CN113310071A - Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine - Google Patents
Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine Download PDFInfo
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- CN113310071A CN113310071A CN202110664338.7A CN202110664338A CN113310071A CN 113310071 A CN113310071 A CN 113310071A CN 202110664338 A CN202110664338 A CN 202110664338A CN 113310071 A CN113310071 A CN 113310071A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Abstract
The invention belongs to the technical field of combustion chambers of gas turbines, and particularly relates to a coaxial staged combustor for a low-pollution combustion chamber of a gas fuel combustion turbine. The invention adopts a tapered rotational flow channel to accelerate the airflow; a reducing mixing section is arranged behind each stage of swirl vane to enhance the mixing between the fuel and the air; the first-stage fuel enters the hub fuel annular cavity from the fuel pipe through the fuel branch, the second-stage fuel and the third-stage fuel enter the rectification fuel annular cavity before entering the hub fuel annular cavity, and enter the hub fuel annular cavity from the inlets of the four fan-shaped hub fuel annular cavities of the hub fuel annular cavity after rectification, so that the uniform fuel flow in the flow passages among the blades at the same stage is ensured, and the premixing effect is enhanced; the first-stage premixing-stage fuel is sprayed out from the fuel spray holes on the hub and enters the backflow zone along with the first-stage premixing-stage air along the first-stage outer hub, so that the fuel is prevented from being accumulated at the outlet of the swirler, and the phenomena of tempering and burning of the burner are effectively prevented.
Description
Technical Field
The invention belongs to the technical field of combustion chambers of gas turbines, and particularly relates to a coaxial staged combustor for a low-pollution combustion chamber of a gas fuel combustion turbine.
Background
Gas turbine pollutant emissions originate from combustion chemical reactions within the combustion chamber. The main pollutants of the combustion chamber include carbon monoxide, nitrogen oxides, unburned hydrocarbons, soot, etc., wherein nitrogen oxides are one of the most difficult pollutants to control. Since the thermodynamic mechanism dominates the formation of nitrogen oxides in the combustion chamber, controlling the combustion temperature is an effective means of reducing nitrogen oxide emissions. The lean premixed combustion technology can enable combustion reaction in the combustion chamber to be carried out at a lower equivalence ratio, effectively control the combustion temperature and further reduce the emission of nitrogen oxides.
Because the problem of unstable combustion easily occurs in lean premixed combustion, a coaxial staged combustion technology is proposed to carry out staged and zoned organization on combustion reaction, so that the generation of pollutants is reduced and the combustion stability is ensured. The coaxial staged combustor at the head of the combustion chamber in the technology consists of a central class and peripheral multistage premixing stages, the class and the premixing stages are coaxially nested together, staged and zoned combustion of fuel is realized by changing fuel flow distribution among different stages, pollutant emission can be effectively reduced, and combustion performance is guaranteed. The coaxial staged combustion technology is one of the important development directions of the low pollution combustion technology.
There have also been many domestic patents for gaseous fuel burners. Patent 20190312864.X discloses a coaxial staged swirling and blending integrated head for a gas fuel combustor, the main body part is a three-stage blending/swirling integrated tower-type swirler, and the technical means for solving the tempering problem is to introduce purge air. Patent 202011162316.2 discloses a coaxially staged low emission gaseous fuel nozzle in which first and second stage fuels are injected through fuel injection orifices in first and second stage swirl vanes, respectively, to achieve coaxial staging, and third stage fuel is injected through fuel injection orifices in the fuel nozzle downstream of the second stage combustion zone to achieve axial staging. Patent 202011161297.1 discloses a radially staged partially premixed type gas fuel nozzle whose combustion staging strategy is radial staging, including two sections, a main and pilot path, and employing an extruder with a one-stage venturi configuration to enhance blending and prevent flashback. Wherein the pilot fuel nozzle can provide non-premixed fuel for diffusion combustion, and the main fuel nozzle can provide premixed fuel for lean premixed combustion.
Disclosure of Invention
The invention aims to provide a coaxial staged combustor for a low-pollution combustor of a gas turbine with gas fuel, which can ensure that the combustion of the combustor of the gas turbine is stable in a wide working condition range, the pollutant discharge is low and the backfire is prevented.
