CN113091095B - Gas turbine combustor nozzle and method for premixing fuel and air in nozzle - Google Patents
Gas turbine combustor nozzle and method for premixing fuel and air in nozzle Download PDFInfo
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- CN113091095B CN113091095B CN202110524594.6A CN202110524594A CN113091095B CN 113091095 B CN113091095 B CN 113091095B CN 202110524594 A CN202110524594 A CN 202110524594A CN 113091095 B CN113091095 B CN 113091095B
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- gas turbine
- nozzle
- premixing
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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
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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
Abstract
The invention provides a gas turbine combustor nozzle and a method for premixing fuel and air in the nozzle. The gas turbine combustor nozzle comprises a fuel conveying main pipe, a fuel distributing pipeline, a fuel spray rod and a fuel air premixing pipe. The fuel delivery manifold is provided with a plurality of fuel distribution holes, each fuel distribution hole corresponding to at least one fuel distribution line. The fuel distribution pipeline is in airflow communication with a plurality of downstream fuel spray bars, and each fuel spray bar is in airflow communication with the corresponding fuel air premixing tube; the fuel enters from the fuel conveying main pipe, enters into the fuel distributing pipeline through the fuel distributing holes, enters into the fuel air premixing pipe through the fuel spray rod and is mixed with air to form a mixture, and the mixture is sprayed out from the fuel air premixing pipe. The gas turbine combustion chamber nozzle and the method for premixing fuel and air in the nozzle can ensure that the whole nozzle has good fuel and air premixing uniformity.
Description
Technical Field
The invention relates to the field of gas turbines, in particular to a gas turbine combustor nozzle and a method for premixing fuel and air in the nozzle.
Background
In a gas turbine DLN (Dry Low NOx) combustor, fuel and air premixing uniformity is a critical factor in controlling combustion NOx emissions. Since the combustion chamber of a gas turbine is mainly thermal NOx, the generation amount and the combustion temperature are closely related. Thus, when the average combustion temperature is the same, the uniformity of mixing of fuel and air causes the local combustion temperatures in different regions to deviate from the average temperature, with some places being higher and some places being lower. In the higher temperature region, thermal NOx is generated in large amounts, ultimately resulting in a large increase in the NOx emissions at the outlet.
The prior art gas turbine combustion chamber nozzle generally adopts to open fuel spray holes on swirler vanes, as shown in a specific structure of a lean premixed combustion chamber of a gas turbine, as shown in fig. 1-2, each vane 002 of a swirler assembly 001 of the lean premixed combustion chamber of the gas turbine is axially provided with a swirler vane blind hole 003, two side wall surfaces of each vane are provided with a plurality of premixed fuel spray holes 004, the vane blind holes 003 are communicated with the premixed fuel spray holes 004, the premixed fuel enters a premixed fuel cavity from a premixed fuel introducing pipe 005, and enters a swirler channel 006 through the swirler vane blind holes 003 on the vanes and the premixed fuel spray holes 004 on the vanes, so that the fuel is mixed with air at the downstream of the swirler.
The disadvantage of this prior art is that, due to the limitation of machining, the number of fuel holes in the rotating blades cannot be excessive and the positions of the openings cannot be too close to the inner and outer surfaces of the premixing passage, thus resulting in a higher fuel concentration near the inner and outer wall surfaces of the premixing passage, a higher flame combustion temperature, a more concentrated heat release, and a higher NOx emission during the operation of the engine at base load.
Disclosure of Invention
To solve the above problems, the present application proposes a gas turbine combustor nozzle and a method of premixing fuel and air in the nozzle.
Therefore, the present application aims to provide a gas turbine combustor nozzle, which precisely adjusts the mixture equivalent of each fuel gas premixing tube through a multi-premixing tube structure, so as to ensure that the whole nozzle has good fuel and air premixing uniformity.
A gas turbine combustor nozzle comprises a fuel conveying main pipe, a fuel distribution pipeline, a fuel spray rod and a fuel air premixing pipe,
the fuel delivery manifold is provided with a plurality of fuel distribution holes;
each fuel distribution hole corresponds to at least one fuel distribution pipeline;
the fuel distribution line being in air flow communication with the downstream fuel boom;
the fuel spray bars are multiple, and each fuel spray bar is in airflow communication with the corresponding fuel air premixing tube;
the fuel enters from the fuel conveying main pipe, enters into the fuel distribution pipeline through the fuel distribution holes, enters into the fuel air premixing pipe through the fuel spray rod and is mixed with air to form a mixture, and the mixture is sprayed out from the fuel air premixing pipe.
Optionally, the fuel-air premixing tube is provided with a swirl structure, and the swirl structure ejects the mixture in a rotary airflow mode.
Optionally, the fuel air premix tube includes an output pipe portion that deflects as the swirl structure at a predetermined angle in a circumferential direction such that the mixture ejected from the fuel air premix tube forms a swirling air flow in a predetermined circumferential direction.
Optionally, each output pipe of the fuel air premix tube deflects clockwise or counter-clockwise in a circumferential direction.
Optionally, the fuel air premix tube comprises an inlet tube portion upstream of the outlet tube portion, the outlet tube portion being deflected relative to the inlet tube portion.
Optionally, the output pipe of the fuel air premix tube comprises a Laval structure nozzle.
Optionally, the fuel distribution pipes are radially arranged outwards from the fuel delivery manifold.
Optionally, the fuel distribution holes are distributed in a circular ring shape along the circumferential direction.
Optionally, the plurality of fuel spray bars are parallel to each other.
