WO1998046873A1 - Structure de refroidissement pour tuyeres terminales de chambre de combustion - Google Patents
Structure de refroidissement pour tuyeres terminales de chambre de combustion Download PDFInfo
- Publication number
- WO1998046873A1 WO1998046873A1 PCT/JP1998/001641 JP9801641W WO9846873A1 WO 1998046873 A1 WO1998046873 A1 WO 1998046873A1 JP 9801641 W JP9801641 W JP 9801641W WO 9846873 A1 WO9846873 A1 WO 9846873A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- jacket
- transition piece
- cooling
- discharge
- downstream
- Prior art date
Links
Classifications
-
- 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
- F23R3/005—Combined with pressure or heat exchangers
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
-
- 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
- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
- F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a combustor transition piece of a gas turbine using steam as a cooling medium.
- Combined cycle power generation plants which combine a gas turbine plant and a steam turbine plant, share the heat energy in the high-temperature region with the gas turbine and the low-temperature region with the steam turbine, and effectively collect and use the heat energy. This is a power generation system that has been particularly spotlighted in recent years.
- the figure shows the transition piece 1 of the gas turbine combustor.
- the transition piece 1 is a transition piece inlet 2 communicating with a combustion chamber (not shown) on the upstream side, a transition piece outlet 3 communicating with a turbine (not shown) on the downstream side, and an intermediate point therebetween. And a bypass passage 10 for bypassing the working gas.
- cooling steam supply pipes 7 and 8 communicate with the inlet-side jacket 4 and the outlet-side jacket 5, and a cooling steam discharge pipe 9 communicates with the merging jacket 6.
- a cooling conduit for guiding cooling steam from the inlet-side jacket 4 and the outlet-side jacket 5 to the merging jacket 6 is provided on the inner wall of the transition piece 1. Many are provided.
- the cooling steam supplied from the bottoming cycle is supplied from the inlet-side jacket 4 and the outlet-side jacket 5 to a plurality of cooling pipes provided on the inner wall portion of the transition piece 1. to go into.
- the cooling steam entering from the inlet jacket 4 which is one of the flows flows in the forward flow direction from the upstream side to the downstream side to cool the inner wall portion of the transition piece 1, and the other side of the outlet jacket 5 which is the cooling water Conversely, the cooling steam entering from the downstream flows in the counterflow direction from the downstream side to the upstream side to cool the inner wall portion of the transition piece 1.
- the cooling steam flows in the counterflow direction, the cooling steam is divided into an upstream side and a downstream side of the merging jacket 6 and observed.
- the portion is sufficiently cooled to be excessive.
- the working gas is accurately guided to the nozzle of the gas turbine.
- the cross-sectional area of the transition piece gradually decreases, so that the flow rate of the combustion gas increases, and as a result, the heat load increases.
- the combustion reaction also progresses gradually toward the downstream side, and the heat load increases due to the influence of the secondary flow at the bending part.
- the distance B from the outlet jacket 5 to the merging jacket 6 is almost equal to the distance from the inlet jacket 4 to the merging jacket 6, and the length is considerably longer. As a result, sufficient cooling cannot be expected with the cooling steam reaching the merging jacket 6, and this portion of the transition piece 1 is eventually maintained at a high heat load.
- the present invention solves such problems in the conventional art, and considers the arrangement relationship and installation position of the inlet-side jacket or the outlet-side jacket, and the supply direction of the cooling steam, and the like, in the axial direction of the transition piece. It is an object of the present invention to provide a material having a gentle temperature distribution and preventing the occurrence of a large thermal stress.
- a first invention is a combustor transition piece provided with a plurality of cooling pipes for cooling a wall surface, the communication pipe being connected to the cooling pipe. Then, a supply jacket for supplying cooling steam to the cooling pipeline is attached to the transition piece, and the cooling steam flowing from the supply jacket to the upstream side of the transition piece through the cooling pipeline is discharged to the upstream discharge jacket. Collected from the supply pipe and connected to the discharge port via a discharge pipe, while the supply The cooling steam flowing to the downstream side of the transition piece is collected in a downstream discharge jacket and connected to a discharge port by a discharge pipe, and the supply jacket is connected to the upstream discharge jacket and downstream. It is a further object to provide a cooling structure for a combustor transition piece which is disposed between the discharge pipe and the side discharge jacket at a reduced diameter portion of the transition piece and at a position close to the downstream discharge jacket.
