CN107620984B

CN107620984B - Fuel nozzle for gas turbine

Info

Publication number: CN107620984B
Application number: CN201710791942.XA
Authority: CN
Inventors: 李珊珊; 吕煊; 刘小龙; 杨旭; 张文军; 王菁菁
Original assignee: China United Heavy Gas Turbine Technology Co Ltd
Current assignee: China United Heavy Gas Turbine Technology Co Ltd
Priority date: 2017-09-05
Filing date: 2017-09-05
Publication date: 2021-02-26
Anticipated expiration: 2037-09-05
Also published as: CN107620984A

Abstract

The invention discloses a fuel nozzle of a gas turbine, which comprises a central body, a sleeve cover, an end plate, a guide cylinder and a clapboard; the shroud has a first end and a second end, the shroud is sleeved on the central body, an annular passage is formed between the shroud and the central body, and a swirler is arranged in the annular passage; the end plate is arranged at the first end of the cover and sleeved on the central body, and an air inlet communicated with the annular channel is formed in the end plate; the guide cylinder is positioned in the annular channel and is arranged between the end plate and the swirler so as to divide the annular channel into a plurality of annular spaces along the radial direction of the annular channel; the partition is disposed in at least one of the annular spaces to partition the at least one annular space into a plurality of zones arranged along a circumferential direction of the annular passage. The invention is convenient for adjusting the uniformity of air flow globally, thereby reducing the air flow loss and improving the overall performance of the gas turbine.

Description

Fuel nozzle for gas turbine

Technical Field

The invention relates to the technical field of gas turbines, in particular to a fuel nozzle of a gas turbine.

Background

In the gas turbine, air is compressed into high-pressure air by a compressor, the high-pressure air enters a combustion chamber from a diffuser, is bent at the head of the combustion chamber and then enters a nozzle at the head of the combustion chamber, is mixed with fuel in the nozzle and then enters a flame tube for combustion. However, the high pressure air is deflected at the head of the combustion chamber, which results in a loss of large flow pressure, non-uniform flow, non-uniform mixing of air and fuel in the nozzle, increased NOx emissions, and an impact on flame stability and is prone to flashback or flame attachment, which affects overall gas turbine performance.

In the related art, the uniformity of the air flow is improved by adjusting the flow rate of different blade passages or locally improving the flow near the wall surface of the blade. However, the above-mentioned ways of adjusting or improving the conditions at the blades can only adjust local areas, and cannot adjust the uniformity of the air flow in a large range or even globally.

Disclosure of Invention

Therefore, the invention aims to provide the fuel nozzle of the gas turbine, which is convenient for controlling the air flow and globally adjusts the uniformity of the air flow, thereby reducing the air flow loss and improving the overall performance of the gas turbine.

A fuel nozzle of a gas turbine according to an embodiment of the present invention includes: a central body; a shroud having a first end and a second end, the shroud being fitted over the central body, an annular passage being formed between the shroud and the central body, the annular passage having a swirler disposed therein; the end plate is arranged at the first end of the sleeve cover and sleeved on the central body, and an air inlet communicated with the annular channel is formed in the end plate; the guide cylinder is positioned in the annular channel and is arranged between the end plate and the swirler so as to divide the annular channel into a plurality of annular spaces along the radial direction of the annular channel; a first end of the peripheral flow guide element is opposite to the end plate in the axial direction of the annular passage, and a second end of the peripheral flow guide element extends along the radial direction of the sleeve cover and exceeds the rear edge of the sleeve cover and extends from the first end of the sleeve cover towards the second end of the sleeve cover.

According to the fuel nozzle of the gas turbine, the annular channel formed between the central body and the shroud is divided into a plurality of annular spaces along the radial direction of the annular channel through the guide cylinder, air outside the annular channel can be guided into the annular channel through the peripheral guide piece, the uniformity of air flowing is adjusted, and therefore the flowing loss of the air is reduced, and the overall performance of the gas turbine is improved.

In some embodiments, the peripheral baffle has a generally L-shaped axial cross-section.

In some embodiments, the first end of the peripheral flow guide is opposite the first end of the flow guide cylinder.

In some embodiments, the peripheral baffle includes an arcuate portion and a flat portion, a first end of the arcuate portion being opposite the first end of the baffle cylinder, a first end of the flat portion being connected to a second end of the arcuate portion that extends beyond the shroud in a radial direction of the shroud, and a second end of the flat portion extending in a direction toward the second end of the shroud.