The purpose of the invention is realized by the following technical scheme: the device comprises an on-duty fuel flow path, a first-stage hub, a second-stage hub, a third-stage hub, a first-stage fuel guide pipe, a second-stage fuel guide pipe and a third-stage fuel guide pipe; the inner side spaces of the inner walls of the first-stage hub, the second-stage hub and the third-stage hub are respectively composed of a gradually-reducing rotational flow channel and a gradually-reducing mixing section, the gradually-reducing rotational flow channel is positioned in front of the gradually-reducing mixing section, and the tail end of each gradually-reducing mixing section is connected with the integrated venturi;
the duty-stage fuel flow path comprises a duty-stage fuel guide pipe and a central blunt body; the central bluff body is arranged in a reducing rotational flow channel of the first-stage hub, and a circle of first rotational flow blades are arranged between the central bluff body and the first-stage hub; a first-stage hub fuel annular cavity is arranged between the inner wall and the outer wall of the first-stage hub, first-premixing-stage fuel spray holes are uniformly distributed on the surface of the inner wall of the first-stage hub, and the first-premixing-stage fuel spray holes are communicated with the first-stage hub fuel annular cavity; the first-stage fuel guide pipe is arranged in front of the first-stage hub and is communicated with the first-stage fuel cavity through a fuel branch; one end of the duty-level fuel guide pipe is connected with the front end of the central blunt body, and the other end of the duty-level fuel guide pipe extends out of the bottom of the first-level fuel guide pipe; the center blunt body is internally provided with an on-duty fuel cavity, an on-duty fuel spray hole is formed along the slope surface and the end surface of the center blunt body, and the on-duty fuel spray hole is communicated with the tapered mixing section of the first-stage hub;
the whole second-stage hub is positioned on the outer side of the outer wall of the first-stage hub, a circle of second swirl blades are arranged between the first-stage hub and the second-stage hub, the second swirl blades are all positioned in a tapered swirl flow channel of the second-stage hub, a blade fuel cavity is arranged inside each second swirl blade, a second premixing-stage fuel spray hole is formed in the surface of each second swirl blade, and the second premixing-stage fuel spray holes are communicated with a tapered mixing section of the second-stage hub; a second-stage hub fuel ring cavity is arranged between the inner wall and the outer wall of the second-stage hub; the front end of the second-stage hub is provided with a first rectification fuel ring cavity which is communicated with the second-stage hub fuel ring cavity; the second-stage fuel guide pipe is arranged in front of the second-stage hub and is connected with the first rectifying fuel ring cavity through the fuel pipe adapter section;
the third-stage hub is integrally positioned on the outer side of the outer wall of the first-stage hub, a circle of third swirl blades are arranged between the second-stage hub and the third-stage hub, the third swirl blades are all positioned in a tapered swirl flow channel of the third-stage hub, a blade fuel cavity is arranged inside each third swirl blade, a third premixing-stage fuel spray hole is formed in the surface of each third swirl blade, and the third premixing-stage fuel spray holes are communicated with a tapered mixing section of the third-stage hub; a third-stage hub fuel ring cavity is arranged between the inner wall and the outer wall of the third-stage hub; a second rectification fuel ring cavity is arranged at the front end of the third-stage hub and communicated with the third-stage hub fuel ring cavity; the third stage fuel conduit is arranged in front of the third stage hub and is connected with the second rectification fuel ring cavity through the fuel pipe adapter section.
The present invention may further comprise:
the integrated venturi comprises a first-stage venturi, a second-stage venturi and a third-stage venturi, wherein the first-stage venturi is positioned at the tail end of the tapered mixing section of the first-stage hub, the second-stage venturi is positioned at the tail end of the tapered mixing section of the second-stage hub, and the third-stage venturi is positioned at the tail end of the tapered mixing section of the third-stage hub; the axial position of the outlet of the first-stage venturi is positioned at the throat part of the second-stage venturi, and the axial position of the outlet of the second-stage venturi is positioned at the throat part of the third-stage venturi.
The first rotational flow blade is a straight blade; the second and third swirl blades are NACA blade type blades, and the blade installation angle is 35-45 degrees.
