KR102019091B1 - Fuel nozzle assembly, combustor and gas turbine having the same - Google Patents

Abstract

Fuel nozzle assembly according to an embodiment of the present invention comprises a plurality of fuel nozzles; A cooling cap having a plurality of slots into which a part of each fuel nozzle is inserted, and supporting the fuel nozzle; And a cushioning portion inserted between the joint surface of the fuel nozzle and the slot.
According to the embodiments of the present invention, even if the components of the fuel nozzle are thermally expanded by the high temperature atmosphere of the combustor, they can be accommodated, and there is an effect of damping vibration generated during combustion. Further, according to embodiments of the present invention, the fuel nozzle can be easily detached from the combustor.

Description

FUEL NOZZLE ASSEMBLY, COMBUSTOR AND GAS TURBINE HAVING THE SAME

The present invention relates to a fuel nozzle assembly, a combustor and a gas turbine comprising the same.

The gas turbine is a power engine that mixes and burns compressed air and fuel compressed in a compressor, and rotates the turbine with hot gas generated by combustion. Gas turbines are used to drive generators, aircraft, ships and trains.

Gas turbines generally include compressors, combustors, and turbines. The compressor sucks and compresses the outside air and delivers it to the combustor. The compressed air in the compressor is at high pressure and high temperature. The combustor mixes and combusts compressed air and fuel introduced from the compressor. The combustion gases generated by the combustion are discharged to the turbine. The combustion gas causes the turbine blades inside the turbine to rotate, thereby generating power. The generated power is used in various fields such as power generation and driving of mechanical devices.

Republic of Korea Patent Publication No. 10-2006-0096319 (Name: Can type combustor)

One aspect of the present invention is to provide a fuel nozzle assembly, a combustor and a gas turbine including the same that can minimize the effects of thermal expansion or vibration generated during combustion.

Fuel nozzle assembly according to an embodiment of the present invention comprises a plurality of fuel nozzles; A cooling cap having a plurality of slots into which a part of each fuel nozzle is inserted, and supporting the fuel nozzle; And a cushioning portion inserted between the joint surface of the fuel nozzle and the slot.

In the fuel nozzle assembly according to an embodiment of the present invention, the fuel nozzle comprises: an injection cylinder extending in one direction to supply fuel fluid to the combustion chamber; And a shroud spaced apart from the injection cylinder to surround the injection cylinder in a longitudinal direction and forming a flow path between the inner wall and the injection cylinder. The buffer part can be inserted between the outer circumferential surface of the shroud and the joint surface of the slot.

In the fuel nozzle assembly according to an embodiment of the present invention, the buffer portion may be disposed downstream of the fuel fluid flow direction.

In the fuel nozzle assembly according to an embodiment of the present invention, a plurality of shock absorbing units may be provided in an annular arrangement along the circumference of the shroud.

In the fuel nozzle assembly according to an embodiment of the present invention, the buffer portion is formed of one curved plate, the fixing portion fixed to one side of the two bonding surfaces; It may include; a convex portion protruding toward the other surface from the fixing portion in contact with the other surface.

Here, the buffer portion may include a convex portion that is continuously arranged in the convex portion and protrudes in a direction opposite to the convex portion between the convex portions.

Here, the joining surface in contact with the convex portion may include a recessed portion formed in correspondence with the convex portion.

In the fuel nozzle assembly according to an embodiment of the present invention, the buffer portion may be elastically bonded between the fuel nozzle and the slot.

In the fuel nozzle assembly according to an embodiment of the present invention, the shock absorbing portion may be a coil spring or a leaf spring disposed crosswise to the joint surface.

A combustor according to an embodiment of the present invention includes a combustion chamber assembly including a combustion chamber in which fuel fluid is combusted; And a fuel nozzle assembly for injecting fuel fluid into the combustion chamber. The fuel nozzle assembly includes a plurality of fuel nozzles; A cooling cap having a plurality of slots into which a part of each fuel nozzle is inserted, and supporting the fuel nozzle; And a cushioning portion inserted between the joint surface of the fuel nozzle and the slot.