In some embodiments, the first end of the peripheral baffle is located axially outward of the annular passage in the shroud.

In some embodiments, the peripheral baffle surrounds the entire shroud or a portion of the shroud in a circumferential direction of the shroud.

In some embodiments, the gas turbine fuel nozzle further comprises a baffle disposed within the at least one annular space to divide the at least one annular space into a plurality of zones arranged along a circumference of the annular passage.

In some embodiments, the guide shell is mounted on the end plate.

In some embodiments, the number of the guide cylinders is plural, the plurality of guide cylinders are sequentially sleeved, and the plurality of annular spaces include an outer annular space between the outermost guide cylinder and the sleeve, an inner annular space between the innermost guide cylinder and the central body, and a middle annular space between adjacent guide cylinders.

In some embodiments, the air intake holes are arranged in a plurality of circles at regular intervals along the circumferential direction of the end plate, and the air intake holes in each circle are arranged in the radial direction of the end plate and spaced apart from each other.

In some embodiments, the annular passage includes a constriction adjacent the swirler that decreases in radial dimension.

In some embodiments, the end plate is mounted within the annular channel a predetermined distance from an end face of the first end of the shroud.

In some embodiments, the opening of the first end of the shroud is flared.

Drawings

FIG. 1 is a general schematic view of a gas turbine combustor nozzle according to an embodiment of the present invention;

FIG. 2 is a cross-sectional view of a gas turbine combustor nozzle according to an embodiment of the present invention;

reference numerals:

the central body 1, the shroud 2, the first end 21, the second end 22, the end plate 3, the guide shell 4, the outer guide shell 41, the inner guide shell 42, the annular passage 5, the first annular space 51, the second annular space 52, the third annular space 53, the swirler 6, the air inlet 7, the peripheral guide 8, the arc-shaped portion 81, the straight portion 82, the fuel passage 9, and the mounting flange 10.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.

As shown in fig. 1 to 2, a fuel nozzle 100 of a gas turbine according to an embodiment of the present invention includes: a central body 1, a shroud 2, end plates 3, a draft tube 4, a swirler 6 and a peripheral baffle 8.

The shroud 2 has a first end 21 (e.g., the left end in fig. 2) and a second end 22 (e.g., the right end in fig. 2). The shrouds 2 are fitted over the central body 1 and radially spaced from each other so that an annular passage 5 is formed between the shrouds 2 and the central body 1, a swirler 6 being provided in the annular passage 5.

The end plate 3 is arranged at the first end 21 of the mantle 2 and is fitted over the central body 1 to cover a first end (e.g. the left end in fig. 2) of the annular passage 5, in other words, the end plate 3 is arranged between the mantle 2 and the central body 3 and covers the left end of the annular passage 5 formed by the mantle 2 and the central body 3; in addition, the end plate 3 is provided with an air intake hole 7 communicating with the annular passage 5.

The guide shell 4 is located in the annular passage 5 between the end plate 3 and the swirler 6, and the guide shell 4 is fitted over the central body 1 and radially (e.g., up and down in fig. 2) spaced from the central body 1 and the shroud 2, respectively, to divide the annular passage 5 into a plurality of annular spaces in a radial direction of the annular passage 5. In other words, an annular space with a length equal to that of the guide shell 4 is formed between the guide shell 4 and the shroud 2, and another annular space with a length equal to that of the guide shell 4 is formed between the guide shell 4 and the central body 1, so that the air entering from the air inlet slot holes 7 respectively enters different annular spaces, thereby improving the uniformity of air flow.

The first end of the peripheral flow guide 8 is opposite to the end plate 3 in the axial direction of the annular passage 5, where the term "opposite" means that the first end of the peripheral flow guide 8 is formed in the region of the annular passage 5 that is opposite to the end plate 3 in the axial direction, in other words, the projection of the first end of the peripheral flow guide 8 on the axial projection of the fuel nozzle of the gas turbine is located in the projection of the end plate 3.

The second end of the peripheral baffle 8 extends in a radial direction of the shroud 2 (e.g. up and down as shown in fig. 2) beyond the rear edge of the shroud 2 in a direction from the first end of the shroud 2 towards the second end of the shroud 2. In other words, as shown in fig. 2, the lower end of the peripheral air guide 8 is located in the area opposite to the end plate 3 in the axial direction of the annular passage 5, and the second end of the peripheral air guide 8 extends upward above the outer wall of the shroud 2 and then extends rightward to guide the outside air to the air intake holes 7 and into the annular passage 5. According to the fuel nozzle of the gas turbine, the air outside the annular channel can be guided into the annular channel through the peripheral flow guide piece, and the uniformity of the air flow is further adjusted. Preferably, the peripheral flow guide 8 has a substantially L-shaped axial section.

