A swirl nozzle device suitable for a gas turbine combustion chamber

Abstract

The present invention discloses a swirl nozzle device suitable for a gas turbine combustion chamber, the swirl nozzle comprises components such as a diffusion air cavity, a diffusion fuel cavity, a nozzle cover, a premixed swirl assembly, a diffusion swirl assembly, a nozzle core, etc., which can be independently processed and disassembled, and a premixed fuel inlet hole and a premixed air inlet hole are arranged in the nozzle cover. When the combustion chamber of the gas turbine is running, the premixed fuel is directly supplied to the premixing channel inside the swirl nozzle from the premixed fuel inlet hole, and is preliminarily mixed with the compressed air upstream of the swirl blade. The preliminary premixed gas is then swirled through the swirl blade and further mixed in the premixing channel. When replacing the fuel nozzle components, the components of the fuel nozzle can be replaced according to the damage of the components. The present invention does not need to set a fuel cavity inside the swirl blade, which can reduce the processing difficulty of the swirl nozzle; because the components of the fuel nozzle provided by the present invention can be independently processed, disassembled, installed and replaced, the maintenance and replacement costs of the swirl nozzle of the gas turbine power plant can be reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of gas turbines, and in particular relates to a swirl nozzle device suitable for a combustion chamber of a gas turbine. Background Art

[0002] As a highly efficient energy conversion device, gas turbines are widely used in the industrial field. As one of the core components of the combustion chamber, the fuel nozzle of the gas turbine needs to be replaced during minor, medium and major repairs of the gas turbine and when the combustion chamber components are damaged. At present, most gas turbines in service use DLN swirl nozzles (or DLN burners), which mainly include nozzle cover, nozzle center body, nozzle swirl blades, purge pipes and other components, and the nozzle swirl blades are installed on the nozzle center body. Among them, the nozzle cover, nozzle center body and swirl blades constitute an annular channel, and the compressed air enters the annular channel from the upstream of the nozzle and flows in the annular channel; the nozzle center body is provided with a premixing and diffusion fuel channel; the swirl blade is provided with a premixing fuel cavity inside, which is connected to the premixing fuel supply channel inside the nozzle center body, and the swirl blade surface is provided with a fuel hole, which is connected to the premixing fuel cavity. The premixed fuel is injected into the premixing fuel cavity of the swirl blade through the premixing fuel channel of the nozzle center body, and is sprayed into the annular cavity through the fuel hole on the surface of the swirl blade, and is premixed with the compressed air in the premixing section downstream of the swirl blade, and then sprayed into the combustion chamber for combustion. The diffusion fuel passes through the channels inside the center body of the diffusion nozzle and is injected into the combustion chamber through the diffusion swirl channel at the head of the center body.

[0003] The swirl nozzles in the combustion chambers of in-service gas turbines have the following problems: 1) The nozzle swirl blades are hollow blades with a fuel cavity and a diffusion air cavity inside, and fuel holes are provided on the swirl blades. The swirl blade processing technology is complicated, resulting in great difficulty and high cost in the design and processing of the swirl nozzles; 2) Except for the nozzle core, the various nozzle components are welded or connected together in a tight fit. Every time the combustion chamber swirl nozzle is replaced during minor, medium and major repairs of the gas turbine, regardless of whether the hot and cold end components of the swirl nozzle are damaged, they must be repaired or replaced as a whole, and gas turbine power generation companies need to spend a lot of extra money every year. Summary of the invention

[0004] In order to solve the problems of difficulty in machining the center body of the fuel nozzle of the combustion chamber of the in-service gas turbine and high replacement and maintenance costs, the present invention provides a swirl nozzle device suitable for the combustion chamber of the gas turbine.

