Gas turbine burner and gas turbine having the same

Abstract

The present invention relates to the technical field of energy conversion equipment, and in particular to a gas turbine burner and a gas turbine having the same. The gas turbine burner includes an air intake assembly, a primary mixing chamber, a secondary mixing chamber and a secondary mixing chamber. The inner cavity of the air intake assembly is divided into a mixing chamber and a fuel gas chamber. The mixing chamber is connected to the combustion-supporting gas inlet, and the fuel gas chamber is connected to the fuel inlet. A primary mixing fuel injection port is provided between the fuel gas chamber and the mixing chamber. By providing a mixing chamber, the combustion-supporting gas and the fuel gas enter the mixing chamber together. After the combustion-supporting gas enters, a local reflux entrainment zone will be formed on the back side, which will entrain the fuel gas ejected from the fuel injection port into the combustion-supporting gas, thereby reducing unstable combustion caused by uneven fuel mixing, reducing the thermal stress impact on the turbine blades caused by uneven gas temperature distribution, and improving the stability of the system operation.

Description

Technical Field

[0001] The present invention relates to the technical field of energy conversion equipment, and in particular to a gas turbine burner and a gas turbine having the same. Background Art

[0002] A gas turbine is an internal combustion engine that uses a continuously flowing gas as a working fluid to drive the high-speed rotation of its impeller, converting the fuel's energy into useful work. During high-temperature combustion, nitrogen and oxygen react in the air to form thermodynamic nitrogen oxides (NOx). To reduce NOx emissions, dry, low-nitrogen, lean-burn premixed combustion technology is now widely used. This premixed combustion reduces the flame surface temperature and thus controls NOx formation. However, during startup, to ensure combustion stability, gas turbines still use diffusion combustion. This high-temperature diffusion combustion flame surface leads to high NOx formation during startup, resulting in the visible yellow smoke at the chimney outlet in severe cases.

[0003] To reduce nitrogen oxide emissions during startup, gas turbines typically operate using lean premixed combustion. However, lean premixed combustion has a lower flame surface temperature, poorer combustion stability than diffusion combustion, and is highly sensitive to air pressure fluctuations at the combustor inlet. This pressure fluctuation disrupts the mixing of air and fuel, leading to uneven fuel mixing and unstable combustion. Furthermore, pressure fluctuations at the combustor inlet can affect the flame surface position, causing flame oscillation and partial flameout, leading to combustion instability and reducing combustion system reliability. Summary of the Invention

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defect of unstable combustion of gas turbines operated by lean premixed combustion technology in the prior art, thereby providing a gas turbine combustor and a gas turbine having the same.

[0005] In order to solve the above technical problems, the present invention provides a gas turbine combustor, comprising:

[0006] An air intake assembly, wherein the inner cavity thereof is divided into a mixing chamber and a fuel gas chamber, the mixing chamber is communicated with the combustion-supporting gas inlet, the fuel gas chamber is communicated with the fuel inlet, and a primary mixed fuel injection port is provided between the fuel gas chamber and the mixing chamber;

[0007] a primary mixing chamber, connected to the mixing chamber;

[0008] The combustion-supporting gas inlet and the fuel inlet are both connected to the mixing chamber, and a fuel injection hole is provided between the fuel inlet and the mixing chamber;

[0009] The post-mixing chamber is connected to the primary mixing chamber, and the outlet end of the post-mixing chamber is flush with the outlet end of the primary mixing chamber.

[0010] Optionally, the air intake assembly includes:

[0011] The flow guide shell has an inner partition plate installed inside, which divides the mixing chamber into an inner mixing area and an outer mixing area;

[0012] The fuel pipeline is communicated with the fuel gas chamber.

[0013] Optionally, the inner partition plate is trumpet-shaped, and the end of the partition plate with a larger opening area is arranged toward the air inlet end.

[0014] Optionally, the fuel pipeline includes a first fuel pipe and a second fuel pipe arranged inside and outside, the first fuel pipe is connected to the fuel gas chamber, the second fuel pipe is connected to the mixing chamber, and the service fuel injection hole is arranged between the second fuel pipe and the mixing chamber.

[0015] Optionally, a purge gas pipe is further installed inside the fuel pipeline, and the purge gas pipe extends to the connection point between the post-mixing chamber and the primary mixing chamber.

