CN215982681U

CN215982681U - Swirl nozzle for combustion chamber of gas turbine

Info

Publication number: CN215982681U
Application number: CN202122476099.0U
Authority: CN
Inventors: 李海峰; 郭洪波; 边立军; 高铭
Original assignee: Liaoneng Fushun Thermal Power Co ltd
Current assignee: Liaoneng Fushun Thermal Power Co ltd
Priority date: 2021-10-14
Filing date: 2021-10-14
Publication date: 2022-03-08
Anticipated expiration: 2031-10-14

Abstract

The utility model discloses a swirl nozzle for a combustion chamber of a gas turbine, which relates to the technical field of gas turbines and comprises a cylindrical central body, wherein the bottom of the cylindrical central body is fixedly connected with a mounting flange; this a swirl nozzle for gas turbine combustion chamber when the air current through whirl seat, forms stable whirl state under the effect of direction whirl blade, compresses when discharging with the gas blowout of compression, because the effect of pressure differential and whirl state for air and gas can the intensive mixing, with the effective combustion area who improves fuel, reduce the loss that the air flows, improve complete machine performance.

Description

Swirl nozzle for combustion chamber of gas turbine

Technical Field

The utility model relates to the technical field of gas turbine nozzles, in particular to a swirl nozzle for a gas turbine combustion chamber.

Background

The Gas Turbine (Gas Turbine) is an internal combustion type power machine which takes continuously flowing Gas as a working medium to drive an impeller to rotate at a high speed and convert the energy of fuel into useful work, and is a rotary impeller type heat engine.

However, in a general nozzle, a large flow pressure is lost, the flow is not uniform, most of air flows to the center of the nozzle, the air flow rate inside the nozzle is low at a position adjacent to the outer side in the radial direction, the uniformity of the air inside the nozzle is affected, the mixing of the air and fuel inside the nozzle is further affected, the pollutant emission is increased, and the risk of backfire and flameout is caused.

SUMMERY OF THE UTILITY MODEL

Solves the technical problem

In view of the deficiencies of the prior art, the present invention provides a swozzle for a gas turbine combustor that addresses the problems set forth above in the background.

Technical scheme

In order to achieve the purpose, the utility model is realized by the following technical scheme: including the tube-shape centrum, the bottom fixedly connected with mounting flange of the tube-shape centrum, the fixed surface of the tube-shape centrum connects whirl air current passageway, the inside wall fixedly connected with guide plate of whirl air current passageway, the air inlet has all been seted up to the side of guide plate and whirl air current passageway, the top fixedly connected with honeycomb duct of whirl air current passageway, the middle part fixedly connected with whirl seat of honeycomb duct inside wall, the top fixedly connected with of honeycomb duct gathers the cover, it has seted up the whirl air and has walked out on the surface of cover to gather together.

Optionally, a fuel supply through groove matched with the cylindrical central body is formed in the middle of the mounting flange, and the fuel supply through groove and the cylindrical central body form a fuel supply channel, so that fuel is conveniently conveyed, the fuel can be fully mixed with air at a discharge end, and the combustion efficiency is improved.

Optionally, the mounting holes have been seted up on the surface of mounting flange, the quantity of mounting hole is a plurality of, a plurality of the mounting hole is annular array distribution on the surface of mounting flange to conveniently install this nozzle in gas turbine's combustor through mounting flange.

Optionally, the tube-shape central body includes the body that contracts in the bottom and the body is extended at the top, the inside of tube-shape central body is provided with the inner chamber that the logical groove was supplied with to the intercommunication fuel, the tip that the body was extended at the top is leaks hopper-shaped to the convenient effect that plays the compression to the fuel, after fuel discharge, because the phenomenon of diffusion can appear in the existence of pressure differential, thereby makes things convenient for the further mixing of gas and air.

Optionally, whirl airflow channel includes outer barrel and interior barrel, the one end of guide plate and the inside wall fixed connection of outer barrel, the other end of guide plate and the outside wall fixed connection of interior barrel, the guide plate can play the effect of direction to the air for the spiral entering honeycomb duct of air plays the effect of preliminary whirl to the air.

Optionally, gather together the cover and be the funnel-shaped that the bottom dwindles to the top, the quantity that the whirl air exited is a plurality of, a plurality of the whirl air exited irregularly arranges the lateral wall at gathering together the cover to make things convenient for the air current to mix with the gas when flowing.

Optionally, the cyclone base comprises a cyclone positioning piece, the surface of the cyclone positioning piece is fixedly connected with a guide cyclone blade, and the guide cyclone blade is arranged on the outer wall of the cyclone positioning piece at an included angle of 30 degrees with the horizontal plane, so that the air is guided and flows along the guide cyclone blade.

