field to be measured in the flame tube.

[0035] 3. The working method of the annular combustion chamber temperature measurement system provided by the present invention involves monitoring the flame tube temperature by movably setting a TDLAS temperature measurement component on the combustion chamber shell; driving a laser emitter and a laser receiver to move synchronously and uniformly along the circumference at the same angular velocity; adjusting the angle of the laser emitter and the laser receiver so that the laser path between the laser emitter and the laser receiver is always perpendicular to the direction of fluid movement in the flame tube; keeping the angular velocity of the laser emitter and the laser receiver constant within a single monitoring cycle; setting one or more sampling times within a single monitoring cycle; monitoring the flow field to be measured in the flame tube at each sampling time; thereby performing 360-degree real-time measurement of the flame tube area of ​​the annular combustion chamber of the gas turbine, which can accurately and timely detect the specific location of combustion faults and determine whether the temperature distribution is uniform, which is beneficial to combustion diagnosis and normal operation of the gas turbine. At the same time, compared with the previous method of indirect temperature measurement through dozens of thermocouples, the working method of the annular combustion chamber temperature measurement system of the present invention can perform 360-degree non-contact direct measurement of the flame tube flow field in the annular combustion chamber by setting only one set of the aforementioned TDLAS temperature measurement component, resulting in lower processing, manufacturing and maintenance costs.

[0036] 4. The working method of the annular combustion chamber temperature measurement system provided by the present invention uses two sets of TDLAS temperature measurement components to simultaneously perform coupled temperature measurement on the flow field to be measured in the flame tube and the flow field to be measured in the transition section, which improves the measurement accuracy and precision, and is more conducive to determining the specific location of the combustion fault and whether the temperature distribution is uniform. It can also be used with one set on standby, that is, only one set of TDLAS temperature measurement components is operated, and the other set of TDLAS temperature measurement components is used as a backup. When the TDLAS temperature measurement component in operation or the bearing slide fails, it is immediately switched to the other set of TDLAS temperature measurement components, thereby significantly improving the reliability and practicality of the TDLAS temperature measurement components. Attached Figure Description

[0037] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0038] Figure 1 This is a radial cross-sectional schematic diagram of the annular combustion chamber temperature measurement system of the present invention in Embodiment 1;

[0039] Figure 2 for Figure 1 A schematic diagram of the axial section of a single nozzle module;

[0040] Figure 3This is a schematic diagram of the axial cross-section of the annular combustion chamber temperature measurement system of the present invention in Embodiment 2;

[0041] Figure 4 This is a schematic diagram illustrating the working principle of the annular combustion chamber temperature measurement system of the present invention in Embodiment 3;

[0042] Figure 5 This is a schematic diagram of the axial cross-section of the annular combustion chamber temperature measurement system of the present invention based on a single nozzle module in Embodiment 4;

[0043] Figure 6 This is a radial cross-sectional schematic diagram of the annular combustion chamber temperature measurement system of the present invention in Example 5;

[0044] Figure 7 for Figure 6 A schematic diagram of the axial section of a single nozzle module.

[0045] Explanation of reference numerals in the attached figures:

[0046] 10. Combustion chamber shell; 11. First side peripheral wall; 12. Second side peripheral wall;

[0047] 20. Flame tube; 200. Nozzle module; 21. First tube wall; 210. First viewing window; 22. Second tube wall; 220. Second viewing window;

[0048] 31. First bearing rail; 311. First bearing slide; 312. First adjusting bracket; 32. Second bearing rail; 321. Second bearing slide; 322. Second adjusting bracket; 33. Third bearing rail; 331. Third bearing slide; 332. Third adjusting bracket; 34. Fourth bearing rail; 341. Fourth bearing slide; 342. Fourth adjusting bracket;

[0049] 40. TDLAS temperature measurement unit; 41. Laser emitter; 42. Laser receiver;

[0050] 50. Transition section; 51. First transition wall; 510. Third viewpoint; 52. Second transition wall; 520. Fourth viewpoint. Detailed Implementation

[0051] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0052] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this 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.

[0053] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0054] Furthermore, 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.

[0055] Example 1

[0056] Combination Figures 1-2 As shown, this embodiment describes the annular combustion chamber temperature measurement system of the present invention in conjunction with the flame tube of the annular combustion chamber. The annular combustion chamber temperature measurement system provided in this embodiment includes:

[0057] Combustion chamber housing 10 includes a first side peripheral wall 11 and a second side peripheral wall 12 arranged radially at intervals; flame tube 20 is disposed between the first side peripheral wall 11 and the second side peripheral wall 12, the flame tube 20 includes a first tube wall 21 and a second tube wall 22 arranged radially at intervals.

[0058] A first window 210 is opened on the first cylindrical wall 21; a second window 220 is opened on the second cylindrical wall 22.