[0016] Optionally, a cooling interlayer is provided in the side wall of the purge gas pipe outlet end, the cooling interlayer is connected to the post-mixing chamber, a cooling gas hole is provided between the purge gas pipe and the cooling interlayer, and a purge gas injection hole is provided between the purge gas pipe and the post-mixing chamber.

[0017] Optionally, a first swirl assembly is fixedly installed between the primary mixing chamber and the post-mixing chamber;

[0018] And / or a second cyclone component is fixedly installed in the mixing chamber, and the second cyclone component is arranged close to the outlet of the mixing chamber.

[0019] Optionally, an outer layer guide plate is installed in the outer mixing zone, and the outer layer guide plate divides the outer mixing zone into an interlayer mixing zone and an outer layer mixing zone.

[0020] The present invention also provides a gas turbine having the gas turbine combustor of the present invention.

[0021] Optionally, it also includes an intake flow duct, an exhaust flow duct and a combustion and compression cylinder body. A silencer structure is provided on the side walls of the intake flow duct and / or the exhaust flow duct and / or the combustion and compression cylinder body. The silencer structure includes a silencer hole plate and a silencer bottom plate arranged in parallel. A silencer tube is fixedly installed between the silencer hole plate and the silencer bottom plate. The silencer tube is provided with silencer holes. A flexible silencer is filled between the silencer hole plate and the silencer bottom plate.

[0022] The technical solution of the present invention has the following advantages:

[0023] 1. The gas turbine burner provided by the present invention, when in operation, the fuel gas enters the fuel gas chamber from the fuel inlet, and the combustion-supporting gas enters the mixing chamber from the combustion-supporting gas inlet. When the fuel gas enters, it passes through the primary mixing fuel injection port between the fuel inlet and the mixing chamber to form a jet. The fuel gas and the combustion-supporting gas pass through the mixing chamber and enter the primary mixing chamber to mix, thereby obtaining a first mixed gas. The first mixed gas flows forward and enters the post-mixing chamber. Another stream of fuel gas entering from the fuel inlet and another stream of combustion-supporting gas entering from the combustion-supporting gas inlet are mixed in the post-mixing chamber. When the fuel gas enters, it passes through the post-mixing fuel injection port to form a jet, and is mixed to form a second mixed gas under the action of the jet. The first mixed gas enters the post-mixing chamber and continues to mix. At the outlet end of the post-mixing chamber of the burner, it mixes with the second mixed gas ejected from the post-mixing chamber. The external ignition device ignites the mixed gas to form a stable high-temperature combustion gas, thereby obtaining a final mixed flame. When the burner is working, a stream of fuel gas forms a jet through the primary mixing fuel injection port. Under the action of the jet, the combustion-supporting gas and the fuel gas are mixed in the primary mixing chamber and then enter the post-mixing chamber. Another stream of fuel gas forms a jet through the duty fuel injection hole and mixes with another stream of combustion-supporting gas in the duty mixing chamber. Finally, the two mixed gases are ejected from the outlet ends of the duty mixing chamber and the post-mixing chamber and ignited. By setting up a mixing chamber, the combustion-supporting gas and the fuel gas enter the mixing chamber together. After the combustion-supporting gas enters, a local reflux entrainment zone will be formed on the back side, which will entrain the fuel gas ejected from the fuel injection port into the combustion-supporting gas, causing the fuel gas and the combustion-supporting gas to collide with each other, and the mixed gas after the two jets are accelerated and mixed is finally mixed at the outlet end of the post-mixing chamber and ignited and output to the outside. By generating a local reflux entrainment zone when the combustion-supporting gas enters the mixing chamber, the fuel ejected from the fuel injection port is entrained into the combustion-supporting gas, which can greatly reduce the unstable combustion induced by uneven fuel mixing, thereby reducing the thermal stress impact on the turbine blades caused by uneven gas temperature distribution, and improving the stability of the gas turbine system operation.

[0024] 2. The gas turbine combustor provided by the present invention divides the mixing chamber by arranging a trumpet-shaped inner partition plate in the inner cavity of the air intake assembly, and allows the gas to enter the mixing chamber from the end with the larger opening, thereby reducing the noise caused by the sudden change in the cross-sectional area of ​​the gas flow path when the gas enters the mixing chamber.