The second-stage fuel guide pipe is connected with the fan-shaped inlet of the first rectification fuel ring cavity through a circular fan-shaped fuel pipe switching section; the third stage fuel conduit is connected with the fan-shaped inlet of the second rectification fuel ring cavity through a circular fan-shaped fuel pipe switching section; the inlets of the second stage hub fuel annular cavity and the third stage hub fuel annular cavity are both fan-shaped.
The invention has the beneficial effects that:
under the condition of premixed combustion, the combustion chamber can lift flame without arranging blowing air or duty-level diffusion fuel, so that the burner is prevented from being ablated due to a tempering phenomenon, the structure is simple, diffusion combustion is avoided, and the pollutant discharge is low; a reducing mixing section is arranged behind each stage of swirl vane to enhance the mixing between the fuel and the air; the first-stage fuel enters the hub fuel annular cavity from the fuel pipe through the fuel branch, the second-stage fuel and the third-stage fuel enter the rectification fuel annular cavity before entering the hub fuel annular cavity, and enter the hub fuel annular cavity from the inlets of the four fan-shaped hub fuel annular cavities of the hub fuel annular cavity after rectification, and the fuel supply mode can ensure that the fuel flow in the flow passages among the blades at the same stage is uniform, so that the premixing effect is enhanced; the first-stage premixing-stage fuel is sprayed out from the fuel spray holes on the hub and enters the backflow zone along with the first-stage premixing-stage air along the first-stage outer hub, so that the fuel is prevented from being accumulated at the outlet of the swirler, and the phenomena of tempering and burning of the burner are effectively prevented. The invention adopts the tapered rotational flow channels to accelerate the airflow to prevent backfire, and the tail ends of the rotational flow channels are provided with the integrated venturi structure, in the venturi structure, the axial position of the outlet of the inner-stage venturi is positioned at the roar position of the adjacent outer-stage venturi, and the venturi structure can accelerate the airflow step by step to prevent backfire.
Drawings
Fig. 1 is a general schematic of the present invention.
Fig. 2 is a cross-sectional view of the present invention.
FIG. 3 is a schematic view of a three stage hub and its blades according to the present invention.
FIG. 4 is a schematic view of a vane fuel cavity of the present invention. .
Detailed Description
The invention is further described below with reference to the accompanying drawings.
The invention designs a coaxial staged combustor for a low-pollution combustion chamber of a gas fuel gas turbine, which consists of a fuel pipe, a fuel pipe switching section, a three-stage tapered premixing stage, a first-stage, a first-stage fuel branch, a rectification fuel ring cavity, a tapered mixing section and an integrated venturi. The first-stage premixing-stage (from inside to outside) fuel enters a first-stage hub fuel ring cavity from a first-stage fuel pipe through a first-stage fuel branch and is sprayed out from a fuel spray hole on a first-stage outer hub, and the spraying mode of the first-stage fuel can avoid the fuel from gathering at the outlet of a combustor and plays a role in preventing backfire; the second-stage premixed fuel and the third-stage premixed fuel respectively enter the rectification fuel ring cavity, the hub fuel ring cavity and the blade fuel cavity through the second-stage fuel pipe and the third-stage fuel pipe in sequence and are sprayed out from fuel spray holes on the blades; the inlet of the hub fuel ring cavity is fan-shaped, so that the flow area can be increased; the duty fuel enters the central bluff body fuel cavity through the duty fuel pipe and is sprayed out from a fuel spray hole at the tail end of the bluff body. The existence of the first-stage fuel branch and the rectification fuel ring cavity can ensure that the fuel flow in the flow channel between the vanes at the same stage is uniform, and the mixing effect is enhanced. A reducing mixing section is arranged behind the blades in the reducing rotational flow channel and used for enhancing fuel/air mixing. The burner premixing stages adopt a tapered rotational flow channel to accelerate airflow, an integrated venturi is arranged at the outlet of each premixing stage, the axial position of the outlet of the inner-stage venturi is located at the throat position of the adjacent outer-stage venturi, and the venturi arrangement mode accelerates airflow step by step and prevents backfire. The fuel flow of each stage can be independently controlled, so that the combustion chamber can be ensured to stably and efficiently combust in a wide working condition range, and the pollutant discharge is controlled. The combustor can realize the staged and zoned combustion of fuel, has stable combustion and less pollutant discharge, and is suitable for the low-pollution combustion chamber of the gas fuel gas turbine.
