Method and system for adjusting combustion in a gas turbine

Abstract

The present invention provides a method and system for adjusting the combustion of a gas turbine. The method comprises the following steps: collecting the operating data of the gas turbine, and the controller calculating the design installation angle θ of the swirl blade according to the operating data. i ,θ i =θ0+θ(x), θ0 is the initial design installation angle of the swirl blade, and x is the operating data of the gas turbine; the swirl blade is hinged to the combustion chamber body through a hinge shaft; the controller controls the motion actuator to drive the swirl blade to rotate around the hinge shaft until the actual installation angle of the swirl blade reaches the designed installation angle. The system includes a swirl blade installed on the combustion chamber body, a motion actuator connected to the swirl blade, a controller connected to the motion actuator in communication, and a sensor connected to the controller in communication, the sensor is used to detect the operating state of the gas turbine, the swirl blade is hinged to the combustion chamber body through a hinge shaft, and the motion actuator can drive the swirl blade to rotate around the hinge shaft.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a method and a system for adjusting combustion of a gas turbine. Background Art

[0002] In a gas turbine, an independent component is required, the combustion chamber is dedicated to the chemical reaction of the working fluid (including fuel oil or gas). In view of the high air flow velocity in the gas turbine combustion chamber, in order to ensure the thermal intensity per unit volume, certain measures need to be taken, namely, to set up a flame stabilization mechanism. Usually, a swirl device is set in the burner to provide a tangential velocity perpendicular to the mainstream direction of the air flow, forming a negative pressure zone inside the combustion chamber, entraining the air flow, increasing the stroke of the fuel working fluid, and prolonging the reaction time, providing a basis for the full reaction of the working fluid. In view of the increasingly stringent requirements for gas turbine emissions (NOx) worldwide, the air and fuel mixing mode inside the combustion chamber is basically a lean premixed state. In this mode, problems such as combustion instability, flashback, and flameout are prone to occur, which poses a great challenge to combustion adjustment.

[0003] At present, the most basic means of regulating the operating state of a gas turbine combustion system is to change the fuel supply and air supply to the combustion chamber. For example, based on the change in gas turbine load, the fuel flow entering the combustion chamber is adjusted to adjust the corresponding heat intensity per unit volume. For example, Mitsubishi Hitachi Power Systems, Ltd. has applied for many patents on modal changes in fuel regulation (such as CN 104169651 B and CN 103225822 B).

[0004] At the same time, numerous theoretical studies and experiments have proved (Lin Yuzhen, Xu Quanhong, Liu Gaoen. Gas Turbine Combustion Chamber) that, when the fuel and air ratio remains constant, changing the burner swirl intensity will affect the flow field organization and fuel distribution at the outlet to a certain extent, thereby affecting the flame morphology, combustion emissions and combustion stability.

[0005] Usually, the swirl angle of the swirl blades in the gas turbine burner is kept fixed in the design value, which means that under the design conditions, the burner outlet flame is the foreseeable optimal solution, but when the operating conditions change, it cannot be adjusted again. The gas turbine combustion system needs to face problems such as poor combustion stability and increased emissions due to deviations from the operating conditions.

[0006] To solve the above problems, swirl-stage arrangement (including axial stage and radial stage) can be used to solve the problem of changes in combustion mode adjustment under different working conditions, such as GE's DLN series and Siemens' ULN combustion system. However, due to the geometric size and structural requirements, the adjustable modes of the staged arrangement are limited. At the same time, the step-like changes in the combustion mode caused by mode switching are likely to cause problems such as reduced combustion stability and increased emissions. Summary of the invention

[0007] In view of the above-mentioned shortcomings of the prior art, the technical problem to be solved by the present invention is to provide a method for adjusting the combustion of a gas turbine, which method can improve the combustion stability of the gas turbine.

[0008] To achieve the above object, the present invention provides a method for adjusting combustion of a gas turbine, comprising the following steps:

[0009] Collect the operating data of the gas turbine, and the controller calculates the design installation angle θ of the swirl blades based on the operating data i ,θ i =θ 0 +θ(x),θ 0 is the initial design installation angle of the swirl blade, and x is the operating data of the gas turbine; the swirl blade is hinged to the combustion chamber body through a hinge shaft;

[0010] The controller controls the motion actuator to move, and the motion actuator drives the swirl blade to rotate around the hinge shaft until the actual installation angle of the swirl blade reaches the designed installation angle.