[0025] 3. The gas turbine burner provided by the present invention transports fuel gas through fuel pipelines arranged inside and outside the burner, reducing the layout of pipelines inside the burner and improving the stability of the burner structure.

[0026] 4. The gas turbine burner provided by the present invention is equipped with a purge gas pipe to introduce purge gas from the fuel pipeline to prevent backfire at the outlet of the fuel pipeline from damaging the fuel pipeline and ensure that the fuel is burned outside the fuel pipeline.

[0027] 5. The gas turbine burner provided by the present invention sets a first swirl component between the primary mixing chamber and the post-mixing chamber; and sets a second swirl component between the value mixing chamber and the post-mixing chamber, so that the primary mixed gas and the secondary mixed gas can generate circumferential movement during the forward flow, forming a rotating airflow with a certain circumferential velocity, and further mixed in the post-mixing chamber, and finally ejected from the burner outlet in the form of a rotating jet for combustion. The rotating jet will also form a recirculation zone in the combustion chamber downstream of the burner, so that the high-temperature fuel gas after combustion is completed will reflux and stabilize at the head of the combustion chamber, playing a role in ignition and stabilizing the combustion flame surface.

[0028] 6. The gas turbine provided by the present invention utilizes a sound-absorbing structure to dissipate the vibration noise energy generated by gas entering or exiting the gas turbine by converting it into internal energy and kinetic energy within the flexible sound-absorbing component. This reduces the pressure pulsation of gas entering the intake assembly, thereby weakening the intensity of the gas pulsation and improving combustion stability in the combustion chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0030] Figure 1 Schematic diagram of the internal structure of a gas turbine combustor provided in an embodiment of the present invention.

[0031] Figure 2 It is a schematic structural diagram of a gas turbine combustor provided in an embodiment of the present invention.

[0032] Figure 3 It is a structural schematic diagram of the sound-absorbing structure provided in an embodiment of the present invention.

[0033] Figure 4 It is a side view of a sound absorption structure provided in an embodiment of the present invention.

[0034] Figure 5 It is a schematic cross-sectional view of the axis of the muffler tube of the muffler structure provided in an embodiment of the present invention.

[0035] Figure 6It is a schematic cross-sectional view of the axis of a column of a sound-absorbing structure provided in an embodiment of the present invention.

[0036] Figure 7 It is a schematic structural diagram of a gas turbine provided in an embodiment of the present invention.

[0037] Explanation of the reference numerals: 1. Intake trumpet flow passage; 2. Compressor; 3. Combustion chamber; 4. Turbine; 5. Combustion and compression cylinder; 6. Exhaust flow passage; 7. Rotor; 8. Generator; 9. Thrust bearing; 10. Turbine bearing; 11. Duty premix fuel pipe; 12. Main premix fuel pipe; 13. Burner body; 14. Fuel nozzle cover; 15. Ignitor; 16. Flame tube; 17. Transition section; 18. Main air inlet; 19. Primary mixed fuel injection port; 20. Inner partition plate; 21. Outer guide plate; 22. Intake assembly; 23. Main premix swirler blade ; 24. Service air inlet hole; 25. Primary mixing chamber; 26. Post-mixing chamber; 27. Service cyclone blade; 28. Purge gas pipe; 29. ​​Purge air injection hole; 30. Cooling gas hole; 31. Service fuel injection hole; 32. Service mixing chamber; 33. Second fuel pipe; 34. First fuel pipe; 35. Main premix fuel chamber; 36. Connecting flange; 37. Central mixing zone; 38. Interlayer mixing zone; 39. Outer mixing zone; 40. Silencer plate; 41. Silencer bottom plate; 42. Column; 43. Silencer wire; 44. Silencer tube; 45. Silencer hole. DETAILED DESCRIPTION

[0038] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0039] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0040] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0041] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0042] Example 1

[0043] like Figures 1 to 6 The figure shows a gas turbine combustor provided by this embodiment, which includes an air inlet assembly 22 , a primary mixing chamber 25 , a secondary mixing chamber 32 and a post-mixing chamber 26 .