- the supply jacket is disposed between the upstream jacket and the downstream jacket, and the upstream jacket and the downstream jacket are each arranged as a discharge jacket 4 in an overall arrangement.
- the supply jacket is arranged so as to be closer to the downstream discharge jacket at the reduced diameter portion of the transition piece so as to shorten the cooling passage between the downstream side discharge jacket and the downstream side discharge jacket.
- the cooling water supply jacket and the downstream discharge jacket are close to each other, and the distance of the cooling passage between them is shortened, so that sufficient cooling can be performed.
- the upstream-side discharge jacket is disposed at a position separated from the transition piece inlet and close to a bypass flow path to the compressed air chamber, and is not cooled near the transition piece inlet.
- the purpose of the present invention is to provide a cooling structure for a combustor transition piece in which an area is formed.
- a supply jacket is provided between the upstream jacket and the downstream jacket, and the upstream jacket and the downstream jacket are respectively arranged as discharge jackets in an overall arrangement.
- the discharge jacket of the tail pipe is lowered from the inlet of the transition piece to a position adjacent to the bypass flow passage, so that the vicinity of the entrance of the transition piece becomes a non-cooling area, and the downstream side discharges downstream as described in the first invention.
- Sufficient cooling is ensured by arranging the supply jacket near the downstream discharge jacket at the reduced diameter portion of the transition piece so as to shorten the cooling passage between it and the jacket.
- the temperature in the axial direction of the transition piece The fabric is made loose to prevent the occurrence of large thermal stress.
- the downstream-side discharge jacket provides a cooling structure for a combustor transition piece provided at a transition piece exit position. That is, according to the present invention, since the downstream discharge jacket is provided at the transition piece outlet position, the supply passage is arranged from the position where the cooling passage is a reduced diameter section of the transition piece and close to the downstream discharge jacket. This section is located at the exit of the transition piece and ensures that this section is cooled sufficiently and sufficiently.
- the downstream-side discharge jacket provides a cooling structure for a combustor transition piece provided at a transition piece exit position.
- the downstream discharge jacket is provided at the transition piece outlet position, the arrangement of the uncooled area near the transition piece inlet and the reliable and sufficient cooling area formed by the transition passage cooling passage at the transition piece outlet is achieved.
- the temperature distribution in the axial direction of the transition piece is moderated over the entire area from the entrance to the exit of the transition piece to prevent the occurrence of large thermal stress.
- FIG. 1 shows a transition piece of a gas turbine combustor according to an embodiment of the present invention, wherein (a) is a plan view and (b) is a front view.
- Fig. 2 shows a transition piece of a conventional gas turbine combustor, where (a) is a plan view and (b) is a front view.
- BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of the present invention will be described with reference to FIG. The same parts as those of the above-mentioned conventional one are denoted by the same reference numerals in the drawings to facilitate mutual understanding, and redundant description is omitted as much as possible.
- the 16 is a cooling steam supply jacket, where the cooling steam is supplied to the transition piece 1 of the combustor, near the transition piece exit 3, and the transition piece 1 gradually narrows the cross section to wake.
- the diameter of the reduced diameter section is selected to change to a fan shape in accordance with the gas turbine nozzle.
- Reference numeral 15 denotes a downstream discharge jacket provided at the position of the transition piece outlet 3.Since the supply jacket 16 has approached the reduced diameter portion, the distance between the supply jacket 16 and the supply jacket 16 is reduced.
- the length of the cooling pipe provided on the inner wall of the transition piece 1, which is schematically shown as a notch in the drawing, that is, the length of the cooling passage in this portion is greatly reduced.
- Reference numeral 14 denotes an upstream discharge jacket, which is disposed adjacent to and upstream of the bypass flow path 10. Since the bypass flow path 10 is separated from the transition piece inlet 2 and descends to almost the center position of the transition piece 1, as a result, the discharge jacket 14 is disposed downstream from the transition piece inlet 2 and on the upstream side. Uncooled area A is formed and secured up to the location.
