KR20170014902A - Gas turbine combustor - Google Patents

Gas turbine combustor Download PDF

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Publication number
KR20170014902A
KR20170014902A KR1020150108925A KR20150108925A KR20170014902A KR 20170014902 A KR20170014902 A KR 20170014902A KR 1020150108925 A KR1020150108925 A KR 1020150108925A KR 20150108925 A KR20150108925 A KR 20150108925A KR 20170014902 A KR20170014902 A KR 20170014902A
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KR
South Korea
Prior art keywords
transition piece
plate
convex portion
gas turbine
support
Prior art date
Application number
KR1020150108925A
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Korean (ko)
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KR101860984B1 (en
Inventor
허영석
Original Assignee
두산중공업 주식회사
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Priority to KR1020150108925A priority Critical patent/KR101860984B1/en
Publication of KR20170014902A publication Critical patent/KR20170014902A/en
Application granted granted Critical
Publication of KR101860984B1 publication Critical patent/KR101860984B1/en

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    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • 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
    • F05D2240/90—Mounting on supporting structures or systems

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

Abstract

A gas turbine combustor is disclosed. A gas turbine combustor according to an embodiment of the present invention includes a liner provided inside a casing forming the outside of a combustor and forming a combustion chamber; A transition piece connected to a rear end of the liner; And a transition piece supporter provided outside the transition piece, wherein the transition piece supporter includes a pair of fixed plates symmetrically fixed on an outer circumferential surface of the transition piece, and a pair of movable plate pieces inserted in the fixed plate and slidable in the fixed plate An inserted connection plate, and a support extending outside the transition piece after being connected to the connection plate, respectively.

Description

GAS TURBINE COMBUSTOR [0002]

The present invention relates to a gas turbine combustor, and more particularly, to a gas turbine combustor having a structure capable of compensating thermal expansion of a transition piece provided in a gas turbine combustor.

A typical gas turbine is composed of a compressor that sucks outside air and compresses it to a high pressure, a combustor that mixes and combusts the fuel and compressed air, and a turbine that generates power by using the exhaust gas obtained from the combustor.

In one form of the combustion system of the gas turbine, a cylindrical combustor is radially provided on the outer circumferential surface of the cylindrical belt. Further, there is provided a casing for introducing compressed air, a liner fixed to the inner wall of the casing so as to be spaced apart from the inner wall, and a fuel mixing device for mixing fuel and air at the tip of the liner.

The fuel flows into the liner through the fuel nozzle unit. The fuel is mixed with the primary air introduced into the swirl furnace, and is ignited by the ignition means and burned.

The transition piece is connected to the rear end of the liner. When the transition piece is heated by the combustion gas and is thermally expanded, the connection part between the liner and the transition piece may be broken. Also, The vibration problem occurs.

(Patent Document 1) US2014 / 0260277A

An embodiment of the present invention is to provide a gas turbine combustor having a structure capable of compensating thermal expansion generated in a transition piece of a gas turbine combustor.

In order to achieve the above-mentioned object, there is provided a liner comprising: a liner provided inside a casing forming the outside of a combustor and forming a combustion chamber; A transition piece connected to a rear end of the liner; And a transition piece supporter provided outside the transition piece, wherein the transition piece supporter includes a pair of fixed plates symmetrically fixed on an outer circumferential surface of the transition piece, and a pair of movable plate pieces inserted in the fixed plate and slidable in the fixed plate An inserted connection plate, and a support extending outside the transition piece after being connected to the connection plate, respectively.

The pair of fixing plates are independently disposed on the left and right sides of the transition piece, and are spaced apart from each other in the vertical direction, and the connecting plate inserted into the spacing fixing plate is held in a plate- .

The support base includes a first support member extending outwardly from the connection plate and extending in a rounded state while being spaced apart from an outer peripheral surface of the transition piece; And a second support member fixed to the lower side of the first support member and extending outwardly.

Wherein the support is elastically deformed by an external force.

The fixing plate is spaced apart from the fixing plate such that a predetermined gap is maintained, and a concave groove is formed on the inner side of the facing fixing plate, and convex portions that can be fitted in the groove are provided on the connecting plate.

And the width (a) of the groove portion is larger than the width (b) of the convex portion.

Wherein the mutually facing surfaces of the fixing plate are formed on the outermost surface excluding the section where the convex portions are arranged and have a flat shape; And a second surface which is parallel to the first surface and is provided inside the first surface to form the groove.

And the second surface extends flat.

And an inclined portion extending between the first surface and the second surface, the inclined portion extending obliquely toward the second surface from the first surface.

And the convex portion has a convex curved shape.

And the convex portion is shaped so as to protrude from both sides of the connecting plate.

And the convex portion is slidable in the width direction and the longitudinal direction of the second surface between the second surfaces.