[0059] The first support rail 31 is fixedly disposed on the side of the first side peripheral wall 11 near the flame tube 20; the second support rail 32 is fixedly disposed on the side of the second side peripheral wall 12 near the flame tube 20.

[0060] The TDLAS temperature measurement component 40 includes a laser emitter 41 and a laser receiver 42. The laser emitter 41 is movably mounted on the first support rail 31 to move circumferentially around the flame tube 20. The laser receiver 42 is movably mounted on the second support rail 32 to always remain on the same laser path as the laser emitter 41.

[0061] During the movement of the TDLAS temperature measurement component 40 relative to the flame tube 20, the laser is emitted from the laser emitter 41, passes through the first viewing window 210 radially through the flow field to be measured inside the flame tube 20, and then exits through the second viewing window 220 and is received by the laser receiver 42 to measure the combustion temperature inside the flame tube 20.

[0062] It should be noted that the working principle of the TDLAS temperature measurement component 40 is based on the Tunable Semiconductor Laser Absorption Spectroscopy (TDLAS) principle. Beer-Lambert's law is the foundation of TDLAS temperature measurement technology, which describes the relationship between the intensity of a substance's absorption of a certain monochromatic light and the absorbing substance. Specifically, Beer-Lambert's law states that: when the incident light intensity is I0, after passing through a certain absorption path L in the temperature measurement region, if the laser output wavelength is the same as the center wavelength of a certain absorption spectral line in the gas, the gas molecules will absorb photon energy and undergo an energy level change, transitioning from a low energy level to a high energy level. At this time, the laser energy will also attenuate, and the light intensity becomes I1. The degree of laser intensity attenuation is related to the temperature and pressure of the gas molecules, which can be described by Beer-Lambert's law. Therefore, by measuring the attenuation of the laser intensity, information about the gas molecules being measured can be obtained, and thus information about the environment in which the molecules are located can be derived. TDLAS is simple in principle, easy to operate, and easy to miniaturize. As a non-contact measurement technology, it is not affected by the flow field being measured, and it has high accuracy and reliable measurement results.

[0063] It should be noted that, please refer to Figure 1 As shown, the combustion chamber housing 10 is an annular combustion chamber structure. The combustion chamber housing 10 includes a first side peripheral wall 11 and a second side peripheral wall 12, which are radially spaced to form an inner cavity within the combustion chamber. The flame tube 20 is disposed within the inner cavity of the combustion chamber and is coaxially arranged with the combustion chamber housing 10. The flame tube 20 includes a first cylindrical wall 21 and a second cylindrical wall 22, which are radially spaced. The first cylindrical wall 21 is located within the inner cavity of the combustion chamber near the first side peripheral wall 11, and the second cylindrical wall 22 is located within the inner cavity of the combustion chamber near the second side peripheral wall 12. By opening a first viewing window 210 on the first cylindrical wall 21 and a second viewing window 220 on the second cylindrical wall 22, a laser propagation path is provided for the TDLAS temperature measurement component 40. See [link to relevant documentation]. Figure 2As shown, the central axes of both the first viewing window 210 and the second viewing window 220 are completely aligned with the laser path γ of the TDLAS temperature measurement component 40, which helps improve measurement accuracy. Please refer to... Figure 1 and Figure 2 As shown, the first support track 31 is fixedly disposed on the side of the first side peripheral wall 11 near the flame tube 20, and the second support track 32 is fixedly disposed on the side of the second side peripheral wall 12 near the flame tube 20. Both the first support track 31 and the second support track 32 are annular structures and are coaxially disposed with the combustion chamber housing 10. The laser emitter 41 is movably disposed on the first support track 31 to move circumferentially around the flame tube 20, and the laser receiver 42 is movably disposed on the second support track 32 to always remain on the same laser path as the laser emitter 41. By fixing the first support track 31 and the second support track 32 to the first side peripheral wall 11 and the second side peripheral wall 12 of the combustion chamber housing 10 respectively, the combustion chamber housing 10 can be effectively controlled. Instead of directly fixing the first bearing rail 31 and the second bearing rail 32 to the flame tube 20 and / or the transition section 50, this significantly reduces the impact of combustion pressure pulsation and rotor rotation vibration on the TDLAS temperature measuring component 40, ensuring measurement accuracy. Furthermore, since the flame tube 20 and / or the transition section 50 are in direct contact with the flame and high-temperature gas during operation, their high temperature is detrimental to the normal operation of the TDLAS temperature measuring component 40. However, the first and second side walls 11 and 12 of the combustion chamber shell 10 are not in direct contact with the flame and high-temperature gas during operation. By fixing the first bearing rail 31 and the second bearing rail 32 to the first and second side walls 11 and 12 respectively, favorable conditions are provided for the normal operation of the TDLAS temperature measuring component 40.