[0005] The present invention is achieved by adopting the following technical solutions:

[0006] A swirl nozzle device suitable for a gas turbine combustion chamber, comprising a diffusion air cavity, a diffusion fuel cavity, a nozzle cover, a premixing swirl assembly, a diffusion swirl assembly and a nozzle core; wherein the diffusion air cavity, the diffusion fuel cavity and the nozzle cover are connected in sequence, the nozzle core is located inside the diffusion swirl assembly, the diffusion swirl assembly is located inside the premixing swirl assembly, and the premixing swirl assembly is located inside the nozzle cover; the nozzle core is installed on the diffusion swirl end cover by using a nozzle core strip located at the front end of the nozzle core; the diffusion swirl assembly and the diffusion fuel cavity are connected by using the internal thread at the upper end of the diffusion fuel end cover of the diffusion swirl assembly; the premixing swirl assembly and the diffusion fuel cavity are tightly connected by relying on the external thread at the lower end of the diffusion fuel cavity and the external thread at the upper end of the premixing swirl assembly front cavity of the premixing swirl assembly; the nozzle cover and the diffusion fuel cavity are tightly connected by relying on the flange on the nozzle cover and the diffusion fuel cavity end cover;

[0007] The diffusion air cavity is provided with a diffusion air inlet hole, the diffusion fuel cavity is provided with a diffusion fuel inlet hole, the nozzle cover is provided with a premixed air inlet hole and a premixed fuel inlet hole, the premixed swirl assembly is provided with swirl blades, the diffusion fuel cavity, the premixed swirl assembly and the nozzle cover together constitute a premixed swirl channel, the diffusion swirl assembly has a diffusion swirl channel, the diffusion fuel cavity, the diffusion swirl assembly and the premixed swirl assembly together constitute a diffusion fuel channel, and the diffusion air cavity, the nozzle inner core and the diffusion swirl assembly together constitute a diffusion air channel.

[0008] A further improvement of the present invention is that a diffusion air inlet hole is provided at the center of the diffusion air end cover of the diffusion air cavity.

[0009] A further improvement of the present invention is that a tongue depressor is reserved at the end cover of the diffusion fuel cavity for further fixing the nozzle core pressure strip, thereby achieving a tight connection between the nozzle core and the diffusion swirl assembly and ensuring that the nozzle core does not loosen.

[0010] A further improvement of the present invention is that a concave sealing groove is reserved at the lower end of the diffusion fuel chamber end cover, and a convex sealing ring is reserved on the flange of the nozzle cover. The sealing groove and the sealing ring are used together to strengthen the seal between the diffusion fuel chamber end cover and the flange of the nozzle cover.

[0011] A further improvement of the present invention is that a plurality of diffusion fuel inlet holes are evenly distributed along the circumference tangent of the diffusion fuel end cover.

[0012] A further improvement of the present invention is that a premix air collecting chamber and a premix fuel collecting chamber are provided on the circumference of the nozzle cover.

[0013] A further improvement of the present invention is that a plurality of premixed air inlet holes are arranged along the circumference tangent direction of the premixed air collecting cavity.

[0014] A further improvement of the present invention is that a plurality of premix fuel inlet holes are arranged along the circumferential tangent direction of the premix fuel collecting cavity.

[0015] A further improvement of the present invention is that small holes are provided between the nozzle shell of the nozzle cover and the premix fuel collecting cavity, and between the nozzle shell and the premix fuel collecting cavity, and the small holes are densely distributed honeycomb holes.