A coaxial staged combustor for a low pollution combustor of a gas-fueled gas turbine comprises an on-duty stage fuel flow path 10, a first stage hub, a second stage hub, a third stage hub, a first stage fuel conduit, a second stage fuel conduit, and a third stage fuel conduit; the inner side spaces of the inner walls of the first-stage hub, the second-stage hub and the third-stage hub are respectively composed of a reducing rotational flow channel 9 and a reducing mixing section 11, the reducing rotational flow channel is positioned in front of the reducing mixing section, and the tail end of each reducing mixing section is connected with an integrated venturi 8;
the duty-stage fuel flow path comprises a duty-stage fuel guide pipe and a central blunt body; the central bluff body is arranged in a reducing rotational flow channel of the first-stage hub, and a circle of first rotational flow blades are arranged between the central bluff body and the first-stage hub; a first-stage hub fuel annular cavity is arranged between the inner wall and the outer wall of the first-stage hub, first-stage premixing fuel spray holes 5 are uniformly distributed on the surface of the inner wall of the first-stage hub, and the first-stage premixing fuel spray holes are communicated with the first-stage hub fuel annular cavity; the first-stage fuel guide pipe is arranged in front of the first-stage hub and is communicated with the first-stage fuel cavity through a fuel branch 4; one end of the duty-level fuel guide pipe is connected with the front end of the central blunt body, and the other end of the duty-level fuel guide pipe extends out of the bottom of the first-level fuel guide pipe; the center blunt body is internally provided with an on-duty fuel cavity 12, an on-duty fuel spray hole 15 is formed along the slope surface and the end surface of the center blunt body, and the on-duty fuel spray hole is communicated with the tapered mixing section of the first-stage hub;
the whole second-stage hub is positioned on the outer side of the outer wall of the first-stage hub, a circle of second swirl blades are arranged between the first-stage hub and the second-stage hub, the second swirl blades are all positioned in a tapered swirl flow channel of the second-stage hub, a blade fuel cavity is arranged inside each second swirl blade, a second premixing-stage fuel spray hole is formed in the surface of each second swirl blade, and the second premixing-stage fuel spray holes are communicated with a tapered mixing section of the second-stage hub; a second-stage hub fuel ring cavity is arranged between the inner wall and the outer wall of the second-stage hub; the front end of the second-stage hub is provided with a first rectification fuel ring cavity which is communicated with the second-stage hub fuel ring cavity; the second-stage fuel guide pipe is arranged in front of the second-stage hub and is connected with the first rectifying fuel ring cavity through the fuel pipe adapter section;
the third-stage hub is integrally positioned on the outer side of the outer wall of the first-stage hub, a circle of third swirl blades are arranged between the second-stage hub and the third-stage hub, the third swirl blades are all positioned in a tapered swirl flow channel of the third-stage hub, a blade fuel cavity 16 is arranged inside each third swirl blade, a third premixing-stage fuel spray hole 6 is formed in the surface of each third swirl blade, and the fuel spray holes of the third premixing stage are communicated with a tapered mixing section of the third-stage hub; a third-stage hub fuel ring cavity 14 is arranged between the inner wall and the outer wall of the third-stage hub; a second rectification fuel ring cavity 13 is arranged at the front end of the third-stage hub and is communicated with the third-stage hub fuel ring cavity; the third stage fuel conduit 2 is arranged in front of the third stage hub and is connected with the second rectification fuel ring cavity through a fuel pipe adapter section 3.