[0044] The inner cavity of the air intake assembly 22 is divided into a mixing chamber and a main premix fuel chamber 35 serving as a fuel gas chamber. The mixing chamber is connected to the combustion-supporting gas inlet, and the fuel gas chamber is connected to the fuel inlet. A primary fuel injection port 19 is provided between the fuel gas chamber and the mixing chamber. The mixing chamber is connected to the primary mixing chamber 25. Both the combustion-supporting gas inlet and the fuel inlet are connected to the value mixing chamber 32, and a service fuel injection port 31 is provided between the fuel inlet and the value mixing chamber 32. The primary mixing chamber 25 is connected to the post-mixing chamber 26, and the outlet end of the post-mixing chamber is arranged flush with the outlet end of the said value mixing chamber.

[0045] The intake assembly 22 includes a flow guide housing and a fuel line. An inner partition plate 20 is installed within the flow guide housing, and the mixing chamber is divided into an inner mixing zone and an outer mixing zone by the inner partition plate. The fuel line is connected to the fuel gas chamber. To reduce the noise generated when the fuel gas enters the intake assembly 22, the inner partition plate 20 in this embodiment is trumpet-shaped, with the end of the inner partition plate 20 with the larger opening area facing the intake end. A trumpet-shaped outer flow guide plate 21 is also installed in the outer mixing zone. The outer flow guide plate 21 divides the outer mixing zone of the mixing chamber into an interlayer mixing zone 38 and an outer mixing zone 39.

[0046] The fuel pipeline includes a first fuel pipe 34 and a second fuel pipe 33 arranged inside and outside. The first fuel pipe 34 is connected to the fuel gas chamber, the second fuel pipe 33 is connected to the mixing chamber 32, and the service fuel injection hole 31 is arranged between the second fuel pipe 33 and the mixing chamber 32.

[0047] A purge gas pipe 28 is also installed inside the fuel pipeline, extending to the connection point between the post-mixing chamber 26 and the value mixing chamber 32. A cooling interlayer is provided in the sidewall of the outlet end of the purge gas pipe 28, which is connected to the post-mixing chamber 26. Cooling gas holes 30 are provided between the purge gas pipe 28 and the cooling interlayer, and purge gas injection holes are provided between the purge gas pipe 28 and the post-mixing chamber 26. A first swirl assembly is fixedly installed between the primary mixing chamber 25 and the post-mixing chamber 26. A second swirl assembly is fixedly installed in the value mixing chamber 32, located near the outlet of the value mixing chamber 32.

[0048] The head air intake assembly 22 of the gas turbine combustor has a double-layer hollow cup-shaped structure. The outer wall of the air intake assembly 22 is provided with a main air intake hole 18, which penetrates the air intake assembly 22 and is evenly arranged at equal angles around the circumference. An interlayer is provided on the outer wall of the air intake assembly 22. Within the interlayer, the wall surface of the main air intake hole 18 and the wall surface of the air intake assembly 22 form a main premix fuel chamber 35, which serves as the fuel gas chamber. Premix fuel injection ports 19 are evenly arranged on the inner wall of the head air intake assembly 22 and communicate with the main premix fuel chamber 35. The premix fuel injection ports 19 are connected to the first fuel pipe 34. The trumpet-shaped inner partition plate 20 and the trumpet-shaped outer guide plate 21 are connected to the inner wall of the air intake assembly 22. To facilitate installation on the gas turbine, a connecting flange 36 is installed on the left end of the air intake assembly 22, and the fuel pipeline is coaxially sleeved and installed within the connecting flange 36. The main premixing cyclone blade 23 as the first cyclone component is fixedly installed on the right side of the air intake component 22. The air intake component 22, the inner wall of the cylindrical primary mixing chamber 25 and the main premixing cyclone blade 23 enclose the primary mixing chamber 25. The on-duty air inlet hole 24 for introducing combustion-supporting gas into the mixing chamber 32 passes through the main premixing cyclone blade 23 and is connected to the mixing chamber 32. The mixing chamber 32 is a mixing chamber 32 formed by the inner wall of the cylindrical mixing chamber 32 and the outer wall of the hollow cylindrical purge gas pipe 28. The on-duty cyclone blade 27 as the second cyclone component is arranged at the right end of the mixing chamber 32. The side wall of the post-mixing chamber 26, the outer wall of the mixing chamber 32 and the main premixing cyclone blade 23 surround and form the post-mixing chamber 26. An annular purge cooling layer is defined within the sidewall interlayer at the right end of purge gas pipe 28 and communicates with the layer via cooling gas holes 30. A purge air injection hole 29 is defined on the right end face of purge gas pipe 28. A service fuel injection hole 31 connects the second fuel pipe 33 to the service mixing chamber 32 on the right side. Service fuel injection hole 31 is located to the right of service air inlet 24. A burner connection flange 36 and the outer wall of the second fuel pipe 33 form an annular first fuel pipe 34.

