KR101860982B1 - Combustor supporting device of gas turbine - Google Patents

Combustor supporting device of gas turbine Download PDF

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Publication number
KR101860982B1
KR101860982B1 KR1020150099495A KR20150099495A KR101860982B1 KR 101860982 B1 KR101860982 B1 KR 101860982B1 KR 1020150099495 A KR1020150099495 A KR 1020150099495A KR 20150099495 A KR20150099495 A KR 20150099495A KR 101860982 B1 KR101860982 B1 KR 101860982B1
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South Korea
Prior art keywords
combustor
radial
wing
support
axial
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KR1020150099495A
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Korean (ko)
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KR20170008395A (en
Inventor
곽주환
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두산중공업 주식회사
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Priority to KR1020150099495A priority Critical patent/KR101860982B1/en
Publication of KR20170008395A publication Critical patent/KR20170008395A/en
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Publication of KR101860982B1 publication Critical patent/KR101860982B1/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
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • 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
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The present invention relates to a combustor in which a combustor which thermally expands in an axial direction or a radial direction by a high-temperature compressed gas during operation of the turbine or thermally expands both in the axial direction and in the radial direction is moved axially by the connecting member and the connecting member The first and second wing portions and the first and second radial engagement members support and move radially to prevent the combustor support or combustor from being damaged or damaged and to maintain the support of the combustor and combustor support device And more particularly to a combustor support apparatus for a gas turbine that can reduce the cost and vibration and noise of the combustor and the turbine to increase the efficiency of the turbine.

Description

[0001] The present invention relates to a combustor supporting device for a gas turbine,

The present invention relates to a combustor supporting apparatus for a gas turbine, and more particularly, to a combustor supporting apparatus for a combustor supporting a gas turbine, The first and second wing portions and the first and second radial engagement members move radially to support and support the combustor support device or the combustor, To a combustor supporting device for a gas turbine, which can reduce maintenance costs and thus reduce maintenance costs.

Generally, a power generation gas turbine is provided with a compressor connected by an axis and driven by a turbine.

Ambient air flows into the compressor and is compressed.

Compressed air compressed in the compressor is introduced into the combustion system, which includes one or more combustors and a fuel nozzle for injecting fuel into the combustor.

The fuel and the compressed air which are introduced through the fuel nozzle in the combustor are burnt together, thereby producing a hot compressed gas.

The hot compressed gas produced by the combustor flows into the turbine.

As the high temperature compressed gas introduced into the turbine expands, the rotor connected to the turbine rotates to generate electricity. The inflation gas generated from the turbine is discharged to the outside or discharged to the outside through the cogeneration facility.

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.

In general, a sealing member is additionally provided to prevent the compressed air from flowing out between the rear end of the transition piece and the front end of the turbine.

Generally, a combustor of a gas turbine thermally expands axially or radially, or both thermally and radially, by a hot compressed gas during operation of the turbine.

As such, thermal expansion of the combustor causes additional mechanical stress to be applied to the combustor supporting device, and thus the combustor supporting device of the conventional gas turbine has a problem that the combustor or the combustor supporting device is damaged or damaged by the mechanical stress due to thermal expansion of the combustor there was.

In addition, the conventional combustor support apparatus for a gas turbine has a problem in that the cost and time for maintenance and repair of the combustor support apparatus or the combustor are increased as the combustor support apparatus or the combustor is damaged or damaged.

In addition, since the combustor support apparatus of the conventional gas turbine is formed so as to be movable only in one of the axial direction and the radial direction, it can not cope with the thermal expansion in the other direction, and the above- there was.

In addition, the combustor support apparatus of the conventional gas turbine has a problem in that vibration or noise is generated as the mechanical stress due to the thermal expansion of the combustor increases, thereby reducing the efficiency of the turbine.

Korean Patent Laid-Open Publication No. 10-2014-0015560

SUMMARY OF THE INVENTION It is an object of the present invention to provide a combustor which performs thermal expansion in an axial direction or a radial direction by a high-temperature compressed gas during operation of the turbine or thermally expands both in the axial direction and in the radial direction, Is supported while being moved in the axial direction by the axial direction engaging member and the linking member and supported while moving in the radial direction by the first and second wing portions and the first and second radial engaging members so that the combustor supporting device and the combustor are damaged To reduce the maintenance cost of the combustor and the combustor supporting device, and to reduce the vibration and noise of the combustor and the turbine, thereby increasing the efficiency of the turbine.