[0064] In this embodiment, a laser propagation path is provided for the TDLAS temperature measurement component 40 by opening a first viewing window 210 on the first cylindrical wall 21 and a second viewing window 220 on the second cylindrical wall 22 of the flame tube 20. The first supporting rail 31 and the second supporting rail 32 are respectively fixed to the first side peripheral wall 11 and the second side peripheral wall 12 of the combustion chamber housing 10. The first supporting rail 31 circumferentially orients the laser emitter 41 so that the laser emitter 41 can only move circumferentially relative to the flame tube 20. The second supporting rail 32 circumferentially orients the laser receiver 42 so that the laser receiver 42 can only move circumferentially relative to the flame tube 20. The laser receiver 42 and the laser emitter 42 are connected in a circumferential manner. The laser emitter 41 is synchronously driven to always remain on the same laser path. The laser receiver 42 and the laser emitter 41 move circumferentially along the first support track 31 and the second support track 32, respectively, thereby monitoring the actual temperature of the flow field to be measured inside the flame tube 20 in real time. This allows for accurate and timely detection of the specific location of combustion faults and determination of whether the temperature distribution is uniform. Compared to the previous method of calculating the combustion temperature based on the exhaust temperature and turbine blade channel temperature measured by thermocouples, the annular combustion chamber temperature measurement system of this invention can directly monitor the temperature of the flow field to be measured inside the flame tube 20 in real time with a rapid response and no "time lag" phenomenon in thermocouple temperature measurement. This is beneficial for combustion diagnosis and temperature measurement, improving the accuracy and timeliness of combustion monitoring and diagnosis of the gas turbine combustion chamber. Furthermore, compared to the previous method of indirect temperature measurement using dozens of thermocouples, the annular combustion chamber temperature measurement system of this invention only requires one set of the TDLAS temperature measurement component 40 to perform 360-degree non-contact direct measurement of the flow field to be measured inside the flame tube 20, significantly reducing processing, manufacturing, and maintenance costs.

[0065] Specifically, both the first window 210 and the second window 220 are annular structures, and the first window 210 and the second window 220 are coaxially arranged with the combustion chamber housing 10.

[0066] It should be noted that the first window 210 and the second window 220 are coaxially arranged with the combustion chamber housing 10 and / or the flame tube 20. The first window 210 and the second window 220 are both annular structures, which on the one hand can provide a reliable and effective path for laser propagation during the circumferential movement of the laser emitter 41 and the laser receiver 42 around the flame tube 20, and on the other hand facilitates the adjustment of the optical path during the operation of the laser emitter 41 and the laser receiver 42.

[0067] Specifically, the annular combustion chamber temperature measurement system further includes:

[0068] The first support slide 311 is slidably disposed on the first support track 31 along one side in the radial direction, and the other side is connected to the laser emitter 41 to drive the laser emitter 41 to move around the flame tube 20;

[0069] The second support slide 321 is slidably disposed on the second support track 32 along one side in the radial direction, and the other side is connected to the laser receiver 42 so that the laser receiver 42 and the laser emitter 41 always remain on the same laser path.

[0070] It should be noted that, in this embodiment, the first bearing slide 311 and the second bearing slide 321 can be configured to be motor driven, and the start-stop and running speed of the first bearing slide 311 and / or the second bearing slide 321 can be adjusted by the motor. Please refer to [link to relevant documentation]. Figure 2 As shown, the first support slide 311 is slidably connected to the first support track 31. The first support slide 311 moves circumferentially along the first support track 31, thereby driving the laser emitter 41 to move around the flame tube 20. The second support slide 321 is slidably connected to the second support track 32. The second support slide 321 moves circumferentially along the second support track 32, thereby driving the laser receiver 42 to move circumferentially. The first support slide 311 and the second support slide 321 can be synchronously driven by a motor to move synchronously and uniformly at the same angular velocity in the circumferential direction. This ensures that the laser receiver 42 and the laser emitter 41 are always on the same laser path and that the laser path is perpendicular to the direction of motion of the flow field to be measured in the flame tube 20, thereby ensuring the accuracy of the temperature measurement of the flow field to be measured in the flame tube 20 by the TDLAS temperature measurement component 40. The first bearing track 31 and the first bearing slide 311 can be configured as a double-slide rail structure. Specifically, the first bearing track 31 includes a first slide rail (not shown) and a second slide rail (not shown), and the first bearing slide 311 includes a first sliding part (not shown) and a second sliding part (not shown). The first slide rail and the first sliding part are slidably connected, and the second slide rail and the second sliding part are slidably connected, effectively preventing axial displacement of the first bearing slide 311 and reducing measurement errors caused by vibrations in the annular combustion chamber. Similarly, the second bearing track 32 and the second bearing slide 321 can also be configured as a double-slide rail structure, which will not be elaborated further here. This invention uses the first bearing slide 311 to drive the laser emitter 41 to move circumferentially along the first bearing track 31, and the second bearing slide 321 to drive the laser receiver 42 to move circumferentially along the second bearing track 32, thereby enabling real-time monitoring of the actual temperature of the flame tube 20 in the annular combustion chamber. The response is rapid and there is no lag, which is beneficial for combustion diagnosis.