Optionally, the fuel boom is arranged coaxially with the fuel air premix tube.
Optionally, the fuel air equivalence ratio of the mixture in the fuel air premix tube is the same as the fuel air equivalence ratio of the mixture in the combustion chamber.
Optionally, the outlet end of the fuel spray rod is provided with a plurality of fuel holes.
Optionally, the fuel hole is provided on an end face and/or chamfer face of the outlet end of the fuel boom.
Optionally, the fuel holes on the end face and/or the chamfer face are uniformly distributed from the center to the outside in the circumferential direction.
Optionally, the gas turbine combustor nozzle further comprises a rectifying hole and an outer wall,
the outer wall is arranged at the downstream of the rectifying hole and surrounds a nozzle chamber;
air enters the nozzle chamber from the rectifying hole, passes through the nozzle chamber and enters the fuel air premixing tube.
To achieve the above object, the present invention also provides a method for premixing fuel and air in a gas turbine combustor nozzle, comprising:
fuel enters from a fuel conveying main pipe, is sprayed out from a fuel distribution hole of the fuel conveying main pipe, enters a fuel distribution pipeline, and enters the fuel air premixing pipe through a fuel spray rod;
air enters a nozzle chamber from the rectifying hole, passes through the nozzle chamber and enters a fuel-air premixing tube to be mixed with the fuel, and a mixture is formed;
the mixture is ejected from the fuel air premix tube.
Optionally, the mixing ratio of the fuel and the air in the fuel-air premixing tube is adjusted by changing the diameter and/or the number of the fuel distribution holes.
Optionally, the downstream section of the fuel-air premixing tube is a Laval-structured nozzle, and the fuel and the air are promoted to be mixed by changing the throat size of the Laval-structured nozzle.
Optionally, the mixing ratio of the fuel and the air in the fuel-air premixing tube is adjusted by changing the size of the outlet end of the fuel boom and/or the number of fuel holes of the outlet end of the fuel boom.
The gas turbine combustor nozzle and the method for premixing fuel and air in the gas turbine combustor nozzle have the beneficial effects that:
1. the nozzle can enable fuel and air to be mixed rapidly, and compared with a traditional nozzle premixing structure for spraying by the blades of the cyclone, the axial length of the special premixing structure can be shortened by 30-50%.
2. The nozzle adopts the nozzle with a multi-premixing pipe structure to premix fuel and air, and the premixing uniformity of the fuel and the air in the whole premixing section is improved by accurately adjusting the air quantity of each premixing pipe.
3. The fuel-air equivalent ratio in each fuel-air premixing tube is the same as the total fuel-air equivalent ratio of the combustion chamber by adjusting the aperture and the number of the fuel holes.
4. The Laval structure spray pipe is combined with the premixing pipe structure, and the mixture ratio in each fuel air premixing pipe is controlled by adjusting the throat size of the Laval structure.
5. The multi-premix tube structure has certain capability of absorbing thermoacoustic oscillations, and contributes to improving the thermoacoustic oscillation characteristics of the combustion chamber.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a partial block diagram of a prior art gas turbine combustor nozzle;
FIG. 2 is a partial cross-sectional view of a prior art gas turbine combustor nozzle;
FIG. 3 is an external configuration of a gas turbine combustor nozzle of the present invention;
FIG. 4 is a cross-sectional view of a gas turbine combustor nozzle of the present invention;
FIG. 5 is an enlarged view of a portion A of a cross-sectional view of a gas turbine combustor nozzle of the present invention;
FIG. 6 is a right side view of a gas turbine combustor nozzle in accordance with an embodiment of the present invention;
FIG. 7 is a partial cross-sectional view of a fuel air premix tube in a gas turbine combustor nozzle in accordance with an embodiment of the invention;
FIG. 8 is an enlarged view of a portion B of a fuel boom 3 in a gas turbine combustor nozzle in accordance with an embodiment of the present invention;
FIG. 9 is a cross-sectional view of a gas turbine combustor nozzle of another embodiment of the invention;
FIG. 10 is a flow chart of a method of premixing fuel and air in a gas turbine combustor nozzle in accordance with embodiment 8 of the present invention;
FIG. 11 is a flow chart of a method of premixing fuel and air in a gas turbine combustor nozzle in accordance with example 9 of the present invention;
FIG. 12 is a flow chart of a method of premixing fuel and air in a gas turbine combustor nozzle in accordance with embodiment 10 of the present invention;
FIG. 13 is a flow chart of a method of premixing fuel and air in a gas turbine combustor nozzle in accordance with example 11 of the present invention.
Detailed Description
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The present application will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
The present application is described in further detail below in conjunction with specific embodiments, which should not be construed as limiting the scope of the claims.
Example 1
Referring to fig. 3-4, the gas turbine combustor nozzle includes a fuel delivery manifold 1, a fuel distribution line 2, a fuel lance 3, and a fuel air premix tube 4. The fuel conveying main pipe 1 is in a spindle shape as a whole, the diameter of a fuel inlet is gradually increased, an outlet at the other end of the fuel conveying main pipe is in a cone shape, and a plurality of circular fuel distribution holes 5 are distributed on the cone shape.
In the present embodiment, the fuel distribution holes 5 are uniformly distributed in a circular ring shape in the circumferential direction at the downstream outlet end of the fuel delivery manifold 1, and optionally, the fuel distribution holes 5 are arranged in a plurality of rows from the center to the outside of the nozzle 100 in the circumferential direction. After entering the system from the fuel conveying main pipe 1, the fuel enters the fuel spray rod 3 after passing through the fuel distribution holes 5 on the downstream outlet end of the fuel conveying main pipe 1, and the process can realize multi-channel transportation of the fuel, thereby effectively improving the transportation efficiency and premixing uniformity of the fuel.
