KR101852006B1 - The shape of inner passage of vane - Google Patents

The shape of inner passage of vane Download PDF

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Publication number
KR101852006B1
KR101852006B1 KR1020150093185A KR20150093185A KR101852006B1 KR 101852006 B1 KR101852006 B1 KR 101852006B1 KR 1020150093185 A KR1020150093185 A KR 1020150093185A KR 20150093185 A KR20150093185 A KR 20150093185A KR 101852006 B1 KR101852006 B1 KR 101852006B1
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South Korea
Prior art keywords
flow path
airfoil
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fuel
fuel injection
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KR1020150093185A
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Korean (ko)
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KR20170003049A (en
Inventor
노우진
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두산중공업 주식회사
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Priority to KR1020150093185A priority Critical patent/KR101852006B1/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
    • F23R3/28—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
    • 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
    • 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
    • F02C7/222—Fuel flow conduits, e.g. manifolds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The present invention relates to an airfoil comprising a pipe, a first flow path formed in the longitudinal direction of the pipe and through which fuel flows, at least one fuel injection airfoil protruding in a radial direction of the pipe from an outer circumferential surface of the pipe, And at least one fuel injection opening provided on the surface of the airfoil and connected to the second flow path, wherein the second flow path is a polyhedron.
The inner flow path shape according to the present invention is advantageous for maintaining the pressure and injecting the fuel without a separate power device. By configuring the flow path inside the fuel injection airfoil to be gradually narrowed, the pressure at the portion where the airfoil starts is relatively lowered, so that the fuel flowing along the fuel injection nozzle can be easily drawn into the airfoil. Further, the pressure is relatively increased when reaching the injection opening, so that the fuel injection can be efficiently performed. This means that the fuel and compressed air are properly mixed to contribute to improved combustion stability.

Description

[0001] The present invention relates to an inner passage of a vane,

The present invention relates to a combustion nozzle of a gas turbine combustion apparatus and relates to a flow path shape formed inside a fuel injection airfoil formed on the outer circumferential surface of a combustion nozzle,

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A gas turbine is a rotary type heat engine that drives a turbine with high-temperature, high-pressure combustion gas. Generally, it consists of compressor, combustor and turbine. In the conventional gas turbine plant, the air flow rate and the fuel flow rate to the combustor are determined according to predetermined data based on the generator output, the atmospheric temperature, and the like, and the gas turbine operation is operated by finely adjusting the value to an appropriate value through trial operation. However, in the control apparatus of the conventional gas turbine plant, it is not possible to immediately adapt to changes in the composition of the fuel, thereby deteriorating the combustion stability or generating combustion vibration.

Conventionally, in order to appropriately control the combustion stability of the gas turbine, air-fuel ratio control is mainly performed on the combustion output. On the other hand, a method of obtaining combustion stability by properly mixing the compressed air and the fuel can be considered. For combustion stability, it is assumed that well-mixed gas enters the combustion chamber.

Patent Document 1 attempts to solve this problem by forming a partition inside a combustion nozzle so that fuel injection can be appropriately performed to disperse the flow. However, the invention disclosed in Patent Document 1 is merely a separation of flow, so that it is insufficient to maintain the fuel injection pressure and to inject the fuel. Therefore, the present invention not only extends to the method disclosed in Patent Document 1, but also suggests an inner flow path shape for more aggressive fuel injection.

U.S. Published Patent Application No. 2003-0089801 (published on May 15, 2003)

It is an object of the present invention to utilize an internal flow path shape which is gradually narrowed so that fuel injection can be efficiently performed without a separate power device, and ultimately to improve combustion stability.

According to an aspect of the present invention, there is provided a fuel cell including a tube, a first flow path formed in the longitudinal direction of the tube and flowing fuel, at least one fuel injected from the outer circumferential surface of the tube in a radial direction of the tube, A second flow path provided so that the fuel flows into the airfoil and at least one fuel injection opening provided on a surface of the airfoil and connected to the second flow path, The gas turbine fuel nozzle may be a gas turbine fuel nozzle.

According to an embodiment of the present invention, the second flow path may be a gas turbine fuel nozzle characterized in that the shape of the cross section perpendicular to the radial direction in which the airfoil protrudes is triangular.

According to an embodiment of the present invention, the second flow path may be a gas turbine fuel nozzle characterized in that the shape of the cross section perpendicular to the radial direction in which the airfoil protrudes is rectangular.

According to an embodiment of the present invention, the shape of the second flow path, the shape of the cross section perpendicular to the radial direction in which the airfoil protrudes, is a shape in which two vertexes of the triangle are curved. Fuel nozzle.

According to an embodiment of the present invention, the cross-sectional shape of the second flow path may be a gas turbine fuel nozzle characterized in that the cross-sectional area decreases as the distance from the radial direction increases.

According to an embodiment of the present invention, the portion where the second flow path and the first flow path meet is a fillet-processed gas turbine fuel nozzle.

According to an embodiment of the present invention, the second flow path is positioned such that a section where the second flow path is cut in the radial direction of the tube is narrowed toward the front end of the airfoil. Fuel nozzle.

