A gas turbine combustor having high stable combustion characteristics

Abstract

This invention discloses a gas turbine combustor and its control method, relating to the field of gas turbine combustor technology. The combustor body forms a combustion channel, which includes an upstream stratified combustion zone and a downstream dilution zone, both sequentially distributed along the airflow direction within the combustion channel. A fuel inlet is located on the side wall of the combustor body and communicates with the upstream stratified combustion zone. An oxidizer inlet is also located on the side wall of the combustor body and communicates with the upstream stratified combustion zone, with the connection point between the oxidizer inlet and the upstream stratified combustion zone located downstream of the connection point between the fuel inlet and the upstream stratified combustion zone. A dilution inlet is located on the side wall of the combustor body and communicates with the downstream dilution zone. By setting up the upstream stratified combustion zone and the downstream dilution zone, and by constructing a three-stage inlet system consisting of the fuel inlet, oxidizer inlet, and dilution inlet sequentially along the axial direction, the vortex burner is improved from a simple burner into a burner with outlet quality control capabilities.

Description

Technical Field

[0001] This invention relates to the field of gas turbine combustor technology, and in particular to a gas turbine combustor with highly stable combustion characteristics, also known as a gas turbine combustor and its control method. Background Technology

[0002] A vortex tube combustor is an advanced combustor configuration that stabilizes the flame by arranging multiple fuel and oxidizer nozzles within a circular tubular combustion chamber. The interaction of these multiple incident jets creates vortices and recirculation structures within the tube. Unlike traditional combustors that rely on swirlers or blunt bodies for flame stabilization, the vortex tube combustor organizes specific airflow structures (such as recirculation zones, vortex pairs, or spiral vortices) within the tube, continuously recirculating high-temperature combusted flue gas to the reaction zone. This creates a dual thermodynamic and hydrodynamic stabilization mechanism, achieving stable flame anchoring without swirlers, blunt bodies, or cavities. Vortex tube combustors are characterized by their simple structure, wide flame stability range, and high combustion efficiency.

[0003] Existing research on vortex burners generally focuses on flame stability and combustion efficiency improvement in the upstream combustion zone, including optimization of multi-nozzle arrangements, numerical and experimental studies on jet interaction and vortex structure formation, and research on the relationship between fuel / oxidizer mixing characteristics and combustion efficiency. A common characteristic of these approaches is that their design focus is on the organization and optimization of the combustion zone, lacking systematic consideration of the downstream dilution section. While some designs include a few cooling holes in the downstream tube wall, these only serve a basic wall cooling function and are not specifically designed as a functional section for regulating the uniformity of the outlet temperature and velocity fields.

[0004] On the other hand, gas turbine combustor dilution section technology is relatively mature in the field of traditional swirl combustors, and has formed the following main solutions: (1) Traditional dilution hole scheme. A circular dilution hole is opened on the downstream wall of the swirl combustor, and cooling air is radially injected into the mainstream to mix with the high-temperature combustion gas. This scheme is technically mature, simple in structure, and highly reliable. It is currently the most widely used dilution method and has achieved good engineering results in traditional swirl combustors.

[0005] (2) Inclined dilution hole scheme. The dilution holes are arranged at a certain inclination angle (usually 15 to 20 degrees). The inclination of the incident holes increases the mixing time and the effective distance, taking into account both mainstream mixing and wall protection. This scheme has a better mixing effect than pure radial incident, but the incident angle is usually fixed in the design stage and it is difficult to adapt and adjust it according to different vortex flow field structures, load conditions and turbine inlet quality requirements.

[0006] (3) Dilution channel scheme. A guide channel is set on the combustion chamber lining to control the injection direction and speed of cooling air, which can improve local mixing (see GE European Patent EP3867555 B1).

[0007] (4) RQL (Rich-Quench-Lean) scheme. A large amount of dilution air is injected into the throat of the combustion chamber to achieve rapid flameout and cooling, which is widely used in low NOx combustion chambers.

[0008] The aforementioned dilution technologies have achieved good engineering results in traditional swirl combustors. However, their design basis and applicable objects are mainly based on the specific flow field structure and temperature distribution characteristics generated by the swirl generator, and have not been systematically transplanted and adapted to the multi-jet vortex structure inside the vortex burner and its outlet flow field characteristics. In particular, existing solutions usually focus on controlling the peak outlet temperature, and are insufficient in the coordinated control of the uniformity of the outlet temperature field and velocity field.