[0011] Furthermore, the sensor collects operating data x of the gas turbine and feeds the operating data x back to the controller.

[0012] Furthermore, the dynamic pressure sensor collects the pressure p in the combustion chamber and feeds p back to the controller, and the combustion temperature sensor collects the temperature t in the combustion chamber. B , and t B Feedback to the controller, the controller calculates the design installation angle θ of the swirl blade i ,θ i =θ 0 +θ(t B ,p).

[0013] Furthermore, the intake air temperature sensor collects the intake air temperature T 0 , and T 0 Feedback to the controller, the exhaust temperature sensor collects the exhaust temperature T of the gas turbine 1 , and T 1Feedback to the controller, the load sensor collects the load P of the gas turbine and feeds P back to the controller, the dynamic pressure sensor collects the pressure p in the combustion chamber and feeds p back to the controller, and the combustion temperature sensor collects the temperature t in the combustion chamber B , and t B Feedback to the controller, the component sensor collects the fuel component s in the combustion chamber and feeds s back to the controller, and the controller calculates the design installation angle θ of the swirl blade i ,θ i =θ 0 +θ 1 (P)+θ 2 (T 0 )+θ 3 (T 1 )+θ 4 (t B ,p)+θ 5 (s).

[0014] As described above, the method for adjusting gas turbine combustion according to the present invention has the following beneficial effects:

[0015] The method for adjusting the combustion of a gas turbine in the present invention calculates the design installation angle θ of the swirl blade according to the operating data of the gas turbine. i The swirl blades are driven to rotate around the hinge shaft through the motion actuator until the actual installation angle of the swirl blades reaches the designed installation angle, so that the installation angle of the swirl blades can be adjusted according to the operating state of the gas turbine, coupled with the fuel and air ratio, to ensure the organization of the appropriate combustion flow field in the combustion chamber, and then realize the stepless adjustment of the combustion mode, and realize stable combustion under variable working conditions, and reduce the formation and emission of harmful substances. The method of the present invention effectively improves the stability of the combustion of the gas turbine.

[0016] Another technical problem to be solved by the present invention is to provide a system for adjusting the combustion of a gas turbine, which can improve the combustion stability of the gas turbine.

[0017] To achieve the above-mentioned purpose, the present invention provides a system for adjusting the combustion of a gas turbine, comprising a swirl blade installed on a combustion chamber body, a motion actuator connected to the swirl blade, a controller connected to the motion actuator for communication, and a sensor connected to the controller for communication, wherein the sensor is used to detect the operating state of the gas turbine, the swirl blade is hinged to the combustion chamber body through a hinge shaft, and the motion actuator can drive the swirl blade to rotate around the hinge shaft.

[0018] Furthermore, the motion execution mechanism is a crank-connecting rod mechanism.

[0019] Furthermore, there are multiple swirl blades, and all of the swirl blades are evenly distributed along the circumference of the combustion chamber body.

[0020] Furthermore, the controller includes an information acquisition module, and the information acquisition module is communicatively connected to the sensor.

[0021] Further, the sensor includes an intake temperature sensor installed at the inlet of the compressor, an exhaust temperature sensor installed at the exhaust port of the gas turbine, a load sensor installed on the gas turbine, or a component sensor installed in the combustion chamber.

[0022] Further, the sensor includes a combustion temperature sensor installed in the combustion chamber and a dynamic pressure sensor installed in the combustion chamber.

[0023] As described above, the system for adjusting gas turbine combustion according to the present invention has the following beneficial effects:

[0024] The working principle of the system for adjusting the combustion of the gas turbine in the present invention is as follows: the sensor detects the operating state of the gas turbine and feeds back the detected operating data of the gas turbine to the controller. The controller controls the action of the motion actuator according to the operating state of the gas turbine, so as to drive the swirl blades to rotate around the hinge shaft through the motion actuator until the actual installation angle of the swirl blades reaches the set requirement, so that the actual installation angle of the swirl blades can be adjusted steplessly according to the operating state of the gas turbine to ensure that a proper flow field is formed in the combustion chamber, thereby ensuring stable combustion even when the gas turbine operates under variable conditions, thereby improving the stability of the combustion of the gas turbine and reducing the formation and emission of harmful substances during combustion. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the structure of the system for adjusting the combustion of a gas turbine in the present invention.

[0026] Figure 2 It is a schematic diagram of the installation structure of the swirl blades in the present invention.