[0049] When the burner is installed on a gas turbine and is working, in the burner body 13, the main air participating in the combustion enters the primary mixing chamber 25 of the burner body 13 through the main air intake hole 18 on the air intake assembly 22; the main fuel participating in the combustion enters the main premixing fuel chamber 35 designed inside the air intake assembly 22 in turn through the main premixing fuel pipe 12 of the gas turbine and the first fuel pipe 34 of the burner, and is sprayed into the primary mixing chamber 25 through the primary mixing fuel injection port 19 opened on the inner wall of the air intake assembly 22; considering that the main air will form a local reflux suction zone on the back of the main air intake hole 18 when entering the primary mixing chamber 25 through the main air intake hole 18, the position of the primary mixing fuel injection port 19 is opened on the back of the main air intake hole 18, which is conducive to strengthening the mixing of air as a combustion-supporting gas and the fuel gas, and improving the mixing uniformity of the fuel. The trumpet-shaped inner partition plate 20 and the trumpet-shaped outer guide plate 21 divide the primary mixing chamber 25 into three fuel and air mixing areas, namely, a central mixing area 37, an interlayer mixing area 38, and an outer layer mixing area 39. The main air and main fuel entering from the left end face of the intake component 22 are mixed in the central mixing area 37 of the primary mixing chamber 25, and part of the main air and main fuel entering from the cylindrical wall of the intake component 22 are mixed in the interlayer mixing area 38 of the primary mixing chamber 25, and part are mixed in the outer layer mixing area 39 of the primary mixing chamber 25; this zoned mixing design divides the main air and main fuel into three parts, and each part of the air and fuel are mixed and then merged for further mixing, which helps to improve the mixing uniformity of air and combustion. After being pre-mixed in the primary mixing chamber 25, the main air and main fuel flow through the main pre-mixing swirler blades 23, which have a specific rotation angle. Under the guidance of the blades, the main air and main fuel mixture forms a swirling airflow with a specific circumferential velocity. It is further mixed in the post-pre-mixing chamber before being ejected from the right end of the burner into the combustion chamber 3 as a swirling jet for combustion. The swirling jet also forms a recirculation zone in the combustion chamber 3, causing the high-temperature combustion gas to reflux and stabilize at the head of the combustion chamber 3, thereby igniting and stabilizing the combustion flame surface. However, the gas turbine requires ignition by the igniter 15 at startup. After successful ignition, the high-temperature recirculation zone stabilizes the flame surface. Air participating in the on-duty combustion enters the on-duty mixing chamber 32 through the on-duty air inlet 24, where it is mixed with the on-duty fuel, which flows sequentially through the gas turbine's on-duty premix fuel pipe 11, the burner's second fuel pipe 33, and the on-duty fuel injection hole 31 and enters the on-duty mixing chamber 32. After mixing, it is formed into a rotating jet by the on-duty swirler blades 27 and injected into the combustion chamber 3 for combustion. After the purge air enters the purge gas pipe 28, a portion enters the cooling interlayer through the cooling gas hole 30, cooling the right end of the purge gas pipe 28 before entering the combustion chamber 3. A portion is injected into the combustion chamber 3 through the purge air injection hole 29 to prevent the recirculation zone from flashing back near the right end face of the burner, which could seriously damage the burner.

[0050] Example 2

[0051] like Figure 7 The figure shows a gas turbine provided by this embodiment, which has the gas turbine combustor described in Example 1.