- Reference numeral 17 denotes a supply pipe for supplying cooling steam to the supply jacket 16, and reference numeral 9 cools the inside of the transition piece 1 and is conveyed to the upstream discharge jacket 14 and the downstream discharge jacket 15.
- the exhaust pipe is used to convey the cooling steam to the recovery section downstream.
- the upstream discharge jacket 14 and the downstream discharge jacket 15 are arranged with the cooling steam supply jacket 16 interposed therebetween, so that the supply jacket 16 is provided.
- the cooling steam that has entered the inner wall of the transition piece 1 is transported by the cooling pipeline, which is schematically shown as a notch in the figure, Cools the inner wall of 1 and is discharged from the inner wall of the transition piece 1 by the discharge jackets 14 and 15, sent to the wake through the cooling steam discharge pipe 9, and received by cooling the inner wall Heat energy is recovered.
- the cooling steam supply jacket 16 and the downstream discharge jacket 15 are close to each other, and the distance of the cooling passage therebetween becomes shorter.
- the non-cooling zone A is formed on the side of the transition piece inlet 2 where the heat load is low, so that excessive cooling is not performed more than necessary.
- the temperature distribution becomes moderate, and there is no danger of generating large thermal stress in the transition piece 1.
- safety is improved and reliability is improved.
- the supply jacket is disposed between the upstream jacket and the downstream jacket, and the upstream jacket and the downstream jacket are each a discharge jacket. j, and the upstream discharge jacket is lowered from the transition piece inlet to the downstream position adjacent to the bypass flow path to form an uncooled area near the transition piece inlet.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA002255883A CA2255883C (en) | 1997-04-15 | 1998-04-09 | Combustor tail tube cooling structure |
DE69811841T DE69811841T2 (de) | 1997-04-15 | 1998-04-09 | KüHLSYSTEM FüR DIE ENDSTüCKE DER VERBRENNUNGSKAMMER |
EP98912743A EP0926324B1 (en) | 1997-04-15 | 1998-04-09 | Cooling structure for combustor tail pipes |
US09/194,016 US6220036B1 (en) | 1997-04-15 | 1998-04-09 | Cooling structure for combustor tail pipes |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP09728197A JP3310900B2 (ja) | 1997-04-15 | 1997-04-15 | 燃焼器尾筒の冷却構造 |
JP9/97281 | 1997-04-15 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1998046873A1 true WO1998046873A1 (fr) | 1998-10-22 |
Family
ID=14188139
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP1998/001641 WO1998046873A1 (fr) | 1997-04-15 | 1998-04-09 | Structure de refroidissement pour tuyeres terminales de chambre de combustion |
Country Status (6)
Country | Link |
---|---|
US (1) | US6220036B1 (ja) |
EP (1) | EP0926324B1 (ja) |
JP (1) | JP3310900B2 (ja) |
CA (1) | CA2255883C (ja) |
DE (1) | DE69811841T2 (ja) |
WO (1) | WO1998046873A1 (ja) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1001221A2 (en) * | 1998-11-12 | 2000-05-17 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor cooling structure |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2001041005A (ja) * | 1999-08-02 | 2001-02-13 | Tohoku Electric Power Co Inc | ガスタービン蒸気冷却燃焼器の配管サポート |
EP1146289B1 (en) * | 2000-04-13 | 2008-12-24 | Mitsubishi Heavy Industries, Ltd. | Cooling structure of combustor tail tube |
JP2002243154A (ja) * | 2001-02-16 | 2002-08-28 | Mitsubishi Heavy Ind Ltd | ガスタービン燃焼器尾筒出口構造及びガスタービン燃焼器 |