[0071] Specifically, the annular combustion chamber temperature measurement system further includes:

[0072] The first adjustment bracket 312 is fixedly mounted on the first support slide 311. The side of the first adjustment bracket 312 away from the first support slide 311 is connected to the laser emitter 41. The first adjustment bracket 312 is adapted to adjust the laser emission angle of the laser emitter 41.

[0073] The second adjustment bracket 322 is fixedly mounted on the second support slide 321. The side of the second adjustment bracket 322 away from the second support slide 321 is connected to the laser receiver 42. The second adjustment bracket 322 is adapted to adjust the laser receiving angle of the laser receiver 42.

[0074] It should be noted that, in this embodiment, both the first adjusting bracket 312 and the second adjusting bracket 322 can be configured as a plurality of telescopic rods lifting the base. These telescopic rods can be electrically driven to extend and retract, thereby tilting the base and achieving angle adjustment. The specific structural forms of the first adjusting bracket 312 and the second adjusting bracket 322 can be adjusted according to actual usage and are not limited to the situation described in this embodiment. Please refer to... Figure 2 As shown, a first adjusting bracket 312 is provided between the first supporting slide 311 and the laser emitter 41. One side of the first adjusting bracket 312 is connected to the first supporting slide 311, and the other side is connected to the laser emitter 41. A second adjusting bracket 322 is provided between the second supporting slide 321 and the laser receiver 42. One side of the second adjusting bracket 322 is connected to the second supporting slide 321, and the other side is connected to the laser receiver 42. The control end of the first adjusting bracket 312 can be coupled to the control end of the second adjusting bracket 322, thereby adjusting the angle between the laser emitter 41 and the laser receiver 42 to ensure that the laser emitted by the laser emitter 41 can be received by the laser receiver 42, which is beneficial to ensuring the stability of the combustion diagnosis process.

[0075] Specifically, a nozzle module 200 is provided inside the flame tube 20; the laser path between the laser emitter 41 and the laser receiver 42 is always perpendicular to the spray axis of the nozzle module 200 and intersects at a target intersection point, which is located in the downstream region of the nozzle module 200 where combustion is sufficient and / or the region where the flame is fully developed.

[0076] It should be noted that, please refer to Figure 2 As shown, the laser path between the laser emitter 41 and the laser receiver 42 refers to... Figure 2The straight line pointed to by the center line "γ"; the injection axis of the nozzle module 200 refers to Figure 2 The straight line indicated by the center line "β". The laser path γ between the laser emitter 41 and the laser receiver 42 is always perpendicular to the jet axis β of the nozzle module 200 and intersects at a target intersection point P. The target intersection point P is located in the downstream region of the nozzle module 200 where combustion is sufficient and / or the region where the flame is fully developed, thereby ensuring the accuracy of the measurement results.

[0077] It should be noted that, in the specific implementation process, shock-absorbing pads can be provided at the connection points between the first bearing rail 31 and the first side wall 11, between the second bearing rail 32 and the second side wall 12, between the first adjusting bracket 312 and the first bearing slide 311, between the second adjusting bracket 322 and the second bearing slide 321, between the laser emitter 41 and the first adjusting bracket 312, and between the laser receiver 42 and the second adjusting bracket 322, so as to reduce the measurement error caused by vibration.

[0078] Example 2

[0079] Combination Figure 3 As shown, this embodiment describes the annular combustion chamber temperature measurement system of the present invention in conjunction with the transition section of the annular combustion chamber.

[0080] Specifically, the annular combustion chamber temperature measurement system further includes a transition section 50, one axial end of which is connected to the flame tube 20, and the other end is adapted to be connected to the turbine inlet.

[0081] The transition section 50 includes a first transition wall 51 and a second transition wall 52 arranged radially at intervals. A third window 510 is provided on the first transition wall 51, and a fourth window 520 is provided on the second transition wall 52.

[0082] During the movement of the TDLAS temperature measurement component 40 relative to the transition section 50, a laser is emitted from the laser emitter 41, passes through the third window 510 radially through the flow field to be measured in the transition section 50, and then exits from the fourth window 520 and is received by the laser receiver 42 to measure the combustion temperature in the transition section 50.

[0083] Specifically, the annular combustion chamber temperature measurement system further includes: a third bearing rail 33, which is fixedly disposed on the side of the first side peripheral wall 11 near the transition section 50; and a fourth bearing rail 34, which is fixedly disposed on the side of the second side peripheral wall 12 near the transition section 50.