[0009] In summary, existing technologies reveal that while vortex burners offer excellent combustion performance, they lack a comprehensive outlet quality control design for downstream turbines. Dilution section technologies possess mature cooling and mixing methods, but primarily serve traditional swirl combustors, failing to develop an integrated stratified combustion-dilution homogenization solution compatible with vortex combustion technology. In essence, existing vortex burners remain at the "burner" level, failing to achieve the leap to a "gas turbine combustor" with outlet temperature and velocity field control capabilities. Summary of the Invention

[0010] The purpose of this invention is to provide a gas turbine combustor and its control method to solve the problems existing in the prior art. By setting an upstream stratified combustion zone and a downstream dilution zone, and forming a three-stage inlet system consisting of a fuel inlet, an oxidizer inlet and a dilution inlet along the axial direction, the vortex burner is improved from a simple burner into a burner with outlet quality control capability.

[0011] To achieve the above objectives, the present invention provides the following solution: The present invention provides a gas turbine combustion chamber, comprising: The combustion chamber body has an axially continuous combustion channel inside, the combustion channel including an upstream stratified combustion zone and a downstream dilution zone, the upstream stratified combustion zone and the downstream dilution zone being distributed sequentially along the axial direction of the combustion channel; A fuel inlet is provided on the side wall of the combustion chamber body and is connected to the upstream stratified combustion zone, and is used to inject fuel into the upstream stratified combustion zone; An oxidizer inlet, located on the side wall of the combustion chamber body and connected to the upstream stratified combustion zone, is used to inject oxidizer into the upstream stratified combustion zone. The connection between the oxidizer inlet and the upstream stratified combustion zone is located downstream of the connection between the fuel inlet and the upstream stratified combustion zone. A dilution inlet is provided on the side wall of the combustion chamber body and communicates with the downstream dilution zone, and is used to introduce dilution air into the downstream dilution zone; The fuel is injected into the upstream stratified combustion zone before the oxidant, and a radial stratification structure is formed between the fuel and the oxidant in the upstream stratified combustion zone; the dilution inlet is used to blend and dilute the combusted gas flowing out of the upstream stratified combustion zone.

[0012] Optionally, at least one set of the fuel inlet, the oxidant inlet, and the dilution inlet are provided and distributed sequentially along the axial direction of the combustion channel; multiple fuel inlets are provided in the same set and are evenly arranged along the circumference of the combustion channel, multiple oxidant inlets are provided in the same set and are evenly arranged along the circumference of the combustion channel, and multiple dilution inlets are provided in the same set and are evenly arranged along the circumference of the combustion channel.

[0013] Optionally, the axial distance between the oxidant inlet and the fuel inlet is smaller than the axial distance between the dilution inlet and the oxidant inlet.

[0014] Optionally, the incident direction of the dilution inlet has an incident angle relative to the tangential direction of the wall of the combustion chamber body. The incident angle is adjustable to change the ratio of the wall adhesion capability to the radial penetration capability of the dilution air after it is injected into the downstream dilution zone.

[0015] Optionally, the incident angle ranges from 0° to 90°; When the incident angle is 0°, the dilution air enters the combustion channel tangentially along the wall of the combustion chamber body to form a wall cooling film; When the incident angle is 90°, the dilution air enters the combustion channel radially along the combustion chamber body to enhance mixing with the high-temperature fuel gas; When the incident angle is greater than 0° and less than 90°, the dilution air simultaneously has a velocity component along the wall tangentially and a velocity component along the radial direction.

[0016] Optionally, the incident angles of all the dilution inlets are the same; or, the incident angles of at least two of the dilution inlets are different, so as to form different dilution air jet directions along the circumference of the combustion chamber body to adapt to the control requirements of the non-uniform outlet temperature field.

[0017] Optionally, each of the dilution inlets is provided with a guide vane, which is rotatably connected to the combustion chamber body via a rotating shaft, and the guide vane is at least partially located inside the dilution inlet, for changing the incident direction of the dilution air entering the combustion channel by rotation.

[0018] Optionally, the incident angle of each of the dilution inlets is a preset fixed angle, and each of the dilution inlets is opened on the combustion chamber body at its respective preset incident angle.

[0019] Optionally, the fuel inlet, the oxidant inlet, and the dilution inlet are all slit-like structures extending axially along the combustion chamber body.

[0020] A method for regulating a gas turbine combustor as described above is also provided, comprising the following steps: Fuel is introduced into the fuel inlet, and oxidant is introduced into the oxidant inlet at the same time, forming stratified combustion in the upstream stratified combustion zone and producing high-temperature combusted gas; Diluting air is introduced into the dilution inlet, so that the high-temperature burned gas is mixed with the diluting air in the downstream dilution zone and cooled down; Adjusting the injection direction of the dilution inlet is used to control the degree of mixing between the high-temperature combusted gas and the dilution air, thereby regulating the temperature and velocity fields at the combustion chamber outlet.