[0052] The gas turbine also features an intake bell duct 1, which serves as the inlet flow passage. This bell-shaped duct features a wall that also utilizes the sound-absorbing structure described in Example 1. Located at the far left end of the gas turbine, this duct silences aerodynamic noise emanating from the gas turbine's air inlet, reducing noise near the gas turbine's air inlet. The compressor 2 is connected to the intake bell duct 1, which features a converging flow passage with a gradually decreasing flow area. The combustion and compression cylinder 5 is connected to the compressor 2, and its wall also utilizes the sound-absorbing structure described in Example 1. This silences the aerodynamic noise of the compressed air discharged from the compressor 2's exhaust port, reduces pressure pulsation within the combustion and compression cylinder 5, and improves the stability of the air entering the combustion chamber 3. The combustion chamber 3 is inserted obliquely into the combustion and compression cylinder 5, with the burner body 13 mounted at the inlet end of the combustion chamber 3. The combustion chamber 3 body is secured to the fuel nozzle cover 14 via a connecting flange 36. The turbine 4 is connected to the outlet of the combustion and compression cylinder 5, and the exhaust duct 6 is connected to the outlet of the turbine 4. The wall of the exhaust duct 6 adopts the sound-absorbing structure design of Example 1 to muffle the airflow noise generated by the gas turbine exhaust, thereby reducing the exhaust noise of the gas turbine. The rotor 7 is mounted at the center of the gas turbine, connecting the compressor 2 and the turbine 4. The compressor 2 is supported by a thrust bearing 9, and the turbine 4 is supported by a turbine bearing 10. The generator 8 is connected to the rotor 7 on the right side of the gas turbine. The gas turbine combustor is mounted on the fuel nozzle cover 14. The flame tube 16 is connected to the fuel nozzle cover 14. The igniter 15 is mounted on the flame tube 16. The transition section 17 is connected to the outlet of the flame tube 16. The outlet of the transition section 17 is connected to the inlet of the turbine 4. The service premix fuel pipe 11 and the main premix fuel pipe 12 are mounted on the fuel nozzle cover 14 and are connected to the second fuel pipe 33 and the first fuel pipe 34 of the gas turbine combustor, respectively.

[0053] The intake and exhaust ducts, as well as the sidewalls of the combustion and compression cylinder, are all equipped with a sound-absorbing structure. This structure comprises a parallel-arranged sound-absorbing plate 40 and a sound-absorbing base plate 41. A sound-absorbing tube 44 is fixedly mounted between the sound-absorbing plate 40 and the sound-absorbing base plate 41. The sound-absorbing tube 44 is provided with sound-absorbing holes 45. Flexible sound-absorbing components are placed between the sound-absorbing plate 40 and the sound-absorbing base plate 41. The intake ducts for fuel gas and combustion-supporting gas are trumpet-shaped, with sound-absorbing structures designed into the duct walls. Located at the far left end of the gas turbine, these structures silence aerodynamic noise emanating from the gas turbine inlet and reduce noise near the gas turbine inlet. The sound-absorbing plate 40 and the sound-absorbing base plate 41 are arranged in parallel, and their shapes align with those of the gas turbine's intake and exhaust ducts and the combustion and compression cylinder 5. The silencer plate 40 and the silencer base plate 41 are fixedly connected by a column 42. The column 42 is a solid cylindrical structure, installed between the silencer plate 40 and the base plate. It is the main load-bearing component of the silencer structure and is also used to install the silencer wire 43 as a flexible silencer. The silencer wire 43 is a millimeter-level metal filament, which is evenly and densely arranged on the column 42 in the circumferential direction. A silencer tube 44 is provided at the position corresponding to the opening on the silencer plate 40, and the silencer holes 45 are evenly arranged on the cylindrical silencer tube 44. The aperture of the opening on the silencer plate 40 is larger than the silencer hole 45. The cylindrical silencer tube 44 is arranged between the silencer plate 40 and the silencer base plate 41, and has the function of strengthening the strength of the silencer structure and improving the silencer effect.

[0054] When the gas turbine is working, the outside air is sucked into the gas turbine by the high-speed rotating compressor 2 through the air inlet horn flow channel 1, and is compressed and pressurized step by step by the compressor 2 before being discharged into the combustion and compression cylinder 5. Because the combustion and compression cylinder 5 is a large annular cavity, it has a buffering effect on the high-pressure air discharged by the compressor 2. At the same time, under the action of the silencer structure on the wall of the combustion and compression cylinder 5, the pressure pulsation energy of the high-pressure air is converted into the mechanical vibration energy of the silencer structure, thereby reducing the pressure pulsation of the high-pressure air in the combustion and compression cylinder 5. After buffering and reducing the pressure pulsation, the high-pressure air enters the sandwich flow channel formed by the outer wall and inner wall of the transition section 17 through the air inlet hole opened on the outer wall of the transition section 17, and then flows back along the sandwich flow channel to the head of the flame tube 16, and enters the gas turbine combustor through the air inlet hole opened on the inner wall of the head of the flame tube 16.

