KR20160139406A - Nozzle hub with fuel injection holes - Google Patents

Nozzle hub with fuel injection holes Download PDF

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Publication number
KR20160139406A
KR20160139406A KR1020150074094A KR20150074094A KR20160139406A KR 20160139406 A KR20160139406 A KR 20160139406A KR 1020150074094 A KR1020150074094 A KR 1020150074094A KR 20150074094 A KR20150074094 A KR 20150074094A KR 20160139406 A KR20160139406 A KR 20160139406A
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KR
South Korea
Prior art keywords
fuel supply
fuel
nozzle
annular cover
hub
Prior art date
Application number
KR1020150074094A
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Korean (ko)
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KR101884694B1 (en
Inventor
김성현
Original Assignee
두산중공업 주식회사
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Priority to KR1020150074094A priority Critical patent/KR101884694B1/en
Publication of KR20160139406A publication Critical patent/KR20160139406A/en
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Publication of KR101884694B1 publication Critical patent/KR101884694B1/en

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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • 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 present invention relates to a fueling nozzle with a nozzle hub having an improved fuel exhaust port, and more specifically, to a fueling nozzle which has improved shape and angle of arrangement of a fuel supply hole inside a nozzle hub, which is an element of a burner used for a gas turbine combustion system, and which increases mixing efficiency of fuel and air. The fueling nozzle comprises a nozzle hub with a ring-shaped mixing passage. The nozzle hub comprises a plurality of air foil-shaped vanes arranged in a direction of a circumference inside the ring-shaped mixing passage at regular intervals. Through the structure, mixing efficiency of fuel and air can be increased. In conclusion, this can bring an increase in efficiency of a burner and a power generator, and can operate a power generator and produce electric power in an economical and environmentally friendly manner.

Description

[0001] The present invention relates to a nozzle hub having a fuel injection hole,

The present invention relates to a fuel supply nozzle including a nozzle hub having an improved fuel supply hole, and more particularly, to an arrangement of an inner fuel supply hole of a nozzle hub which is a component of a burner used in a gas turbine combustion system, To increase the mixing efficiency between the fuel and the air.

Turbine generators, commonly used in gas turbine power generation, operate on the principle of burning fuel through compressed air to generate powerful energy and using it to operate the turbine.

Here, in the operation of the fuel supply nozzle for supplying the fuel to the inside of the combustor, the operation of mixing air with the fuel to be supplied is extremely important in order to increase the combustion efficiency.

For this purpose, in some generators, the fuel supply nozzle may include a nozzle hub for spraying and supplying the fuel in advance to the air supplied to the nozzle during the construction of the fuel supply nozzle.

In the case of the nozzle hub provided in the conventional fuel supply nozzle, the fuel supply hole provided in the nozzle hub internal airfoil structure may exist in a simple circular shape, or may not be smoothly mixed with the air to which the injected fuel flows, So that there is a problem that efficient mixing can not be performed.

As a result, the ratio of the fuel injected from the nozzle hub to air can not be mixed with each other, which ultimately becomes a problem of directly connecting the efficiency of the combustor and the generator itself.

Therefore, in the case where the fuel supply nozzle is provided with a nozzle hub, a technique for maximizing the mixing performance of fuel and air in the nozzle hub and ultimately improving the performance of the generator is required.

US registered patent US 8925323

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and an object of the present invention is to improve the arrangement and arrangement angle of the inner fuel supply holes of the nozzle hub so that the mixing ratio of fuel and air mixture introduced into the combustion chamber can be increased And a fuel supply nozzle.

According to an aspect of the present invention, there is provided a fuel supply nozzle for supplying fuel to a combustor, the fuel supply nozzle including a nozzle hub provided with an annular mixing passage, The fuel supply nozzle may be provided with a plurality of fuel supply holes.

The nozzle hub may have an annular shape, a structure suitable for uniformly passing the fluid, or a shape other than an annular shape.

Further, the annular mixing passage of the nozzle hub includes an outer annular cover and an inner annular cover, and a plurality of vanes in the form of an airfoil are arranged at regular intervals in the circumferential direction in a space between the outer annular cover and the inner annular cover The fuel supply nozzle may be provided.

