KR20190055920A - Burner Having Transition Piece Supporting Member, And Gas Turbine Having The Same - Google Patents

Abstract

Provided are a combustor of a gas turbine engine including a transition piece support unit, and a gas turbine including the same. An embodiment of the present invention provides the combustor, including: a combustion unit combusting a fuel to generate high temperature compressed gas; and a transition piece inducing the high temperature compressed gas generated by the combustion unit into a turbine, wherein the rear end of the transition piece is coupled to the front end of the turbine, the front end of the transition piece is an outer surface of a compressor casing by the transition support unit and the transition piece support unit concurrently supporting two adjacent transition pieces. The present invention provides a combustor and gas turbine including the same which can stably support the transition piece even though an installation space is narrow and can stably support the transition piece by external force due to thermal deformation.

Description

[0001] The present invention relates to a combustor of a gas turbine engine including a transition piece support, and a gas turbine including the transition piece supporting member,

The present invention relates to a combustor and a gas turbine including the same.

The thermodynamic cycle of a gas turbine engine ideally follows the Brayton cycle. The Breton cycle consists of four processes leading to isentropic compression (adiabatic compression), constant pressure heat radiation, isentropic expansion (adiabatic expansion), and static pressure heat radiation. In other words, after sucking the air in the air and compressing it to a high pressure, the fuel is burned in a constant pressure environment to release heat energy, and the high temperature combustion gas is expanded to kinetic energy, and then the exhaust gas containing residual energy is discharged to the atmosphere . That is, the cycle is performed in four steps of compression, heating, expansion, and heat radiation.

A gas turbine engine that realizes the above-mentioned Brayton cycle includes a compressor, a combustor, and a turbine. 1 is a view schematically showing the overall configuration of a gas turbine engine 1000. As shown in FIG. Although the following description refers to Fig. 1, the description of the present invention can be widely applied to a turbine engine having a configuration equivalent to that of the gas turbine engine 1000 exemplarily shown in Fig.

The compressor 1100 of the gas turbine engine 1000 functions to suck and compress air and supplies combustion air to the combustor 1200 while cooling the gas turbine engine 1000 in a high- The main role is to supply air. The sucked air is adiabatically compressed in the compressor 1100, so that the pressure and the temperature of air passing through the compressor 1100 are increased.

The compressor 1100 included in the gas turbine engine 1000 is usually designed as a centrifugal compressor or an axial compressor while a centrifugal compressor is applied in a small gas turbine engine, Since the gas turbine engine 1000 has to compress a large amount of air, it is common that a multi-stage axial compressor 1100 is applied. The rotary shaft of the compressor 1100 and the rotary shaft of the turbine 1300 are directly connected to each other so that the compressor 1100 is driven using a part of the power output from the turbine 1300.

The combustor 1200 mixes the compressed air supplied from the outlet of the compressor 1100 with the fuel and burns the compressed air at a constant pressure to produce a combustion gas of high energy. 2 shows an example of a combustor 1200 provided in the gas turbine engine 1000. As shown in FIG. The combustor 1200 is disposed downstream of the compressor 1100 and a plurality of burners 1220 are disposed along the annular combustor casing 1210. Each of the burners 1220 is provided with several combustion nozzles 1230. The fuel injected from the combustion nozzles 1230 is mixed with air in an appropriate ratio to be in a state suitable for combustion.

The combustor 1200 requires the proper cooling because it is the hottest environment in the gas turbine engine 1000. Referring to FIG. 2, a duct assembly 1250 connecting the burner 1220 and the turbine 1300 with a high-temperature combustion gas flow, that is, a tube assembly 1250 comprising a transition piece 1260 and a flow sleeve 1270, The compressed air flows along the outer surface of the combustion nozzle 1230 and is supplied to the combustion nozzle 1230. During the course of the compressed air moving along the outer surface of the tube assembly, the heated duct assembly is suitably cooled by the hot combustion gases.

2. Description of the Related Art Generally, a plurality of combustors constituting a combustion system of a gas turbine are arranged in a casing formed in a cell shape, and each combustor includes a combustion section for burning fuel to generate a high-temperature compressed gas, And a transition piece (a transition piece) that directs the gas to the turbine.