[0055] After passing through the burner body 13, the air and fuel are fully combusted in the flame tube 16 via premixed combustion to form high-temperature combustion gas. This is then further mixed and evenly mixed in the transition section 17, resulting in a more uniform temperature distribution at the outlet of the transition section 17 and reducing the thermal stress impact on the turbine blades caused by uneven temperature distribution. The high-temperature, high-pressure combustion gas ejected from the outlet of the transition section 17 expands step by step within the turbine 4, generating work and driving the rotor 7 to rotate at high speed. The rotor 7 then drives the generator 8 to continuously output electrical energy. After completing the work, the exhaust gas is discharged from the gas turbine through the exhaust duct 6. To improve the utilization of the exhaust gas's waste heat, a waste heat boiler is typically deployed downstream of the gas turbine to further utilize the exhaust gas's heat and improve energy efficiency.

[0056] The gas turbine provided in this embodiment has premixed chamber structures for the main air and main fuel, as well as the pilot air and pilot fuel, designed in the fully premixed burner. This allows the main air and main fuel, as well as the pilot air and pilot fuel, to be evenly mixed before combustion. After this mixing, a stable premixed combustion flame is formed within the combustion chamber 3. Compared to diffusion combustion, premixed combustion has the advantage of generating less nitrogen oxide emissions due to the lower combustion flame surface temperature. Premixed combustion can be achieved throughout the entire process from startup to shutdown, reducing nitrogen oxide emissions.

[0057] Premixed combustion in gas turbines is very sensitive to fluctuations in the fuel-air equivalence ratio and fuel calorific value of the combustible mixture, and can easily lead to combustion instability failures due to pulsations in the fuel-air equivalence ratio and fuel calorific value. Designing the primary fuel injection port 19 of the fully premixed burner on the back side of the main air intake port 18 can take advantage of the fact that the main air passing through the main air intake port 18 forms an entrainment recirculation zone on the back side thereof. This allows the main fuel to be entrained and mixed with the main air immediately after being ejected from the primary fuel injection port 19, thereby improving the mixing uniformity of the main air and main fuel. This ensures that the fuel-air equivalence ratio and fuel calorific value of the combustible mixture entering the combustion chamber 3 remain essentially unchanged, thereby improving the combustion stability of the gas turbine.

[0058] The sidewalls of the intake and exhaust ducts feature a silencer design. Noise emitted during gas turbine operation enters the silencer structure through holes in the silencer plate 40 on the duct wall, compressing the air within. The viscous force of the air within the silencer structure initially attenuates the noise. The attenuated noise then enters the interlayer space between the silencer plate 40 and the silencer base plate 41 through the silencer holes 45 in the silencer tube 44. The silencer wire 43 vibrates and deforms under the influence of the noise pressure, converting the noise energy into mechanical vibration energy. This significantly reduces the noise emitted from the gas turbine's intake bell duct 1 and exhaust duct 6. This reduces the pressure pulsation of the air discharged from the compressor 2, thereby weakening the pulsation intensity of the air entering the combustion chamber 3 and improving the combustion stability of the combustion chamber 3.

[0059] A muffler structure is designed on the wall of the combustion and compression cylinder 5 downstream of the exhaust port of the gas turbine compressor 2. A muffler wire 43 is used to convert noise energy into vibrational mechanical energy, significantly reducing the exhaust noise of compressor 2. This reduces the pressure pulsation of the compressor 2 exhaust, allowing air in the combustion and compression cylinder 5 to enter the combustion chamber 3 continuously and stably. This eliminates the excitation factor of the pressure pulsation of the air inlet to the combustion chamber 3 that induces combustion instability, thereby improving the combustion stability of the combustion chamber 3. A muffler structure is designed on the gas turbine's intake horn flow passage 1 and exhaust flow passage 6. A muffler wire 43 is used to convert noise energy into vibrational mechanical energy, significantly reducing the noise emitted by the gas turbine's intake horn flow passage 1 and exhaust flow passage 6.