A plurality of vanes may be provided in the annular mixing passage of the nozzle hub. In order to smoothly advance and mix air mixed with the fuel, the plurality of vanes may be in the form of an airfoil, but may not be in the form of an airfoil .

Finally, the high-pressure air directed to the fuel supply nozzle passes through the nozzle hub before being supplied to the fuel supply nozzle and mixed with the fuel.

In addition to this, it is possible that the plurality of fuel supply holes are provided on the inner surface of the outer annular cover of the nozzle hub and on the outer surface of the inner annular cover.

The inner side surface of the outer annular cover of the nozzle hub and the outer side surface of the inner annular cover mainly pass through the compressed high-pressure air, and the fuel supply hole is located in the above section to improve the mixing efficiency of the fuel and air It is important.

Further, the fuel supply nozzle is characterized in that the plurality of fuel supply holes are located on one side of the plurality of vanes.

As described above, as well as the configuration in which a plurality of fuel supply holes are provided on the inner side surface of the outer annular cover and the outer side surface of the inner annular cover of the nozzle hub, also located on one side of the plurality of vanes, Which is important in increasing the mixing efficiency of the mixture.

The plurality of vanes in the form of the airfoil are vertically positioned inside the annular mixing passage, and the surfaces of the plurality of vanes are provided with pores for supplying fuel, that is, a plurality of fuel supply holes.

In order to inject fuel into the plurality of fuel supply holes of the plurality of vanes, a fuel inlet may be provided in the nozzle hub.

In addition, the plurality of fuel supply holes may be provided on the inner surface of the outer annular cover of the nozzle hub, the outer surface of the inner annular cover, and one side of the plurality of vanes. .

This corresponds to the case where the above two cases are simultaneously applied. High pressure air passing through a plurality of vanes having an airfoil shape in the nozzle hub is injected into the inner peripheral surface of the outer annular cover of the nozzle hub and the outer peripheral surface of the inner annular cover and the fuel supply hole provided in one side of the plurality of vanes And is efficiently mixed with the supplied fuel.

The plurality of fuel supply holes may have a circular or elliptical shape fuel supply outlet, and the plurality of fuel supply holes may be arranged at regular intervals to form a group. The plurality of fuel supply holes may include a plurality of fuel supply holes, And a fuel supply nozzle may be provided at a center thereof.

The position where the above-described fuel supply hole is provided is generally one side of the inner annular cover of the nozzle hub and the outer side of the inner annular cover and one side of the plurality of vanes, so that the fuel supply hole is located outside the nozzle hub When the fuel injection hole is located on the outer surface of the inner annular cover of the nozzle hub, the fuel injection hole is provided on the outer surface of the outer annular cover when the inner annular cover is located on the inner surface of the annular cover. And the fuel injection port is provided on the side surface.

In the same manner, when the fuel supply holes are provided on one side of the plurality of vanes, it is preferable that the fuel injection holes are provided on the back surfaces of the plurality of vanes.

Also, the plurality of fuel supply holes constituting the one group does not necessarily mean that the group should be formed with a certain standard, but refers to a plurality of fuel supply holes that receive fuel from one fuel injection hole.

In addition, the direction of the outlet of the plurality of fuel supply holes through which the fuel is injected may be provided at 120 to 150 degrees with respect to the direction in which air is injected into the nozzles.

The angle of 120 to 150 degrees is easier to generate vortices when the angle with respect to the direction in which air is injected into the nozzle is set larger than when the fuel is injected vertically, And the angle is set based on the height.

Finally, a fuel supply nozzle may be provided, wherein a protruding step is attached to one side of the outlet of the plurality of fuel supply holes through which the fuel is ejected.

The protruding jaws are generally arranged such that the air is directed in the direction of the fuel injection opening of the nozzle.

The shape of the protruding jaw can be set without any particular constraint such as a semi-circle, a square, or a triangle. Due to the presence of the protruding jaw, the fuel supplied from the fuel supply hole meets high pressure air, There is a characteristic that the mixing efficiency of fuel and air can be increased.