In the combustor according to an embodiment of the present invention, the fuel nozzle, the injection cylinder is formed extending in one direction for supplying a fuel fluid to the combustion chamber; And a shroud spaced apart from the injection cylinder in a longitudinal direction to form a flow path between the inner wall and the injection cylinder. The buffer part is inserted between the outer peripheral surface of the shroud and the joint surface of the slot.

In the combustor according to an embodiment of the present invention, a plurality of buffer units may be provided in an annular shape along the circumference of the shroud.

In the combustor according to an embodiment of the present invention, the buffer portion is formed of one curved plate, the fixing portion fixed to one side of the two bonding surfaces; And a convex portion protruding from the fixing portion toward the other surface and in contact with the other surface.

In the combustor according to an embodiment of the present invention, the buffer portion includes convex portions arranged contiguously and protruding in a direction opposite to the convex portion between the convex portions.

Gas turbine according to an embodiment of the present invention, a compressor for compressing the incoming air; A combustor for mixing and combusting compressed air and fuel in a compressor; And a turbine for generating power from the gas combusted in the combustor. The combustor may include a combustion chamber assembly including a combustion chamber in which fuel fluid combusts; And a fuel nozzle assembly for injecting fuel fluid into the combustion chamber. The fuel nozzle assembly includes: a plurality of fuel nozzles; A cooling cap having a plurality of slots into which a part of each fuel nozzle is inserted, and supporting the fuel nozzle; And a cushioning portion inserted between the joint surface of the fuel nozzle and the slot.

According to the embodiments of the present invention, even if the components of the fuel nozzle are thermally expanded by the high temperature atmosphere of the combustor, they can be accommodated, and there is an effect of damping vibration generated during combustion. Further, according to embodiments of the present invention, the fuel nozzle can be easily detached from the combustor.

1 is a view showing the inside of a gas turbine according to an embodiment of the present invention.
2 is a view showing a combustor according to an embodiment of the present invention.
3 is a perspective view illustrating a fuel nozzle assembly according to an embodiment of the present invention.
4 is a cross-sectional view of a fuel nozzle assembly according to one embodiment of the present invention taken along cut line AA of FIG. 3.
5 to 8 are enlarged views illustrating region B of FIG. 4.
FIG. 9 is a perspective view illustrating the buffer part illustrated in FIG. 5.
FIG. 10 is a perspective view illustrating the buffer part illustrated in FIG. 6.
11 is a perspective view illustrating a fuel nozzle assembly according to another embodiment of the present invention.
12 to 14 are longitudinal cross-sectional views cut along the cutting line C-C of FIG. 9.

Hereinafter, a fuel nozzle, a combustor and a gas turbine including the same according to the present invention will be described in detail with reference to the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below, but will be implemented in various forms, and only the embodiments are intended to complete the disclosure of the present invention, and to those skilled in the art to fully understand the scope of the invention. It is provided to inform you. Like numbers refer to like elements in the figures.

In addition, throughout the specification, when a part is said to "include" a certain component, it means that it may further include other components, except to exclude other components unless specifically stated otherwise. In addition, throughout the specification, "on" means to be located above or below the target portion, and does not necessarily mean to be located above the gravity direction.

1 is a view showing the interior of a gas turbine according to an embodiment of the present invention, Figure 2 is a view showing a combustor according to an embodiment of the present invention.

1 and 2, the gas turbine according to an embodiment of the present invention is a compressor 10 for compressing the incoming air to a high pressure, a combustor 20 for mixing and burning the compressed air and fuel compressed from the compressor And a turbine 30 generating a rotational force with the combustion gas generated in the combustor. In this specification, the upstream and downstream of the fuel or air flow is defined.

The thermodynamic cycle of the gas turbine can ideally follow the Brayton cycle. The Brayton cycle consists of four processes: isotropic compression (thermal insulation compression), static pressure quenching, isotropic expansion (thermal insulation expansion), and constant pressure heat dissipation. That is, the air is inhaled and compressed to high pressure, and the fuel is combusted in a constant pressure environment to release thermal energy. The high-temperature combustion gas is expanded and converted into kinetic energy, and the exhaust gas containing residual energy is released into the atmosphere. . That is, the cycle consists of four processes: compression, heating, expansion, and heat dissipation. The description of the present invention can also be widely applied to a turbine engine having a configuration equivalent to that of the gas turbine illustrated by way of example in FIG. 1.