According to the gas turbine combustor according to the embodiment of the present invention, since the transition piece supporting part can compensate the expansion of the transition piece by the heating by the flame, breakage of the transition piece is prevented.

In addition, due to the sliding structure of the transition piece supporting part, the thermal expansion of the transition piece can be compensated and the vibration generated in the transition piece can be attenuated.

1 is a schematic side view of a gas turbine combustor in accordance with an embodiment of the present invention;
Fig. 2 is a perspective view showing a support table provided in a transition piece. Fig.
Figure 3 is a front view of Figure 2;
Fig. 4 is a detailed view of the transition piece support portion in the coupled state in Fig. 2; Fig.
Fig. 5 is a detailed view of the transition piece supporting portion in the separated state in Fig. 2; Fig.
6 is a schematic front view of a gas turbine combustor in accordance with another embodiment of the present invention.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings, which will be readily apparent to those skilled in the art. The present invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. In order to clearly explain the present invention in the drawings, parts not related to the description are omitted.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The singular expressions may include plural expressions unless the context clearly dictates otherwise.

In this specification, the terms "comprise", "comprising", and the like are used interchangeably to designate the presence of stated features, integers, steps, operations, elements, components, or combinations thereof, But do not preclude the presence or addition of features, numbers, steps, operations, components, parts, or combinations thereof.

Also, unless otherwise defined, all terms used herein, including technical or scientific terms, may have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs . Terms such as those defined in commonly used dictionaries can be interpreted as having a meaning consistent with the meaning in the context of the related art and, unless explicitly defined herein, are interpreted in an ideal or overly formal sense .

In addition, the following embodiments are provided so as to explain the invention more clearly to those skilled in the art. The shapes and sizes of the elements in the drawings may be exaggerated for clarity.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, the present invention will be described in detail with reference to the accompanying drawings.

1 is a schematic side view of a gas turbine combustor according to an embodiment of the present invention, FIG. 2 is a perspective view showing a support member installed on a transition piece, FIG. 3 is a front view of FIG. 2, FIG. 5 is a detailed view of the transition piece support portion in the separated state in FIG. 2; FIG.

1 to 5, the gas turbine combustor 100 according to an embodiment of the present invention is provided for use in a gas turbine engine used in a power plant or the like. The gas turbine compresses air with a compressor and directs compressed air to the combustion chamber, which injects and burns fuel in the combustion chamber. High-temperature / high-pressure gas generated during combustion is blown into the turbine while expanding to rotate the turbine. The gas turbine combustor 100 includes a liner 120, a transition piece 130, and a transition piece support 160, and the casing 110 is configured to surround the outside of the combustor. For reference, the casing 110 is shown in Fig.

The casing 110 is a portion that forms an appearance in the gas turbine combustor 100, and is made of a material resistant to high temperature and high pressure and resistant to corrosion. example In the example The casing 110 Approximately Made of a cylindrical shape, a transition, which will be described later (130) And a cylindrical shape surrounding the outer side .

A fuel injection nozzle 150 through which fuel is injected is coupled to one side of the casing 110 and an air inflow portion (not shown) through which combusting air flows into the other side of the casing 110. The fuel injection nozzle 150 is for injecting fuel into the combustion chamber in the liner 120.

The liner 120 is installed inside the casing 110 and is provided to form a combustion chamber of a flame. The liner 120 according to the present embodiment has a cylindrical shape. The liner 120 forms a combustion chamber of a flame ignited by the combustion and combustion air therein. The liner 120 is A casing (110) and a casing Coaxially disposed, and forms a casing (110) and the liner (not shown), the flow area for the flow of combustion air between 120.

The liner 120 is formed to have a smaller volume than the casing 110 and is coaxially coupled to the casing 110 inside the casing 110. A transition piece 130 is connected to the downstream portion of the liner 120, and flows toward the turbine at high speed through the transition piece.

The transition piece supporter 160 is installed on the outer side of the transition piece 130 in a state where the liner 120 is inserted into the transition piece 130, In order to achieve stable support in accordance with the present invention.

The transition piece support unit 160 includes a pair of fixed plates 163a and 163b symmetrically fixed on the outer circumferential surface of the transition piece 130 and a pair of fixed plates 163a and 163b inserted into the fixed plates 163a and 163b, And a supporter 161 extending outside the transition piece 130 after the connection plate 167 is connected to the connection plate 167.

The fixing plates 163a and 163b are fixed in a symmetrical state on the left and right sides of the transition piece 130 with reference to the drawing and are moved relative to the supporting table 161. The fixing plates 163a, The connecting plate 167 inserted into the spaced fixed plates 163a and 163b is inserted into the plate 130 in a state of being inserted in a plate shape maintain.