Optionally, the number of the guiding rotational flow blades is a plurality of, and the guiding rotational flow blades are arranged on the outer wall of the rotational flow positioning piece in an annular array mode, and divide the flow guide pipe into a plurality of air rotational flow channels.

Advantageous effects

The utility model provides a swirl nozzle for a combustion chamber of a gas turbine, which has the following beneficial effects: this a whirl nozzle for gas turbine combustor, through the tube-shape centrum, mounting flange, whirl airflow channel, the guide plate, the air inlet, the honeycomb duct, the whirl seat, gather together the setting that cover and whirl air outlet, whirl airflow channel cooperation guide plate, make the air current when getting into the nozzle, the effect that has the drainage direction, make the air current form preliminary whirl state, when the air current is through the whirl seat, form stable whirl state under the effect of direction whirl blade, compress and the gas blowout of compression when discharging, because the effect of pressure differential and whirl state, make air and gas can the intensive mixing, with the effective combustion area who improves fuel, reduce the loss that the air flows, improve the complete machine performance.

Drawings

FIG. 1 is a schematic perspective view of the present invention;

FIG. 2 is a schematic view of the disassembled structure of the present invention;

FIG. 3 is a schematic bottom view of the present invention;

FIG. 4 is a schematic top view of the cyclone base of the present invention;

FIG. 5 is a partial cross-sectional view of the swirling air flow passage of the present invention.

In the figure: 1-cylindrical central body, 2-mounting flange, 3-cyclone airflow channel, 4-guide plate, 5-air inlet, 6-guide pipe, 7-cyclone seat, 701-cyclone positioning piece, 702-guide cyclone blade, 8-gathering cover, 9-cyclone air outlet, 10-fuel supply through groove and 11-mounting hole.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative efforts based on the embodiments of the present invention belong to the protection scope of the present invention.

Referring to fig. 1 to 5, the present invention provides a technical solution: the utility model provides a swirl nozzle for gas turbine combustor, including tube-shape centrum 1, the bottom fixedly connected with mounting flange 2 of tube-shape centrum 1, the fixed surface of tube-shape centrum 1 connects whirl airflow channel 3, inside wall fixedly connected with guide plate 4 of whirl airflow channel 3, air inlet 5 has all been seted up to the side of guide plate 4 and whirl airflow channel 3, the top fixedly connected with honeycomb duct 6 of whirl airflow channel 3, the middle part fixedly connected with whirl seat 7 of 6 inside walls of honeycomb duct, the top fixedly connected with of honeycomb duct 6 gathers together cover 8, it has the whirl air to export 9 to gather together the surface of cover 8 and set up.

The gathering cover 8 is funnel-shaped with the bottom reduced to the top, the number of the rotational flow air outlets 9 is a plurality, the rotational flow air outlets 9 are irregularly arranged on the side wall of the gathering cover 8, thereby facilitating the mixing of the air flow and the fuel gas when the air flow flows out, the rotational flow seat 7 comprises a rotational flow positioning piece 701, the surface of the rotational flow positioning piece 701 is fixedly connected with a guiding rotational flow blade 702, the guiding rotational flow blade 702 is arranged on the outer wall of the rotational flow positioning piece 7 in an included angle of 30 degrees with the horizontal plane, thereby having the effect of guiding the air, leading the air to flow along the guiding rotational flow blade 702, the number of the guiding rotational flow blades 702 is a plurality, the guiding rotational flow blades 702 are arranged on the outer wall of the rotational flow positioning piece 701 in an annular array, the guiding rotational flow blade 701 divides the guiding pipe 6 into a plurality of air rotational flow channels, the middle part of the mounting flange 2 is provided with a fuel supply through groove 10 matched with the cylindrical central body 1, the fuel supply through groove 10 and the cylindrical central body 1 form a fuel supply channel, thereby facilitating fuel delivery, enabling the fuel to be fully mixed with air at a discharge end, and improving combustion efficiency, mounting holes 11 are formed on the surface of the mounting flange 2, the number of the mounting holes 11 is a plurality, the mounting holes 11 are distributed on the surface of the mounting flange 2 in an annular array manner, thereby facilitating the nozzle to be installed in a combustor of a gas turbine through the mounting flange 2, the cylindrical central body 1 comprises a bottom retraction pipe body and a top extension pipe body, an inner cavity 2 communicated with the fuel supply through groove 10 is arranged inside the cylindrical central body 1, the end part of the top extension pipe body is funnel-shaped, thereby facilitating the compression effect on the fuel, after the fuel is discharged, the phenomenon of diffusion can occur due to the existence of pressure difference, thereby facilitating the further mixing of the fuel and the air, the rotational flow air channel 3 comprises an outer cylinder body and an inner cylinder body, one end of the guide plate 4 is fixedly connected with the inner side wall of the outer barrel, the other end of the guide plate 4 is fixedly connected with the outer side wall of the inner barrel, and the guide plate can play a guiding role for air so as to spirally enter the guide pipe 6 and play a primary rotational flow role for air.