The invention has the beneficial effects that
Under the condition of premixed combustion, the combustion chamber can lift flame without arranging blowing air or duty-level diffusion fuel, so that the burner is prevented from being ablated due to a tempering phenomenon, the structure is simple, diffusion combustion is avoided, and the pollutant discharge is low; a reducing mixing section is arranged behind each stage of swirl vane to enhance the mixing between the fuel and the air; the first-stage fuel enters the hub fuel annular cavity from the fuel pipe through the fuel branch, the second-stage fuel and the third-stage fuel enter the rectification fuel annular cavity before entering the hub fuel annular cavity, and enter the hub fuel annular cavity from the inlets of the four fan-shaped hub fuel annular cavities of the hub fuel annular cavity after rectification, and the fuel supply mode can ensure that the fuel flow in the flow passages among the blades at the same stage is uniform, so that the premixing effect is enhanced; the first-stage premixing-stage fuel is sprayed out from the fuel spray holes on the hub and enters the backflow zone along with the first-stage premixing-stage air along the first-stage outer hub, so that the fuel is prevented from being accumulated at the outlet of the swirler, and the phenomena of tempering and burning of the burner are effectively prevented.
The invention adopts the tapered rotational flow channels to accelerate the airflow to prevent backfire, and the tail ends of the rotational flow channels are provided with the integrated venturi structure, in the venturi structure, the axial position of the outlet of the inner-stage venturi is positioned at the roar position of the adjacent outer-stage venturi, and the venturi structure can accelerate the airflow step by step to prevent backfire.
Example 1:
referring to fig. 1 to 4, in the coaxial staged combustor for a low-pollution combustor of a gas turbine according to the present embodiment, a main body portion is composed of a three-stage tapered premixing stage, a first-stage, a tapered mixing section and an integrated venturi; a hub fuel ring cavity is arranged in an outer hub of each stage of swirler, blade fuel cavities are arranged in second-stage and third-stage swirl blades, and a central bluff body fuel cavity is arranged in a central bluff body of the swirler; four fuel branches are arranged outside the first-stage hub fuel ring cavity, and the rectification fuel ring cavities are arranged in front of the second-stage outer hub and the third-stage outer hub, so that the uniform flow of fuel in the flow passages among the blades at the same stage is ensured.
The swirl vane is positioned in the reducing swirl flow channel, the reducing mixing section is positioned behind the swirl vane in the reducing swirl flow channel, the first-stage fuel branch is positioned in front of the first-stage outer hub, the rectifying fuel ring cavity is positioned in the second stage and in front of the third-stage outer hub, the hub fuel ring cavity is positioned in each stage outer hub of the swirler, the blade fuel cavity is positioned in the second stage and the third-stage swirl vane, the central blunt body fuel cavity is positioned in a blunt body in the center of the swirler, the integrated venturi tube is positioned at the tail end of the reducing swirl flow channel of the swirler, the fuel spray hole of the first premixing stage is positioned on the first-stage outer hub of the swirler, the fuel spray holes of the second and third premixing stages are respectively positioned on the second and third-stage swirl vanes, the fuel spray hole of the class is positioned at the tail end of the blunt body in the center of the swirler, and the fuel flow of each stage can be independently controlled. Wherein, the air inlet, the reducing rotational flow channel, the reducing mixing section, the integrated venturi and the outlet of the cyclone form an air flow path. A rotational flow blade is arranged in the gradually-reduced rotational flow channel, and air rotationally flows under the action of the rotational flow blade; the integrated venturi is used for increasing the air flow speed step by step to prevent backfire; the first-stage fuel pipe, the first-stage fuel branch, the first-stage hub fuel annular cavity and the first-stage hub fuel spray holes form a first-stage premixed fuel flow path; the second-stage third-stage fuel pipe, the second-stage third-stage rectification fuel ring cavity, the second-stage third-stage hub fuel ring cavity and the second-stage third-stage blade fuel cavity form a second-stage third-stage premixed fuel flow path through second-stage third-stage blade fuel spray holes; the duty-class fuel pipe, the central blunt body fuel cavity and the duty-class fuel spray hole form a duty-class fuel flow path.
The main part of the three-stage premixing stage is a three-stage axial flow cyclone, and each stage adopts a gradually reducing cyclone flow channel. The fuel pipe is connected with the rectification fuel ring cavity by a circular sector fuel pipe switching section. A reducing mixing section is arranged behind the swirl vanes for strengthening mixing.