Further, as shown in fig. 4-5, each fuel distribution hole 5 corresponds to at least one fuel distribution pipeline 2, and the fuel distribution pipelines 2 are radially distributed in a multi-turn layer by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel distribution pipeline 2 on each ring layer has the same axial angle with the fuel delivery main pipe 1, and the fuel distribution pipelines 2 on different ring layers have different axial angles with the fuel delivery main pipe 1, and the angles gradually become larger along the radial direction of the fuel delivery main pipe 1. Further, the fuel distribution pipes 2 on each ring layer are bent on the same plane in the extending direction, and the outlet angle of each bent fuel distribution pipe 2 is parallel to the fuel conveying main pipe 1.
The fuel spray bars 3 are parallel to each other. The outlet end of the fuel distribution pipeline 2 is connected with the inlet end of the fuel spray rod 3, and the fuel distribution pipeline and the inlet end of the fuel spray rod are communicated with each other in an air flow mode; the center of the inlet of each fuel premixing tube 4 is coaxially and correspondingly provided with a fuel spray rod 3, and each fuel spray rod 3 is in air flow communication with the corresponding fuel air premixing tube 4.
In this embodiment, the mixture ratio in each fuel-air premixing tube 4 can be controlled by adjusting the aperture D of the fuel distribution holes 5 and the number N thereof, so that the fuel and air amounts of the individual fuel-air premixing tubes 4 are well matched.
When the gas turbine combustion chamber nozzle is in an operating state, fuel enters through the fuel conveying main pipe 1, enters the fuel distribution pipeline 2 through the fuel distribution holes 5, enters the fuel air premixing pipe 4 through the fuel spray rod 3 and is mixed with air to form a mixture, and the mixture is sprayed out of the fuel air premixing pipe 4.
Example 2
Referring to fig. 3-4, the gas turbine combustor nozzle includes a fuel delivery manifold 1, a fuel distribution line 2, a fuel lance 3, and a fuel air premix tube 4. The fuel conveying main pipe 1 is in a spindle shape as a whole, the diameter of a fuel inlet is gradually increased, an outlet at the other end of the fuel conveying main pipe is in a cone shape, and a plurality of circular fuel distribution holes 5 are distributed on the cone shape.
In the present embodiment, the fuel distribution holes 5 are uniformly distributed in a circular ring shape in the circumferential direction at the downstream outlet end of the fuel delivery manifold 1, and optionally, the fuel distribution holes 5 are arranged in a plurality of rows from the center to the outside of the nozzle 100 in the circumferential direction. After entering the system from the fuel conveying main pipe 1, the fuel enters the fuel spray rod 3 after passing through the fuel distribution holes 5 on the downstream outlet end of the fuel conveying main pipe 1, and the process can realize multi-channel transportation of the fuel, thereby effectively improving the transportation efficiency and premixing uniformity of the fuel.
Further, as shown in fig. 4-5, each fuel distribution hole 5 corresponds to at least one fuel distribution pipeline 2, and the fuel distribution pipelines 2 are radially distributed in a multi-turn layer by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel distribution pipeline 2 on each ring layer has the same axial angle with the fuel delivery main pipe 1, and the fuel distribution pipelines 2 on different ring layers have different axial angles with the fuel delivery main pipe 1, and the angles gradually become larger along the radial direction of the fuel delivery main pipe 1. Further, the fuel distribution pipes 2 on each ring layer are bent on the same plane in the extending direction, and the outlet angle of each bent fuel distribution pipe 2 is parallel to the fuel conveying main pipe 1.
The fuel spray bars 3 are parallel to each other. The outlet end of the fuel distribution pipeline 2 is connected with the inlet end of the fuel spray rod 3, and the fuel distribution pipeline and the inlet end of the fuel spray rod are communicated with each other in an air flow mode; the center of the inlet of each fuel premixing tube 4 is coaxially and correspondingly provided with a fuel spray rod 3, and each fuel spray rod 3 is in air flow communication with the corresponding fuel air premixing tube 4.
In the present embodiment, the fuel air pre-mixing pipe 4 includes an output pipe portion 41, and the output pipe portion 41 is deflected at a predetermined angle α in a clockwise or counterclockwise direction along a periphery Xiang Anzhao to form a swirling structure. Fig. 6 shows the case where the output pipe 41 is deflected in the clockwise direction. This structure can form a circumferential swirling flow of the fuel-air mixture ejected from the output pipe 41 of the fuel-air premixing pipe 4 in the downstream space direction, enhancing the premixing effect of the fuel and air.
In this embodiment, the mixture ratio in each fuel-air premixing tube 4 can be controlled by adjusting the aperture D of the fuel distribution holes 5 and the number N thereof, so that the fuel and air amounts of the individual fuel-air premixing tubes 4 are well matched.
When the gas turbine combustion chamber nozzle is in an operating state, fuel enters through the fuel conveying main pipe 1, enters the fuel distribution pipeline 2 through the fuel distribution holes 5, enters the fuel air premixing pipe 4 through the fuel spray rod 3 and is mixed with air to form a mixture, and the mixture is sprayed out of the fuel air premixing pipe 4. The swirling airflow ejected downstream from the output pipe 41 of the fuel-air premixing pipe 4 can effectively enhance the premixing effect of fuel and air. Meanwhile, the structure can jet out rotary air flow, and can replace a cyclone structure in the traditional scheme, so that the mechanical structure of the combustion chamber is simpler.