In conclusion, when the swirl nozzle for the combustion chamber of the gas turbine is used, a worker installs the nozzle in a combustor of the gas turbine through the installation hole 11 on the surface of the installation flange 2, air enters the swirl airflow channel 3 through the air inlet 5 by arranging the cylindrical central body 1, the swirl airflow channel 3, the guide plate 4, the air inlet 5, the flow guide pipe 6, the swirl seat 7, the converging cover 8 and the swirl air outlet 9, the swirl airflow channel 3 is matched with the guide plate 4, so that airflow has the effect of flow guide when entering the nozzle, the airflow forms a primary swirl state, when the airflow passes through the swirl seat 7, a stable swirl state is formed under the action of the guide swirl vanes 702, and the compressed gas is ejected through the converging cover 8 during discharge, so that the air and the gas can be fully mixed due to the effects of pressure difference and the swirl state, so as to improve the effective combustion area of the fuel, reduce the loss of air flow and improve the performance of the whole machine.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

In the description of the present application, the terms "connect", "mount", "fix", "set", and the like are used in a broad sense, for example, the term "connect" may be a fixed connection or an indirect connection through intermediate components without affecting the relationship and technical effects of the components, or may be an integral connection or a partial connection, and as such, for a person skilled in the art, the specific meaning of the above terms in the present invention or the present invention can be understood according to specific situations.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. A swirler for a gas turbine combustor, comprising a cylindrical central body (1), characterized in that: the utility model discloses a cyclone air flow guiding device, including tube-shape central body (1), the bottom fixedly connected with mounting flange (2) of tube-shape central body (1), the fixed surface of tube-shape central body (1) is connected with whirl airflow channel (3), inside wall fixedly connected with guide plate (4) of whirl airflow channel (3), air inlet (5) have all been seted up to the side of guide plate (4) and whirl airflow channel (3), the top fixedly connected with honeycomb duct (6) of whirl airflow channel (3), middle part fixedly connected with whirl seat (7) of honeycomb duct (6) inside wall, the top fixedly connected with of honeycomb duct (6) gathers together cover (8), it has whirl air to offer on the surface of gathering together cover (8) to have the whirl air to bore (9).

2. A swozzle for a gas turbine combustor as claimed in claim 1, wherein: the fuel supply through groove (10) matched with the cylindrical central body (1) is formed in the middle of the mounting flange (2), and the fuel supply through groove (10) and the cylindrical central body (1) form a fuel supply channel.

3. A swozzle for a gas turbine combustor as claimed in claim 2, wherein: mounting hole (11) have been seted up on the surface of mounting flange (2), the quantity of mounting hole (11) is a plurality of, a plurality of mounting hole (11) are the surface of annular array distribution at mounting flange (2).

4. A swozzle for a gas turbine combustor as claimed in claim 2, wherein: the cylindrical central body (1) comprises a bottom internal contraction body and a top extension body, an inner cavity communicated with the fuel supply through groove (10) is formed in the cylindrical central body (1), and the end part of the top extension body is funnel-shaped.

5. A swozzle for a gas turbine combustor as claimed in claim 1, wherein: the cyclone airflow channel (3) comprises an outer cylinder and an inner cylinder, one end of the guide plate (4) is fixedly connected with the inner side wall of the outer cylinder, and the other end of the guide plate (4) is fixedly connected with the outer side wall of the inner cylinder.

6. A swozzle for a gas turbine combustor as claimed in claim 1, wherein: gather together cover (8) and be the funnel-shaped of narrowing down to the top in the bottom, the quantity that the whirl air outlet hole (9) is a plurality of, a plurality of whirl air outlet hole (9) are irregularly arranged at the lateral wall of gathering together cover (8).

7. A swozzle for a gas turbine combustor as claimed in claim 1, wherein: the cyclone base (7) comprises a cyclone positioning piece (701), the surface of the cyclone positioning piece (701) is fixedly connected with a guide cyclone blade (702), and the guide cyclone blade (702) is arranged on the outer wall of the cyclone positioning piece (701) in an included angle mode of 30 degrees with the horizontal plane.

8. The swozzle for a gas turbine combustor of claim 7, wherein: the number of the guide swirl blades (702) is a plurality, the guide swirl blades (702) are arranged on the outer wall of the swirl positioning piece (701) in an annular array, and the guide swirl blades (702) divide the guide pipe (6) into a plurality of air swirl channels.