To achieve the object of the present invention, there is provided an apparatus for supporting a combustor of a gas turbine, comprising: a combustor for combusting fuel; A support unit for supporting the combustor to allow axial and radial movement of the combustor; A coupling unit for coupling the supporting unit and the combustor; And a support member installed at a lower portion of the support unit and supporting the support unit.

Further, the supporting unit of the combustor supporting device of the gas turbine includes a base portion; A first wing portion extending from one side of the base portion; A second wing portion extending to the other side of the base portion to face the first wing portion; And an axial coupling member installed on the base or the first and second wings for axial movement of the combustor.
In addition, the axial coupling member of the support unit of the combustor support device of the gas turbine includes a body portion; And a guide groove portion formed on an upper surface of the main body portion along an axial direction.
The connecting unit of the combustor supporting device of the gas turbine may include a connecting member installed on the outer circumferential surface of the combustor for axial movement of the combustor and inserted into the guide groove of the axial coupling member.

Further, in another embodiment of the combustor supporting device of the gas turbine according to the present invention, the first wing portion of the supporting unit of the combustor supporting device of the gas turbine is formed with a first bending portion formed to be bent from the front end of the first wing portion toward the combustor Section.

Further, in another embodiment of the combustor supporting apparatus of the gas turbine according to the present invention, the second wing portion of the supporting unit of the combustor supporting apparatus of the gas turbine is arranged so as to face the first bending portion at the front end of the second wing portion, And a second bent portion formed to be bent toward the second bent portion.

delete

Further, in another embodiment of the combustor supporting device of the gas turbine according to the present invention, the coupling unit of the combustor supporting device of the gas turbine is installed on the outer peripheral surface of the combustor for radial movement of the combustor, A first radial engagement member; And a second radial engagement member installed on an outer circumferential surface of the combustor to be coupled to the second bent portion to face the first radial engagement member for radial movement of the combustor.

Further, in another embodiment of the combustor supporting apparatus of the gas turbine according to the present invention, the first radial coupling member of the coupling unit of the combustor supporting apparatus of the gas turbine includes a first body portion; And a first groove portion formed on a lower surface of the first body portion along a radial direction and inserted into the first bent portion.

Further, in another embodiment of the combustor supporting apparatus of the gas turbine according to the present invention, the second radial coupling member of the coupling unit of the combustor supporting apparatus of the gas turbine includes a second body portion; And a second groove portion formed on a lower surface of the second body portion along a radial direction and inserted into the second bent portion.

A combustor supporting apparatus for a gas turbine according to the present invention comprises a combustor which thermally expands in an axial direction or a radial direction due to a high-temperature compressed gas during operation of the turbine or thermally expands both axially and radially, And the first and second wing portions and the first and second radial engagement members move in the radial direction while being supported by the first and second wing portions and the first and second radial engagement members to prevent the combustor supporting device or the combustor from being damaged or damaged There is an effect.

Further, since the combustor supporting apparatus of the gas turbine according to the present invention can cope with both the axial expansion and the radial expansion of the combustor, the maintenance cost and the maintenance time of the combustor supporting apparatus can be reduced.

Further, since the combustor supporting apparatus of the gas turbine according to the present invention can cope with both the axial expansion and the radial expansion of the combustor, the increase of the mechanical stress due to the expansion of the combustor is minimized to reduce vibration and noise, So that the efficiency of the turbine can be increased.

FIG. 1 is a conceptual diagram of a state in which a combustor supporting apparatus of a gas turbine is installed according to an embodiment of the present invention.
Figure 2 shows a side cross-sectional view of the combustor support apparatus of the gas turbine in Figure 1;
Figure 3 shows a perspective view of an axial coupling member of a support unit of a combustor support apparatus of a gas turbine according to an embodiment of the invention.
Figure 4 shows a side cross-sectional view of a coupling unit of a combustor support apparatus of a gas turbine according to an embodiment of the invention.
5 shows a side cross-sectional view of a combustor support apparatus of a gas turbine according to another embodiment of the present invention.

Preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In the drawings, like reference numerals are used to refer to like elements throughout.

Fig. 1 is a conceptual diagram of a state in which a combustor supporting device of a gas turbine according to an embodiment of the present invention is installed, and Fig. 2 is a side sectional view of a combustor supporting device of a gas turbine in Fig. Fig. 3 is a perspective view of an axial coupling member of a support unit of a combustor support apparatus of a gas turbine according to an embodiment of the present invention, and Fig. 4 is a perspective view of a coupling unit of a combustor support apparatus of a gas turbine according to an embodiment of the present invention 5 is a side cross-sectional view of a combustor support apparatus of a gas turbine according to another embodiment of the present invention.