[0016] A further improvement of the present invention is that when the swirl nozzle is working, the diffused air is injected into the nozzle through the diffused air inlet hole on the diffused air cavity, and is injected into the combustion chamber through the diffused air channel composed of the diffused air cavity, the diffused swirl component and the nozzle inner core, and is mixed with the diffused fuel and burned; the diffused fuel is injected into the nozzle through the diffused fuel inlet hole on the diffused fuel cavity, and is injected into the combustion chamber through the diffused fuel channel composed of the diffused fuel cavity, the diffused swirl component and the premixed swirl component, and is mixed with the diffused air and the premixed air to form a flow field condition suitable for diffusion combustion; the premixed air is first ... inlet hole on the diffused fuel cavity, and is injected into the combustion chamber through the diffused fuel inlet hole on the diffused fuel cavity, and is injected into the combustion chamber through the diffused fuel inlet hole on the diffused fuel cavity, and is injected into the combustion chamber through the diffused fuel inlet hole The premixed air inlet hole on the cover is injected into the premixed air collecting chamber, and then injected into the nozzle through a small hole located between the nozzle shell and the premixed air collecting chamber, mixed with the premixed fuel in the premixing channel composed of the nozzle cover and the premixing swirl component, and injected into the combustion chamber for combustion; the premixed fuel is first injected into the premixed fuel collecting chamber through the premixed fuel inlet hole on the nozzle cover, and then injected into the nozzle through a small hole located between the nozzle shell and the premixed fuel collecting chamber, mixed with the premixed air in the premixing channel composed of the nozzle cover and the premixing swirl component, and injected into the combustion chamber to form flow field conditions suitable for premixed combustion.

[0017] The present invention has at least the following beneficial technical effects:

[0018] The present invention provides a swirl nozzle device suitable for a gas turbine combustion chamber, comprising a diffusion air chamber, a diffusion fuel chamber, a nozzle cover, a premixed swirl assembly, a diffusion swirl assembly, a nozzle core and other components. The diffusion air chamber is connected to the diffusion fuel chamber, and the diffusion air chamber has a diffusion air inlet hole, and the diffusion fuel chamber has a diffusion fuel inlet hole. The nozzle cover is connected to the diffusion fuel chamber, and the nozzle cover has a premixed air inlet hole and a premixed fuel inlet hole. The premixed swirl assembly is located inside the nozzle cover, connected to the diffusion fuel chamber, and the premixed swirl assembly has swirl blades; in addition, the diffusion fuel chamber, the premixed swirl assembly and the nozzle cover together form a premixed swirl channel, and the premixed fuel and premixed air are mixed in the premixed swirl channel and injected into the combustion chamber. The diffusion swirl assembly is located inside the premixing swirl assembly and is connected to the diffusion cavity, and the diffusion swirl assembly has a diffusion swirl channel; in addition, the diffusion fuel cavity, the diffusion swirl assembly and the premixing swirl assembly together form a diffusion fuel channel, and the diffusion fuel is injected into the combustion chamber through the diffusion swirl channel to mix with the air injected into the combustion chamber and burn. The nozzle core is located inside the diffusion swirl assembly and is connected to the diffusion fuel cavity; in addition, the diffusion air cavity, the nozzle core and the diffusion swirl assembly together form a diffusion air channel, and the diffusion air is injected into the combustion chamber through the diffusion swirl channel to mix with the diffusion fuel injected into the combustion chamber and burn. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the system structure of the present invention.

[0020] Figure 2 It is a cross-sectional view of the swirl nozzle in the present invention.

[0021] Figure 3 It is a cross-sectional view of the diffused air cavity in the present invention.

[0022] Figure 4 It is a cross-sectional view of the diffusion fuel cavity in the present invention.

[0023] Figure 5 It is a cross-sectional view of the nozzle cover in the present invention.

[0024] Figure 6 It is a cross-sectional view of the premixing swirl component in the present invention.

[0025] Figure 7 It is a cross-sectional view of the diffusion cyclone component in the present invention.

[0026] Figure 8 It is a cross-sectional view of the inner core of the nozzle in the present invention.

[0027] Fig. 9 It is a schematic diagram of an embodiment of the present invention.