The nozzle hub having the fuel injection hole of the present invention as described above has an arrangement structure and an arrangement angle of the fuel supply holes maximizing the friction and vortex between the high-pressure air and the fuel supply hole, It is possible to increase. In conclusion, this can lead to an increase in the efficiency of the combustor and the generator, thereby enabling the economical and environmentally friendly operation of the generator and the power generation process.

1 is a perspective view of a fuel supply nozzle provided with a nozzle hub having an annular mixing passage showing one embodiment of the present invention.
FIG. 2 is a perspective view showing an airfoil-shaped vane positioned in the interior of a nozzle hub according to one embodiment of the present invention and a fuel supply hole located on the nozzle hub; FIG.
3 is a side cross-sectional view showing a plurality of fuel supply holes and fuel injection ports according to an embodiment of the present invention.
4 is a side sectional view showing an arrangement angle of a fuel supply hole according to an embodiment of the present invention.
5 is a side cross-sectional view showing the shape of a fuel supply hole including a protrusion showing an embodiment of the present invention.

Hereinafter, some embodiments of the present invention will be described in detail with reference to exemplary drawings. It should be noted that, in adding reference numerals to the constituent elements of the drawings, the same constituent elements are denoted by the same reference symbols as possible even if they are shown in different drawings. In the following description of the embodiments of the present invention, a detailed description of known functions and configurations incorporated herein will be omitted when it may make the difference that the embodiments of the present invention are not conclusive.

In describing the components of the embodiment of the present invention, terms such as first, second, A, B, (a), and (b) may be used. These terms are intended to distinguish the constituent elements from other constituent elements, and the terms do not limit the nature, order or order of the constituent elements. When a component is described as being "connected", "coupled", or "connected" to another component, the component may be directly connected or connected to the other component, Quot; may be "connected,""coupled," or "connected. &Quot;

1 shows a perspective view of a fuel supply nozzle provided with a nozzle hub having an annular mixing passage showing one embodiment of the present invention.

The fuel supply nozzle 10 is characterized in that the fuel is injected at a high pressure and mixed with the air, and at the same time, combustion takes place at the end of the fuel supply nozzle 10.

As a process before the above-described combustion process, the nozzle hub 20 may be provided in the fuel supply nozzle 10 in some generators.

The nozzle hub 20 may have an annular shape, a structure suitable for uniformly passing the fluid, or a shape other than an annular shape.

The nozzle hub 20 injects a small amount of fuel into the high-pressure air supplied to the fuel supply nozzle 10 and mixes the fuel.

Through the above-described mixing process, the rate of complete combustion can be increased as compared with a process in which the fuel is injected and burned alone in the fuel supply nozzle 10 alone.

Such a nozzle hub 20 is generally disposed to surround one side of the fuel supply nozzle 10.

FIG. 2 is a perspective view showing an airfoil-shaped vane positioned in the interior of a nozzle hub according to one embodiment of the present invention and a fuel supply hole located on the nozzle hub; FIG.

The annular mixing passage 30 and the plurality of vanes 23 of the nozzle hub 20 are provided with a fuel injection port 41 through which the fuel moves to the fuel supply hole 40.

The fuel that has been transferred to the annular mixing passage 30 is moved to a plurality of vanes 23 arranged in the circumferential direction at regular intervals in the annular mixing passage 30 and the annular mixing passage 30 and the plurality of vanes Through the plurality of fuel supply holes (40) provided in the fuel tank (23).

The inner side surface of the outer annular cover 21 of the nozzle hub 20 and the outer side surface of the inner annular cover 22 mainly pass through the compressed high pressure air and the fuel supply hole 40 It is important to increase the mixing efficiency of fuel and air.

The nozzle hub 20 does not rotate and is generally fixed.

In order to efficiently distribute the introduced air and increase the mixing efficiency with the fuel, the plurality of vanes 23 preferably have an airfoil shape in general.

The vanes are provided with a plurality of fuel supply holes 40. The plurality of fuel supply holes 40 are generally arranged in a row in consideration of the influence of the backflow of high pressure air, May also be included.

As shown in the figure, it includes a plurality of columns including one column.

The fuel which is moved from the annular mixing passage 30 to the plurality of vanes 23 is finally moved to the fuel supply hole 40 provided in the plurality of vanes 23 where the high pressure air is met, .