The definitions of terms used below are as follows. The term "axial direction" means the longitudinal direction of a rotary shaft such as a rotor of a turbine, and the term "radial direction" means a direction from the center of the rotary shaft to the outer peripheral surface of the rotary shaft and the reverse direction thereof.

1 to 4, a combustor support apparatus for a gas turbine according to an embodiment of the present invention will be described. 1 to 4, a combustor supporting apparatus of a gas turbine according to an embodiment of the present invention comprises a combustor 100, a support unit 200, a coupling unit 300, and a support member 400 .

The combustor 100 is fixed to the casing 2 and is combusted in a state where the fuel introduced through the nozzle and the compressed air introduced through the compressor are mixed in the internal combustion chamber of the combustor 100.

The high-temperature gas generated by the combustion flows into the turbine to rotate the rotor of the turbine, and the generator is connected to the rotor.

A transition piece is installed at the rear end of the combustor, that is, at the tip of the combustor adjacent to the turbine. The hot compressed gas burned into the combustion chamber through the transition piece is directed to the turbine.

The support unit 200 is installed below the outer circumferential surface of the combustor 100.

The support unit 200 supports the combustor 100 so as to be movable in the axial direction and the radial direction of the combustor.

The support unit 200 is installed inside the housing of the combustor 100 or inside the casing 2, though not necessarily limited thereto.

A coupling unit (300) is installed on the outer peripheral surface of the combustor (100).

The coupling unit 300 functions to couple the combustor 100 and the support unit 200 together.

The support member 400 is provided at the lower portion of the support unit 200 and the upper portion inside the casing 2. The support member 400 functions to support the combustor 100 through the support unit 200.

As described above, the combustor supporting apparatus of the gas turbine according to the present invention has a stable structure in which the combustor 100 which thermally expands in the axial direction or the radial direction inside the casing 2 or thermally expands both in the axial direction and the radial direction, .

2, the support unit 200 of the combustor support apparatus of the gas turbine according to an embodiment of the present invention includes a base portion 210, a first wing portion 220, a second wing portion 230, And an axial coupling member 240.

The base portion 210 forms the outer shape of the support unit 200.

The base portion 210 is formed to have a predetermined length perpendicular to the axial direction. Although not limited thereto, the base 210 is formed of a metal material.

The first wing portion 220 is formed on one side of the base portion 210. More preferably, the first wing portion 220 is formed to be bent at a predetermined angle at one end of the base portion 210.

The first bent portion 221 is formed to be bent at a predetermined angle from the front end of the first wing portion 220 toward the combustor 100.

The first bent portion 221 is inserted into the first groove portion 312 of the first radial engagement member 310 to be described later.

The second wing portion 230 is formed on the other side of the base portion 210 so as to face the first wing portion 220. More preferably, the second wing 230 is bent at an opposite end of the base 210 where the first wing 220 is formed to have the same angle as that of the first wing 220.

The second bent portion 231 is formed to be bent at a predetermined angle toward the combustor 100 while facing the first bent portion 221 at the tip of the second wing portion 231.

The second bent portion 231 is inserted into the second groove portion 322 of the second radial engagement member 320 to be described later.

As the first bent portion 221 is movably engaged with the first groove portion 312 and the second bent portion 321 is movably coupled to the second groove portion 322, It is possible to flexibly cope with the radial thermal expansion of the combustor by the high-temperature compressed gas.

Accordingly, it is possible to prevent the combustor supporting device or the combustor of the gas turbine from being damaged or damaged, and to reduce their maintenance cost and maintenance time.

2 and 5 that the first wing 220 is formed at the right end of the base 210 and the second wing 230 is formed at the left end of the base 210, But the present invention is not limited thereto. That is, when the first wing portion 220 is formed at the left end of the base portion 210, the second wing portion 230 is positioned at the right end of the base portion 210 so as to face the first wing portion 220 .

An axial coupling member 240 is formed in the base portion 210. That is, the axial coupling member 240 is formed on the upper side of the center of the base portion 210.

3, the axial coupling member 240 is composed of a body portion 241 and a guide groove portion 242. As shown in FIG.