[0028] Description of reference numerals:

[0029] 1 diffusion air cavity; 1-1 diffusion air cavity end cover; 1-2 diffusion air inlet hole; 2 diffusion fuel cavity; 2-1 diffusion fuel cavity end cover; 2-2 diffusion fuel inlet hole; 3 nozzle cover; 3-1 nozzle cover flange; 3-2 premixed air inlet hole; 3-3 premixed fuel inlet hole; 3-4 premixed air collecting cavity; 3-5 premixed fuel collecting cavity; 3-6 nozzle shell; 4 premixed swirl assembly; 4-1 premixed swirl assembly front cavity; 4-2 swirl blade; 4-3 premixed swirl inner tube; 5 diffusion swirl assembly; 5-1 diffusion swirl end cover; 5-2 diffusion inner tube; 5-3 diffusion swirl nozzle; 6 nozzle inner core; 6-1 nozzle inner core bead; 6-2 nozzle inner core rod. DETAILED DESCRIPTION

[0030] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments, but the present invention is not limited to these embodiments.

[0031] The application fields of the present invention are as follows Figure 4 The gas turbine swirl nozzle shown. Figures 1 to 9 As shown, the present invention provides a swirl nozzle device suitable for a gas turbine combustion chamber, comprising a nozzle diffusion air cavity 1, a diffusion fuel cavity 2, a nozzle outer cover 3, a premixing swirl component 4, a diffusion swirl component 5 and a nozzle inner core 6.

[0032] Among them, the diffusion air cavity 1 is connected to the diffusion fuel cavity 2, the diffusion fuel cavity 2 is connected to the nozzle cover 3, and the nozzle core 6 is located inside the diffusion swirl assembly 5, the diffusion swirl assembly 5 is located inside the premixed swirl assembly 4, and the premixed swirl assembly 4 is located inside the nozzle cover 3; the nozzle core 6 is provided with a nozzle core strip 6-1 and a nozzle core rod 6-2, and the nozzle core strip 6-1 is arranged at the front end of the nozzle core rod 6-2; the nozzle core strip 6-1 is installed in the pressure groove at the upper end of the diffusion swirl end cover 5-1 to achieve a tight fit connection between the nozzle core 6 and the diffusion swirl assembly 5; the diffusion swirl assembly 5 is provided with a diffusion swirl end cover 5-1, a diffusion inner tube 5-2 and a diffusion swirl nozzle 5-3, and the diffusion swirl end cover 5-1 is located at the front end of the diffusion inner tube 5-2, and the diffusion swirl nozzle 5-3 is located downstream of the diffusion inner tube 5-2; the diffusion swirl assembly 5 and the diffusion fuel cavity 2 are tightly fitted and connected by the internal thread at the upper end of the diffusion fuel end cover 5-1;

[0033] The premixed swirl assembly 4 has a premixed swirl assembly front chamber 4-1, swirl blades 4-2 and a premixed swirl inner tube 4-3, and the premixed swirl blades 4-2 are evenly distributed on the outer wall surface of the premixed swirl inner tube 4-3 in the circumferential direction; the premixed swirl assembly 4 and the diffusion fuel chamber 2 are tightly connected by the external thread at the lower end of the diffusion fuel end cover 2-1 and the external thread at the upper end of the premixed swirl assembly front chamber 4-1;

[0034] The nozzle cover 3 has a nozzle cover flange 3-1, a premixed air inlet hole 3-2 and a premixed fuel inlet hole 3-3; the nozzle cover 3 and the diffusion fuel chamber 2 are tightly connected by the nozzle cover flange 3-1 and the diffusion fuel chamber end cover 2-1.

[0035] The diffusion air end cover 1-1 of the diffusion air cavity 1 has a diffusion air inlet hole 1-2 at the center; the diffusion fuel end cover 2-1 of the diffusion fuel cavity 2 has a diffusion fuel inlet hole 2-2; the diffusion fuel cavity 2, the premixed swirl component 4 and the nozzle outer cover 3 together constitute a premixed swirl channel, the diffusion swirl component 4 has a diffusion swirl channel, the diffusion fuel cavity 2, the diffusion swirl component 5 and the premixed swirl component 4 together constitute a diffusion fuel channel, and the diffusion air cavity 1, the nozzle inner core 6 and the diffusion swirl component 5 together constitute a diffusion air channel.