Therefore, in order to smoothly perform the mixing process, it is preferable that the fuel supply hole 40 through which the fuel is injected is provided at a predetermined angle with the surface of the airfoil-shaped vane 23.

This is to induce a vortex phenomenon and natural friction occurring on the surface of the fuel supply hole 40 while preventing the reverse flow of the fuel into the fuel supply hole 40 as much as possible.

3 is a side sectional view showing a plurality of fuel supply holes and a fuel injection port showing one embodiment of the present invention.

3 shows the plurality of fuel supply holes 40 and the fuel injection port 41 as a passage for supplying fuel to the fuel supply hole 40 in detail.

The position where the fuel supply hole 40 is provided is determined by the inner surface of the outer annular cover 21 of the nozzle hub 20 and the outer surface of the inner annular cover 22, When the fuel supply hole 40 is located on the inner surface of the outer annular cover 21 of the nozzle hub 20, the fuel injection hole 41 When the fuel supply hole 40 is located on the outer surface of the inner annular cover 22 of the nozzle hub 20, the fuel injection hole 41 is formed in the inner surface of the inner annular cover 22 .

The plurality of fuel supply holes 40 constituting one group generally refers to the entire fuel supply hole 40 to which fuel is supplied from one fuel injection port 41.

Therefore, a plurality of thin fuel tubes provided inside the outer annular cover 21, the inner annular cover 22 and the plurality of vanes 23 are generated from the fuel inlet 41 and lead to the fuel supply hole 40.

Therefore, the fuel injection holes 41 corresponding to one group are provided for each fuel supply hole 40, and one fuel injection hole 41 is provided for each fuel supply hole 40, It is possible.

4 is a side sectional view showing an arrangement angle of the fuel supply holes according to one embodiment of the present invention.

4, it is confirmed that the plurality of fuel supply holes 40 provided in the outer annular cover 21, the inner annular cover 22, and the plurality of vanes 23 are not vertically arranged but are arranged obliquely have.

According to the structure of the inclined fuel supply hole 40, as the high-pressure air passes through the plurality of fuel supply holes 40, resistance and vortex of the air naturally occur, thereby increasing the mixing efficiency of the fuel and the air There is a feature that can be made.

It is preferable that the direction in which the air is introduced is indicated by an arrow and the angle between the arrow and the inclined passage of the fuel supply hole is 120 to 150 degrees as an optimum angle for increasing the air mixing efficiency.

5 is a side cross-sectional view showing the shape of a fuel supply hole including a protrusion showing an embodiment of the present invention.

In order to generate the aforementioned resistance and vortex of the air to increase the mixing efficiency of the fuel and the air, it is preferable to generate the protrusion at the last point where the fuel supply hole and the high-pressure air come into contact with each other.

It is preferable that the protruding portion does not exceed the diameter of the fuel supply hole, and it is possible that the shape is not particularly restricted.

In addition, the inner annular cover referred to in the present invention may not be provided separately, and may be replaced with the surface of the nozzle.

In this case, a fuel supply hole may be provided on the surface of the nozzle, and a fuel may be injected.

While the present invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the disclosed embodiments. That is, within the scope of the present invention, all of the components may be selectively coupled to one or more of them. Furthermore, the terms "comprises", "comprising", or "having" described above mean that a component can be implanted unless otherwise specifically stated, But should be construed as including other elements. All terms, including technical and scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs, unless otherwise defined. Commonly used terms, such as predefined terms, should be interpreted to be consistent with the contextual meanings of the related art, and are not to be construed as ideal or overly formal, unless expressly defined to the contrary.

The foregoing description is merely illustrative of the technical idea of the present invention, and various changes and modifications may be made by those skilled in the art without departing from the essential characteristics of the present invention. Therefore, the embodiments disclosed in the present invention are intended to illustrate rather than limit the scope of the present invention, and the scope of the technical idea of the present invention is not limited by these embodiments. The scope of protection of the present invention should be construed according to the following claims, and all technical ideas within the scope of equivalents should be construed as falling within the scope of the present invention.