[0027] Figure 3 It is a schematic diagram of the connection structure between the swirl blades and the motion actuator in the present invention.

[0028] Figure 4 It is a structural schematic diagram of the motion execution mechanism in the present invention.

[0029] Component number description

[0030] 1 Swirl blade 53 Intake air temperature sensor

[0031] 2 Articulated shaft 54 ​​Exhaust temperature sensor

[0032] 3 Combustion chamber 55 Load sensor

[0033] 31 Combustion chamber body 56 Component sensor

[0034] 4 Motion actuator 6 Controller

[0035] 5 Sensor 7 Compressor

[0036] 51 Dynamic pressure sensor 8 Turbine

[0037] 52 Combustion temperature sensor DETAILED DESCRIPTION

[0038] The following is a description of the implementation of the present invention by means of specific embodiments. Those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification.

[0039] It should be noted that the structures, proportions, sizes, etc. illustrated in the drawings of this specification are only used to match the contents disclosed in the specification for people familiar with this technology to understand and read, and are not used to limit the limiting conditions for the implementation of the present invention, so they have no substantial technical significance. Any modification of the structure, change in the proportion relationship, or adjustment of the size should still fall within the scope of the technical content disclosed by the present invention without affecting the effects and purposes that can be achieved by the present invention. At the same time, the terms such as "upper", "lower", "left", "right", "middle" and "one" quoted in this specification are only for the convenience of description, and are not used to limit the scope of the implementation of the present invention. The change or adjustment of their relative relationship should also be regarded as the scope of the implementation of the present invention without substantially changing the technical content.

[0040] like Figures 1 to 4 As shown, the present invention provides a method for adjusting combustion of a gas turbine, comprising the following steps:

[0041] Collect the operating data of the gas turbine, and the controller 6 calculates the design installation angle θ of the swirl blade 1 according to the operating data i ,θ i =θ 0 +θ(x),θ 0 is the initial design installation angle of the swirl blade 1, and x is the operating data of the gas turbine; the swirl blade 1 is hinged to the combustion chamber body 31 through the hinge shaft 2;

[0042] The controller 6 controls the motion actuator 4 to move, and the motion actuator 4 drives the swirl blade 1 to rotate around the hinge shaft 2 until the actual installation angle of the swirl blade 1 reaches the designed installation angle.

[0043] The method for adjusting the combustion of a gas turbine in the present invention calculates the design installation angle θ of the swirl blade 1 according to the operating data of the gas turbine. i The swirl blade 1 is driven to rotate around the hinge shaft 2 through the motion actuator 4 until the actual installation angle of the swirl blade 1 reaches the designed installation angle, so that the installation angle of the swirl blade 1 can be adjusted according to the operating state of the gas turbine, coupled with the fuel and air ratio, to ensure the organization of the appropriate combustion flow field in the combustion chamber 3, and then realize the stepless adjustment of the combustion mode, and realize stable combustion under variable working conditions, and reduce the formation and emission of harmful substances. The method of the present invention effectively improves the stability of the combustion of the gas turbine.

[0044] At the same time, if Figures 1 to 4 As shown, the present invention provides a system for adjusting the combustion of a gas turbine, comprising a swirl blade 1 installed on a combustion chamber body 31, a motion actuator 4 connected to the swirl blade 1, a controller 6 communicatively connected to the motion actuator 4, and a sensor 5 communicatively connected to the controller 6, wherein the sensor 5 is used to detect the operating state of the gas turbine, the swirl blade 1 is hinged to the combustion chamber body 31 through a hinge shaft 2, and the motion actuator 4 can drive the swirl blade 1 to rotate around the hinge shaft 2. The working principle of the system for adjusting the combustion of the gas turbine in the present invention is as follows: the sensor 5 detects the operating state of the gas turbine and feeds back the detected operating data of the gas turbine to the controller 6. The controller 6 controls the motion actuator 4 to act according to the operating state of the gas turbine, so as to drive the swirl blade 1 to rotate around the hinge shaft 2 through the motion actuator 4 until the actual installation angle of the swirl blade 1 reaches the set requirement, so that the actual installation angle of the swirl blade 1 can be adjusted steplessly according to the operating state of the gas turbine to ensure that a proper flow field is formed in the combustion chamber 3, thereby ensuring stable combustion even when the gas turbine is in a variable operating condition, thereby improving the stability of the combustion of the gas turbine and reducing the formation and emission of harmful substances during combustion.