[0036] When the swirl nozzle is working, the diffused air is injected into the nozzle through the diffused air inlet hole 1-2 on the diffused air cavity 1, and is guided by the diffused swirl nozzle 5-3 to form a swirl through the diffused air channel composed of the diffused air cavity 1, the diffused swirl component 5 and the nozzle inner core 6, and is injected into the combustion chamber, and is mixed with the diffused fuel and burned; the diffused fuel is injected into the nozzle through the diffused fuel inlet hole 2-2 on the diffused fuel cavity 2, and is guided by the diffused swirl nozzle 5-3 to form a swirl through the diffused fuel channel composed of the diffused fuel cavity 2, the diffused swirl component 5 and the premixed swirl component 4, and is injected into the combustion chamber, and is mixed with the diffused air and premixed air to form a flow field condition suitable for diffusion combustion; the premixed air is first injected into the premixed air collecting cavity 3-4 through the premixed air inlet hole 3-2 on the nozzle outer cover 3, and then is injected into the combustion chamber by the diffused swirl nozzle 5-3 located at the nozzle cover 3 The small hole between the nozzle shell 3-6 and the premixed air collecting chamber 3-4 is injected into the nozzle, preliminarily mixed with the premixed fuel upstream of the swirl blade 4-2, and guided by the swirl blade 4-2 to form a swirl, mixed with the premixed fuel in the premixing channel composed of the nozzle cover 3 and the premixing swirl component 4, and injected into the combustion chamber for combustion; the premixed fuel is first injected into the premixed fuel collecting chamber 3-5 through the premixed fuel inlet hole 3-3 on the nozzle cover 3, and then injected into the nozzle through the small hole located between the nozzle shell 3-6 and the premixed fuel collecting chamber 3-5, preliminarily mixed with the premixed air upstream of the swirl blade 4-2, and guided by the swirl blade 4-2 to form a swirl, mixed with the premixed air in the premixing channel composed of the nozzle cover 3 and the premixing swirl component 4, and injected into the combustion chamber to form flow field conditions suitable for premixed combustion.

[0037] Preferably, a pressing tongue can be reserved on the diffusion fuel end cover 2-1. When the diffusion fuel chamber 2 and the diffusion swirl assembly 5 are connected, the pressing tongue can further tighten the nozzle core strip 6-2 fixed in the diffusion swirl end cover 5-1, thereby achieving a tight connection between the nozzle core 6 and the diffusion swirl assembly 5 and ensuring that the nozzle core 6 will not loosen.

[0038] Preferably, a concave sealing groove may be reserved at the lower end of the diffusion fuel end cover 2-1, and a convex sealing ring may be reserved on the nozzle cover flange 3-1, so as to further strengthen the sealing between the diffusion fuel end cover 2-1 and the nozzle cover flange 3-1.

[0039] Preferably, a plurality of diffusion fuel inlet holes 2-2 can be evenly distributed tangentially along the circumference of the diffusion fuel end cover 2-1, so as to reduce the flow resistance of the diffusion fuel while ensuring the flow rate of the diffusion fuel, and form a pre-swirl flow before the fuel enters the diffusion fuel inlet channel to increase the turbulence of the diffusion fuel and promote the mixing between the diffusion fuel and the air.

[0040] Preferably, multiple premixed air inlet holes 3-2 can be evenly arranged tangentially along the circumference of the premixed air collecting chamber 3-4, so as to reduce the flow resistance of the premixed air while ensuring the premixed air flow rate, and form a pre-swirl flow before the premixed air enters the premixed air intake channel to increase the turbulence of the premixed air and promote the mixing between the premixed air and the premixed fuel.