Since the fixing plates 163a and 163b are formed in a rectangular parallelepiped shape and extend a predetermined length in the axial direction of the transition piece 130 and the connecting plate 167 is inserted between the fixing plates 163a and 163b, 130, the fixing plates 163a, 163b are moved in the axial direction with respect to the connecting plate 167, and vibration and shock are minimized through movement due to rapid thermal expansion.

The fixing plates 163a and 163b are spaced apart from each other such that a predetermined gap is maintained and are formed with concave grooves 170 inwardly facing the fixing plates 163a and 163b. And the connecting portion 167 is provided with a portion 169.

The connection plate 167 is formed with a convex portion 169 at a portion inserted into the fixing plates 163a and 163b. The convex portion 169 may be formed as a vertically symmetrical hemispherical shape, for example.

The convex portion 169 is configured to protrude from both sides of the connecting plate 167 in the middle portion of the connecting plate 167 and the convex portion 169 has a predetermined width b .

The mutually facing surfaces of the fixing plates 163a and 163b are formed on the outermost surface except the section where the convex portion 169 is disposed and the first surface 164 and the first surface 164, And a second surface 165 formed on the inner side of the first surface 164 to form the groove 170. In this embodiment, the second surface 165 has a substantially flat shape and has a predetermined width a. An inclined portion 166 having a predetermined angle? Is provided between the first surface 164 and the second surface 165.

Since the width b of the convex portion 169 is smaller than the width a of the second surface 165 of the opposing plates 163a and 163b, The first surface 165 may be slidable in the width and length direction of the second surface 165. That is, it can slide forward, backward and left and right with reference to the drawing. Here, the width a of the groove portion is larger than the width b of the convex portion in order to stably slide the convex portion 169.

2, the convex portion 169 of the connecting plate 167 does not protrude from the opposing plates 163a, 163b even if the transition piece 130 thermally expands in the longitudinal direction x and the radial direction y, for example, The thermal expansion of the transition piece 130 can be compensated for by being slidably moved between the second surface 165 of the transition piece 130a and the second surface 165b of the transition piece 130b. Further, the vibration caused by the flow of the flame and the thermal expansion of the combustor can be reduced. In this case, since the second surface 165 has a flat structure, the convex portion 169 of the connecting plate 167 can be sufficiently slidable.

The support base 161 includes a first support base 161a that extends outward from the connection plate 167 and is extended from the outer periphery of the transition piece 130 so as to be rounded, And a second support part 161b extending outward after being fixed to the lower side of the first support part 161a.

The first support base 161a is formed in a U-shape after extending outward from the connection plate 167. In this case, even if stress concentration is locally generated while the transition piece 130 is moved in the axial direction, It is possible to minimize breakage and deformation of the bushing 161 and prevent fatigue breakdown due to long-term use.

The second support base 161b is fixed to the center of the lower end of the first support base 161a and then extends outwardly. The extended end of the second support base 161b is fixed to a main body casing (not shown) surrounding the transition piece 130.

The support base 161 may be configured to be elastically deformed by an external force. In this case, breakage and deformation due to abrupt vibration and impact can be minimized, which is advantageous for long-term use.

In this case, the support table 161 may compensate for vibration and volumetric expansion due to thermal expansion of the transition piece 130, or may be made of a non-elastic material for increasing rigidity.

The distance c between the grooves of the pair of fixing plates 163a and 163b is designed to be slightly smaller than the width b of the convex portion 169 of the connecting plate 167, In the initial installation, the connecting plate 167 is sandwiched between the pair of fixing plates 163a and 163b and can be supported without a gap.

The convex portion 169 of the arc plate 167 of the connecting plate 167 contacts with the fixing plates 163a and 163b due to the sharp portion when the inclined portion 166 is provided on the pair of the fixing plates 163a and 163b It is possible to prevent damage.

According to the gas turbine combustor of the above-described embodiment, the transition piece support 160 can compensate for the expansion of the transition piece 130 by the heating by the flame, and the transition piece 130 and the combustor casing are cracked cracks or the like can be prevented. In addition, due to the sliding structure of the transition piece supporter 160, the thermal expansion of the transition piece can be compensated and the vibration can be reduced.

Hereinafter, a gas turbine combustor according to another embodiment of the present invention will be described with reference to FIG.

Referring to FIG. 6, the illustrated gas turbine combustor 101 is provided for use in a gas turbine engine used in a power plant or the like. In comparison with the gas turbine combustor 100 according to the above-described embodiment, Only the transition piece supporting portion will be described in detail below.

As shown in the gas turbine combustor 101 according to the present embodiment, the structure of the pair of fixing plates 163a and 163b and the connecting plate 167 is the same as that of the above-described embodiment. However, in this embodiment, the transition piece supporting portions are provided on both sides of the transition piece 130, and each of the transition piece supporting portions includes a pair of fixing plates 163a and 163b and a plate-like connecting plate 167. [

One end of each of the pair of fixing plates 163a and 163b is fixed to the outer surface of the transition piece 130 and is arranged to face each other in parallel.