[0084] The laser emitter 41 is movably mounted on the third support track 33 to move circumferentially around the transition section 50, and the laser receiver 42 is movably mounted on the fourth support track 34 to always remain on the same laser path as the laser emitter 41.

[0085] It should be noted that the annular combustion chamber temperature measurement system of this invention can not only monitor the combustion temperature inside the flame tube in real time, but also the gas temperature in the transition section region in real time. Since the transition section outlet is connected to the turbine inlet, the turbine blade inlet temperature can be directly obtained, which is beneficial for determining the operating status of the turbine blades. Please refer to [link to relevant documentation]. Figure 3 As shown, the third support track 33 is slidably connected to the third support slide 331. The laser emitter 41 is disposed on the third support slide 331. The third support slide 331 moves circumferentially along the third support track 33, thereby driving the laser emitter 41 to move around the transition section 50. The fourth support track 34 is slidably connected to the fourth support slide 341. The laser receiver 42 is disposed on the fourth support slide 341. The fourth support slide 341 moves circumferentially along the fourth support track 34, thereby driving the laser receiver 42 to move circumferentially. The third support slide 331 and the fourth support slide 341 can be synchronously driven by a motor to move synchronously and uniformly along the circumferential direction at the same angular velocity, so that the laser emitter 41 and the laser receiver 42 always remain on the same laser path and the laser path is perpendicular to the direction of motion of the flow field to be measured in the transition section 50, thereby ensuring the accuracy of the temperature measurement of the flow field to be measured in the transition section 50 by the TDLAS temperature measurement component 40. The present invention uses a third support slide 331 to drive the laser emitter 41 to move circumferentially along the third support track 33 and a fourth support slide 341 to drive the laser receiver 42 to move circumferentially along the fourth support track 34, thereby real-time monitoring of the actual temperature of the transition section 50 in the annular combustion chamber. The response is rapid and there is no lag, which is beneficial for combustion diagnosis.

[0086] It should be noted that, please refer to Figure 3As shown, a third adjusting bracket 332 is provided between the third supporting slide 331 and the laser emitter 41. One side of the third adjusting bracket 332 is connected to the third supporting slide 331, and the other side is connected to the laser emitter 41. A fourth adjusting bracket 342 is provided between the fourth supporting slide 341 and the laser receiver 42. One side of the fourth adjusting bracket 342 is connected to the fourth supporting slide 341, and the other side is connected to the laser receiver 42. The control end of the third adjusting bracket 332 can be coupled to the control end of the fourth adjusting bracket 342 to adjust the angle between the laser emitter 41 and the laser receiver 42, ensuring that the laser emitted by the laser emitter 41 can be received by the laser receiver 42, which is beneficial to ensuring the stability of the combustion diagnosis process.

[0087] Example 3

[0088] Please see Figure 4 As shown, this embodiment describes the working method of the annular combustion chamber temperature measurement system of the present invention based on the flame tube of the annular combustion chamber and taking a single set of the TDLAS temperature measurement component 40 as an example.

[0089] The working method of the annular combustion chamber temperature measurement system provided in this embodiment includes:

[0090] S1. A TDLAS temperature measurement component 40 is movably installed on the combustion chamber shell 10 to monitor the temperature of the flame tube 20;

[0091] S2, drive the laser emitter 41 and the laser receiver 42 to move synchronously and uniformly along the circumferential direction at the same angular velocity;

[0092] S3. Adjust the angle of the laser emitter 41 and the laser receiver 42 so that the laser path between the laser emitter 41 and the laser receiver 42 is always perpendicular to the direction of fluid movement in the flame tube 20.

[0093] S4. The angular velocities of the laser emitter 41 and the laser receiver 42 remain constant within a single monitoring cycle. One or more sampling times are set within a single monitoring cycle, and the flow field to be measured in the flame tube 20 is monitored at each sampling time.