Example 3
Referring to fig. 3-4, the gas turbine combustor nozzle includes a fuel delivery manifold 1, a fuel distribution line 2, a fuel lance 3, and a fuel air premix tube 4. The fuel conveying main pipe 1 is in a spindle shape as a whole, the diameter of a fuel inlet is gradually increased, an outlet at the other end of the fuel conveying main pipe is in a cone shape, and a plurality of circular fuel distribution holes 5 are distributed on the cone shape.
In the present embodiment, the fuel distribution holes 5 are uniformly distributed in a circular ring shape in the circumferential direction at the downstream outlet end of the fuel delivery manifold 1, and optionally, the fuel distribution holes 5 are arranged in a plurality of rows from the center to the outside of the nozzle 100 in the circumferential direction. After entering the system from the fuel conveying main pipe 1, the fuel enters the fuel spray rod 3 after passing through the fuel distribution holes 5 on the downstream outlet end of the fuel conveying main pipe 1, and the process can realize multi-channel transportation of the fuel, thereby effectively improving the transportation efficiency and premixing uniformity of the fuel.
Further, as shown in fig. 4-5, each fuel distribution hole 5 corresponds to at least one fuel distribution pipeline 2, and the fuel distribution pipelines 2 are radially distributed in a multi-turn layer by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel distribution pipeline 2 on each ring layer has the same axial angle with the fuel delivery main pipe 1, and the fuel distribution pipelines 2 on different ring layers have different axial angles with the fuel delivery main pipe 1, and the angles gradually become larger along the radial direction of the fuel delivery main pipe 1. Further, the fuel distribution pipes 2 on each ring layer are bent on the same plane in the extending direction, and the outlet angle of each bent fuel distribution pipe 2 is parallel to the fuel conveying main pipe 1.
The fuel spray bars 3 are parallel to each other. The outlet end of the fuel distribution pipeline 2 is connected with the inlet end of the fuel spray rod 3, and the fuel distribution pipeline and the inlet end of the fuel spray rod are communicated with each other in an air flow mode; the center of the inlet of each fuel premixing tube 4 is coaxially and correspondingly provided with a fuel spray rod 3, and each fuel spray rod 3 is in air flow communication with the corresponding fuel air premixing tube 4.
In the present embodiment, the fuel air premix tube 4 includes an output tube portion 41 located downstream and an input tube portion 42 located upstream. The output pipe 41 deflects relative to the input pipe 42, and the output pipe 41 deflects at a predetermined angle α in the circumferential direction, forming a swirling structure. This structure can form a circumferential swirling flow of the fuel-air mixture ejected from the output pipe 41 of the fuel-air premixing pipe 4 in the downstream space direction, enhancing the premixing effect of the fuel and air.
In this embodiment, the mixture ratio in each fuel-air premixing tube 4 can be controlled by adjusting the aperture D of the fuel distribution holes 5 and the number N thereof, so that the fuel and air amounts of the individual fuel-air premixing tubes 4 are well matched.
Fig. 7 shows the deflection angle α of the output pipe 41 of each fuel premix tube 4.
When the gas turbine combustion chamber nozzle is in an operating state, fuel enters through the fuel conveying main pipe 1, enters the fuel distribution pipeline 2 through the fuel distribution holes 5, enters the fuel air premixing pipe 4 through the fuel spray rod 3 and is mixed with air to form a mixture, and the mixture is sprayed out of the fuel air premixing pipe 4. The output pipe 41 of the fuel-air premixing pipe 4 can deflect an angle alpha to spray downstream rotary airflow, thereby effectively enhancing the premixing effect of fuel and air.
Example 4
Referring to fig. 3-4, the gas turbine combustor nozzle includes a fuel delivery manifold 1, a fuel distribution line 2, a fuel lance 3, and a fuel air premix tube 4. The fuel conveying main pipe 1 is in a spindle shape as a whole, the diameter of a fuel inlet is gradually increased, an outlet at the other end of the fuel conveying main pipe is in a cone shape, and a plurality of circular fuel distribution holes 5 are distributed on the cone shape.
In the present embodiment, the fuel distribution holes 5 are uniformly distributed in a circular ring shape in the circumferential direction at the downstream outlet end of the fuel delivery manifold 1, and optionally, the fuel distribution holes 5 are arranged in a plurality of rows from the center to the outside of the nozzle 100 in the circumferential direction. After entering the system from the fuel conveying main pipe 1, the fuel enters the fuel spray rod 3 after passing through the fuel distribution holes 5 on the downstream outlet end of the fuel conveying main pipe 1, and the process can realize multi-channel transportation of the fuel, thereby effectively improving the transportation efficiency and premixing uniformity of the fuel.
Further, as shown in fig. 4-5, each fuel distribution hole 5 corresponds to at least one fuel distribution pipeline 2, and the fuel distribution pipelines 2 are radially distributed in a multi-turn layer by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel distribution pipeline 2 on each ring layer has the same axial angle with the fuel delivery main pipe 1, and the fuel distribution pipelines 2 on different ring layers have different axial angles with the fuel delivery main pipe 1, and the angles gradually become larger along the radial direction of the fuel delivery main pipe 1. Further, the fuel distribution pipes 2 on each ring layer are bent on the same plane in the extending direction, and the outlet angle of each bent fuel distribution pipe 2 is parallel to the fuel conveying main pipe 1.