Compressor 10 of the gas turbine is a part that sucks air and compresses the air, and supplies combustion air to the combustor 20 while supplying cooling air to a high temperature region requiring cooling in the gas turbine. . Since the sucked air is subjected to adiabatic compression in the compressor 10, the pressure and temperature of the air passing through the compressor 10 are increased.

The compressor 10 constituting the gas turbine may be designed as centrifugal compressors or axial compressors. In a small gas turbine, a centrifugal compressor is applied, whereas a large gas turbine compresses a large amount of air. It is common to apply a multistage axial compressor as shown in FIG.

The compressor 10 is driven using a portion of the power output from the turbine 30. To this end, as shown in FIG. 1, the rotating shaft of the compressor 10 and the rotating shaft of the turbine 30 are directly connected to each other.

The combustor 20 mixes the compressed air supplied from the outlet of the compressor 10 with the fuel and isostatically burns to produce a high energy combustion gas.

The combustor 20 is disposed downstream of the compressor 10 and includes a plurality of burner modules 21 arranged in an annular shape about a rotating shaft. The burner module 21 includes a combustion chamber assembly 22 including a combustion chamber 240 in which fuel fluid combusts; And a fuel nozzle assembly 23 including a plurality of fuel nozzles for injecting fuel fluid into the combustion chamber 240.

Gas turbines and liquid fuels, or combination fuels in combination thereof may be used in the gas turbine, and the fuel fluid in the present invention means them. It is important to create a combustion environment to reduce the amount of emission gas such as carbon monoxide and nitrogen oxide, which are legally regulated. Although combustion control is relatively difficult, it is possible to reduce the emission gas by lowering combustion temperature and making uniform combustion. Many premixed combustion is applied.

In the case of premixed combustion, compressed air and fuel introduced from the compressor 10 in the fuel nozzle assembly 23 are mixed and then enter the combustion chamber 240. The initial ignition of the premixed gas is performed using an igniter, and then combustion is maintained by supplying fuel and air once the combustion is stable.

The fuel nozzle assembly 23 includes a plurality of fuel nozzles 100 for injecting fuel fluid, which enables the fuel to be mixed with air at an appropriate ratio to achieve a state suitable for combustion. The fuel nozzle 100 and the fuel nozzle assembly 23 will be described in detail later.

Combustion chamber assembly 22 includes combustion chamber 240, which is a space where combustion occurs, and includes a liner 250 and a transition piece 260.

The liner 250 is disposed downstream of the fuel nozzle assembly 23 and may have a dual structure of an inner liner and an outer liner. That is, the inner liner may have a double structure in which the outer liner is surrounded. At this time, the inner liner is a hollow tubular member and forms the combustion chamber 240. Compressed air can penetrate into the annular space inside the outer liner to cool the inner liner.

Meanwhile, a transition piece 260 is positioned downstream of the liner 250, and the transition piece 260 may send the combustion gas generated in the combustion chamber 240 to the turbine 30 at high speed. The transition piece 260 may have a dual structure of an inner transition piece and an outer transition piece. That is, the inner transition piece may have a double structure in which the outer transition piece is surrounded. At this time, the inner transition piece is also formed of a hollow tubular member like the inner liner, and may have a shape in which the diameter decreases gradually from the liner 250 toward the turbine 30 side.

At this time, the inner liner and the inner transition piece may be coupled to each other by a plate spring seal (not shown). Since each end of the inner liner and the inner transition piece is fixed to the combustor 20 and the turbine 30, respectively, the plate spring seal has a structure that can accommodate the elongation of the length and diameter due to thermal expansion, and the inner liner and the inner transition. It can support the piece.

The gas turbine according to the present embodiment has a structure in which the inner liner and the inner transition piece surround the outer liner and the outer transition piece, and the annular space between the inner liner and the outer liner and the environmental space between the inner transition piece and the outer transition piece. Compressed air can penetrate inside. Compressed air that penetrates the annular space can cool the inner liner and the inner transition piece.