[0021] The present invention achieves the following technical effects compared to the prior art: The gas turbine combustor disclosed in this invention features a fuel inlet, an oxidizer inlet, and a dilution inlet arranged sequentially along the axial direction. This allows fuel and oxidizer to enter the upstream stratified combustion zone sequentially, forming stratified combustion. The resulting high-temperature combusted gas then flows into the downstream dilution zone, where dilution air introduced through the dilution inlet mixes, cools, and homogenizes the combusted gas. The fuel inlet, oxidizer inlet, and dilution inlet together constitute a three-stage inlet system. The upstream stratified combustion zone is responsible for converting the chemical energy of the fuel into thermal energy, generating high-temperature combusted flue gas. The downstream dilution zone is responsible for cooling and homogenizing the flue gas. These two functional sections are sequentially connected along the axial direction of the combustor, each fulfilling a portion of the functions required by the gas turbine combustor. Together, they form a complete combustor workflow, enabling the vortex burner to control the outlet flow field quality. This addresses the problem that while existing vortex burners offer excellent combustion performance, they lack the ability to control the outlet temperature and velocity fields, failing to meet the downstream turbine inlet quality requirements. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the combustion chamber body structure from a single perspective in an example disclosed in this invention; Figure 2 This is a schematic diagram of the combustion chamber body structure from another perspective in one example disclosed in this invention; Figure 3 for Figure 2 Cross-sectional view at point AA; Figure 4 for Figure 2 Cross-sectional view at point BB; Figure 5 for Figure 2 Cross-sectional view at CC; Among them, 1-combustion chamber body, 2-combustion channel, 3-fuel inlet, 4-oxidant inlet, and 5-dilution inlet. Detailed Implementation

[0024] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. 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.

[0025] The purpose of this invention is to provide a gas turbine combustor and its control method to solve the problems existing in the prior art. By setting an upstream stratified combustion zone and a downstream dilution zone, and forming a three-stage inlet system consisting of a fuel inlet, an oxidizer inlet and a dilution inlet along the axial direction, the vortex burner is improved from a simple burner into a burner with outlet quality control capability.

[0026] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0027] like Figures 1 to 5 As shown, the present invention provides a gas turbine combustor, including a combustor body 1, a fuel inlet 3, an oxidant inlet 4 and a dilution inlet 5. An axially through combustion channel 2 is formed inside the combustor body 1. The combustion channel 2 includes an upstream stratified combustion zone and a downstream dilution zone, which are distributed sequentially along the axial direction of the combustion channel 2.

[0028] As a preferred example, the combustion chamber body 1 has a cylindrical structure, and the combustion channel 2 is arranged through the axial direction of the combustion chamber body 1. The outer diameter of the combustion chamber body 1 is 50mm, and the total axial length is 500mm.

[0029] Fuel inlet 3 is located on the side wall of combustion chamber body 1 and connects to the upstream stratified combustion zone, and is used to inject fuel into the upstream stratified combustion zone. Oxidant inlet 4 is located on the side wall of combustion chamber body 1 and connects to the upstream stratified combustion zone, and is used to inject oxidant into the upstream stratified combustion zone. The connection between oxidant inlet 4 and the upstream stratified combustion zone is located downstream of the connection between fuel inlet 3 and the upstream stratified combustion zone. Dilution inlet 5 is located on the side wall of combustion chamber body 1 and connects to the downstream dilution zone, and is used to introduce dilution air into the downstream dilution zone. Fuel is injected into the upstream stratified combustion zone before oxidant, forming a radial stratification structure between fuel and oxidant in the upstream stratified combustion zone. Dilution inlet 5 is used to mix and dilute the combusted gas flowing out of the upstream stratified combustion zone.

[0030] Therefore, the gas turbine combustor disclosed in this invention, by sequentially arranging a fuel inlet 3, an oxidizer inlet 4, and a dilution inlet 5 along the axial direction, allows fuel and oxidizer to enter the upstream stratified combustion zone sequentially to form stratified combustion. The resulting high-temperature combusted gas then flows into the downstream dilution zone, where dilution air introduced through the dilution inlet 5 mixes, cools, and homogenizes the combusted gas. The fuel inlet 3, oxidizer inlet 4, and dilution inlet 5 together constitute a three-stage inlet system. The upstream stratified combustion zone is responsible for converting the chemical energy of the fuel into thermal energy, generating high-temperature combusted flue gas, while the downstream dilution zone is responsible for cooling and homogenizing the flue gas. The two functional sections are sequentially connected along the axial direction of the combustor, each fulfilling a part of the functions required by the gas turbine combustor. Together, they form a complete combustor workflow, enabling the vortex burner to have the ability to control the outlet flow field quality. This solves the problem that while existing vortex burners have excellent combustion performance, they lack the ability to control the outlet temperature and velocity fields, thus failing to meet the downstream turbine inlet quality requirements.