In some embodiments, a first end (e.g., the lower end shown in fig. 2) of the peripheral baffle 8 is opposite a first end (e.g., the left end shown in fig. 2) of the baffle cylinder 4. In other words, the lower end of the peripheral guide member 8 is opposite to the left end of the guide cylinder 4 in the axial direction of the annular passage 5, and external air can be guided into a specific annular space, so as to adjust the flow uniformity of air in different annular spaces. It can be understood that the number of the peripheral flow guiding members 8 may be multiple, and the plurality of peripheral flow guiding members 8 correspond to the plurality of flow guiding cylinders 4 one to one, so that the external air enters different annular spaces through different peripheral flow guiding members 8, respectively, so as to further adjust the air flowing uniformity in different annular spaces.

In some embodiments, the peripheral flow guide 8 includes an arc portion 81 and a flat portion 82, a first end (e.g., a lower end shown in fig. 2) of the arc portion 81 is opposite to a first end of the flow guide cylinder 4, a first end (e.g., a left end shown in fig. 2) of the flat portion 82 is connected to a second end (e.g., an upper end shown in fig. 2) of the arc portion 81, a second end of the arc portion 81 extends in a radial direction of the shroud 2 and beyond the shroud 2, and a second end (e.g., a right end shown in fig. 2) of the flat portion 82 extends in a direction toward the second end of the shroud 2. It can be understood that the air flowing backward is guided by the straight portion 82 on the radially outer side of the shroud 2, and the turning of the air is facilitated by the arc portion 81 on the axially left side of the shroud 2, so that the loss of the air flow is reduced.

In some embodiments, the first end of the peripheral flow guide 8 is located axially outside the annular channel 5 of the shroud 2. It will be understood that the peripheral baffle 8 mainly serves to guide the flow of air outside the annular channel 5, and therefore the peripheral baffle 8 may be located outside the annular channel 5, and preferably the peripheral baffle 8 may be mounted on the end plate 3 or supported by a mounting bracket and axially spaced from the end plate 3 by a predetermined distance. It will be appreciated that the invention is not limited thereto and that the first end of the peripheral baffle member 8 may also extend through the end plate 3 into the annular passage 5, for example.

In some embodiments, the peripheral baffle 8 surrounds the entire shroud 2 or a portion of the shroud 2 in the circumferential direction of the shroud 2. In other words, the peripheral air guide 8 is disposed around a circumference of the shroud 2, or a part of the circumference of the shroud 2, and it is understood that the range of disposition of the peripheral air guide 8 in the circumference of the shroud 2 may be set according to actual needs.

In some embodiments, as shown in fig. 1 and 2, the guide shell 4 is multiple, the guide shells 4 are sequentially sleeved, and the multiple annular spaces include an outer annular space between the outermost guide shell and the sleeve 2, an inner annular space between the innermost guide shell and the central body 1, and a middle annular space between adjacent guide shells. In other words, the plurality of guide cylinders 4 are sequentially nested together in the radial direction, so that a portion of the annular passage 5 (a portion corresponding to the guide cylinder 4) is divided into a plurality of annular spaces, i.e., an outermost annular space between the outermost guide cylinder 4 and the shroud 2, an innermost annular space between the innermost guide cylinder 4 and the central body 1, and one or more intermediate annular spaces between adjacent guide cylinders 4. This further improves the rectification effect.

In the example shown in fig. 1 and 2, the guide shell 4 is two: an inner layer guide shell 42 and an outer layer guide shell 41 sleeved on the inner layer guide shell 42. Thus, a first annular space 51 is formed between the inner guide shell 42 and the central body 1, a second annular space 52 is formed between the inner guide shell 42 and the outer guide shell 41, and a third annular space 53 is formed between the outer guide shell 41 and the shroud 2. Of course, the number of guide cylinders 4 may be selected according to the particular application.

In some embodiments, preferably, the plurality of guide cylinders 4 are coaxial, further preferably, the plurality of guide cylinders 4, the shroud 2 and the central body 1 are arranged coaxially with each other. In alternative embodiments, each guide shell 4 may be mounted on the end plate 3.