[0045] Embodiment 1

[0046] like Figure 3 and Figure 4As shown, in the present embodiment, there are multiple swirl blades 1, and all the swirl blades 1 are evenly distributed along the circumference of the combustion chamber body 31. In the present embodiment, the motion actuator 4 is a crank-connecting rod mechanism. In other embodiments, the motion actuator 4 adopts other devices that can change the installation angle of the swirl blade 1. In addition, in the present embodiment, the controller 6 includes an information acquisition module, and the information acquisition module is communicatively connected with the sensor 5. The swirl blade 1 is hinged to the combustion chamber body 31. In the present embodiment, the crank-connecting rod mechanism is connected to the hinge shaft 2, and the swirl blade 1 is fixedly connected to the hinge shaft 2. The crank-connecting rod mechanism drives the swirl blade 1 to rotate by driving the hinge shaft 2 to rotate, and realizes the rotation of the swirl blade 1 around its hinge point with the combustion chamber body 31, that is, around the hinge shaft 2.

[0047] like Figure 1 As shown, the method for adjusting the combustion of the gas turbine in this embodiment uses the sensor 5 to collect the operating data x of the gas turbine and feed the operating data x back to the controller 6, specifically to the information collection module of the controller 6. The controller 6 obtains the operating data of the gas turbine through the information collection module and sequentially calculates the design installation angle θ of the swirl blade 1. i ,θ i =θ 0 +θ(x), the controller 6 sends a control instruction to the crank-connecting rod mechanism, the crank-connecting rod mechanism operates and drives all the swirl blades 1 to rotate around the corresponding hinge shafts 2 respectively, until the actual installation angle of the swirl blades 1 reaches the designed installation angle θ i , thereby realizing stepless adjustment of the installation angle of the swirl blade 1 according to the operating state of the gas turbine, ensuring that a good combustion flow field can still be formed in the combustion chamber 3 and a good combustion effect can be maintained when the operating conditions of the gas turbine change, thereby improving the stability of the combustion of the gas turbine.

[0048] The method in this embodiment can be specifically referred to as a method for adjusting the mixed flow of air and gas in the combustion chamber of a gas turbine. This embodiment provides a means for adjusting the mixing and flow of air and gas in the combustion chamber. By changing the installation angle of the swirl blade 1, the ratio of gas, air, or other working fluids is coupled to ensure the organization of a proper combustion flow field, thereby achieving stepless adjustment of the combustion mode, and achieving stable combustion under variable working conditions, thereby reducing NOx and CO emissions. The method and system in this embodiment are used in the combustion chamber 3 of a gas turbine. In this embodiment, the combustion chamber 3 includes the above-mentioned combustion chamber body 31. And the combustion chamber body 31 is a rotating body extending along the mainstream direction of the combustion chamber 3, and the swirl blade 1 extends radially from the outer contact surface of the combustion chamber body 31 to the mainstream direction of the combustion chamber 3 and has a fixed length. This swirl blade 1 can cause the fluid flowing along the mainstream direction of the combustion chamber 3 to generate radial velocity, thereby generating a swirl fluid.

[0049] In this embodiment, the motion actuator 4 drives the swirl blades 1 to rotate around the hinge shaft 2, adjusts the installation angle of the swirl blades 1, thereby changing the swirl state of the fluid, ensuring the organization of a proper combustion flow field, and further achieving stepless adjustment of the combustion mode. All swirl blades 1 form a swirl blade group, and the swirl blade group maintains a matrix state on the extended surface of the outer contact surface of the combustion chamber body 31. The controller 6 receives the operating data of the gas turbine and issues instructions to the motion actuator 4 based on the built-in logic. After receiving the instructions from the controller 6, the motion actuator 4 will drive the swirl blades 1 to rotate on the extended surface with the installation axis of each swirl blade 1 as the central axis. The control logic set in the controller 6 is used to couple the operating data of the gas turbine from startup to full load operation with the installation angle of the swirl blade 1.

[0050] Embodiment 2

[0051] like Figure 1 As shown, based on the above-mentioned embodiment 1, the sensor 5 of this embodiment includes a load sensor 55 installed on the gas turbine, and the load sensor 55 is connected to the information acquisition module of the controller 6 for communication. In this embodiment, the load sensor 55 is used to collect the load P of the gas turbine and feed P back to the controller 6, and the controller 6 sequentially calculates the design installation angle θ of the swirl blade 1 i ,θ i =θ 0 +θ 1 (P).