[0031] In one embodiment, at least one set of fuel inlet 3, oxidizer inlet 4, and dilution inlet 5 are provided, and they are distributed sequentially along the axial direction of the combustion channel 2. Multiple fuel inlets 3, multiple oxidizer inlets 4, and multiple dilution inlets 5 are provided in the same set and are uniformly arranged circumferentially along the combustion channel 2. This multi-jet uniform circumferential arrangement ensures that fuel, oxidizer, and dilution air can enter the combustion chamber evenly along the circumference of the combustion channel 2, avoiding excessive concentration or uneven distribution in any one direction. The uniform circumferential arrangement of the fuel inlets 3 helps ensure uniform fuel distribution around the circumference, promoting aerodynamic stability, and thus thermodynamic and flame dynamic stability. The uniform circumferential arrangement of the oxidizer inlets 4 allows for more even oxidizer entry into the combustion chamber, enhancing the consistency of circumferential flow, improving the circumferential uniformity of the flow field and component field in the upstream stratified combustion zone, and providing good inlet conditions for homogenization of the downstream dilution zone and outlet flow field.

[0032] Based on this embodiment, in some specific examples, there are two fuel inlets 3, symmetrically arranged circumferentially along the combustion chamber body 1, with the two fuel inlets 3 spaced 180° apart circumferentially. The symmetrical arrangement of the two fuel inlets 3 ensures the symmetrical distribution of fuel on the circumference, which is beneficial for forming a stable vortex structure.

[0033] In some specific examples, there are eight oxidizer inlets 4, evenly arranged around the circumference of the combustion chamber body 1, with adjacent oxidizer inlets 4 spaced 45° apart around the circumference. The equidistant distribution of the eight oxidizer inlets 4 allows the oxidizer to enter the combustion channel 2 simultaneously from eight directions. The multiple incident jets interact within the tube, forming a turbulent vortex structure. The high-temperature combusted flue gas is continuously drawn back to the reaction zone through the vortex, enhancing the flame anchoring capability.

[0034] In some specific examples, there are eight dilution inlets 5, which are evenly arranged around the circumference of the combustion chamber body 1, so that the dilution air enters the downstream dilution zone evenly in the circumference, and the combusted gas is uniformly mixed and diluted.

[0035] In one embodiment, the axial distance between the oxidant inlet 4 and the fuel inlet 3 is smaller than the axial distance between the dilution inlet 5 and the oxidant inlet 4. The smaller axial distance between the fuel inlet 3 and the oxidant inlet 4 allows the fuel and oxidant to be injected into the upstream stratified combustion zone sequentially at adjacent positions, forming a stratified distribution. This avoids locally overly rich or overly lean mixtures and broadens the stable combustion range. The larger axial distance between the dilution inlet 5 and the oxidant inlet 4 provides sufficient reaction space for the mixing and combustion of fuel and oxidant, as well as the flow of flue gas in the upstream stratified combustion zone. This ensures that the high-temperature burned gas has fully developed and reacted before entering the downstream dilution zone, which is beneficial for the mixing and cooling of the dilution air.

[0036] Based on this embodiment, in some specific examples, the fuel inlet 3 is located near the upstream end, and the oxidant inlet 4 is located about 1 mm downstream of the fuel inlet 3. The oxidant inlet 4 is arranged adjacent to the fuel inlet 3, so that the fuel comes into contact with the oxidant immediately after being injected into the combustion channel 2, and begins to mix and react before the fuel has spread excessively, thus ensuring the stable anchoring of the flame near the fuel inlet 3.

[0037] In some specific examples, the dilution inlet 5 is located approximately 250 mm from the combustion chamber outlet. The dilution inlet 5 is positioned downstream of the oxidizer inlet 4, allowing sufficient residence time for the high-temperature combusted gas to react and flow before being mixed with dilution air in the downstream dilution zone.

[0038] In one embodiment, the incident direction of the dilution inlet 5 has an incident angle relative to the tangential direction of the combustion chamber body 1 wall. The incident angle is adjustable to change the ratio of the wall adhesion ability and radial penetration ability of the dilution air after it enters the downstream dilution zone. The incident angle determines the flow direction of the dilution air after it enters the combustion channel 2. Different incident angles result in different adhesion abilities of the dilution air near the wall and different radial penetration abilities into the mainstream zone. By adjusting the incident angle, dilution inlets 5 with different incident angles can be arranged at different positions around the combustion chamber according to the actual temperature distribution characteristics generated by the upstream stratified combustion zone. A smaller incident angle is used in areas with excessively high wall temperatures to enhance wall protection, while a larger incident angle is used in areas with high mainstream temperatures to enhance mainstream mixing and cooling, thereby achieving targeted control of the outlet temperature field and velocity field.