The combustion section is fixed to the casing by a bracket or the like, and the rear end portion of the transition piece is engaged with the front end portion of the turbine.

Conventionally, however, a support device for a transition piece of a gas turbine has been coupled and supported by a bolt, welding, or the like, to a front end portion of a turbine through a sealing member or the like.

In order to firmly mount the transition piece supporting device according to the prior art on the front end of the turbine, as shown in Fig. 3, a structure in which a plurality of members are combined is adopted. For this reason, the support device of the transition piece is relatively bulky, making it very difficult to be mounted in a narrow space.

Furthermore, the conventional apparatus for supporting a transition piece of a gas turbine is capable of actively and continuously controlling the temperature of the transition piece when the high temperature compressed gas generated in the combustion section of the turbine flows through the transition piece and flows into the turbine, There is a problem that it can not cope.

In addition, the support device for the transition piece of the conventional gas turbine has a problem in that a high-temperature compressed gas can flow out as the rear end of the transition piece and the front end of the turbine are separated from each other by thermal expansion and contraction.

Furthermore, in the conventional support device for a transition piece of a gas turbine, the parts of the supporting part and the connecting part are damaged by the thermal expansion, thereby increasing the maintenance cost.

Therefore, as described above, there is a need for a technique capable of solving the problems of the prior art.

Korean Patent Laid-Open Publication No. 10-2017-0008394 (published Jan. 24, 2017)

The present invention provides a combustor including a structure capable of stably supporting a transition piece even when a space to be installed is small and stably supporting a transition piece by an external force due to thermal deformation, and a gas turbine including the same .

A combustor according to an embodiment of the present invention includes a combustion unit for combusting fuel to generate a high temperature compressed gas and a transition piece for guiding the high temperature compressed gas generated in the combustion unit to the turbine, The rear end of the piece is engaged with the front end of the turbine, and the front end of the transition piece is coupled by the outer surface of the compressor casing and the transition piece support. The transition piece support part simultaneously supports two transition pieces have.

In one embodiment of the present invention, a sliding groove having a structure extending a predetermined length in a direction parallel to the extending direction of the transition piece is formed on the outer peripheral surface of the front end portion of the transition piece, and at one end of the transition piece supporting portion, A protrusion having a structure corresponding to the sliding groove can be formed.

In this case, the projection may be a structure capable of changing its position along the sliding groove by thermal deformation of the transition piece.

In addition, the transition piece support portion can maintain a distance between the front end of the transition piece and the outer surface of the compressor casing at a predetermined distance.

In one embodiment of the present invention, the sliding groove is a " C " -shaped structure in which the opening surface faces sideways, and the projection may be a "? &Quot; structure on the section toward the opening surface of the sliding groove.

In addition, the sliding groove is a " P " -shaped structure having a downwardly directed opening face, and the projection may have an " I " shape in a cross section facing the opening surface of the sliding groove.

In addition, the sliding groove may be a " C " -shaped structure having a side face oriented toward the side, and the projection may be an " i " -shaped structure on the section toward the opening face of the sliding groove.

A combustor according to an embodiment of the present invention includes a combustion section for combusting fuel to generate a high temperature compressed gas and two or more transition pieces for introducing a high temperature compressed gas generated in the combustion section to the turbine, Both side surfaces of the adjacent transition pieces may be coupled to each other by a transition piece support portion and the transition piece support portion may be coupled to a fixed support portion having a structure extending from a side of the compressor casing by a predetermined height.

In this case, the fixed support portion may have a structure extending from the outer circumferential surface of the outer cylinder of the compressor diffuser by a predetermined height.

The transition piece supporting part may be integrally formed with the fixed supporting part.

In one embodiment of the present invention, the transition piece support portion and the stationary support portion may form a " Y "

According to an embodiment of the present invention, the transition piece may have sliding grooves formed on both sides of the transition piece so as to extend by a predetermined length in a direction parallel to the extension direction of the transition piece. At both ends of the transition piece supporting portion, A protrusion having a structure corresponding to the protrusion can be formed.