The inner flow path shape according to the present invention is advantageous for maintaining the pressure and injecting the fuel without a separate power device. By configuring the flow path inside the fuel injection airfoil to be gradually narrowed, the pressure at the portion where the airfoil starts is relatively lowered, so that the fuel flowing along the fuel injection nozzle can be easily drawn into the airfoil. Further, the pressure is relatively increased when reaching the injection opening, so that fuel injection can be efficiently performed. This means that the fuel and compressed air are properly mixed to contribute to improved combustion stability.

1 shows a gas turbine combustor and a combustion nozzle.
2 shows various shapes of the second flow path inside the airfoil.
Fig. 3 shows that the second flow path is filled.

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 combustor and a combustion nozzle of a general gas turbine. Fig. 1 (a) shows a cross-sectional view of a combustor of a gas turbine, and Fig. 2 (b) shows a combustion nozzle of a combustor. The structure of the gas turbine combustor may have various structures depending on the manufacturer and the purpose, but FIG. 1 shows a general gas turbine combustor. The description of the present invention is based on a general gas turbine.

1 (a) shows only a combustor in a gas turbine comprising a compressor, a combustor, and a turbine. A typical gas turbine has a structure in which a plurality of combustors are arranged in an annular shape to increase the output. The figure shows only one combustor among a plurality of combustors, and the combustor is composed of a fuel injection nozzle, a liner, a transition piece, and the like. Air compressed through the compressor flows into the combustor and passes from the top of the combustor to the bottom. Some of the introduced air flows into the combustion chamber through the combustion nozzle.

Referring to Fig. 1 (b), a flow path through which fuel flows is formed in the combustion nozzle, and fuel is injected from the outer peripheral surface of the nozzle. At this time, the flow path formed in the longitudinal direction of the fuel nozzle tube 10 is referred to as a first flow path 100. The compressed air passes through the injection nozzle and is mixed with the injected fuel. The combustion nozzle is generally a pipe 10, and a plurality of airfoils 20 for injecting fuel are formed on the outer circumferential surface. One end of the tube 10 may be clogged or open. Similarly, the airfoil 20 may be either closed at one end or open.

The compressed air flowing along the outer circumferential surface of the fuel injection nozzle passes through the airfoil 20. At this time, a fuel injection opening 30 is formed on the surface of the airfoil 20 so that fuel flowing inside the airfoil 20 is injected and mixed with the compressed air at the surface of the airfoil 20 in a vaporized state. Fuel injection from the airfoil 20 is a very important problem because the combustion stability and the combustion efficiency can be improved as the fuel and the compressed air are properly mixed and introduced into the combustion chamber. The passage through which the fuel flows in the airfoil 20 is referred to as a second flow path 200 and the opening from the second flow path 200 to the surface of the airfoil 20 is referred to as a fuel injection opening 30. That is, the fuel flows into the gas turbine combustor, flows through the first flow path 100 in the fuel injection nozzle, enters the second flow path 200, and is injected into the airfoil 20 through the fuel injection opening 30 do.

Fig. 2 shows various modifications of the second flow path 200 inside the airfoil 20. Fig. Referring to the drawings, the second flow path 200 may or may not pass the airfoil 20 through the pipe 10, if necessary. In general, the internal flow path of the airfoil 20 is formed in a cylindrical shape, but the present invention is characterized in that the second flow path 200 in the airfoil 20 is angular or gradually narrowed.

According to an embodiment of the present invention, when the airfoil 20 is cut in a plane perpendicular to the radial direction in which the airfoil 20 protrudes, the shape of the cross section may be triangular. At this time, the size of the cross-section triangle may change as the radius of the airfoil 20 increases or decreases. Accordingly, the second flow path 200 can be widened or narrowed. The embodiment in which the shape of the cross section is triangular is shown in Figs. 2 (a), 2 (b) and 2 (c).

2 (a) is an embodiment in which the shape of the cross section of the second flow path 200 is a triangle, which is shaped like a triangular prism. 2 (b) is an embodiment in which the shape of the cross section of the second flow path 200 gradually decreases and converges to one point, in the form of triangular pyramids. 2C is an embodiment in which the shape of the cross section of the second flow path 200 gradually decreases but does not converge to a single point, in the form of a triangular frustum. The above-mentioned forms (a), (b) and (c) are only examples in which the shape of the cross section is a triangular shape and have a particularly geometrical name, and various modifications are practically possible.

According to one embodiment of the present invention, when the airfoil 20 is cut in a plane perpendicular to the radial direction in which the airfoil 20 protrudes, the shape of the cross section may be rectangular. At this time, the size of the section rectangle may change as the radius of the airfoil 20 increases or decreases. Accordingly, the second flow path 200 can be widened or narrowed. The embodiment in which the shape of the cross section is triangular is shown in (d), (e), and (f) of FIG.