[0041] Preferably, a plurality of premixed fuel inlet holes 3-3 can be evenly arranged tangentially along the circumference of the premixed fuel collecting cavity 3-5, so as to reduce the flow resistance of the premixed fuel while ensuring the flow rate of the premixed fuel, and form a pre-swirl flow before the premixed fuel enters the premixed fuel inlet channel, so as to increase the turbulence of the premixed fuel and promote the mixing between the premixed fuel and the premixed air.

[0042] Preferably, the small holes located between the nozzle housing 3-6 and the premixed air collecting chamber 3-4 and the small holes located between the nozzle housing 3-6 and the premixed fuel collecting chamber 3-5 can be replaced by densely distributed honeycomb holes to ensure the flow rate of premixed air and fuel and promote the uniform injection of premixed air and premixed fuel into the premixing channel of the swirl nozzle.

[0043] Example

[0044] like Fig. 9As shown, the present invention provides a swirl nozzle suitable for a gas turbine, comprising a nozzle diffusion air cavity 1, a diffusion fuel cavity 2, a nozzle cover 3, a premixed swirl assembly 4, a diffusion swirl assembly 5 and a nozzle core 6. The diffusion air cavity 1 is connected to the diffusion fuel cavity 2, the diffusion fuel cavity 2 is connected to the nozzle cover 3, and the nozzle core 6 is located inside the diffusion swirl assembly 5, the diffusion swirl assembly 5 is located inside the premixed swirl assembly 4, and the premixed swirl assembly 4 is located inside the nozzle cover 3; the nozzle core pressure strip 6-2 is installed in the pressure groove at the upper end of the diffusion swirl end cover 5-1; the diffusion swirl assembly 5 and the diffusion fuel cavity 2 are tightly matched and connected by the internal thread at the upper end of the diffusion fuel end cover 5-1; the premixed swirl assembly 4 and the diffusion fuel cavity 2 are tightly matched and connected by the external thread at the lower end of the diffusion fuel end cover 2-1 and the external thread at the upper end of the premixed swirl assembly front cavity 4-1; the nozzle cover 3 and the diffusion fuel cavity 2 are tightly matched and connected by the nozzle cover flange 3-1 and the diffusion fuel cavity end cover 2-1.

[0045] When the swirl nozzle is working, the diffused air is injected into the nozzle from the 2 diffused air inlet holes 1-2 on the diffused air cavity 1, and is injected into the combustion chamber through the diffused air channel composed of the diffused air cavity 1, the diffused swirl component 5 and the nozzle inner core 6, and is guided by the diffused swirl nozzle 5-3 to form a swirl, and is mixed with the diffused fuel and burned; the diffused fuel is injected into the nozzle from the diffused fuel inlet hole 2-2 on the diffused fuel cavity 2, and is injected into the nozzle through the diffused fuel channel composed of the diffused fuel cavity 2, the diffused swirl component 5 and the premixed swirl component 4, and is guided by the diffused swirl nozzle 5-3 to form a swirl, and is mixed with the diffused air and the premixed air to form a flow field condition suitable for diffusion combustion; the premixed air First, the premixed air is injected into the premixed air collecting chamber 3-4 through the premixed air inlet hole 3-2 on the nozzle outer cover 3, and then injected into the nozzle through the small hole located between the nozzle shell 3-6 and the premixed air collecting chamber, mixed with the premixed fuel in the premixing channel composed of the nozzle outer cover 3 and the premixed swirl component 4, and injected into the combustion chamber for combustion; the premixed fuel is first injected into the premixed fuel collecting chamber 3-5 through the premixed fuel inlet hole 3-3 on the nozzle outer cover 3, and then injected into the nozzle through the small hole located between the nozzle shell 3-6 and the premixed fuel collecting chamber 3-5, mixed with the premixed air in the premixing channel composed of the nozzle outer cover 3 and the premixed swirl component 4, and injected into the combustion chamber to form flow field conditions suitable for premixed combustion.