The fuel spray bars 3 are parallel to each other. The outlet end of the fuel distribution pipeline 2 is connected with the inlet end of the fuel spray rod 3, and the fuel distribution pipeline and the inlet end of the fuel spray rod are communicated with each other in an air flow mode; the center of the inlet of each fuel premixing tube 4 is coaxially and correspondingly provided with a fuel spray rod 3, and each fuel spray rod 3 is in air flow communication with the corresponding fuel air premixing tube 4.
In this embodiment, as shown in fig. 7, in order to further promote uniform mixing of fuel and air, the output pipe 41 of the fuel-air premixing tube 4 includes a raval-structured nozzle C. The Laval nozzle structure C is an integral structure formed by a shrinkage pipe on the left side and an expansion pipe on the right side, and the structure can enable the speed of air flow to be changed due to the change of the spray sectional area. In this embodiment, the shrink tube may further promote a uniform degree of mixing of the fuel and air, and the subsequent expansion structure may be advantageous in reducing the flow pressure loss of the fuel-air premix tube 4.
Alternatively, the throat area of the Laval-structured nozzle C may be adjusted to control the mixture ratio in each fuel-air premixing tube 4.
In this embodiment, the mixture ratio in each fuel-air premixing tube 4 can be controlled by adjusting the aperture D of the fuel distribution holes 5 and the number N thereof, so that the fuel and air amounts of the individual fuel-air premixing tubes 4 are well matched.
When the gas turbine combustion chamber nozzle is in an operating state, fuel enters through the fuel conveying main pipe 1, enters the fuel distribution pipeline 2 through the fuel distribution holes 5, enters the fuel air premixing pipe 4 through the fuel spray rod 3 and is mixed with air to form a mixture, and the mixture is sprayed out of the fuel air premixing pipe 4. The Laval-structured nozzle C of the output pipe 41 of the fuel-air premixing tube 4 effectively increases the degree of mixing of fuel and air by the contracted and expanded structures and reduces the flow pressure loss of the mixture to the fuel-air premixing tube.
Example 5
Referring to fig. 3-4, the gas turbine combustor nozzle includes a fuel delivery manifold 1, a fuel distribution line 2, a fuel lance 3, and a fuel air premix tube 4. The fuel conveying main pipe 1 is in a spindle shape as a whole, the diameter of a fuel inlet is gradually increased, an outlet at the other end of the fuel conveying main pipe is in a cone shape, and a plurality of circular fuel distribution holes 5 are distributed on the cone shape.
In the present embodiment, the fuel distribution holes 5 are uniformly distributed in a circular ring shape in the circumferential direction at the downstream outlet end of the fuel delivery manifold 1, and optionally, the fuel distribution holes 5 are arranged in a plurality of rows from the center to the outside of the nozzle 100 in the circumferential direction. After entering the system from the fuel conveying main pipe 1, the fuel enters the fuel spray rod 3 after passing through the fuel distribution holes 5 on the downstream outlet end of the fuel conveying main pipe 1, and the process can realize multi-channel transportation of the fuel, thereby effectively improving the transportation efficiency and premixing uniformity of the fuel.
Further, as shown in fig. 4-5, each fuel distribution hole 5 corresponds to at least one fuel distribution pipeline 2, and the fuel distribution pipelines 2 are radially distributed in a multi-turn layer by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel distribution pipeline 2 on each ring layer has the same axial angle with the fuel delivery main pipe 1, and the fuel distribution pipelines 2 on different ring layers have different axial angles with the fuel delivery main pipe 1, and the angles gradually become larger along the radial direction of the fuel delivery main pipe 1. Further, the fuel distribution pipes 2 on each ring layer are bent on the same plane in the extending direction, and the outlet angle of each bent fuel distribution pipe 2 is parallel to the fuel conveying main pipe 1.
The fuel spray bars 3 are parallel to each other. The outlet end of the fuel distribution pipeline 2 is connected with the inlet end of the fuel spray rod 3, and the fuel distribution pipeline and the inlet end of the fuel spray rod are communicated with each other in an air flow mode; the center of the inlet of each fuel premixing tube 4 is coaxially and correspondingly provided with a fuel spray rod 3, and each fuel spray rod 3 is in air flow communication with the corresponding fuel air premixing tube 4.
In this embodiment, the mixture ratio in each fuel-air premixing tube 4 can be controlled by adjusting the aperture D of the fuel distribution holes 5 and the number N thereof, so that the fuel and air amounts of the individual fuel-air premixing tubes 4 are well matched.
In the present embodiment, the fuel-air equivalent ratio of the mixture in the fuel-air premixing tube 4 is the same as that of the mixture in the combustion chamber.
When the gas turbine combustion chamber nozzle is in an operating state, fuel enters through the fuel conveying main pipe 1, enters the fuel distribution pipeline 2 through the fuel distribution holes 5, enters the fuel air premixing pipe 4 through the fuel spray rod 3 and is mixed with air to form a mixture, and the mixture is sprayed out of the fuel air premixing pipe 4.
Example 6
Referring to fig. 3-4, the gas turbine combustor nozzle includes a fuel delivery manifold 1, a fuel distribution line 2, a fuel lance 3, and a fuel air premix tube 4. The fuel conveying main pipe 1 is in a spindle shape as a whole, the diameter of a fuel inlet is gradually increased, an outlet at the other end of the fuel conveying main pipe is in a cone shape, and a plurality of circular fuel distribution holes 5 are distributed on the cone shape.