[0052] In this embodiment, when the gas turbine is at 100% basic load, the design installation angle of the swirl blade 1 is θ 0 , when the gas turbine is at 30% basic load, the design installation angle of the swirl blade 1 is θ 0 +10, to ensure that the swirl state of the mainstream gas in the combustion chamber 3 is enhanced, so that the combustion is more complete and the CO emission is reduced.

[0053] Embodiment 3

[0054] like Figure 1 As shown, based on the above-mentioned embodiment 1, the sensor 5 of this embodiment includes a component sensor 56 installed in the gas turbine, and the component sensor 56 is connected to the information acquisition module of the controller 6 for communication. In this embodiment, the component sensor 56 is used to collect the fuel component s in the combustion chamber 3 and feed the fuel component s back to the controller 6, and the controller 6 sequentially calculates the design installation angle θ of the swirl blade 1 i ,θ i =θ 0 +θ 5 (s).

[0055] In this embodiment, when the gas turbine combustion medium is assumed to be natural gas, the installation angle of the swirl blade 1 is θ 0 , when the combustion medium is natural gas mixed with a certain proportion of hydrogen, the design installation angle of the swirl blade 1 is θ 0 -10, to ensure that the swirl state of the mainstream gas in the combustion chamber 3 is weakened to avoid combustion backfire.

[0056] Embodiment 4

[0057] like Figure 1 As shown, based on the above-mentioned embodiment 1, the sensor 5 of this embodiment includes a combustion temperature sensor 52 installed in the combustion chamber 3 and a dynamic pressure sensor 51 installed in the combustion chamber 3. The combustion temperature sensor 52 and the dynamic pressure sensor 51 are both connected to the controller 6 for communication. In this embodiment, the dynamic pressure sensor 51 is used to collect the pressure p in the combustion chamber 3 and feed p back to the controller 6, and the combustion temperature sensor 52 is used to collect the temperature t in the combustion chamber 3. B , and t B Feedback to the controller 6, the controller 6 calculates the design installation angle θ of the swirl blade 1 i ,θ i =θ 0 +θ 4 (t B ,p).

[0058] In this embodiment, when the gas turbine is in stable combustion, the installation angle of the swirl blade 1 is θ 0 , when the dynamic pressure sensor 51 detects that the pressure in the combustion chamber 3 exceeds the warning value, and the combustion temperature sensor 52 detects that the temperature in the combustion chamber 3 is lower than the warning value, the design installation angle of the swirl blade 1 is θ 0 +10, to enhance the swirl and increase the intensity of the central flame.

[0059] In this embodiment, the dynamic pressure sensor 51 is specifically installed on the wall of the combustion chamber 3 to monitor the combustion stability. When the feedback value of the dynamic pressure sensor 51 is higher than the warning value, the adjustment information of the motion actuator 4 is fed back. In this embodiment, the combustion temperature sensor 52 is installed at the outlet or head of the combustion chamber 3 to monitor the combustion intensity. When the feedback value of the combustion temperature sensor 52 is higher or lower than the warning value, the adjustment information of the motion actuator 4 is fed back.

[0060] Embodiment 5

[0061] like Figure 1As shown, based on the above-mentioned embodiment 1, the sensor 5 of this embodiment includes a combustion temperature sensor 52 installed in the combustion chamber 3 and a dynamic pressure sensor 51 installed in the combustion chamber 3. The combustion temperature sensor 52 and the dynamic pressure sensor 51 are both connected to the controller 6 for communication. In this embodiment, the dynamic pressure sensor 51 is used to collect the pressure p in the combustion chamber 3 and feed p back to the controller 6, and the combustion temperature sensor 52 is used to collect the temperature t in the combustion chamber 3. B , and t B Feedback to the controller 6, the controller 6 calculates the design installation angle θ of the swirl blade 1 i ,θ i =θ 0 +θ 4 (t B ,p).

[0062] In this embodiment, when the gas turbine is in stable combustion, the installation angle of the swirl blade 1 is set to θ 0 , when the dynamic pressure sensor 51 detects that the pressure in the combustion chamber 3 exceeds the warning value, and the combustion temperature sensor 52 detects that the temperature in the combustion chamber 3 is higher than the warning value, the design installation angle of the swirl blade 1 is θ 0 -10, used to reduce swirl and weaken the intensity of the central flame.