Meanwhile, the hot and high pressure combustion gas produced by the combustor 20 is supplied to the turbine 30 through the liner 250 and the transition piece 260. In the turbine 30, while the combustion gas is adiabaticly expanded, a collision and reaction force are applied to a plurality of blades radially disposed on the rotation axis of the turbine 30, so that thermal energy of the combustion gas is converted into mechanical energy in which the rotation axis rotates. Part of the mechanical energy obtained from the turbine 30 is supplied to the energy required to compress the air in the compressor, and the rest is used as the effective energy, such as driving the generator to produce power.

Hereinafter, a fuel nozzle assembly according to an embodiment of the present invention will be described with reference to the drawings.

3 is a perspective view illustrating a fuel nozzle assembly according to an embodiment of the present invention. 4 is a cross-sectional view of the fuel nozzle assembly according to the exemplary embodiment of the present invention, taken along cut line A-A of FIG. 3.

3 and 4, the fuel nozzle assembly 23 according to an embodiment includes a plurality of fuel nozzles 100, a cooling cap 200, and a buffer 160.

As illustrated in FIG. 3, the fuel nozzle 100 may have a plurality of external fuel nozzles disposed radially around one internal fuel nozzle.

Each fuel nozzle 100 includes an injection cylinder 110 and a shroud 150.

The injection cylinder 110 is a means for supplying fuel and premixing fuel and air and extending in one direction. The injection cylinder 110 may be generally formed in a cylindrical shape, but is not limited thereto. In the embodiment of the present invention, the injection cylinder 110 is illustrated.

The head end plate 220 is coupled to the nozzle casing 230 at the end of the nozzle casing 230 forming the outer wall of the fuel nozzle assembly 23 to seal the casing 230, supplying fuel to the injection cylinder 110. To a manifold, associated valve, and the like. Head end plate 220 also supports fuel nozzle 100 arranged in nozzle casing 230. The fuel nozzle 100 is fixed to the head end plate 220 by a nozzle flange 140 disposed at one end of the injection cylinder 110.

Fuel flows through the head end plate 220 through a fuel injector (not shown), moves along the longitudinal direction of the injection cylinder 110 of the fuel nozzle 100, and is injected into the combustion chamber 240.

The shroud 150 is formed to be spaced apart from the injection cylinder 110 to surround the injection cylinder 110 in the longitudinal direction, so as to constitute a flow path so that fuel and air can pass. The shroud 150 is formed to extend along the direction in which the injection cylinder 110 extends. Preferably, the shroud 150 is formed to have a concentric axis with the injection cylinder 110 and to be spaced apart from the injection cylinder 110 at a predetermined interval to surround the injection cylinder 110. Can be. In the embodiment of the present invention, a cylindrical shroud 150 is exemplified. In this case, the cross section of the flow path formed by the injection cylinder 110 and the shroud 150 may be formed in an annular shape.

The swirler 120 is radially arranged on the outer circumferential surface of the middle of the injection cylinder 110 so that rotational flow occurs in the fuel fluid introduced into the space between the shroud 150 and the injection cylinder 110. The swirler 120 may communicate with an internal space of the injection cylinder 110 therein to form a flow path. The fuel introduced into the injection cylinder 110 may be injected through an injection hole penetrating the inside and outside of the swirler 120 through a flow path inside the swirler 120 in communication with each other.

The cooling cap 200 supports the fuel nozzle 100, blocks high heat generated during combustion from propagating toward the nozzle, and prevents the fuel nozzle 100 from being damaged by the high heat. In addition, the cooling cap 200 may serve to absorb combustion vibrations generated during combustion. A portion of the cooling cap 200 in contact with the combustion chamber 240 side may be formed of a material having excellent heat dissipation performance and corrosion resistance that can withstand the high temperature atmosphere of the combustion chamber.

The cooling cap 200 may include a plurality of slots 210 into which a part of the fuel nozzle 100 is inserted. The plurality of slots 210 may also be formed to correspond to the arrangement of the fuel nozzle 100 so that the plurality of external fuel nozzles may be disposed radially about one internal fuel nozzle.

5 to 8 are enlarged views illustrating region B of FIG. 4 and illustrate various embodiments of the buffer unit.

The buffer unit 160 may be inserted between the joint surface of the fuel nozzle 100 and the slot 210 to absorb vibrations generated during combustion and to accommodate thermal expansion of the shroud 150.