In this case, the projection may be a structure capable of changing its position along the sliding groove by thermal deformation of the transition piece.

In one embodiment of the present invention, the sliding groove is a " C " -shaped structure in which the opening surface faces sideways, and the projection may be a "? &Quot; structure on the section toward the opening surface of the sliding groove.

In addition, the sliding groove is a " P " -shaped structure having a downwardly directed opening face, and the projection may have an " I " shape in a cross section facing the opening surface of the sliding groove.

In addition, the sliding groove may be a " C " -shaped structure having a side face oriented toward the side, and the projection may be an " i " -shaped structure on the section toward the opening face of the sliding groove.

The present invention can also provide a gas turbine including the combustor.

According to the embodiment of the present invention, by arranging the transition piece support portion having a specific structure at a specific position, the transition piece can be stably supported even when the installation space is narrow, and the transition piece can be stably It is possible to provide a combustor including a structure capable of supporting a gas turbine and a gas turbine including the combustor.

According to still another aspect of the present invention, since the transition piece support is provided between the transition pieces so as to simultaneously support two adjacent transition pieces, it is possible to stably support the transition piece even when the installation space is narrow have.

Further, according to another embodiment of the present invention, a sliding groove having a specific structure is formed on the outer circumferential surface of the transition piece, a protrusion having a structure corresponding to the sliding groove is formed at one end of the transition piece support portion, The position of the projection along the sliding groove can be changed naturally even if the length of the transition piece is changed by the thermal deformation, so that the transition piece can be stably supported even in the thermally deformed state.

According to still another aspect of the present invention, sliding grooves having various structures are formed on the outer circumferential surface of the transition piece, and protrusions corresponding to the sliding grooves are formed on one end of the transition piece support portion, It is easy to assemble and disassemble.

1 is a perspective view showing the overall structure of a gas turbine engine according to the prior art.
FIG. 2 is a cross-sectional view showing only a combustor portion in the gas turbine engine shown in FIG. 1; FIG.
3 is a partially enlarged perspective view showing a combustor and a transition piece support according to the prior art.
4 is a cross-sectional view illustrating a combustor according to an embodiment of the present invention.
5 is a cross-sectional schematic diagram illustrating a combustor and a transition piece support according to an embodiment of the present invention.
6 is a cross-sectional schematic diagram illustrating a combustor and a transition piece support according to another embodiment of the present invention.
7 is a cross-sectional schematic diagram illustrating the structure of a sliding groove and a projection according to an embodiment of the present invention.
8 is a schematic cross-sectional view showing a structure of a sliding groove and a projection according to another embodiment of the present invention.
9 is a schematic cross-sectional view illustrating the structure of a sliding groove and a projection according to another embodiment of the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

In describing the embodiments of the present invention, a description of well-known structures that can be easily understood by those skilled in the art will be omitted so as not to obscure the gist of the present invention. In the drawings, like reference numerals refer to like elements throughout. The same elements will be denoted by the same reference numerals even though they are shown in different drawings. Referring to the drawings, The size of the elements, etc., may be exaggerated for clarity and convenience of explanation.

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; coupled " or " connected " indirectly while intervening in the context of the present invention.

FIG. 4 is a cross-sectional view illustrating a combustor according to an embodiment of the present invention. FIG. 5 is a schematic cross-sectional view illustrating a combustor and a transition piece support according to an embodiment of the present invention. Sectional view illustrating a combustor and a transition piece support according to another embodiment of the present invention.

Referring to these figures, the combustor 100 according to the present embodiment includes a combustion section 101 for generating a high-temperature compressed gas by burning fuel, and a high-temperature compressed gas generated in the combustion section 101 to a turbine And a transition piece (102) to which the transition piece (102) is connected.

Concretely, the liner 107 is bound to the front end of the transition piece 102, and the burner 101 having the combustion nozzle 106 is disposed at the front end thereof.

The rear end of the transition piece 102 of the combustor 100 according to the present embodiment is coupled to the front end of the turbine and the front end of the transition piece 102 is coupled to the outer surface of the compressor casing 103 and the transition piece support portion 110 do.