[0039] Based on this implementation, in some cases, the incident angle can be preset to different fixed angles during the design phase. The incident angle of each dilution inlet 5 is determined separately based on simulation or experimental results and remains fixed after assembly. No moving parts are required, resulting in a simple structure, high reliability, and the fixed angle scheme is suitable for applications with relatively stable operating conditions, reducing manufacturing and maintenance costs. In other cases, the incident angle can be adjusted in real time during operation via external levers, rotating shafts, or sliding mechanisms to meet the control requirements under different load conditions. For example, each dilution inlet 5 is equipped with a guide vane, which is rotatably connected to the combustion chamber body 1 via a rotating shaft, and the guide vane is at least partially located within the dilution inlet 5. This guide vane is used to change the incident direction of the dilution air entering the combustion channel 2 by rotation. The guide vane provides a mechanical means of adjusting the flow direction of the dilution air. Located within the dilution inlet 5, the dilution air is guided and its flow direction is changed as it flows over the surface of the guide vane. By rotating the guide vane to change its angle with the tangential direction of the wall, the dilution air can enter the combustion channel 2 at different incident angles. The rotating shaft connection structure allows the guide vane to be driven by external levers, connecting rods, or electromagnetic drive structures during operation, achieving real-time adjustment of the incident angle to adapt to the control requirements under different load conditions.

[0040] In one embodiment, the incident angle ranges from 0° to 90°. When the incident angle is 0°, the dilution air enters the combustion channel 2 tangentially along the wall of the combustion chamber body 1 to form a wall cooling film. When the incident angle is 90°, the dilution air enters the combustion channel 2 radially along the combustion chamber body 1 to enhance mixing with the high-temperature fuel gas. When the incident angle is greater than 0° and less than 90°, the dilution air simultaneously has a velocity component tangentially along the wall and a velocity component radially.

[0041] When the incident angle is 0°, the dilution air flows almost entirely tangentially along the wall, forming a well-covering cooling film near the wall to separate the high-temperature combusted gas from the wall and reduce the wall's heat load. This injection method is suitable for applications where wall protection is primary and mixing and cooling are secondary. When the incident angle is 90°, the dilution air is injected directly into the central region of combustion channel 2 in a near-radial manner, resulting in the maximum jet penetration depth and the strongest direct mixing with the central high-temperature combustion gas. This is beneficial for reducing local temperature peaks and improving cross-sectional temperature uniformity. This injection method is suitable for applications requiring rapid cooling, enhanced mixing, and control of outlet temperature peaks. When the incident angle is between 0° and 90°, the dilution air has both velocity components, creating a combined effect of swirling mixing and radial penetration within combustion channel 2. This achieves a balance between wall protection and mainstream mixing, making it suitable for applications requiring both wall cooling and outlet flow field homogenization.

[0042] In one embodiment, all dilution inlets 5 have the same incident angle; or, at least two dilution inlets 5 have different incident angles to form different dilution air jet directions along the circumference of the combustion chamber body 1, adapting to the control requirements of a non-uniform outlet temperature field. The temperature distribution generated in the upstream stratified combustion zone is not completely uniform along the circumference in actual operating conditions. Factors such as fuel injection method and vortex formation location may cause localized circumferential temperature variations. When all dilution inlets 5 use the same incident angle, the cooling and mixing effects of each dilution air jet on the combusted gas remain consistent along the circumference, suitable for operating conditions where the outlet temperature field is relatively uniform along the circumference. When at least two dilution inlets 5 use different incident angles, the wall adhesion and radial penetration capabilities of each dilution air jet differ along the circumference, thereby enabling differentiated control of the non-uniform outlet temperature field.

[0043] When the incident angles of each dilution inlet 5 are the same, specifically, each dilution inlet 5 is opened at a uniform angle on the side wall of the combustion chamber body 1, and each dilution air jet enters the downstream dilution zone in the same direction to uniformly mix and dilute the combusted gas. The advantage of this method is that the structure is uniform, the processing and manufacturing are simple, the assembly and debugging are convenient, and it is suitable for working conditions with good circumferential uniformity of the outlet temperature field.

[0044] When the incident angles of at least two dilution inlets 5 are different, specifically, by setting dilution inlets 5 with different incident angles at different circumferential positions, a larger incident angle is used in areas with higher temperatures to enhance mainstream mixing and cooling, and a smaller incident angle is used in areas with lower temperatures to reduce mixing intensity, so that the cooling and mixing effects of the dilution air are distributed differentially along the circumference, thereby improving the circumferential uniformity of the outlet temperature field.