10: Fuel supply nozzle
20: nozzle hub
21: outer annular cover
22: Inner annular cover
23: Multiple vanes
30: Annular mixing nozzle
40: fuel supply hole
41: fuel inlet
42: protruding chin

Claims (8)

A fuel supply nozzle (10) for supplying fuel to a combustor,
The fuel supply nozzle 10 includes a nozzle hub 20 provided with an annular mixing passage 30, and the nozzle hub 20 is provided with a plurality of fuel supply holes 40;
(10).
The method according to claim 1,
The annular mixing passage 30 of the nozzle hub 20 includes an outer annular cover 21 and an inner annular cover 22 and a space between the outer annular cover 21 and the inner annular cover 22 Characterized in that a plurality of foil-shaped vanes (23) are arranged at regular intervals in the circumferential direction.
3. The method of claim 2,
Wherein the plurality of fuel supply holes (40) are provided on the inner side surface of the outer annular cover (21) of the nozzle hub (20) and the outer side surface of the inner annular cover (22).
3. The method of claim 2,
Wherein the plurality of fuel supply holes (40) are located on one side of the plurality of vanes (23).
3. The method of claim 2,
The plurality of fuel supply holes 40 are formed on the inner surface of the outer annular cover 21 of the nozzle hub 20 and the outer surface of the inner annular cover 22 and on one side of the plurality of vanes 23 (10).
6. The method according to any one of claims 1 to 5,
The plurality of fuel supply holes 40 have a circular or elliptical fuel supply outlet, and the plurality of fuel supply holes 40 are arranged at regular intervals to form a group. The plurality of fuel supply holes 40, And a fuel injection port (41) is provided at the center of the rear surface of the installed surface.
The method according to claim 6,
Wherein the direction of the outlet of the plurality of fuel supply holes (40) through which the fuel is injected is formed to be 120 to 150 degrees with respect to a direction in which air is injected into the nozzles.
8. The method according to any one of claims 1 to 7,
And a protruding step (42) is attached to one side of an outlet through which the fuel of the plurality of fuel supply holes (40) is ejected.
KR1020150074094A 2015-05-27 2015-05-27 Nozzle hub with fuel injection holes KR101884694B1 (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102096580B1 (en) * 2019-04-01 2020-04-03 두산중공업 주식회사 Combustion nozzle enhancing spatial uniformity of pre-mixture and gas turbine having the same

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2005180799A (en) * 2003-12-19 2005-07-07 Mitsubishi Heavy Ind Ltd Premixing fuel nozzle, combustor, and gas turbine using it
CN101563533A (en) * 2006-10-06 2009-10-21 通用电气公司 Combustor nozzle for a fuel-flexible combustion system
JP2012102995A (en) * 2010-11-08 2012-05-31 General Electric Co <Ge> Self-oscillating fuel injection jets
JP2013053844A (en) * 1999-12-15 2013-03-21 Osaka Gas Co Ltd Burner device, gas turbine engine, and cogeneration system
US8925323B2 (en) 2012-04-30 2015-01-06 General Electric Company Fuel/air premixing system for turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013053844A (en) * 1999-12-15 2013-03-21 Osaka Gas Co Ltd Burner device, gas turbine engine, and cogeneration system
JP2005180799A (en) * 2003-12-19 2005-07-07 Mitsubishi Heavy Ind Ltd Premixing fuel nozzle, combustor, and gas turbine using it
CN101563533A (en) * 2006-10-06 2009-10-21 通用电气公司 Combustor nozzle for a fuel-flexible combustion system
JP2012102995A (en) * 2010-11-08 2012-05-31 General Electric Co <Ge> Self-oscillating fuel injection jets
US8925323B2 (en) 2012-04-30 2015-01-06 General Electric Company Fuel/air premixing system for turbine engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102096580B1 (en) * 2019-04-01 2020-04-03 두산중공업 주식회사 Combustion nozzle enhancing spatial uniformity of pre-mixture and gas turbine having the same
US11608986B2 (en) 2019-04-01 2023-03-21 Doosan Enerbility Co., Ltd. Combustor nozzle enhancing spatial uniformity of pre-mixture and gas turbine having same

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