The body portion 241 is formed in a substantially hexahedron shape to form an outer shape of the axial coupling member 240.

The guide groove portion 242 is formed along the axial direction on the upper surface of the main body portion 241.

As the connecting member 330 is inserted into the guide groove 242 of the axial coupling member 240 and the axial coupling member 240 is movably coupled in the axial direction, It is possible to flexibly cope with the thermal expansion not only in the radial direction but also in the axial direction of the combustor by the gas.

Accordingly, it is possible to prevent the combustor supporting device or the combustor of the gas turbine from being damaged or damaged, to reduce the maintenance cost and the maintenance time, to minimize the increase of the mechanical stress due to the expansion of the combustor, The efficiency of the turbine can be increased.

5, according to another preferred embodiment of the present invention, the axial engagement member 240 of the support unit 200 is fixed to the base portion 210, the first wing portion 220, And is installed on the upper side of the wing portion 230.

The first and second wings 220 and 230 are symmetrically disposed about the axial coupling member 240 installed on the upper surface of the base 210, As shown in Fig.

The axial direction coupling member 240 may be disposed on the upper side of the base 210 in the axial direction of the first and second wings 220 and 230, The stress applied to the first wing portion 220 and the second wing portion 230 is minimized at the time of radial expansion of the combustor due to thermal expansion, It is possible to prevent the wing portion 220 and the second wing portion 230 from being deformed by mechanical stress.

The axial coupling member 240 is provided at an odd number in the base portion 210.

The axial direction coupling member 240 is disposed on the base 210 in an odd number so that the axial direction coupling member 240 is coupled to the combustor 100 along the first wing portion 220 and the second wing portion 230 about the base portion 210 The axial direction expansion of the combustor 100 can minimize the stress generated by the axial expansion of the combustor 100.

5 is not an example for the number of the axial coupling members 240 to be installed. The length of the base unit 210, the first wing unit 220, and the second wing unit 230 of the support unit 200 and the size of the combustor 100 may be additionally provided.

4, a coupling unit 300 of a combustor support apparatus of a gas turbine according to an embodiment of the present invention includes a first radial engagement member 310, a second radial engagement member 320, Member 330 as shown in FIG.

The first radial engagement member 310 is installed on the outer circumferential surface of the combustor 100 so that the combustor 100 can move in the radial direction when the combustor 100 is radially expanded by thermal expansion. That is, on the outer circumferential surface of the combustor 100 so as to correspond to the first bent portion 221 of the first wing portion 220.

The first radial coupling member 310 is formed in a hexahedron shape and includes a first body portion 311 forming an outer surface of the first radial coupling member 310 and a second body portion 311 formed in a radial direction And a first groove part 312 formed along the first bent part 221 and coupled with the first bent part 221. [

The first radial engagement member 310 is engaged with the first bent portion 221.

That is, the first groove portion 312 of the first radial engagement member 310 is engaged with the first bent portion 221.

The second radial engagement member 320 is configured such that when the combustor 100 is radially expanded by thermal expansion, the combustor 100 can move radially and cause the first radial engagement member 310 to be misaligned Is installed on the outer peripheral surface of the combustor (100). That is, on the outer peripheral surface of the combustor 100 so as to correspond to the second bent portion 231 of the second wing portion 230.

The second radial coupling member 320 is formed in a hexahedron shape and includes a second body portion 321 forming an outer appearance of the second radial coupling member 320 and a second body portion 321 formed on the lower surface of the second body portion 321 in a radial direction And a second groove portion 322 formed along the first bent portion 231 and coupled to the second bent portion 231.

The second radial engagement member 320 is engaged with the second bend 231.

That is, the second groove portion 322 of the second radial engagement member 320 is engaged with the second bent portion 231.

The connecting member 330 is installed on the outer peripheral surface of the combustor 100 so as to cope with axial thermal expansion of the combustor and the connecting member 330 is inserted into the guide groove portion 242 of the axial coupling member 240, And the coupling unit.

4 and 5, the connecting member 330 includes a base portion 210, an axial coupling member 240 installed on the upper surfaces of the first and second wing portions 220 and 230, And is installed on the outer circumferential surface of the combustor 100 so as to correspond to the installation number and installation position of the combustor 100.