[0045] In some examples, the incident angle of each dilution inlet 5 is a preset fixed angle, and each dilution inlet 5 is opened on the combustion chamber body 1 at its own preset incident angle. According to the upstream temperature distribution characteristics measured by simulation or experiment, dilution inlets 5 with smaller incident angles are set in areas with excessively high wall temperatures to enhance wall protection, and dilution inlets 5 with larger incident angles are set in areas with excessively high mainstream temperatures to enhance mainstream mixing and cooling. After assembly, the angle of each dilution inlet 5 remains fixed, the structure is simple and reliable, and the manufacturing and maintenance costs are low.

[0046] In one embodiment, the fuel inlet 3, oxidant inlet 4, and dilution inlet 5 are all slit-like structures extending axially along the combustion chamber body 1. Compared to circular orifices, slit-like structures have a larger aspect ratio, allowing the injected fuel, oxidant, and dilution air to form a longer axially effective area. For the fuel inlet 3, the slit-like structure makes the fuel distribution more uniform along the axial direction, which is beneficial for the formation of stratified combustion. For the oxidant inlet 4, the slit-like structure allows the oxidant jet to fully expand along the axial direction, resulting in more thorough mixing with the fuel. For the dilution inlet 5, the slit-like structure allows the dilution air to continuously enter the downstream dilution zone along the axial direction, resulting in a more uniform mixing and cooling effect, and avoiding localized temperature drops and flow field disturbances caused by concentrated injection.

[0047] In some specific examples, fuel inlet 3 is a rectangular slit structure with a slit width of 2 mm and a height of 5 mm. Oxidant inlet 4 is a rectangular slit structure with a slit width of 2 mm and a height of 20 mm. Dilution inlet 5 is a rectangular slit structure with a slit width of 2 mm and an axial length of 20 mm. The height of oxidant inlet 4 is greater than that of fuel inlet 3, so that the axial coverage of the oxidant jet is greater than that of the fuel jet, ensuring that the fuel can fully contact the oxidant within a wider axial range, promoting mixing and combustion.

[0048] Furthermore, the present invention also provides a method for controlling the combustion chamber of a gas turbine using any of the above embodiments, comprising the following steps: Fuel is introduced into fuel inlet 3, and oxidant is introduced into oxidant inlet 4 at the same time, forming stratified combustion in the upstream stratified combustion zone and producing high-temperature combusted gas; Diluting air is introduced into dilution inlet 5 to mix the high-temperature burned gas with the diluting air in the downstream dilution zone and cool it down; The injection direction of the dilution inlet 5 is adjusted to control the degree of mixing between the high-temperature combusted gas and the dilution air, thereby regulating the temperature field and velocity field at the combustion chamber outlet.

[0049] In this process, fuel is first injected into the upstream stratified combustion zone through fuel inlet 3, followed by oxidizer injected downstream through oxidizer inlet 4. Both fuel and oxidizer form an axially stratified distribution within the upstream stratified combustion zone and undergo combustion, producing high-temperature combusted gas. This high-temperature combusted gas flows into the downstream dilution zone along combustion channel 2. Diluent air enters through dilution inlet 5 and mixes with the high-temperature combusted gas, reducing the gas temperature and improving the uniformity of temperature distribution. By adjusting the incident direction of dilution inlet 5, the ratio of wall adhesion and radial penetration of the dilution air can be controlled, altering the mixing intensity and cooling effect, thereby regulating the temperature and velocity fields at the combustion chamber outlet to meet the downstream turbine inlet quality requirements.

[0050] To facilitate understanding, the following explanation of the gas turbine combustion chamber and control method, based on specific implementation examples from the original records, will further illustrate the following: Example 1: Tangential dilution inlet 5 with an incident angle of 0°.

[0051] In this example, the incident angle of all eight downstream dilution inlets 5 is 0°, meaning the dilution air enters the combustion channel 2 tangentially along the wall of the combustion chamber body 1. In this configuration, the dilution air flows primarily near the wall after entering the combustion channel 2, which helps form a cooling film near the inner wall of the combustion chamber, reducing the direct contact between the high-temperature combustion gas and the wall, thereby enhancing the wall protection effect. Simultaneously, the tangentially entering dilution air can gradually mix with the high-temperature combusted gas downstream, achieving a more gradual cooling and homogenization process. This example is suitable for operating conditions that place greater emphasis on wall thermal protection and gradual dilution cooling.

[0052] Example 2: Deflection dilution inlet 5 with an incident angle of 20°.