[0094] It should be noted that the specific arrangement of the TDLAS temperature measurement component 40 on the combustion chamber housing 10 in step S1 has been detailed in the above embodiments and will not be repeated here. In step S2, the laser emitter 41 can be driven by the first support slide 311 and move circumferentially along the first support track 31, and the laser receiver 42 can be driven by the second support slide 321 and move circumferentially along the second support track 32. The moving speed of the laser emitter 41 and the laser receiver 42 during circumferential movement can be adjusted but should not be too large. Within one monitoring cycle, that is, during the period when the first support slide 311 and the second support slide 321 have just completed one circumferential movement, the angular velocity of the first support slide 311 and the second support slide 321 must remain constant. Only when entering the next monitoring cycle can the angular velocity of the first support slide 311 and the second support slide 321 be changed, thereby ensuring the measurement accuracy and result accuracy within a single monitoring cycle. In step S3, the emission angle of the laser emitter 41 can be adjusted by the first adjusting bracket 312, and the receiving angle of the laser receiver 42 can be adjusted by the second adjusting bracket 322. By coupling the control end of the first adjusting bracket 312 with the control end of the second adjusting bracket 322, the laser path between the laser emitter 41 and the laser receiver 42 is always perpendicular to the direction of fluid movement within the flame tube 20, ensuring the accuracy of the measurement results. In step S4, please refer to... Figure 4 As shown, within a monitoring cycle, at the initial time t1, the laser emitter 41 and the laser receiver 42 are located at the twelve o'clock position of the radial section of the combustion chamber housing 10. From time t1 to t2, the laser emitter 41 and the laser receiver 42 move from the twelve o'clock position to the nine o'clock position of the radial section of the combustion chamber housing 10. From time t2 to t3, the laser emitter 41 and the laser receiver 42 move from the nine o'clock position to the six o'clock position of the radial section of the combustion chamber housing 10. From time t3 to t4... At time t1, the laser emitter 41 and the laser receiver 42 move from the six o'clock position to the three o'clock position in the radial section of the combustion chamber housing 10. At time t4 to t5, the laser emitter 41 and the laser receiver 42 move from the three o'clock position to the twelve o'clock position in the radial section of the combustion chamber housing 10. Then, the real-time monitoring continues for the next cycle. The circumferential movement is repeated in this manner. The time intervals from time t1 to time t2, from time t2 to time t3, from time t3 to time t4, and from time t4 to time t5 are all equal.

[0095] It should be noted that the previous method of calculating the combustion temperature from the exhaust temperature and turbine blade passage temperature measured by thermocouples required dozens of thermocouples to be evenly arranged circumferentially along the blade passage and flue. Since there were angular intervals between adjacent thermocouples, it was impossible to measure the flow field under test in 360 degrees. This made it difficult to detect uneven temperature distribution or combustion faults between adjacent thermocouples. The working method of the annular combustion chamber temperature measurement system of this invention involves: movably setting the TDLAS temperature measurement component 40 on the combustion chamber shell 10 to monitor the temperature of the flame tube 20; driving the laser emitter 41 and laser receiver 42 to move synchronously and uniformly along the circumferential direction at the same angular velocity; adjusting the angle of the laser emitter 41 and laser receiver 42 so that the laser path between them is always perpendicular to the direction of fluid movement within the flame tube 20; keeping the angular velocity of the laser emitter 41 and laser receiver 42 constant within a single monitoring cycle; and setting one or more sampling times within a single monitoring cycle. The flow field within the flame tube 20 is monitored at each sampling moment, thereby enabling 360-degree real-time measurement of the flame tube region of the gas turbine annular combustion chamber. This allows for accurate and timely detection of the specific location of combustion faults and assessment of temperature distribution uniformity, which is beneficial for combustion diagnosis and normal operation of the gas turbine. Furthermore, compared to the previous method of indirect temperature measurement using dozens of thermocouples, the working method of the annular combustion chamber temperature measurement system of this invention can perform 360-degree non-contact direct measurement of the flame tube flow field within the annular combustion chamber by setting only one set of the aforementioned TDLAS temperature measurement component 40, resulting in lower processing, manufacturing, and maintenance costs.

[0096] Example 4

[0097] Please see Figure 5 As shown, this embodiment, based on the two structures of the annular combustion chamber—the flame tube and the transition section—and using multiple sets of the aforementioned TDLAS temperature measurement components 40 to simultaneously couple and measure the temperature of the flame tube and the transition section, illustrates the working method of the annular combustion chamber temperature measurement system of the present invention. The specific steps are as follows:

[0098] S1. Two sets of TDLAS temperature measuring components 40 are axially arranged on the combustion chamber shell 10. One set of TDLAS temperature measuring components 40 is used to measure the temperature inside the flame tube 20, and the other set of TDLAS temperature measuring components 40 is used to measure the temperature in the transition section 50 area. The control terminals of the two sets of TDLAS temperature measuring components 40 are coupled.

[0099] S2, drive the laser emitter 41 and the laser receiver 42 to move synchronously and uniformly along the circumferential direction at the same angular velocity;

[0100] S3. Adjust the angle of the laser emitter 41 and the laser receiver 42 so that the laser path between the laser emitter 41 and the laser receiver 42 is always perpendicular to the direction of fluid movement in the flame tube 20 and / or the transition section 50.

[0101] S4. The angular velocities of the laser emitter 41 and the laser receiver 42 remain constant within a single monitoring cycle. One or more sampling times are set within a single monitoring cycle, and the flow field to be measured in the flame tube 20 is monitored at each sampling time.

[0102] It should be noted that in step S1, the control terminals of the two sets of TDLAS temperature measuring components 40 are coupled, and the control terminals of the bearing slide and the adjusting bracket of the two sets of TDLAS temperature measuring components 40 are also coupled. The specific arrangement of the two sets of TDLAS temperature measuring components 40 on the combustion chamber housing 10 has been given in detail in the above embodiments one and two, and will not be repeated here.