In some embodiments, the air inlet holes 7 are uniformly spaced in a plurality of circles along the circumference of the end plate 3, and the air inlet holes 7 in each circle are arranged along the axial direction of the end plate 3 and spaced from each other, thereby effectively controlling the air flow into different annular spaces or different zones.

In some embodiments, the end plate 3 is mounted on an end face of the first end 21 of the shroud 2 or within the annular channel 5 and at a predetermined distance from the end face of the first end 21 of the shroud 2. In other words, the specific position of the end plate 3 at the left end of the shroud 2 is not limited, and may be on the left end surface of the shroud 2 or at a position at a predetermined distance from the left end surface.

In some embodiments, the opening of the first end of the shroud 2 is flared. For example, the left end of the shroud 2 shown in fig. 2 is flared, in other words, the inner diameter of the shroud 2 increases from the left end of the shroud 2 to the right, so as to guide the air flow.

In some embodiments, the annular channel 5 comprises a constriction adjacent to the swirler 6 and of reduced radial dimension. In other words, the radial dimension of the annular channel 5 at a location adjacent to the swirler 6 is reduced to form a constriction by which the gas flow in the annular channel 5 can be accelerated at a location adjacent to the swirler 6, ensuring a gas flow rate of the annular channel 5 at a location adjacent to the swirler 3, reducing the risk of flashback.

In some alternative embodiments, the inner diameter of the shroud 2 is constricted inwardly by 5-10 mm adjacent the swirler 6 to form a constriction. In other alternative embodiments, the outer diameter of the central body 1 is flared outwardly by 2-6 mm adjacent the swirler 6 to form a constriction.

In some embodiments, a first end (e.g., the left end in fig. 2) of the central body 1 extends out of the first end of the shroud 2 through the end plate 3, and a second end (e.g., the right end in fig. 2) of the central body 1 is located within the shroud 2. In other embodiments, a fuel passage 9 is provided in the central body 1, the fuel in the fuel passage 9 being adapted to be injected into the annular passage 5 through the swirler 6 to be mixed with the air in the annular passage 5, the fuel passage 9 may extend in the axial direction of the central body 1 as shown in fig. 2. In some embodiments, a first end of the center body 1 is provided with a mounting flange 10, for example, the left end of the center body 1 shown in FIG. 2 is provided with a mounting flange 10 to facilitate mounting a fuel nozzle 100 of a gas turbine within a combustion chamber of the gas turbine.

A fuel nozzle for a gas turbine in accordance with a specific embodiment of the present invention is described below with reference to FIGS. 1 and 2.

As shown in fig. 1-2, a fuel nozzle 100 for a gas turbine engine includes a center body 1, a shroud 2, an end plate 3, a guide tube 4, a swirler 6, a peripheral guide 8, and a mounting flange 10. The central body 1, the mantle 2 and the guide shell 4 are arranged coaxially with each other and the cross sections of the central body, the mantle 2 and the guide shell are all circular.

The shroud 2 has a first end (left end) 21 and a second end (right end) 22. The shroud 2 is fitted over the central body 1 and spaced apart from each other in the radial direction so that an annular passage 5 is formed between the shroud 2 and the central body 1, a swirler 6 is provided in the annular passage 5, and the left end opening of the shroud 2 is flared.

The end plate 3 is arranged at the left end of the sleeve cover 2 and is a preset distance away from the left end surface of the sleeve cover 2 and used for covering the left end of the end plate 3, the end plate 3 can be welded to the left end of the sleeve cover 2, the end plate 3 is provided with a central hole, the central body 1 penetrates through the central hole of the end plate 3, and the end plate 3 and the central body 1 can also be welded; the end plate 3 is provided with air inlet holes 7 communicated with the annular channel 5, the air inlet holes 7 are uniformly arranged into a plurality of circles at intervals along the circumferential direction of the end plate 3, and the air inlet holes 7 in each circle are axially arranged along the end plate 3 and are spaced from each other, so that the air flow entering different annular spaces or different areas can be effectively controlled.

The guide shell 4 is two: the inner guide shell 42 and the outer guide shell 41 are coaxially sleeved outside the inner guide shell 42, and the inner guide shell 42 and the outer guide shell 41 are arranged in the annular channel 5 and located between the end plate 3 and the swirler 6. The inner and

outer guide shell

42, 41 may be mounted to the end plate 3, for example welded to the end plate 3. The inner guide shell 42 is sleeved on the central body 1 and is spaced from the central body 1, the inner guide shell 42 is spaced from the outer guide shell 41, the outer guide shell 41 is spaced from the sleeve cover 2 to form a first annular space 51, a second annular space 52 and a third annular space 63 from inside to outside in sequence in the radial direction, and air entering from the air inlet 7 can enter different annular spaces respectively to improve the air flowing uniformity.