At this time, the transition piece support unit 110 according to the present embodiment can simultaneously support two transition pieces 102 disposed adjacent to each other.

The combustion apparatus 100 according to the present embodiment can stably support the transition piece even when the space to be installed is narrow by disposing the transition piece support portion 110 having a specific structure at a specific position, It is possible to provide a combustor including a structure capable of stably supporting a transition piece and a gas turbine including the same.

Hereinafter, each constitution of the combustor 100 according to the present embodiment will be described in detail with reference to the drawings.

FIG. 7 is a schematic cross-sectional view illustrating the structure of a sliding groove and a projection according to an embodiment of the present invention, and FIG. 8 is a sectional schematic view showing a structure of a sliding groove and a projection according to another embodiment of the present invention. And FIG. 9 is a schematic cross-sectional view illustrating a structure of a sliding groove and a projection according to another embodiment of the present invention.

5 and 7, the transition piece 102 according to the present embodiment is provided with a sliding groove 104 (see Fig. 5) having a structure extending by a predetermined length in a direction parallel to the extending direction of the transition piece 102 May be formed. At this time, a protrusion 111 having a structure corresponding to the sliding groove 104 may be formed at one end of the transition piece support portion 110. In this case, the protrusion 111 is engaged with and fixed to the sliding groove 104, so that the transition piece 102 can be stably fixed at a specific position.

In some cases, when the thermal deformation of the transition piece 102 occurs, the transition piece 102 changes its length in the extended longitudinal direction, at which time the protrusion 111 is displaced along the sliding groove 104. As a result, even if the transition piece 102 is changed in length by thermal deformation, the transition piece support 110 according to the present embodiment can stably support the transition piece 102.

As shown in Figs. 5 and 7, the protrusion 111 is not particularly limited as long as the protrusion 111 can be engaged with the sliding groove 104 to be slidably moved. For example, as shown in Fig. 7, Quot; C " structure in which the opening faces toward the side of the sliding groove 104, and the projection 111 may have a "? &Quot;

As shown in FIG. 8, the sliding groove 104 is a " P " -shaped structure having a downwardly directed opening face, and the projection 111 is an " I " have.

9, the sliding groove 104 is a " C " -shaped structure in which the opening faces sideways, and the projection 111 has a cross section " i &Quot;

It is a matter of course that the sectional structure of the sliding groove 104 and the projection 111 can be appropriately changed according to the designer's intention.

Meanwhile, the combustor 100 according to the present embodiment may be configured to include a transition piece support portion 110 and a stationary support portion 120 having a specific structure, as shown in FIG.

Specifically, both side surfaces of the adjacent transition pieces 102 can be bound to each other by the transition piece supporting portion 110. [ At this time, the transition piece support part 110 may be coupled to the fixed support part 120 having a structure extending from the one side of the compressor casing 103 by a predetermined height.

More specifically, the fixed support 120 according to the present embodiment may have a structure extending from the outer circumferential surface of the outer cylinder of the compressor diffuser by a predetermined height.

In this case, it is preferable that the transition piece supporting part 110 is integrally formed with the fixed supporting part 120.

The transition piece support portion 110 and the stationary support portion 120 according to the present embodiment can form a " Y " character structure on the side surface as shown in Fig.

Such a structure can maintain the separation distance between the adjacent transition pieces and can absorb the external force due to lateral vibration and deformation of the transition piece 102 and consequently to ensure the structural stability of the transition piece 102 can do.

In addition, when a damping structure (not shown) capable of buffering the longitudinal external force of the length changing structure (not shown) or the fixed supporting portion 120 capable of changing the length of the fixed supporting portion 120 is further provided, It is possible to absorb the external force due to the vertical vibration and deformation of the transition piece 102, and consequently the structural stability of the transition piece 102 can be further ensured.

The present invention can also provide a gas turbine including the compressor according to the above-mentioned present invention, and more particularly to a gas turbine including a structure capable of reducing the stress applied to the compressor while improving the flow characteristics of the compressed air A turbine can be provided.

It will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit of the invention as set forth in the appended claims. The present invention can be variously modified and changed by those skilled in the art, and it is also within the scope of the present invention.