[0103] In this embodiment, two sets of TDLAS temperature measurement components 40 are used to simultaneously perform coupled temperature measurement on the flow field to be measured in the flame tube 20 and the flow field to be measured in the transition section 50, which improves the measurement accuracy and precision, and is also more conducive to determining the specific location of the combustion fault and whether the temperature distribution is uniform. Alternatively, one set of TDLAS temperature measurement components 40 can be used as a backup, that is, only one set of TDLAS temperature measurement components 40 is operated, and the other set of TDLAS temperature measurement components 40 is used as a backup. When the TDLAS temperature measurement component 40 in operation or the support slide fails, it is immediately switched to the other set of TDLAS temperature measurement components 40, thereby significantly improving the reliability and practicality of the TDLAS temperature measurement components 40.

[0104] Example 5

[0105] Please see Figure 6 and Figure 7 As shown, this embodiment describes the operation of the annular combustion chamber temperature measurement system of the present invention based on the flame tube of the annular combustion chamber and using multiple sets of the aforementioned TDLAS temperature measurement components 40 as examples. The specific steps are as follows:

[0106] S1. Three sets of TDLAS temperature measuring components 40 are circumferentially arranged on the combustion chamber shell 10. The same area to be measured is monitored by the three sets of TDLAS temperature measuring components 40, and the three sets of TDLAS temperature measuring components 40 are staggered along the axial direction.

[0107] S2, drive the laser emitter 41 and the laser receiver 42 to move synchronously and uniformly along the circumferential direction at the same angular velocity;

[0108] S3. Adjust the angle of the laser emitter 41 and the laser receiver 42 so that the laser path between the laser emitter 41 and the laser receiver 42 is always perpendicular to the direction of fluid movement in the flame tube 20.

[0109] S4. The angular velocities of the laser emitter 41 and the laser receiver 42 remain constant within a single monitoring cycle. One or more sampling times are set within a single monitoring cycle, and the flow field to be measured in the flame tube 20 is monitored at each sampling time.

[0110] It should be noted that when it is necessary to promptly obtain information about the combustion status within the flame tube or transition section, or to rapidly monitor each flame tube or transition section (i.e., shorten the monitoring cycle of the TDLAS temperature measurement component 40), but the moving speed of the supporting slide cannot be increased, multiple sets of TDLAS temperature measurement components 40 can be set. These multiple sets of TDLAS temperature measurement components 40 are evenly arranged circumferentially and staggered axially, thereby enabling simultaneous monitoring of the same area to be measured. In this embodiment, in step S1, please refer to... Figure 6 As shown, three sets of TDLAS temperature measuring components 40 are circumferentially arranged on the combustion chamber shell 10. The three sets of TDLAS temperature measuring components 40 move circumferentially at the same speed, and the circumferential angle between any two adjacent sets of TDLAS temperature measuring components 40 is 120 degrees. This shortens the monitoring cycle to one-third of the original measurement time using a single set of TDLAS temperature measuring components 40. The three sets of TDLAS temperature measuring components 40 are evenly spaced circumferentially. This avoids interference caused by close proximity, facilitating the movement of the support slide along the support track. Furthermore, it ensures that the time interval for monitoring each area is the same when multiple sets of TDLAS temperature measuring components 40 move at the same speed, facilitating simultaneous online monitoring by multiple sets of TDLAS temperature measuring components 40. Please refer to [link to relevant documentation]. Figure 7 As shown, the three sets of TDLAS temperature measurement components 40 are staggered along the axial direction to prevent the laser beams emitted by different TDLAS temperature measurement components 40 from intersecting in the flow field to be measured, thus avoiding affecting the measurement effect.

[0111] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A temperature measurement system for an annular combustion chamber, characterized in that, include: The combustion chamber shell (10) includes a first side peripheral wall (11) and a second side peripheral wall (12) arranged radially at intervals; the flame tube (20) is disposed between the first side peripheral wall (11) and the second side peripheral wall (12), and the flame tube (20) includes a first tube wall (21) and a second tube wall (22) arranged radially at intervals. A first viewing window (210) is opened on the first cylindrical wall (21); a second viewing window (220) is opened on the second cylindrical wall (22); The first support rail (31) is fixedly disposed on the side of the first side wall (11) near the flame tube (20); the second support rail (32) is fixedly disposed on the side of the second side wall (12) near the flame tube (20); The TDLAS temperature measurement component (40) includes a laser emitter (41) and a laser receiver (42). The laser emitter (41) is movably mounted on the first support rail (31) to move circumferentially around the flame tube (20). The laser receiver (42) is movably mounted on the second support rail (32) to always remain on the same laser path as the laser emitter (41). During the movement of the TDLAS temperature measurement component (40) relative to the flame tube (20), the laser is emitted from the laser emitter (41), passes through the first window (210) radially through the flow field to be measured in the flame tube (20), and then exits from the second window (220) and is received by the laser receiver (42) to measure the combustion temperature in the flame tube (20).