The first stage swirl blades are straight blades 7a, the second stage swirl blades and the third stage swirl blades are NACA blade profile blades 7b, the number of the swirl blades is 6-12, and the blade installation angle is 35-45 degrees.
The fuel of the first-stage premixing stage enters the fuel ring cavity of the first-stage hub from the fuel pipe through four first-stage fuel branches and is sprayed out from the fuel spray holes on the first-stage hub. Wherein, two rows of fuel spray holes are arranged in each inter-leaf flow passage of the first stage, each row is 3, and the aperture is 1.0 mm-1.5 mm.
The second-stage premixed fuel and the third-stage premixed fuel sequentially enter the rectification fuel ring cavity, the hub fuel ring cavity and the blade fuel cavity from the fuel pipe and are sprayed out from fuel spray holes in the blades. The inlet of the hub fuel ring cavity is fan-shaped, each of the second stage and the third stage of swirl vanes is provided with three fuel spray holes penetrating through the vanes, and the aperture is 1.0 mm-1.5 mm.
In this embodiment, the air inlet 1, the tapering rotational flow channel 9, the tapering blending section 11, the integrated venturi 8, and the cyclone outlet 17 form an air flow path, wherein the tapering rotational flow channel can accelerate the air flow to prevent backfire. The tapered cyclone flow channel is internally provided with 6, 10 and 12 cyclone blades of the first, second and third stages in sequence, and the installation angles of the blades are 35 degrees, 40 degrees and 40 degrees in sequence. The first stage swirl vanes are straight vanes, the second stage swirl vanes and the third stage swirl vanes are NACA vane profile vanes, and air passes through the gradually-reduced swirl flow channel 9 and forms swirl under the action of the swirl vanes. The tail ends of the three-stage tapered rotational flow channels are respectively provided with an integrated venturi, the axial position of the outlet of the inner-stage venturi is located at the roar position of the adjacent outer-stage venturi, and the venturi can accelerate airflow step by step in an arrangement mode to prevent backfire.
In the embodiment, the first-stage fuel pipe, the first-stage fuel branch, the first-stage hub fuel annular cavity and the first-stage hub fuel spray holes form a first-stage fuel flow path, and the first-stage premixed fuel is sprayed from the hub to prevent the fuel from being gathered at the outlet of the swirler; the second-stage third-stage fuel pipe, the second-stage third-stage rectification fuel ring cavity, the second-stage third-stage hub fuel ring cavity and the second-stage third-stage blade fuel cavity form a second-stage third-stage fuel flow path; the inlet of the hub fuel ring cavity is fan-shaped, so that the flow area can be increased; the duty-class fuel pipe, the central blunt body fuel cavity and the duty-class fuel spray hole form a duty-class fuel flow path. All levels of fuel flow can be controlled independently, so that stable combustion and low pollutant discharge are ensured.
The specific working process of the burner fuel circuit is as follows:
and fuel is only supplied to the class and the first-stage premixing stage under the ignition working condition, and the fuel supply of the second-stage premixing stage and the third-stage premixing stage is sequentially opened and increased along with the increase of the working condition and is gradually reduced until the fuel supply of the class on duty is cut off. The on-duty fuel enters the central bluff body fuel cavity from the on-duty fuel pipe and is sprayed out from the axial and inclined radial fuel spray holes at the tail end of the central bluff body; the fuel of the first-stage premixing stage enters the fuel ring cavity of the first-stage hub from the fuel pipe through the first-stage fuel branch and is sprayed out from the fuel spray holes on the first-stage outer hub, and the spraying mode can avoid the fuel from gathering at the outlet of the swirler and prevent backfire; the second and third stage premixed stage fuel enters the rectification fuel ring cavity from the fuel pipe, then enters the hub fuel ring cavity through the hub fuel ring cavity inlet, then enters the blade fuel cavity and is sprayed out from the fuel spray holes on the blades, and the fuel supply mode can ensure that the fuel flow in the flow passages among the blades is uniform, and the mixing effect is enhanced.