[0046] Preferably, a pressing tongue can be reserved on the diffusion fuel end cover 2-1. When the diffusion fuel chamber 2 and the diffusion swirl assembly 5 are connected, the pressing tongue can further tighten the nozzle core strip 6-2 fixed in the diffusion swirl end cover 5-1, thereby achieving a tight connection between the nozzle core 6 and the diffusion swirl assembly 5 and ensuring that the nozzle core 6 will not loosen.

[0047] Preferably, a concave sealing groove may be reserved at the lower end of the diffusion fuel end cover 2-1, and a convex sealing ring may be reserved on the nozzle cover flange 3-1, so as to further strengthen the sealing between the diffusion fuel end cover 2-1 and the nozzle cover flange 3-1.

[0048] Preferably, four diffusion fuel inlet holes 2-2 can be evenly distributed tangentially along the circumference of the diffusion fuel end cover 2-1, while ensuring the diffusion fuel flow rate, reducing the diffusion fuel flow resistance, and forming a pre-swirl flow before the fuel enters the diffusion fuel inlet channel to increase the turbulence of the diffusion fuel and promote mixing between the diffusion fuel and air.

[0049] Preferably, 8 premixed air inlet holes 3-2 can be evenly arranged tangentially along the circumference of the premixed air collecting chamber 3-4, with a hole diameter ranging from 12mm to 18mm. While ensuring the premixed air flow rate, the premixed air flow resistance is reduced, and a pre-swirl is formed before the premixed air enters the premixed air intake channel to increase the turbulence of the premixed air and promote the mixing between the premixed air and the premixed fuel.

[0050] Preferably, four premixed fuel inlet holes 3-3 may be evenly arranged tangentially along the circumference of the premixed fuel collecting cavity 3-5, with a hole diameter ranging from 6 mm to 10 mm. While ensuring the flow rate of the premixed fuel, the flow resistance of the premixed fuel is reduced, and a pre-swirl flow is formed before the premixed fuel enters the premixed fuel inlet channel to increase the turbulence of the premixed fuel and promote the mixing between the premixed fuel and the premixed air.

[0051] Preferably, the small holes located between the nozzle housing 3-6 and the premixed air collecting chamber 3-4, and the small holes located between the nozzle housing 3-6 and the premixed fuel collecting chamber 3-5 can be replaced by densely distributed honeycomb holes, and the equivalent pore size is between 4mm and 6mm, so as to ensure the flow rate of premixed air and fuel, and promote the uniform injection of premixed air and premixed fuel into the premixing channel of the swirl nozzle.

Claims

1. A swirl nozzle device suitable for a gas turbine combustion chamber, characterized in that: It includes a diffusion air cavity, a diffusion fuel cavity, a nozzle cover, a premixing swirl component, a diffusion swirl component and a nozzle core; wherein, The diffusion air cavity, the diffusion fuel cavity and the nozzle cover are connected in sequence, the nozzle core is located inside the diffusion swirl assembly, the diffusion swirl assembly is located inside the premixing swirl assembly, and the premixing swirl assembly is located inside the nozzle cover; the nozzle core is installed on the diffusion swirl end cover by using the nozzle core strip located at the front end of the nozzle core; the diffusion swirl assembly and the diffusion fuel cavity are connected by using the internal thread at the upper end of the diffusion fuel end cover of the diffusion swirl assembly; the premixing swirl assembly and the diffusion fuel cavity are tightly connected by the external thread at the lower end of the diffusion fuel cavity and the external thread at the upper end of the premixing swirl assembly front cavity of the premixing swirl assembly; the nozzle cover and the diffusion fuel cavity are tightly connected by the flange on the nozzle cover and the diffusion fuel cavity end cover; The diffusion air cavity is provided with a diffusion air inlet hole, the diffusion fuel cavity is provided with a diffusion fuel inlet hole, the nozzle cover is provided with a premixed air inlet hole and a premixed fuel inlet hole, the premixed swirl assembly is provided with swirl blades, the diffusion fuel cavity, the premixed swirl assembly and the nozzle cover together constitute a premixed swirl channel, the diffusion swirl assembly has a diffusion swirl channel, the diffusion fuel cavity, the diffusion swirl assembly and the premixed swirl assembly together constitute a diffusion fuel channel, and the diffusion air cavity, the nozzle inner core and the diffusion swirl assembly together constitute a diffusion air channel.