The plate-shaped connecting plate 167 has one end fixed to the inside of the casing 110 and the other end positioned between the pair of fixing plates 163a and 163b so as to be slidable.

The configuration of the pair of fixing plates 163a and 163b and the connecting plate 167 is the same as that of the above-described embodiment, and thus a detailed description thereof will be omitted.

The gas turbine combustor 101 according to the present embodiment also compensates the thermal expansion of the transition piece 130 by sliding the connection plate 167 between the pair of fixed plates 163a and 163b even if the transition piece 130 thermally expands. can do. Further, the vibration generated by the flow of the flame and the thermal expansion of the combustor can be controlled.

It will be understood by those skilled in the art that the foregoing description of the present invention is for illustrative purposes only and that those of ordinary skill in the art can readily understand that various changes and modifications may be made without departing from the spirit or essential characteristics of the present invention. will be. It is therefore to be understood that the above-described embodiments are illustrative in all aspects and not restrictive.

The scope of the present invention is defined by the appended claims rather than the detailed description and all changes or modifications derived from the meaning and scope of the claims and their equivalents are to be construed as being included within the scope of the present invention do.

100, 101: Gas turbine combustor
110: casing
120: Liner
122: a floating space
130: Transition piece
150: fuel injection nozzle
160: Transition piece support
161: Support
161a and 161b:
163a, 163b: fixed plate
164: first side
165: second side
166:
167: connection plate
169:

Claims (12)

A liner disposed inside the casing forming the outside of the combustor and defining a combustion chamber;
A transition piece connected to a rear end of the liner; And
And a transition piece supporter provided outside the transition piece,
The transition piece supporter includes:
A pair of fixing plates symmetrically fixed on an outer circumferential surface of the transition piece; a connection plate inserted in the fixing plate and slidably inserted in the fixing plate; and a connection plate extending outwardly of the transition piece after being connected to the connection plate, A gas turbine combustor comprising a support. The method according to claim 1,
Wherein the pair of fixing plates comprises:
Wherein the first, second, and third transition pieces are independently disposed on left and right sides of the transition piece,
Wherein the connecting plate inserted in the spaced apart fixing plate is kept inserted into the plate shape. The method according to claim 1,
The support includes:
A first support extending from the connection plate to extend outwardly and laterally separated from an outer peripheral surface of the transition piece;
And a second support member fixed to the lower side of the first support member and extending outwardly. The method according to claim 1,
Wherein the support is elastically deformed by an external force. The method of claim 2,
The fixing plate is spaced apart so as to maintain a predetermined gap therebetween, and a recessed groove is formed on the inner side of the facing fixing plate,
And a convex portion that can be fitted in the groove portion is provided in the connecting plate. The method of claim 5,
And a width (a) of the groove portion is larger than a width (b) of the convex portion. The method of claim 5,
The opposite surfaces of the fixing plates are opposed to each other,
A first surface which is provided on an outermost side except a section where the convex portion is arranged and has a flat shape; And
And a second surface that is parallel to the first surface and is provided inside the first surface to form the groove. The method of claim 7,
And the second surface extends flat. The method of claim 7,
And an inclined portion extending between the first surface and the second surface, the inclined portion extending obliquely toward the second surface from the first surface. The method of claim 5,
Wherein the convex portion has a convex curved shape. The method of claim 5,
Wherein the convex portion has a shape protruding to both sides from the connecting plate. The method according to claim 5 or 7,
And the convex portion is slidable in the width direction and the longitudinal direction of the second surface between the second surfaces.
KR1020150108925A 2015-07-31 2015-07-31 Gas turbine combustor KR101860984B1 (en)

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KR101860984B1 KR101860984B1 (en) 2018-05-24

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20190048901A (en) * 2017-10-31 2019-05-09 두산중공업 주식회사 Transition piece mount assembly of combustor and gas turbine having the same
KR20190055920A (en) * 2017-11-16 2019-05-24 두산중공업 주식회사 Burner Having Transition Piece Supporting Member, And Gas Turbine Having The Same
KR20190086265A (en) * 2018-01-12 2019-07-22 두산중공업 주식회사 Supporting structure of combustion duct for gas turbine engine

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7909300B2 (en) * 2007-10-18 2011-03-22 General Electric Company Combustor bracket assembly

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20190048901A (en) * 2017-10-31 2019-05-09 두산중공업 주식회사 Transition piece mount assembly of combustor and gas turbine having the same
KR20190055920A (en) * 2017-11-16 2019-05-24 두산중공업 주식회사 Burner Having Transition Piece Supporting Member, And Gas Turbine Having The Same
KR20190086265A (en) * 2018-01-12 2019-07-22 두산중공업 주식회사 Supporting structure of combustion duct for gas turbine engine

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