[0053] In this example, the incident angle of all eight downstream dilution inlets 5 is 20°, meaning the dilution air deflects 20° radially relative to the wall tangential direction before entering the combustion channel 2. In this configuration, the dilution air possesses both tangential and radial velocity components. The tangential velocity component helps maintain a certain level of wall cooling and circumferential flow, while the radial velocity component enhances the penetration of the dilution jet into the mainstream region, allowing the dilution air to more effectively enter and mix with the high-temperature combustion gas. Compared to tangential incidence at 0°, deflected incidence at 20° achieves a better balance between wall protection and mainstream mixing, thus improving the uniformity of the temperature and velocity fields at the outlet section. This example is suitable for applications requiring both wall cooling and outlet flow field homogenization.

[0054] Example 3: Radial dilution inlet 5 with an incident angle of 90°.

[0055] In this example, the incident angle of all eight downstream dilution inlets 5 is 90°, meaning the dilution air enters the combustion channel 2 primarily radially along the combustion chamber body 1. In this configuration, the dilution air enters the combustion channel 2 as a radial jet, exhibiting strong mainstream penetration capability and enabling it to quickly enter the central region of the combustion chamber and mix with the high-temperature combusted gas. Compared to inlet configurations with incident angles of 0° and 20°, radial incidence at 90° is more conducive to enhancing the direct mixing between the dilution air and the central high-temperature combustion gas, reducing local temperature peaks, and improving the uniformity of the outlet cross-section temperature distribution. This example is suitable for operating conditions that prioritize rapid cooling, enhanced mixing, and control of the outlet temperature peak.

[0056] The three examples above correspond to three typical forms of dilution inlet 5: tangential incidence, deflected incidence, and radial incidence. In practical applications, the incidence angle of dilution inlet 5 can be selected or combined according to the cooling requirements of the combustion chamber wall, the uniformity requirements of the outlet temperature field, the quality requirements of the outlet velocity field, and the downstream turbine inlet conditions.

[0057] Furthermore, the three examples above demonstrate the continuous changes in the flow characteristics and control focus of the diluted air after entering the combustion channel 2 as the incident angle varies from 0° to 90°. At an incident angle of 0°, wall protection is the primary function; as the incident angle increases, radial penetration gradually strengthens, and the mixing and cooling effect gradually increases; at an incident angle of 90°, mainstream mixing and cooling is the primary function. By combining dilution inlets 5 with different incident angles at different circumferential positions within the same combustion chamber, differentiated control can be achieved based on the actual distribution of the outlet temperature field, realizing synergistic optimization of the outlet temperature and velocity fields.

[0058] In summary, this invention addresses the problem that while existing vortex burners offer excellent combustion performance, they lack the ability to control the outlet temperature and velocity fields, thus failing to meet the downstream turbine inlet quality requirements. It provides a gas turbine combustor and its control method. The combustor body 1 forms an axially continuous combustion channel 2, which is sequentially divided into an upstream stratified combustion zone and a downstream dilution zone along the airflow direction. A fuel inlet 3 is located on the side wall of the upstream stratified combustion zone, an oxidizer inlet 4 is located on the downstream side wall of the fuel inlet 3, and a dilution inlet 5 is located on the side wall of the downstream dilution zone. Fuel is injected into the upstream stratified combustion zone before the oxidizer, forming axial stratified combustion. The resulting high-temperature combusted gas flows into the downstream dilution zone, where it is mixed with and cooled by dilution air introduced through the dilution inlet 5.

[0059] Thus, fuel inlet 3, oxidizer inlet 4, and dilution inlet 5 are arranged sequentially along the axial direction of combustion channel 2. The upstream stratified combustion zone is responsible for converting the chemical energy of the fuel into thermal energy, generating high-temperature combustible gas, while the downstream dilution zone is responsible for cooling and homogenizing the flue gas. Upstream and downstream parameters are matched at the system design level. The equivalence ratio range of upstream combustion is constrained by the downstream dilution capacity, and the downstream dilution angle is determined based on the upstream temperature distribution characteristics. These two functions work in tandem to form a complete gas turbine combustion chamber. Furthermore, fuel is injected before oxidizer, forming a stratified fuel-oxidizer distribution along the axial direction, avoiding locally overly rich or lean mixtures and widening the stable combustion range. Multiple oxidizer jets are uniformly injected circumferentially, forming a turbulent vortex structure within the tube. The high-temperature combustible gas is continuously drawn back to the reaction zone through the vortex, enhancing flame anchoring capability and combustion stability. Meanwhile, the incident angle of the dilution inlet 5 can be adjusted within the range of 0° to 90°. By changing the ratio of the wall adhesion capability and radial penetration capability of the dilution air, the wall cooling protection, jet penetration depth, mixing intensity, and uniformity of the outlet temperature field and velocity field are coordinated and optimized so that the combustion chamber outlet flow field meets the downstream turbine inlet quality requirements.