Since the upstream side of the fuel nozzle 100 is fixed to the head end plate 220 via the nozzle flange 140, the buffer 160 is preferably disposed downstream of the fuel fluid flow direction.

The buffer unit 160 may be provided in plural and may be arranged in an annular shape along the circumference of the shroud 150. Each of the buffer units 160 may be spaced apart from each other at regular intervals. 9 is a perspective view illustrating the buffer unit illustrated in FIG. 5, and FIG. 10 is a perspective view illustrating the buffer unit illustrated in FIG. 6.

As shown in FIGS. 5 and 9, the shock absorbing portion 160a is formed of one curved plate material, and the fixing portion 1601 is fixed to one surface of the joint surface of the shroud 150 and the slot 210. The convex portion 1602 may protrude from the fixing portion 1601 toward the other surface and contact the other surface. When the shroud 150 thermally expands or vibrates during combustion, the deformation amount or the impact may be absorbed by the deformation of the convex portion 1602.

Alternatively, as shown in FIGS. 6 and 10, the shock absorbing portion 160b includes convex portions 1602a, 1602a, 1602b, 1602c..., Which are opposite to the convex portion 1602 between the convex portions 1602. And concave portions 1603: 1603a, 1603b, etc., protruding in the direction. The recesses 1603 may be spaced apart by a predetermined distance d without contacting the joining surface. When the recesses 1603 are spaced in this manner, more deformation or impact can be absorbed.

The shock absorbing portions 160a and 160b are disposed such that the fixing portion 1601 and the convex portion 1602 correspond to the longitudinal direction (up and down directions in FIGS. 5 and 6) of the fuel nozzle 100 or the convex portion 1602. And concave portions 1603 may be disposed to correspond to the longitudinal direction.

The bonding surface contacting the convex portion 1602 may include a recessed portion 165 recessed in correspondence with the convex portion 1602. The recess 165 may be formed in an annular shape on the joining surface of the shroud 150 or the slot 210 in correspondence with the buffer portions 160a and 160b.

The shock absorbing portions 160c and 160d may be elastically bonded between the fuel nozzle 100 and the slot 210 and may be plate springs (see FIG. 7) or coil springs (see FIG. 8) disposed in a cross direction on the joint surface. ) Form. By these elastic deformations, the amount of deformation due to thermal expansion of the shroud 150 or the impact due to vibration can be absorbed.

FIG. 11 is a perspective view illustrating a fuel nozzle assembly according to another exemplary embodiment of the present invention, and FIGS. 12 to 14 are various cross-sectional views cut along the cutting lines C-C of FIG.

As shown in FIGS. 12 to 14, the buffer parts 160e, 160f, and 160g are formed of one curved plate, as shown in FIGS. 5 and 9, and the shroud 150 and the slot 210. The fixing part 1601 is fixed to one side of the bonding surface of, and may include a convex portion 1602 protruding from the fixing part 1601 toward the other surface in contact with the other surface.

5 and 6, the fixing parts 1601 and the convex parts 1602 are disposed in a direction intersecting the longitudinal direction of the fuel nozzle 100, or the convex parts 1602 are different from each other. The recessed portions 1603 may be disposed in a direction crossing the longitudinal direction. In addition, as shown in FIG. 14, the convex portions 1602 and the concave portions 1603 may be formed in an annular shape while being alternately arranged in succession.

In the above description, when joining or bonding (connecting) different elements, separate joining members are provided for joining them. In addition, a separate sealing means may be further added as necessary to prevent leakage at the joint surface. In addition, predetermined protrusions or grooves may be formed in a fitting form for convenience of the coupling process and prevention of leakage.

The embodiments and drawings attached to this specification are merely to clearly show some of the technical ideas included in the present invention, and those skilled in the art can easily infer within the scope of the technical ideas included in the specification and drawings of the present invention. Various modifications and specific embodiments that can be made will be apparent to be included in the scope of the invention.