JP2002309903A (ja) * | 2001-04-10 | 2002-10-23 | Mitsubishi Heavy Ind Ltd | ガスタービンの蒸気配管構造 |
US7178341B2 (en) * | 2004-06-17 | 2007-02-20 | Siemens Power Generation, Inc. | Multi-zone tubing assembly for a transition piece of a gas turbine |
US20060130486A1 (en) * | 2004-12-17 | 2006-06-22 | Danis Allen M | Method and apparatus for assembling gas turbine engine combustors |
US8549861B2 (en) * | 2009-01-07 | 2013-10-08 | General Electric Company | Method and apparatus to enhance transition duct cooling in a gas turbine engine |
JP5649486B2 (ja) * | 2011-03-09 | 2015-01-07 | 三菱重工業株式会社 | 配管サポート調整加工用治具 |
EP2691609A1 (en) * | 2011-03-31 | 2014-02-05 | General Electric Company | Power augmentation system with dynamics damping |
US9574498B2 (en) * | 2013-09-25 | 2017-02-21 | General Electric Company | Internally cooled transition duct aft frame with serpentine cooling passage and conduit |
WO2016093829A1 (en) * | 2014-12-11 | 2016-06-16 | Siemens Aktiengesellschaft | Transition duct support and method to provide a tuned level of support stiffness |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS62111131A (ja) * | 1985-11-07 | 1987-05-22 | Mitsubishi Heavy Ind Ltd | 低カロリ−ガス焚ガスタ−ビン用燃焼器 |
JPH0544494A (ja) * | 1991-08-13 | 1993-02-23 | Mitsubishi Heavy Ind Ltd | ガスタービン高温部の冷却方法 |
JPH0821207A (ja) * | 1994-07-01 | 1996-01-23 | Mitsubishi Heavy Ind Ltd | 蒸気、ガスタービン複合プラントの廃熱による蒸気生成システム |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2356572C3 (de) * | 1973-11-13 | 1979-03-29 | Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen | Flüssigkeitsgekühlte Raketenbrennkammer mit Schubdüse |
US4195474A (en) * | 1977-10-17 | 1980-04-01 | General Electric Company | Liquid-cooled transition member to turbine inlet |
WO1997014875A1 (en) * | 1995-10-17 | 1997-04-24 | Westinghouse Electric Corporation | Gas turbine regenerative cooled combustor |
JP3619599B2 (ja) | 1995-11-30 | 2005-02-09 | 株式会社東芝 | ガスタービンプラント |
US5906093A (en) * | 1997-02-21 | 1999-05-25 | Siemens Westinghouse Power Corporation | Gas turbine combustor transition |
-
1997
- 1997-04-15 JP JP09728197A patent/JP3310900B2/ja not_active Expired - Fee Related
-
1998
- 1998-04-09 CA CA002255883A patent/CA2255883C/en not_active Expired - Fee Related
- 1998-04-09 US US09/194,016 patent/US6220036B1/en not_active Expired - Lifetime
- 1998-04-09 EP EP98912743A patent/EP0926324B1/en not_active Expired - Lifetime
- 1998-04-09 DE DE69811841T patent/DE69811841T2/de not_active Expired - Lifetime
- 1998-04-09 WO PCT/JP1998/001641 patent/WO1998046873A1/ja active IP Right Grant
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS62111131A (ja) * | 1985-11-07 | 1987-05-22 | Mitsubishi Heavy Ind Ltd | 低カロリ−ガス焚ガスタ−ビン用燃焼器 |
JPH0544494A (ja) * | 1991-08-13 | 1993-02-23 | Mitsubishi Heavy Ind Ltd | ガスタービン高温部の冷却方法 |
JPH0821207A (ja) * | 1994-07-01 | 1996-01-23 | Mitsubishi Heavy Ind Ltd | 蒸気、ガスタービン複合プラントの廃熱による蒸気生成システム |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1001221A2 (en) * | 1998-11-12 | 2000-05-17 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor cooling structure |
EP1001221A3 (en) * | 1998-11-12 | 2002-07-10 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor cooling structure |
Also Published As
Publication number | Publication date |
---|---|
DE69811841D1 (de) | 2003-04-10 |
DE69811841T2 (de) | 2003-12-04 |
US6220036B1 (en) | 2001-04-24 |
CA2255883C (en) | 2001-08-07 |
CA2255883A1 (en) | 1998-10-22 |
EP0926324A4 (en) | 2000-08-23 |
EP0926324B1 (en) | 2003-03-05 |
JP3310900B2 (ja) | 2002-08-05 |
EP0926324A1 (en) | 1999-06-30 |
JPH10288048A (ja) | 1998-10-27 |
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