2 (d) is an embodiment in which the shape of the cross section of the second flow path 200 is unchanged, in the form of a square pillar. FIG. 2 (e) is an embodiment in which the shape of the cross section of the second flow path 200 gradually decreases and converges to one point, in the form of quadrangular pyramids. 2F is an embodiment in which the shape of the cross section of the second flow path 200 gradually decreases but does not converge to one point and is shaped like a quadrangular frustum. The above-mentioned forms (d), (e), and (f) are only examples in which the geometry of the cross section is a quadrangular shape in particular, and various modifications are practically possible.

According to an embodiment of the present invention, when the cross section of the second flow path 200 is cut in a plane perpendicular to the radial direction in which the airfoil 20 protrudes, the shape of the cross section is a shape in which two vertexes of a triangle are curved Lt; / RTI > At this time, the size of the cross section may change as the distance from the airfoil 20 to the radial direction increases or decreases. Accordingly, the second flow path 200 can be widened or narrowed. An embodiment in which the shape of the cross section is a shape in which two vertexes of a triangle are curved is shown in (g), (h), and (i) of FIG.

FIG. 2 (g) shows an embodiment in which the shape of the cross section of the second flow path 200 is not changed, and it is in the form of a column. 2 (h) is an embodiment in which the shape of the cross section of the second flow path 200 gradually decreases and converges to one point, in the form of pyramids. 2 (i) is an embodiment in which the shape of the cross-section of the second flow path 200 gradually decreases but does not converge to one point, in the form of frustum. The above-mentioned forms (g), (h) and (i) are only examples in which the cross-sectional shape is a geometric name in the embodiment in which the two vertexes of the triangle are curved, and various modifications are actually possible .

The above embodiment is characterized in that the flow path becomes narrower as the second flow path 200 moves away from the radial direction of the pipe 10 or the flow path becomes narrower toward the fuel injection opening 30 in the second flow path 200 . The narrowing of the flow path is characterized by the pressure of the fuel and the pressure of the fuel. Bernoulli's principle can be applied that the flow velocity increases as the cross-sectional area of the flow path becomes narrower for the same flow rate, and the flow rate decreases as the cross-sectional area becomes narrower.

According to the conventional technology, when the pressure of the fuel flowing through the first flow path 100 drops to the second flow path 200, the flow rate is slowed. Therefore, sufficient injection and vaporization can be performed in the fuel injection opening 30 A problem that does not occur may occur. However, according to the embodiment of the present invention, as the cross-sectional area of the second flow path 200 gradually decreases, the pressure of the fuel flowing into the second flow path 200 becomes higher, and the flow path near the fuel injection opening 30 becomes narrower The high pressure is maintained and efficient injection and vaporization are achieved through the fuel injection opening 30. [ This is a way to increase the efficiency of gas turbine combustion by increasing the pressure without a separate power source.

FIG. 3 shows various modifications of the second flow path 200 inside the airfoil 20. The embodiment shown in Fig. 3 is the addition of the fillet 300 feature in addition to the embodiment shown in Fig. The second flow path 200 is filled with the fillet 300 with respect to the portion where the second flow path 200 and the first flow path 100 meet, thereby enlarging the sectional area of the portion into which the fuel flows. As a result, the pressure in the vicinity of the inlet of the second flow path 200 becomes lower than that of the fuel passing through the first flow path 100, so that the fuel can flow easily into the second flow path 200. Further, by treating the second flow path 200 with the fillet 300, the boundary between the first flow path 100 and the first flow path 100 is not angled, but is connected with a smooth curved surface to prevent stalling of the fuel. As a result, the fuel can be stably supplied to the second flow path 200, and the supplied fuel can be efficiently injected as the cross-sectional area of the second flow path 200 gradually becomes narrower.

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.

1: Gas turbine combustor
10: tube
20: airfoil
30: Fuel injection opening
100: First Euro
200: the second euro
300: fillet

Claims (22)

tube;
A first flow path formed in the longitudinal direction of the pipe and through which fuel flows;
At least one fuel injection airfoil protruding from the outer circumferential surface of the pipe in a radial direction of the pipe;
A second flow path having a structure in which the fuel flows to the inside of the airfoil, and a cross section cut in the radial direction of the pipe becomes narrower toward an end of the airfoil; And
At least one fuel injection opening provided on the surface of the airfoil, connected to the second flow path, and configured to communicate with a second flow path in a direction at a predetermined angle with an airfoil surface;
Lt; / RTI >
The second flow path may have a polyhedral structure,
The second flow path may have a polygonal cross-sectional shape perpendicular to the radial direction in which the airfoil protrudes, a triangular shape, a curved line between two curved points of the triangle, or a cross- It is a shrinking form,
Wherein a portion where the second flow path and the first flow path meet is a fillet machined portion.
delete delete delete delete delete delete delete delete delete delete delete delete delete delete delete delete delete delete delete delete A gas turbine combustor comprising a gas turbine fuel nozzle according to claim 1.
KR1020150093185A 2015-06-30 2015-06-30 The shape of inner passage of vane KR101852006B1 (en)

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KR102096580B1 (en) * 2019-04-01 2020-04-03 두산중공업 주식회사 Combustion nozzle enhancing spatial uniformity of pre-mixture and gas turbine having the same

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