In the present embodiment, the fuel distribution holes 5 are uniformly distributed in a circular ring shape in the circumferential direction at the downstream outlet end of the fuel delivery manifold 1, and optionally, the fuel distribution holes 5 are arranged in a plurality of rows from the center to the outside of the nozzle 100 in the circumferential direction. After entering the system from the fuel conveying main pipe 1, the fuel enters the fuel spray rod 3 after passing through the fuel distribution holes 5 on the downstream outlet end of the fuel conveying main pipe 1, and the process can realize multi-channel transportation of the fuel, thereby effectively improving the transportation efficiency and premixing uniformity of the fuel.
Further, as shown in fig. 4-5, each fuel distribution hole 5 corresponds to at least one fuel distribution pipeline 2, and the fuel distribution pipelines 2 are radially distributed in a multi-turn layer by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel distribution pipeline 2 on each ring layer has the same axial angle with the fuel delivery main pipe 1, and the fuel distribution pipelines 2 on different ring layers have different axial angles with the fuel delivery main pipe 1, and the angles gradually become larger along the radial direction of the fuel delivery main pipe 1. Further, the fuel distribution pipes 2 on each ring layer are bent on the same plane in the extending direction, and the outlet angle of each bent fuel distribution pipe 2 is parallel to the fuel conveying main pipe 1.
The fuel spray bars 3 are parallel to each other. The outlet end of the fuel distribution pipeline 2 is connected with the inlet end of the fuel spray rod 3, and the fuel distribution pipeline and the inlet end of the fuel spray rod are communicated with each other in an air flow mode; the center of the inlet of each fuel premixing tube 4 is coaxially and correspondingly provided with a fuel spray rod 3, and each fuel spray rod 3 is in air flow communication with the corresponding fuel air premixing tube 4.
In this embodiment, as shown in fig. 8, the fuel boom 3 has a tubular structure, and its outlet end includes an end surface 32 and a chamfer surface 33. The end face 32 and/or chamfer face 33 are provided with fuel holes 31.
Alternatively, the fuel holes 31 on each face are the same diameter, and the number of fuel holes 31 on the chamfer face 33 is greater than the end face 32. The fuel holes 31 at the outlet end of the fuel boom 3 thus form a pattern that is uniformly distributed from the center to the outside in the circumferential direction of the fuel boom 3.
In this embodiment, the mixture ratio in each fuel-air premixing tube 4 can be controlled by adjusting the aperture D of the fuel distribution holes 5 and the number N thereof, so that the fuel and air amounts of the individual fuel-air premixing tubes 4 are well matched.
When the gas turbine combustion chamber nozzle is in an operating state, fuel enters through the fuel conveying main pipe 1, enters the fuel distribution pipeline 2 through the fuel distribution holes 5, enters the fuel air premixing pipe 4 through the fuel spray rod 3 and is mixed with air to form a mixture, and the mixture is sprayed out of the fuel air premixing pipe 4.
Example 7
Referring to fig. 3-4, the gas turbine combustor nozzle includes a fuel delivery manifold 1, a fuel distribution line 2, a fuel lance 3, and a fuel air premix tube 4. The fuel conveying main pipe 1 is in a spindle shape as a whole, the diameter of a fuel inlet is gradually increased, an outlet at the other end of the fuel conveying main pipe is in a cone shape, and a plurality of circular fuel distribution holes 5 are distributed on the cone shape.
In the present embodiment, the fuel distribution holes 5 are uniformly distributed in a circular ring shape in the circumferential direction at the downstream outlet end of the fuel delivery manifold 1, and optionally, the fuel distribution holes 5 are arranged in a plurality of rows from the center to the outside of the nozzle 100 in the circumferential direction. After entering the system from the fuel conveying main pipe 1, the fuel enters the fuel spray rod 3 after passing through the fuel distribution holes 5 on the downstream outlet end of the fuel conveying main pipe 1, and the process can realize multi-channel transportation of the fuel, thereby effectively improving the transportation efficiency and premixing uniformity of the fuel.
Further, as shown in fig. 4-5, each fuel distribution hole 5 corresponds to at least one fuel distribution pipeline 2, and the fuel distribution pipelines 2 are radially distributed in a multi-turn layer by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel distribution pipeline 2 on each ring layer has the same axial angle with the fuel delivery main pipe 1, and the fuel distribution pipelines 2 on different ring layers have different axial angles with the fuel delivery main pipe 1, and the angles gradually become larger along the radial direction of the fuel delivery main pipe 1. Further, the fuel distribution pipes 2 on each ring layer are bent on the same plane in the extending direction, and the outlet angle of each bent fuel distribution pipe 2 is parallel to the fuel conveying main pipe 1.
The fuel spray bars 3 are parallel to each other. The outlet end of the fuel distribution pipeline 2 is connected with the inlet end of the fuel spray rod 3, and the fuel distribution pipeline and the inlet end of the fuel spray rod are communicated with each other in an air flow mode; the center of the inlet of each fuel premixing tube 4 is coaxially and correspondingly provided with a fuel spray rod 3, and each fuel spray rod 3 is in air flow communication with the corresponding fuel air premixing tube 4.
In the present embodiment, as shown in fig. 9, the gas turbine combustor nozzle 100 further includes a rectifying hole 6 and an outer wall 7, the outer wall 7 being disposed downstream of the rectifying hole 6, surrounding a nozzle chamber 8. Air enters the nozzle chamber 8 from the rectifying holes 6, passes through the nozzle chamber 8 and enters the fuel air premix tube 4.