The specific working process of the air circuit of the burner is as follows:
air enters from the air inlet and automatically distributes flow in each stage of rotational flow channel, rotational flow blades are arranged in the gradually-reduced rotational flow channel to enable the air flow to rotate, and the air flow can be accelerated by the gradual reduction of the flow channel. The air enters the contraction section of the venturi tube to be accelerated step by step after passing through the gradually-reduced rotational flow channel, so that the tempering phenomenon is prevented. The air then enters the venturi diverging section to form a diverging angle and finally exits the cyclone outlet.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A coaxial staged combustor for a low pollution combustor of a gas turbine engine, characterized by: the device comprises an on-duty fuel flow path, a first-stage hub, a second-stage hub, a third-stage hub, a first-stage fuel guide pipe, a second-stage fuel guide pipe and a third-stage fuel guide pipe; the inner side spaces of the inner walls of the first-stage hub, the second-stage hub and the third-stage hub are respectively composed of a gradually-reducing rotational flow channel and a gradually-reducing mixing section, the gradually-reducing rotational flow channel is positioned in front of the gradually-reducing mixing section, and the tail end of each gradually-reducing mixing section is connected with the integrated venturi;
the duty-stage fuel flow path comprises a duty-stage fuel guide pipe and a central blunt body; the central bluff body is arranged in a reducing rotational flow channel of the first-stage hub, and a circle of first rotational flow blades are arranged between the central bluff body and the first-stage hub; a first-stage hub fuel annular cavity is arranged between the inner wall and the outer wall of the first-stage hub, first-premixing-stage fuel spray holes are uniformly distributed on the surface of the inner wall of the first-stage hub, and the first-premixing-stage fuel spray holes are communicated with the first-stage hub fuel annular cavity; the first-stage fuel guide pipe is arranged in front of the first-stage hub and is communicated with the first-stage fuel cavity through a fuel branch; one end of the duty-level fuel guide pipe is connected with the front end of the central blunt body, and the other end of the duty-level fuel guide pipe extends out of the bottom of the first-level fuel guide pipe; the center blunt body is internally provided with an on-duty fuel cavity, an on-duty fuel spray hole is formed along the slope surface and the end surface of the center blunt body, and the on-duty fuel spray hole is communicated with the tapered mixing section of the first-stage hub;
the whole second-stage hub is positioned on the outer side of the outer wall of the first-stage hub, a circle of second swirl blades are arranged between the first-stage hub and the second-stage hub, the second swirl blades are all positioned in a tapered swirl flow channel of the second-stage hub, a blade fuel cavity is arranged inside each second swirl blade, a second premixing-stage fuel spray hole is formed in the surface of each second swirl blade, and the second premixing-stage fuel spray holes are communicated with a tapered mixing section of the second-stage hub; a second-stage hub fuel ring cavity is arranged between the inner wall and the outer wall of the second-stage hub; the front end of the second-stage hub is provided with a first rectification fuel ring cavity which is communicated with the second-stage hub fuel ring cavity; the second-stage fuel guide pipe is arranged in front of the second-stage hub and is connected with the first rectifying fuel ring cavity through the fuel pipe adapter section;
the third-stage hub is integrally positioned on the outer side of the outer wall of the first-stage hub, a circle of third swirl blades are arranged between the second-stage hub and the third-stage hub, the third swirl blades are all positioned in a tapered swirl flow channel of the third-stage hub, a blade fuel cavity is arranged inside each third swirl blade, a third premixing-stage fuel spray hole is formed in the surface of each third swirl blade, and the third premixing-stage fuel spray holes are communicated with a tapered mixing section of the third-stage hub; a third-stage hub fuel ring cavity is arranged between the inner wall and the outer wall of the third-stage hub; a second rectification fuel ring cavity is arranged at the front end of the third-stage hub and communicated with the third-stage hub fuel ring cavity; the third stage fuel conduit is arranged in front of the third stage hub and is connected with the second rectification fuel ring cavity through the fuel pipe adapter section.
2. The coaxial staged combustor for a low pollution combustor of a gas fuel turbine as claimed in claim 1, wherein: the integrated venturi comprises a first-stage venturi, a second-stage venturi and a third-stage venturi, wherein the first-stage venturi is positioned at the tail end of the tapered mixing section of the first-stage hub, the second-stage venturi is positioned at the tail end of the tapered mixing section of the second-stage hub, and the third-stage venturi is positioned at the tail end of the tapered mixing section of the third-stage hub; the axial position of the outlet of the first-stage venturi is positioned at the throat part of the second-stage venturi, and the axial position of the outlet of the second-stage venturi is positioned at the throat part of the third-stage venturi.