[0060] Any adaptive changes made according to actual needs are within the scope of protection of this invention.

[0061] It should be noted that, for those skilled in the art, it is obvious that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0062] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A gas turbine combustion chamber, characterized in that, include: The combustion chamber body has an axially continuous combustion channel inside, the combustion channel including an upstream stratified combustion zone and a downstream dilution zone, the upstream stratified combustion zone and the downstream dilution zone being distributed sequentially along the axial direction of the combustion channel; A fuel inlet is provided on the side wall of the combustion chamber body and is connected to the upstream stratified combustion zone, and is used to inject fuel into the upstream stratified combustion zone; An oxidizer inlet, located on the side wall of the combustion chamber body and connected to the upstream stratified combustion zone, is used to inject oxidizer into the upstream stratified combustion zone. The connection between the oxidizer inlet and the upstream stratified combustion zone is located downstream of the connection between the fuel inlet and the upstream stratified combustion zone. A dilution inlet is provided on the side wall of the combustion chamber body and communicates with the downstream dilution zone, and is used to introduce dilution air into the downstream dilution zone; The fuel is injected into the upstream stratified combustion zone before the oxidant, and a radial stratification structure is formed between the fuel and the oxidant in the upstream stratified combustion zone; the dilution inlet is used to blend and dilute the combusted gas flowing out of the upstream stratified combustion zone.

2. The gas turbine combustion chamber according to claim 1, characterized in that, The fuel inlet, the oxidant inlet, and the dilution inlet are each provided in at least one set and are distributed sequentially along the axial direction of the combustion channel; the fuel inlets in the same set are provided in multiple sets and are evenly arranged along the circumference of the combustion channel, the oxidant inlets in the same set are provided in multiple sets and are evenly arranged along the circumference of the combustion channel, and the dilution inlets in the same set are provided in multiple sets and are evenly arranged along the circumference of the combustion channel.

3. The gas turbine combustion chamber according to claim 1, characterized in that, The axial distance between the oxidant inlet and the fuel inlet is less than the axial distance between the dilution inlet and the oxidant inlet.

4. The gas turbine combustion chamber according to claim 1, characterized in that, The incident direction of the dilution inlet has an incident angle relative to the tangential direction of the wall of the combustion chamber body. The incident angle is adjustable to change the ratio of the wall adhesion capability and radial penetration capability of the dilution air after it is injected into the downstream dilution zone.

5. The gas turbine combustion chamber according to claim 4, characterized in that, The incident angle ranges from 0° to 90°; When the incident angle is 0°, the dilution air enters the combustion channel tangentially along the wall of the combustion chamber body to form a wall cooling film; When the incident angle is 90°, the dilution air enters the combustion channel radially along the combustion chamber body to enhance mixing with the high-temperature fuel gas; When the incident angle is greater than 0° and less than 90°, the dilution air simultaneously has a velocity component along the wall tangentially and a velocity component along the radial direction.

6. The gas turbine combustion chamber according to claim 4, characterized in that, The incident angles of all the dilution inlets are the same; or, the incident angles of at least two of the dilution inlets are different, so as to form different dilution air jet directions along the circumference of the combustion chamber body, to adapt to the control requirements of the non-uniform outlet temperature field.

7. The gas turbine combustion chamber according to claim 4, characterized in that, Each of the dilution inlets is provided with a guide vane, which is rotatably connected to the combustion chamber body via a rotating shaft, and the guide vane is at least partially located inside the dilution inlet, for changing the incident direction of the dilution air entering the combustion channel by rotation.

8. The gas turbine combustion chamber according to claim 4, characterized in that, The incident angle of each of the dilution inlets is a preset fixed angle, and each of the dilution inlets is opened on the combustion chamber body at its respective preset incident angle.

9. The gas turbine combustion chamber according to claim 1, characterized in that, The fuel inlet, the oxidant inlet, and the dilution inlet are all slit-like structures extending axially along the combustion chamber body.

10. A method for controlling a gas turbine combustion chamber as described in any one of claims 1 to 9, comprising the following steps: Fuel is introduced into the fuel inlet, and oxidant is introduced into the oxidant inlet at the same time, forming stratified combustion in the upstream stratified combustion zone and producing high-temperature combusted gas; Diluting air is introduced into the dilution inlet, so that the high-temperature burned gas is mixed with the diluting air in the downstream dilution zone and cooled down; Adjusting the injection direction of the dilution inlet is used to control the degree of mixing between the high-temperature combusted gas and the dilution air, thereby regulating the temperature and velocity fields at the combustion chamber outlet.

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