2. The annular combustion chamber temperature measurement system according to claim 1, characterized in that, Both the first window (210) and the second window (220) are annular structures, and the first window (210) and the second window (220) are coaxially arranged with the combustion chamber housing (10).

3. The annular combustion chamber temperature measurement system according to claim 1, characterized in that, Also includes: The first support slide (311) is slidably disposed on the first support track (31) on one side in the radial direction, and the other side is connected to the laser emitter (41) to drive the laser emitter (41) to move around the flame tube (20); The second support slide (321) is slidably disposed on the second support track (32) along one side in the radial direction, and the other side is connected to the laser receiver (42) so that the laser receiver (42) and the laser emitter (41) always remain on the same laser path.

4. The annular combustion chamber temperature measurement system according to claim 3, characterized in that, Also includes: The first adjustment bracket (312) is fixedly mounted on the first support slide (311). The side of the first adjustment bracket (312) away from the first support slide (311) is connected to the laser emitter (41). The first adjustment bracket (312) is adapted to adjust the laser emission angle of the laser emitter (41). The second adjustment bracket (322) is fixedly mounted on the second support slide (321). The side of the second adjustment bracket (322) away from the second support slide (321) is connected to the laser receiver (42). The second adjustment bracket (322) is adapted to adjust the laser receiving angle of the laser receiver (42).

5. The annular combustion chamber temperature measurement system according to claim 1, characterized in that, The flame tube (20) is provided with a nozzle module (200); the laser path between the laser emitter (41) and the laser receiver (42) is always perpendicular to the spray axis of the nozzle module (200) and intersects at a target intersection point, which is located in the downstream area of ​​the nozzle module (200) where combustion is sufficient and / or the area where the flame is fully developed.

6. The annular combustion chamber temperature measurement system according to any one of claims 1-5, characterized in that, It also includes a transition section (50), one axial end of which is connected to the flame tube (20), and the other end is adapted to be connected to the turbine inlet; The transition section (50) includes a first transition wall (51) and a second transition wall (52) arranged radially at intervals. A third window (510) is provided on the first transition wall (51), and a fourth window (520) is provided on the second transition wall (52). During the movement of the TDLAS temperature measurement component (40) relative to the transition section (50), a laser is emitted from the laser emitter (41), passes through the third window (510) radially through the flow field to be measured in the transition section (50), and then exits from the fourth window (520) and is received by the laser receiver (42) to measure the combustion temperature in the transition section (50).

7. The annular combustion chamber temperature measurement system according to claim 6, characterized in that, It also includes: a third bearing rail (33), which is fixedly disposed on the side of the first side wall (11) near the transition section (50); and a fourth bearing rail (34), which is fixedly disposed on the side of the second side wall (12) near the transition section (50). The laser emitter (41) is movably mounted on the third support track (33) to move circumferentially around the transition section (50), and the laser receiver (42) is movably mounted on the fourth support track (34) to always remain on the same laser path as the laser emitter (41).

8. A method for operating an annular combustion chamber temperature measurement system, characterized in that, The annular combustion chamber temperature measurement system according to any one of claims 1 to 7 further includes the following steps: S1. A TDLAS temperature measurement component (40) is movably installed on the combustion chamber shell (10) to monitor the temperature of the flame tube (20); S2, drive the laser emitter (41) and laser receiver (42) to move synchronously and uniformly along the circumferential direction at the same angular velocity; S3. Adjust the angle of the laser emitter (41) and the laser receiver (42) so that the laser path between the laser emitter (41) and the laser receiver (42) is always perpendicular to the direction of fluid movement in the flame tube (20); S4. The angular velocities of the laser emitter (41) and the laser receiver (42) remain constant during a single monitoring cycle. One or more sampling times are set during a single monitoring cycle, and the flow field to be measured in the flame tube (20) is monitored at each sampling time.

9. The operating method of the annular combustion chamber temperature measurement system according to claim 8, characterized in that, Step S1 also includes: At least two sets of TDLAS temperature measurement components (40) are arranged axially on the combustion chamber shell (10) to couple the temperature of the flame tube (20) and the temperature of the transition section (50) through the at least two sets of TDLAS temperature measurement components (40).

10. The operating method of the annular combustion chamber temperature measurement system according to claim 8 or 9, characterized in that, In step S1, at least two sets of TDLAS temperature measuring components (40) are circumferentially arranged on the combustion chamber shell (10) to monitor the same area to be measured by at least two sets of TDLAS temperature measuring components (40), and the TDLAS temperature measuring components (40) are staggered along the axial direction.

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