In this embodiment, the mixture ratio in each fuel-air premixing tube 4 can be controlled by adjusting the aperture D of the fuel distribution holes 5 and the number N thereof, so that the fuel and air amounts of the individual fuel-air premixing tubes 4 are well matched.
When the gas turbine combustor nozzle is in operation, air then enters the fuel air premix tube 4 through the nozzle chamber 8 via the orifice 6. Fuel enters through the fuel conveying main pipe 1, enters the fuel distributing pipeline 2 through the fuel distributing holes 5, enters the fuel air premixing pipe 4 through the fuel spray rod 3, and is mixed with air to form a mixture, and the mixture is sprayed out of the fuel air premixing pipe 4. The double-passage structure distinguishes fuel and air passages, and enables the fuel and the air to be fully mixed in the fuel-air premixing tube 4 in a specific area and then sprayed out, so that the premixing uniformity of fuel and air in the whole nozzle is improved.
Example 8
The invention also discloses a method for premixing fuel and air in a gas turbine combustor nozzle.
As shown in fig. 10, the method includes:
step S1: fuel enters from the fuel delivery manifold 1 and is ejected from the fuel distribution holes 5 of the fuel delivery manifold 1, enters the fuel distribution pipeline 2, and then enters the fuel-air premixing tube 4 through the fuel spray bars 3.
Step S2: air enters the nozzle chamber 7 from the orifice 6, passes through the nozzle chamber 7 into the fuel-air premixing tube 4 to mix with the fuel and form a mixture.
Step S3: the mixture is ejected from the fuel air premix tube 4.
Example 9
As shown in fig. 11, the method includes:
step S4: the diameter and/or the number of the fuel distribution holes 5 are set, and the mixing ratio of the fuel and the air in the fuel-air premixing tube 4 is adjusted.
Step S1: fuel enters from the fuel delivery manifold 1 and is ejected from the fuel distribution holes 5 of the fuel delivery manifold 1, enters the fuel distribution pipeline 2, and then enters the fuel-air premixing tube 4 through the fuel spray bars 3.
Step S2: air enters the nozzle chamber 7 from the orifice 6, passes through the nozzle chamber 7 into the fuel-air premixing tube 4 to mix with the fuel and form a mixture.
Step S3: the mixture is ejected from the fuel air premix tube 4.
According to the embodiment of the invention, the mixing proportion of the fuel and the air in the fuel-air premixing tube 4 can be adjusted by setting the diameter and/or the number of the fuel distribution holes 5, so that the premixing uniformity of the fuel and the air is effectively improved.
Example 11
In this embodiment, the downstream section of the fuel air premix tube 4 is a Laval structure nozzle C.
As shown in fig. 12, the method includes:
step S5: the throat dimension of the raval-structured nozzle C is set.
Step S1: fuel enters from the fuel delivery manifold 1 and is ejected from the fuel distribution holes 5 of the fuel delivery manifold 1, enters the fuel distribution pipeline 2, and then enters the fuel-air premixing tube 4 through the fuel spray bars 3.
Step S2: air enters the nozzle chamber 7 from the orifice 6, passes through the nozzle chamber 7 into the fuel-air premixing tube 4 to mix with the fuel and form a mixture.
Step S3: the mixture is ejected from the fuel air premix tube 4.
According to the embodiment of the invention, the premixing uniformity of fuel and air is further improved by setting the throat size of the Laval structure spray pipe C.
Example 12
As shown in fig. 13, the method includes:
step S6: the size of the outlet end of the fuel boom 3 and/or the number of fuel holes 3 at the outlet end of the fuel boom 3 are provided.
Step S1: fuel enters from the fuel delivery manifold 1 and is ejected from the fuel distribution holes 5 of the fuel delivery manifold 1, enters the fuel distribution pipeline 2, and then enters the fuel-air premixing tube 4 through the fuel spray bars 3.
Step S2: air enters the nozzle chamber 7 from the orifice 6, passes through the nozzle chamber 7 into the fuel-air premixing tube 4 to mix with the fuel and form a mixture.
Step S3: the mixture is ejected from the fuel air premix tube 4.
According to the embodiment of the invention, the mixing proportion of the fuel and the air in the fuel-air premixing tube 4 is adjusted by changing the size of the outlet end of the fuel spray rod 3 and/or the number of the fuel holes 31 at the outlet end of the fuel spray rod 3, so that the premixing uniformity of the fuel and the air is further improved.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (18)
1. A gas turbine combustor nozzle (100) is characterized by comprising a fuel conveying main pipe (1), a fuel distributing pipeline (2), a fuel spray rod (3) and a fuel air premixing pipe (4),
the fuel delivery manifold (1) is provided with a plurality of fuel distribution holes (5);
each fuel distribution hole (5) corresponds to at least one fuel distribution pipeline (2);
-said fuel distribution line (2) being in air flow communication with said fuel boom (3) downstream;
the fuel spray bars (3) are multiple, and each fuel spray bar (3) is in air flow communication with the corresponding fuel air premixing tube (4);
fuel enters from the fuel conveying main pipe (1), enters the fuel distributing pipeline (2) through the fuel distributing holes (5), enters the fuel air premixing pipe (4) through the fuel spray rod (3) and is mixed with air to form a mixture, and the mixture is sprayed out from the fuel air premixing pipe (4);
the gas turbine combustor nozzle (100) further comprises a rectifying hole (6) and an outer wall (7),
the outer wall (7) is arranged downstream of the rectifying hole (6) and surrounds a nozzle chamber (8);
air enters the nozzle chamber (8) from the rectifying hole (6), passes through the nozzle chamber (8) and enters the fuel air premixing tube (4).