[0063] In this embodiment, the dynamic pressure sensor 51 is specifically installed on the wall of the combustion chamber 3 to monitor the combustion stability. When the feedback value of the dynamic pressure sensor 51 is higher than the warning value, the adjustment information of the motion actuator 4 is fed back. In this embodiment, the combustion temperature sensor 52 is installed at the outlet or head of the combustion chamber 3 to monitor the combustion intensity. When the feedback value of the combustion temperature sensor 52 is higher or lower than the warning value, the adjustment information of the motion actuator 4 is fed back.

[0064] Embodiment 6

[0065] like Figure 1 As shown, based on the above-mentioned embodiment 1, the sensor 5 of this embodiment includes an intake air temperature sensor 53 installed at the inlet of the compressor 7, and the intake air temperature sensor 53 is communicatively connected with the information acquisition module of the controller 6. This embodiment uses the intake air temperature sensor 53 to collect the intake air temperature T of the compressor 7 0 , and T 0 Feedback is given to the controller 6, which calculates the design installation angle θ of the swirl blade 1 accordingly. i ,θ i =θ 0 +θ 2 (T 0 ).

[0066] In this embodiment, when the air intake temperature of the compressor 7 is 25°C, the design installation angle of the swirl blade 1 is θ0 .

[0067] Embodiment 7

[0068] like Figure 1 As shown, based on the above-mentioned embodiment 1, the sensor 5 of this embodiment includes an exhaust temperature sensor 54 installed at the exhaust port of the gas turbine, and the exhaust temperature sensor 54 is communicatively connected with the information acquisition module of the controller 6. This embodiment uses the exhaust temperature sensor 54 to collect the exhaust temperature T of the gas turbine. 1 , and T 1 Feedback is given to the controller 6, which calculates the design installation angle θ of the swirl blade 1 accordingly. i ,θ i =θ 0 +θ 3 (T 1 ).

[0069] In this embodiment, when the exhaust temperature of the gas turbine, that is, the exhaust temperature of the turbine 8, is 400°C, the design installation angle of the swirl blade 1 is θ 0 .

[0070] Embodiment 8

[0071] like Figure 1 As shown, based on the above-mentioned embodiment 1, the sensor 5 of this embodiment includes an intake temperature sensor 53 installed at the inlet of the compressor 7, an exhaust temperature sensor 54 installed at the exhaust port of the gas turbine, a load sensor 55 installed on the gas turbine, a component sensor 56 installed in the gas turbine, a combustion temperature sensor 52 installed in the combustion chamber 3, and a dynamic pressure sensor 51 installed in the combustion chamber 3. In this embodiment, the combustion temperature sensor 52 is specifically installed at the head of the combustion chamber 3. The dynamic pressure sensor 51, the combustion temperature sensor 52, the intake temperature sensor 53, the exhaust temperature sensor 54, the load sensor 55, and the component sensor 56 are all connected to the controller 6 for communication.

[0072] In this embodiment, the intake air temperature sensor 53 collects the intake air temperature T of the compressor 7. 0 , and T 0 Feedback to the controller 6, the exhaust temperature sensor 54 collects the exhaust temperature T of the gas turbine 1 , and T 1 The load sensor 55 collects the load P of the gas turbine and feeds P back to the controller 6. The dynamic pressure sensor 51 collects the pressure p in the combustion chamber 3 and feeds p back to the controller 6. The combustion temperature sensor 52 collects the temperature t in the combustion chamber 3. B , and t BThe component sensor 56 collects the fuel component s in the combustion chamber 3 and feeds s back to the controller 6. The controller 6 calculates the design installation angle θ of the swirl blade 1. i ,θ i =θ 0 +θ 1 (P)+θ 2 (T 0 )+θ 3 (T 1 )+θ 4 (t B ,p)+θ 5 (s).

[0073] This embodiment sets the control function table shown in the following table according to the optimal design and debugging results, and fills it according to the linear principle.

[0074] Table 1 Design and installation angle control function table of swirl blades

[0075]

[0076]

[0077] In this embodiment, when the gas turbine is at 100% base load, the intake temperature of the compressor 7 is 25°C, the exhaust temperature of the gas turbine is 400°C, the fuel type in the combustion chamber 3 is 100% CH4, the head temperature of the combustion chamber 3 is 100°C, and the pressure vibration mean value in the combustion chamber 3 is <1g, the design installation angle of the swirl blade 1 is θ 0 .