1000: gas turbine according to the prior art
1100: Compressor
1200: Combustor
1300: Turbine
100: Combustor
101: Combustion part
102: Transition piece
103: compressor casing
104: Sliding groove
105: Outer cylinder of compressor diffuser
106: Combustion nozzle
107: Liner
110: Transition piece support
111: projection
120: Fixed support

Claims (17)

A combustor (100) comprising a combustion section (101) for burning fuel to generate a high temperature compressed gas and a transition piece (102) for guiding the high temperature compressed gas produced in the combustion section (101)
The rear end portion of the transition piece 102 is engaged with the front end portion of the turbine,
The front end of the transition piece 102 is bound by the outer surface of the compressor casing 103 and the transition piece supporting portion 110,
Wherein the transition piece support part (110) simultaneously supports two adjacent transition pieces (102).
The method according to claim 1,
Sliding grooves 104 and protrusions 111 having a structure corresponding to each other are formed at the outer peripheral surface of the distal end portion of the transition piece 102 or one end portion of the transition piece support portion 110,
The sliding groove 104 is extended by a predetermined length in a direction parallel to the extending direction of the transition piece 102,
And the protrusion (111) has a structure corresponding to the sliding groove (104).
3. The method of claim 2,
Wherein the protrusion (111) is positionable along the sliding groove (104) by thermal deformation of the transition piece (102).
The method of claim 3,
Wherein the transition piece support part (110) maintains a distance between a front end of the transition piece (102) and an outer surface of the compressor casing (103) at a predetermined distance.
3. The method of claim 2,
The sliding groove 104 is a " C " -shaped structure in which the opening faces sideways,
Characterized in that the projection (111) has a " B " structure on the cross section facing the opening surface of the sliding groove (104).
3. The method of claim 2,
The sliding groove (1040) has a "?&Quot; character structure in a section with its opening face facing downward,
Wherein the projections (111) have an " I " -shaped structure on a section toward the opening surface of the sliding groove.
3. The method of claim 2,
The sliding groove 104 has a " C "
Wherein the projections (111) have an " i " -shaped structure on the cross section facing the opening surface of the sliding groove.
A combustor (100) comprising a combustion section (101) for burning fuel to generate a high temperature compressed gas and two or more transition pieces (102) for guiding the high temperature compressed gas produced in the combustion section (101) to a turbine ,
Both side surfaces of the adjacent transition piece 102 are bound together by a transition piece support 110,
Wherein the transition piece support part (110) is engaged with a fixed support part (120) having a structure extended from a side of the compressor casing (103) by a predetermined height.
9. The method of claim 8,
Wherein the fixed support part (120) has a structure extending from the outer circumferential surface of the outer cylinder of the compressor diffuser by a predetermined height.
9. The method of claim 8,
Wherein the transition piece support part (110) is formed integrally with the fixed support part (120).
11. The method of claim 10,
Wherein the transition piece support part (110) and the stationary support part (120) form a " Y "
9. The method of claim 8,
On both sides of the transition piece 102, a sliding groove 104 having a structure extending by a predetermined length in a direction parallel to the extension direction of the transition piece 102 is formed,
Wherein a projection (111) having a structure corresponding to the sliding groove (104) is formed at both ends of the transition piece supporting part (110).
13. The method of claim 12,
Wherein the protrusion (111) is positionable along the sliding groove (104) by thermal deformation of the transition piece (102).
13. The method of claim 12,
The sliding groove 104 is a " C " -shaped structure in which the opening faces sideways,
Characterized in that the projection (111) has a " B " structure on the cross section facing the opening surface of the sliding groove (104).
13. The method of claim 12,
The sliding groove 104 has a " P " -perpendicular structure in a section where the opening faces downward,
Characterized in that the projection (111) has an " I " -shaped structure on the cross section facing the opening surface of the sliding groove (104).
13. The method of claim 12,
The sliding groove 104 has a " C "
Characterized in that the projection (111) has an " i " -shaped structure on the cross section facing the opening surface of the sliding groove (104).
A gas turbine comprising a combustor (100) according to any one of claims 1 to 16.

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