10: compressor 20: combustor
21: burner module 22: combustion chamber assembly
23 fuel nozzle assembly 30 turbine
100: fuel nozzle 110: injection cylinder
120: Swallower 150: Shroud
160: shock absorber 200: cooling cap
210: slot

Claims (15)

A plurality of fuel nozzles;
A cooling cap having a plurality of slots into which a part of each fuel nozzle is inserted, and supporting the fuel nozzle; And
And a buffer inserted between the fuel nozzle and the joint surface of the slot.
The fuel nozzle,
An injection cylinder extending in one direction to supply fuel fluid to the combustion chamber; And a shroud spaced apart from the injection cylinder in a longitudinal direction to form a flow path between an inner wall and the injection cylinder.
The buffer part is inserted between the outer peripheral surface of the shroud and the bonding surface of the slot,
The buffer portion is formed of one curved plate,
A fixing part fixed to one of the two joining surfaces;
And a convex portion protruding from the fixing portion toward the other surface and in contact with the other surface.
The joining surface in contact with the convex portion includes a recessed portion formed corresponding to the convex portion, wherein the recessed portion is formed in an annular shape on the joining surface corresponding to the plurality of the buffer portion arranged in an annular shape. delete The method of claim 1,
The buffer part,
A fuel nozzle assembly disposed downstream of the fuel fluid flow direction. The method of claim 1,
The shock absorbing portion is provided with a plurality of fuel nozzle assembly arranged in an annular along the circumference of the shroud. delete The method of claim 1,
The buffer part
And the convex portion is continuously arranged, and further comprising a concave portion protruding in the opposite direction to the convex portion between the convex portions. delete The method of claim 1,
And the shock absorbing portion is elastically bonded between the fuel nozzle and the slot. delete A combustion chamber assembly comprising a combustion chamber in which fuel fluid combusts; And
A fuel nozzle assembly for injecting a fuel fluid into the combustion chamber;
The fuel nozzle assembly
A plurality of fuel nozzles;
A cooling cap having a plurality of slots into which a part of each fuel nozzle is inserted, and supporting the fuel nozzle; And
And a buffer inserted between the fuel nozzle and the joint surface of the slot.
The fuel nozzle,
An injection cylinder extending in one direction to supply fuel fluid to the combustion chamber; And a shroud spaced apart from the injection cylinder in a longitudinal direction to form a flow path between an inner wall and the injection cylinder.
The buffer part is inserted between the outer peripheral surface of the shroud and the bonding surface of the slot,
The buffer portion is formed of one curved plate,
A fixing part fixed to one of the two joining surfaces;
And a convex portion protruding from the fixing portion toward the other surface and in contact with the other surface.
And a joining surface in contact with the convex portion includes a recessed portion formed in correspondence with the convex portion, wherein the recess portion is formed in an annular shape on the joining surface corresponding to the plurality of buffer parts. delete The method of claim 10,
And a plurality of shock absorbing units arranged in an annular shape along the circumference of the shroud. delete The method of claim 10,
The buffer part
And a convex portion arranged contiguously with the convex portions, the concave portion protruding in the opposite direction to the convex portion between the convex portions. A compressor for compressing incoming air;
A combustor for mixing and combusting the compressed air and fuel in the compressor; And
And a turbine generating power from the gas burned in the combustor.
The combustor,
A combustion chamber assembly comprising a combustion chamber in which fuel fluid combusts; And
A fuel nozzle assembly for injecting a fuel fluid into the combustion chamber;
The fuel nozzle assembly;
A plurality of fuel nozzles;
A cooling cap having a plurality of slots into which a part of each fuel nozzle is inserted, and supporting the fuel nozzle; And
And a buffer inserted between the fuel nozzle and the joint surface of the slot.
The fuel nozzle,
An injection cylinder extending in one direction to supply fuel fluid to the combustion chamber; And a shroud spaced apart from the injection cylinder in a longitudinal direction to form a flow path between an inner wall and the injection cylinder.
The buffer part is inserted between the outer peripheral surface of the shroud and the bonding surface of the slot,
The buffer portion is formed of one curved plate,
A fixing part fixed to one of the two joining surfaces;
And a convex portion protruding from the fixing portion toward the other surface and in contact with the other surface.
The joining surface in contact with the convex portion includes a recessed portion formed in correspondence with the convex portion, wherein the recess portion is formed in an annular shape on the joining surface corresponding to the plurality of the buffer portion arranged in a gas turbine.

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