3. The coaxial staged combustor for a low pollution combustor of a gas fuel gas turbine as claimed in claim 1 or 2, wherein: the first rotational flow blade is a straight blade; the second and third swirl blades are NACA blade type blades, and the blade installation angle is 35-45 degrees.
4. The coaxial staged combustor for a low pollution combustor of a gas fuel gas turbine as claimed in claim 1 or 2, wherein: the second-stage fuel guide pipe is connected with the fan-shaped inlet of the first rectification fuel ring cavity through a circular fan-shaped fuel pipe switching section; the third stage fuel conduit is connected with the fan-shaped inlet of the second rectification fuel ring cavity through a circular fan-shaped fuel pipe switching section; the inlets of the second stage hub fuel annular cavity and the third stage hub fuel annular cavity are both fan-shaped.
5. The coaxial staged combustor for a low pollution combustor of a gas fuel turbine as claimed in claim 3, wherein: the second-stage fuel guide pipe is connected with the fan-shaped inlet of the first rectification fuel ring cavity through a circular fan-shaped fuel pipe switching section; the third stage fuel conduit is connected with the fan-shaped inlet of the second rectification fuel ring cavity through a circular fan-shaped fuel pipe switching section; the inlets of the second stage hub fuel annular cavity and the third stage hub fuel annular cavity are both fan-shaped.
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| CN115342384A (en) * | 2022-07-06 | 2022-11-15 | 哈尔滨工程大学 | Lean oil premixing integrated head structure of gas turbine combustor |
| CN115342379A (en) * | 2022-07-06 | 2022-11-15 | 哈尔滨工程大学 | Natural gas coaxial grading low-emission combustion chamber head with lobe swirl blades |
| WO2023235078A1 (en) * | 2022-06-01 | 2023-12-07 | Siemens Energy Global GmbH & Co. KG | Combustor having secondary fuel injector |
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| CN112815356A (en) * | 2020-12-31 | 2021-05-18 | 哈尔滨工程大学 | Self-adaptive adjustable hydrogen-rich fuel low-emission micro-flame combustion chamber |
| CN112815356B (en) * | 2020-12-31 | 2022-07-15 | 哈尔滨工程大学 | Self-adaptive adjustable hydrogen-rich fuel low-emission micro-flame combustion chamber |
| CN114183772A (en) * | 2021-11-30 | 2022-03-15 | 哈尔滨工程大学 | High-efficient low emission combustor head that hydrogen mixes in advance |
| CN114810358A (en) * | 2022-04-25 | 2022-07-29 | 中国船舶重工集团公司第七0三研究所 | Low-emission dual-fuel system of gas turbine and control method thereof |
| CN114810358B (en) * | 2022-04-25 | 2024-02-20 | 中国船舶重工集团公司第七0三研究所 | Low-emission dual-fuel system of gas turbine and control method thereof |
| WO2023235078A1 (en) * | 2022-06-01 | 2023-12-07 | Siemens Energy Global GmbH & Co. KG | Combustor having secondary fuel injector |
| CN114877377A (en) * | 2022-06-02 | 2022-08-09 | 清航空天(北京)科技有限公司 | Outer ring detonation combustion chamber |
| CN115342384A (en) * | 2022-07-06 | 2022-11-15 | 哈尔滨工程大学 | Lean oil premixing integrated head structure of gas turbine combustor |
| CN115342379A (en) * | 2022-07-06 | 2022-11-15 | 哈尔滨工程大学 | Natural gas coaxial grading low-emission combustion chamber head with lobe swirl blades |
| CN115342379B (en) * | 2022-07-06 | 2023-07-07 | 哈尔滨工程大学 | Natural gas coaxial grading low-emission combustion chamber head with lobe swirl vanes |
| CN115342384B (en) * | 2022-07-06 | 2023-07-07 | 哈尔滨工程大学 | Lean oil premixing integrated head structure of combustion chamber of gas turbine |
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