The peripheral guide 8 includes an arc portion 81 and a flat portion 82, a first end of the arc portion 81 is located in a region facing the end plate 3 in the axial direction of the annular passage 5, a second end of the arc portion 81 extends in the radial direction of the shroud 2 beyond the outer wall of the shroud 2, a first end of the flat portion 82 is connected to a second end of the arc portion 92, and a second end of the flat portion 82 extends rightward. It will be appreciated that the peripheral baffle 8 is generally L-shaped in axial cross-section.

The left end of the central body 1 extends out from the left end of the shroud 2 through the end plate 3, and the right end of the central body 1 is located inside the shroud 2. Inside the central body 1, a fuel channel 9 is provided extending in the axial direction of the central body 1, and fuel in the fuel channel 9 is injected into the annular channel 5 through the swirler 6 to be mixed with air in the annular channel 5. The left end of the central body 1 is provided with a mounting flange 10 to facilitate mounting of the fuel nozzle of the gas turbine in the combustion chamber of the gas turbine.

Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.

Claims

1. A fuel nozzle for a gas turbine engine, comprising:

a central body;

a shroud having a first end and a second end, the shroud being fitted over the central body, an annular passage being formed between the shroud and the central body, the annular passage having a swirler disposed therein;

the end plate is arranged at the first end of the sleeve cover and sleeved on the central body, the end plate is installed in the annular channel and is away from the end face of the first end of the sleeve cover by a preset distance, the end plate is provided with air inlet holes, the air inlet holes are arranged into a plurality of circles at intervals along the radial direction of the end plate, the air inlet holes in each circle are uniformly arranged along the circumferential direction of the end plate and are separated from each other, the plurality of circles of air inlet holes comprise the outermost circle of air inlet holes which are positioned at the outermost side along the radial direction of the end plate, and the cross-sectional area of the outermost circle of air inlet holes is larger;

the guide cylinder is positioned in the annular channel and is arranged between the end plate and the swirler so as to divide the annular channel into a plurality of annular spaces along the radial direction of the annular channel, and the annular spaces are correspondingly communicated with the air inlet holes;

a first end of the peripheral flow guide element is opposite to the end plate in the axial direction of the annular passage, and a second end of the peripheral flow guide element extends along the radial direction of the sleeve cover and exceeds the rear edge of the sleeve cover and extends from the first end of the sleeve cover towards the second end of the sleeve cover.

2. The gas turbine fuel nozzle of claim 1, wherein the peripheral flow guide has a generally L-shaped axial cross-section.

3. The gas turbine fuel nozzle of claim 1, wherein the first end of the peripheral flow guide is opposite the first end of the flow sleeve.

4. The gas turbine fuel nozzle of claim 1, wherein the peripheral flow guide includes an arcuate portion and a flat portion, a first end of the arcuate portion being opposite the first end of the flow guide sleeve, a first end of the flat portion being connected to a second end of the arcuate portion that extends beyond the shroud in a radial direction of the shroud, and a second end of the flat portion extending in a direction toward the second end of the shroud.

5. The gas turbine fuel nozzle of claim 1, wherein the first end of the peripheral flow guide is located axially outward of the annular passage in the shroud.

6. The gas turbine fuel nozzle of claim 1, wherein the peripheral flow guide surrounds the entire shroud or a portion of the shroud in a circumferential direction of the shroud.

7. The gas turbine fuel nozzle of any of claims 1-6, wherein the flow sleeve is mounted on the end plate.

8. The fuel nozzle of a gas turbine according to any one of claims 1 to 6, wherein the number of the guide cylinders is plural, the plural guide cylinders are sequentially sleeved, and the plural annular spaces include an outer annular space between the outermost guide cylinder and the shroud, an inner annular space between the innermost guide cylinder and the center body, and a middle annular space between adjacent guide cylinders.

9. The gas turbine fuel nozzle as set forth in any one of claims 1-6, wherein said annular passage includes a constriction adjacent said swirler of decreasing radial dimension.

10. The gas turbine fuel nozzle as set forth in any one of claims 1 to 6, wherein said shroud first end opening is flared.