The combustor support apparatus of the gas turbine according to the present invention is formed so as to flexibly correspond to the thermal expansion of the combustor in both the axial direction and the radial direction by the high temperature compressed gas in the operation of the turbine, Thereby reducing the maintenance cost and time of the combustor supporting device and the combustor, minimizing the increase of the mechanical stress due to the expansion of the combustor, reducing vibration and noise, and ultimately increasing the efficiency of the turbine.

The present invention is not limited to the modifications shown in the drawings and the embodiments described above, but may be extended to other embodiments falling within the scope of the appended claims.

2: casing,
3: turbine, 100: combustor,
200: support unit, 210: base portion,
220: first wing portion, 221: first bent portion,
230: second wing portion, 231: second bending portion,
240: axial coupling member, 241: main body part,
242: guide groove portion, 300: coupling unit,
310: first radial coupling member, 311: first body part,
312: first groove portion, 320: second radial engagement member,
321: second body part, 322: second groove part,
330: Connection member.

Claims (8)

A combustor in which fuel is combusted;
A support unit for supporting the combustor to allow axial and radial movement of the combustor;
A coupling unit for coupling the supporting unit and the combustor; And
And a support member installed at a lower portion of the support unit to support the support unit,
The support unit includes:
A base portion;
A first wing portion extending from one side of the base portion;
A second wing portion extending to the other side of the base portion to face the first wing portion; And
And an axial coupling member installed on the base portion or the first and second wing portions for axial movement of the combustor,
Wherein the axial engagement member of the support unit comprises:
A body portion; And
And a guide groove portion formed on an upper surface of the main body portion along an axial direction,
The coupling unit includes:
And a connecting member installed on an outer circumferential surface of the combustor for axial movement of the combustor and inserted into the guide groove of the axial coupling member.
delete The method according to claim 1,
The first wing portion of the support unit,
And a first bent portion formed to be bent from a tip end of the first wing portion toward the combustor.
The method of claim 3,
The second wing portion of the support unit,
And a second bent portion bent toward the combustor from a front end of the second wing portion to face the first bent portion.
delete 5. The method of claim 4,
The coupling unit includes:
A first radial coupling member installed on an outer circumferential surface of the combustor for radial movement of the combustor and coupled with the first bent portion; And
A second radial engagement member mounted on an outer circumferential surface of the combustor to engage with the second bent portion to face the first radial engagement member for radial movement of the combustor;
Wherein the combustor support device further comprises a gas turbine.
The method according to claim 6,
Wherein the first radial engagement member comprises:
A first body portion; And
And a first groove portion formed along a radial direction on a lower surface of the first body portion and inserted into the first bent portion.
8. The method of claim 7,
Wherein the second radial engagement member comprises:
A second body portion; And
And a second groove portion formed on a lower surface of the second body portion along a radial direction and inserted into the second bent portion.












KR1020150099495A 2015-07-14 2015-07-14 Combustor supporting device of gas turbine KR101860982B1 (en)

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Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101912528B1 (en) 2017-05-02 2018-10-26 두산중공업 주식회사 Supporting unit for power unit and the turbine
KR102075409B1 (en) * 2017-09-21 2020-02-10 두산중공업 주식회사 Combustor and gas turbine including the same
KR102010661B1 (en) * 2017-10-31 2019-08-13 두산중공업 주식회사 Transition piece mount assembly of combustor and gas turbine having the same
KR102044668B1 (en) 2018-11-30 2019-11-20 한국기계연구원 Gas turbine combustor having nozzle guide for combustion oscillation reduction
KR102117531B1 (en) 2019-11-07 2020-06-10 한국기계연구원 Burner for gas turbine combustor with acoustic damping structure for reduction of combustion oscillation
KR102379124B1 (en) 2020-10-15 2022-03-28 한국기계연구원 Burner for gas turbine combustor with structure for reduction of combustion oscillation and gas turbine combustor having the same

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JP2011058496A (en) * 2009-09-11 2011-03-24 General Electric Co <Ge> Circumferentially self expanding support for turbine engine
KR101482573B1 (en) * 2013-03-22 2015-01-21 두산중공업 주식회사 Supporting device for a gas turbine

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Publication number Priority date Publication date Assignee Title
US8955331B2 (en) 2011-05-20 2015-02-17 Siemens Energy, Inc. Turbine combustion system coupling with adjustable wear pad

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011058496A (en) * 2009-09-11 2011-03-24 General Electric Co <Ge> Circumferentially self expanding support for turbine engine
KR101482573B1 (en) * 2013-03-22 2015-01-21 두산중공업 주식회사 Supporting device for a gas turbine

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