[0078] In this embodiment, the design installation angle of the swirl blade 1 is θ i The intake air temperature T of the compressor 7 0 , gas turbine exhaust temperature T 1 , gas turbine load P, pressure p in combustion chamber 3, temperature t in combustion chamber 3 B , and the fuel component s in the combustion chamber 3 can be linear or nonlinear, exponential or power relationship, etc. The above calculation formula is a control function for designing the installation angle, and the control function is set in the controller 6. In this embodiment, the dynamic pressure sensor 51 collects the mean pressure value in the combustion chamber 3.

[0079] Compared with the prior art, the present invention can obtain more flow field organizational forms and flame forms under the premise of fixed combustion chamber 3 structure and fuel ratio, laying the foundation for optimized combustion adjustment, and at the same time, by coupling with the overall control logic of the gas turbine, under the premise of access to the feedback control of the sensor 5, it ensures the combustion stability and low emissions of each working condition. After coupling with the combustion temperature sensor 52 and the dynamic pressure sensor 51, it can cope with the flow field deviation caused by sudden changes in working conditions, thereby avoiding flameout, flashback, thermoacoustic oscillation, and sharp increase in emissions.

[0080] In summary, the present invention effectively overcomes various shortcomings of the prior art and has high industrial utilization value.

[0081] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical ideas disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A method for adjusting combustion of a gas turbine, characterized in that The steps include: The operating data of the gas turbine is collected, and the controller (6) calculates the design installation angle θ of the swirl blade (1) according to the operating data. i ,θ i =θ0+θ(x), θ0 is the initial design installation angle of the swirl blade (1), and x is the operating data of the gas turbine; The swirl blade (1) is hinged to the combustion chamber body (31) via a hinge shaft (2); The controller (6) controls the motion actuator (4) to move, and the motion actuator (4) drives the swirl blade (1) to rotate around the hinge shaft (2) until the actual installation angle of the swirl blade (1) reaches the designed installation angle; The sensor (5) collects operating data x of the gas turbine and feeds the operating data x of the gas turbine back to the controller (6); the intake air temperature sensor (53) collects the intake air temperature T0 of the compressor (7) and feeds T0 back to the controller (6); the exhaust temperature sensor (54) collects the exhaust temperature T1 of the gas turbine and feeds T1 back to the controller (6); the load sensor (55) collects the load P of the gas turbine and feeds P back to the controller (6); the dynamic pressure sensor (51) collects the pressure p in the combustion chamber (3) and feeds p back to the controller (6); the combustion temperature sensor (52) collects the temperature t in the combustion chamber (3) B , and t B The component sensor (56) collects the fuel component s in the combustion chamber (3) and feeds s back to the controller (6). The controller (6) calculates the design installation angle θ of the swirl blade (1). i , i i =θ0+θ1(P)+θ2(T0)+θ3(T1)+θ4(t B ,p)+θ5(s).

2. A system for implementing the method for adjusting combustion of a gas turbine according to claim 1, characterized in that: The invention comprises a swirl blade (1) mounted on a combustion chamber body (31), a motion actuator (4) connected to the swirl blade (1), a controller (6) connected to the motion actuator (4) in communication, and a sensor (5) connected to the controller (6), wherein the sensor (5) is used to detect the operating state of the gas turbine, the swirl blade (1) is hinged to the combustion chamber body (31) via a hinge shaft (2), and the motion actuator (4) can drive the swirl blade (1) to rotate around the hinge shaft (2).

3. The system according to claim 2, characterized in that: The motion execution mechanism (4) is a crank-connecting rod mechanism.

4. The system according to claim 2, characterized in that: There are a plurality of swirl blades (1), and all of the swirl blades (1) are evenly distributed along the circumference of the combustion chamber body (31).

5. The system according to claim 2, characterized in that: The controller (6) comprises an information acquisition module, and the information acquisition module is communicatively connected to the sensor (5).

6. The system according to claim 2, characterized in that: The sensor (5) includes an intake air temperature sensor (53) installed at the inlet of a compressor (7), an exhaust temperature sensor (54) installed at the exhaust port of a gas turbine, a load sensor (55) installed on the gas turbine, or a component sensor (56) installed in a combustion chamber (3).

7. The system according to claim 2, characterized in that: The sensor (5) comprises a combustion temperature sensor (52) installed in the combustion chamber (3) and a dynamic pressure sensor (51) installed in the combustion chamber (3).

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