2. The gas turbine combustor nozzle (100) of claim 1, wherein the fuel air premix tube (4) is provided with a swirl structure that ejects the mixture in a swirling flow.
3. The gas turbine combustor nozzle (100) of claim 2, wherein the fuel air premix tube (4) comprises an output tube portion (41), the output tube portion (41) being deflected at a predetermined angle in a circumferential direction as the swirl structure such that the mixture ejected from the fuel air premix tube (4) forms a swirling air flow in a predetermined circumferential direction.
4. A gas turbine combustor nozzle (100) according to claim 3, wherein each output pipe (41) of the fuel air premix tube (4) is deflected clockwise or counter-clockwise in circumferential direction.
5. A gas turbine combustor nozzle (100) according to claim 3, wherein the fuel air premixing tube (4) comprises an inlet tube portion (42) upstream of the outlet tube portion (41), the outlet tube portion (41) being deflected relative to the inlet tube portion (42).
6. A gas turbine combustor nozzle (100) according to claim 3, wherein the output pipe (41) of the fuel air premix tube (4) comprises a rahal structure nozzle.
7. The gas turbine combustor nozzle (100) of claim 1, wherein the fuel distribution piping (2) is radially arranged outwardly from the fuel delivery manifold (1).
8. The gas turbine combustor nozzle (100) of claim 1, wherein the fuel distribution holes (5) are circumferentially distributed in a ring shape.
9. The gas turbine combustor nozzle (100) of claim 1, wherein the plurality of fuel rods (3) are parallel to each other.
10. The gas turbine combustor nozzle (100) of claim 1, wherein the fuel boom (3) is arranged coaxially with the fuel air premix tube (4).
11. The gas turbine combustor nozzle (100) of any one of claims 1-10, wherein the fuel-air equivalence ratio of the mixture in the fuel-air premix tube (4) is the same as the fuel-air equivalence ratio of the mixture in the combustor.
12. The gas turbine combustor nozzle (100) of any one of claims 1-10, wherein the outlet end of the fuel lance (3) is provided with a plurality of fuel holes (31).
13. The gas turbine combustor nozzle (100) of claim 12, wherein the fuel holes (31) are provided on an end face (32) and/or chamfer face (33) of the outlet end of the fuel lance (3).
14. The gas turbine combustor nozzle (100) of claim 13, wherein the fuel holes (31) on the end face (32) and/or the chamfer face (33) are evenly distributed circumferentially from the center to the outside.
15. A method of premixing fuel and air in a gas turbine combustor nozzle, the method being applied to a gas turbine combustor nozzle (100) as claimed in any one of claims 1 to 14, comprising:
the fuel enters from the fuel conveying main pipe (1), is sprayed out from the fuel distributing holes (5) of the fuel conveying main pipe (1), enters into the fuel distributing pipeline (2), and then enters into the fuel air premixing pipe (4) through the fuel spray rod (3);
air enters a nozzle chamber (8) from a rectifying hole (6), passes through the nozzle chamber (8) and enters a fuel air premixing tube (4) to be mixed with the fuel, and a mixture is formed;
the mixture is ejected from the fuel air premix tube (4).
16. The method of claim 15, wherein,
the mixing ratio of the fuel and the air in the fuel-air premixing tube (4) is adjusted by changing the diameter and/or the number of the fuel distribution holes (5).
17. The method of claim 15, wherein,
the downstream section of the fuel-air premixing tube (4) is a Laval structure spray tube, and the fuel and the air are promoted to be mixed by changing the throat size of the Laval structure spray tube.
18. The method of claim 15, wherein,
the mixing ratio of the fuel and the air in the fuel-air premixing tube (4) is adjusted by changing the size of the outlet end of the fuel boom (3) and/or the number of fuel holes (31) of the outlet end of the fuel boom (3).
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| CN202110524594.6A CN113091095B (en) | 2021-05-13 | 2021-05-13 | Gas turbine combustor nozzle and method for premixing fuel and air in nozzle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US5408830A (en) * | 1994-02-10 | 1995-04-25 | General Electric Company | Multi-stage fuel nozzle for reducing combustion instabilities in low NOX gas turbines |
| US20120180487A1 (en) * | 2011-01-19 | 2012-07-19 | General Electric Company | System for flow control in multi-tube fuel nozzle |
| CN102878580B (en) * | 2012-09-12 | 2015-04-22 | 中国科学院工程热物理研究所 | Lean premixed combustion chamber for gas turbine |
| JP6228434B2 (en) * | 2013-11-15 | 2017-11-08 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
| WO2016063222A1 (en) * | 2014-10-20 | 2016-04-28 | A.S.EN. ANSALDO SVILUPPO ENERGIA S.r.l. | Gas turbine unit with multifluid fuel supply and method of supplying a burner of a gas turbine unit |
| JP6822894B2 (en) * | 2017-04-28 | 2021-01-27 | 三菱パワー株式会社 | Fuel injector and gas turbine |
| KR102046457B1 (en) * | 2017-11-09 | 2019-11-19 | 두산중공업 주식회사 | Combustor and gas turbine including the same |
| CN111928295A (en) * | 2020-09-08 | 2020-11-13 | 中国科学院工程热物理研究所 | Micro-premixing on-duty nozzle assembly and micro-premixing combustion chamber of gas turbine |
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