2. A swirl nozzle device suitable for a gas turbine combustion chamber according to claim 1, characterized in that: The diffusion air end cover of the diffusion air cavity is provided with a diffusion air inlet hole at the center.

3. The swirl nozzle device suitable for a gas turbine combustion chamber according to claim 1, characterized in that: The end cover of the diffusion fuel cavity is provided with a tongue depressor for further fixing the nozzle core pressure strip, so as to achieve a tight connection between the nozzle core and the diffusion swirl assembly and ensure that the nozzle core does not loosen.

4. The swirl nozzle device suitable for a gas turbine combustion chamber according to claim 1, characterized in that: A concave sealing groove is reserved at the lower end of the diffusion fuel cavity end cover, and a convex sealing ring is reserved on the flange of the nozzle cover. The sealing groove and the sealing ring are used together to strengthen the seal between the diffusion fuel cavity end cover and the flange of the nozzle cover.

5. The swirl nozzle device suitable for a gas turbine combustion chamber according to claim 1, characterized in that: A plurality of diffusion fuel inlet holes are evenly distributed in the tangential direction along the circumference of the diffusion fuel end cover.

6. The swirl nozzle device suitable for a gas turbine combustion chamber according to claim 1, characterized in that: A premix air collecting chamber and a premix fuel collecting chamber are arranged on the circumference of the nozzle cover.

7. A swirl nozzle device suitable for a gas turbine combustion chamber according to claim 6, characterized in that: A plurality of premixed air inlet holes are arranged tangentially along the circumference of the premixed air collecting cavity.

8. The swirl nozzle device suitable for a gas turbine combustion chamber according to claim 6, characterized in that: A plurality of premix fuel inlet holes are arranged along the circumference tangent direction of the premix fuel collecting cavity.

9. The swirl nozzle device suitable for a gas turbine combustion chamber according to claim 6, characterized in that: Small holes are provided between the nozzle shell of the nozzle cover and the premixed fuel collecting cavity, and between the nozzle shell and the premixed fuel collecting cavity, and the small holes are densely distributed honeycomb holes.

10. A swirl nozzle device suitable for a gas turbine combustion chamber according to claim 9, characterized in that: When the swirl nozzle is working, the diffusion air is injected into the nozzle from the diffusion air inlet hole on the diffusion air cavity, and then injected into the combustion chamber through the diffusion air cavity, the diffusion swirl assembly and the diffusion air channel composed of the nozzle core, and mixed with the diffusion fuel and burned; The diffusion fuel is injected into the nozzle through the diffusion fuel inlet hole on the diffusion fuel cavity, and is injected into the combustion chamber through the diffusion fuel channel composed of the diffusion fuel cavity, the diffusion swirl component and the premixing swirl component, and is mixed with the diffusion air and the premixed air to form a flow field condition suitable for diffusion combustion; the premixed air is first injected into the premixed air collecting cavity through the premixed air inlet hole on the nozzle cover, and then injected into the nozzle through a small hole located between the nozzle shell and the premixed air collecting cavity, mixed with the premixed fuel in the premixing channel composed of the nozzle cover and the premixing swirl component, and injected into the combustion chamber for combustion; the premixed fuel is first injected into the premixed fuel collecting cavity through the premixed fuel inlet hole on the nozzle cover, and then injected into the nozzle through a small hole located between the nozzle shell and the premixed fuel collecting cavity, mixed with the premixed air in the premixing channel composed of the nozzle cover and the premixing swirl component, and is injected into the combustion chamber to form a flow field condition suitable for premixed combustion.

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