[0060] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Those skilled in the art will readily appreciate that other variations or modifications based on the above descriptions are possible. It is not necessary and impossible to enumerate all implementation methods here. Obvious variations or modifications arising therefrom remain within the scope of protection of the present invention.

Claims

1. A gas turbine combustor, characterized in that: include: An air intake assembly (22), the inner cavity of which is divided into a mixing chamber and a fuel gas chamber, the mixing chamber being in communication with the combustion-supporting gas inlet, the fuel gas chamber being in communication with the fuel inlet, and a primary fuel injection port (19) being provided between the fuel gas chamber and the mixing chamber; a primary mixing chamber (25) communicating with the blending chamber; A mixing chamber (32), an inlet of a combustion-supporting gas participating in on-duty combustion and the fuel inlet are in communication with the mixing chamber (32), and an on-duty fuel injection hole (31) is provided between the fuel inlet and the mixing chamber (32); A post-mixing chamber (26), wherein the primary mixing chamber (25) is connected to the post-mixing chamber (26), and the outlet end of the post-mixing chamber is flush with the outlet end of the primary mixing chamber; The air intake assembly (22) comprises: A flow guide housing is installed inside thereof with an inner layer partition plate (20), the inner layer partition plate divides the mixing chamber into an inner layer mixing zone and an outer layer mixing zone, the inner layer partition plate (20) is trumpet-shaped, and the end of the inner layer partition plate (20) with a larger opening area is arranged toward the air inlet end, and an outer layer guide plate (21) is installed in the outer layer mixing zone, and the outer layer guide plate (21) divides the outer layer mixing zone into an interlayer mixing zone (38) and an outer layer mixing zone (39); A fuel pipeline is connected to the fuel gas chamber, the fuel pipeline includes a first fuel pipe (34) and a second fuel pipe (33) arranged inside and outside, the first fuel pipe (34) is connected to the fuel gas chamber, the second fuel pipe (33) is connected to the mixing chamber (32), and the duty fuel injection hole (31) is provided between the second fuel pipe (33) and the mixing chamber (32); A main air inlet is provided on the outer wall of the air intake assembly, and the main air inlet runs through the air intake assembly. An interlayer is provided on the outer wall of the air intake assembly. The wall of the main air inlet and the wall of the air intake assembly in the interlayer form a main premixed fuel chamber serving as a fuel gas chamber. The primary mixed fuel injection port is arranged on the inner wall of the head air intake assembly and is connected to the main premixed fuel chamber. The primary mixed fuel injection port is connected to the first fuel pipe, and the duty air inlet for introducing combustion-supporting gas into the value mixing chamber passes through the main premixed swirler blades and is connected to the value mixing chamber.

2. The gas turbine combustor according to claim 1, characterized in that A purge gas pipe (28) is also sleeved and installed inside the fuel pipeline, and the purge gas pipe (28) extends to the connection point between the post-mixing chamber (26) and the value mixing chamber (32).

3. The gas turbine combustor according to claim 2, characterized in that A cooling interlayer is provided in the side wall of the outlet end of the purge gas pipe (28), the cooling interlayer is communicated with the post-mixing chamber (26), a cooling gas hole (30) is provided between the purge gas pipe (28) and the cooling interlayer, and a purge gas injection hole is provided between the purge gas pipe (28) and the post-mixing chamber (26).

4. The gas turbine combustor according to claim 1, wherein: A first swirl assembly is fixedly installed between the primary mixing chamber (25) and the post-mixing chamber (26); And / or a second cyclone component is fixedly installed in the mixing chamber (32), and the second cyclone component is arranged close to the outlet of the mixing chamber (32).

5. A gas turbine, characterized in that: A gas turbine combustor according to any one of claims 1 to 4.

6. The gas turbine according to claim 5, further comprising an intake flow passage, an exhaust flow passage and a combustion and compression cylinder, characterized in that: A silencer structure is provided on the side wall of the intake flow channel and / or the exhaust flow channel and / or the combustion and compression cylinder body, and the silencer structure includes a silencer hole (45) plate and a silencer bottom plate (41) arranged in parallel, a silencer tube (44) is fixedly installed between the silencer hole (45) plate and the silencer bottom plate (41), a silencer hole (45) is provided on the silencer tube (44), and a flexible silencer is filled between the silencer hole (45) plate and the silencer bottom plate (41).

Images