RU2016142340A - Газотурбинная установка - Google Patents

Газотурбинная установка Download PDF

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Publication number
RU2016142340A
RU2016142340A RU2016142340A RU2016142340A RU2016142340A RU 2016142340 A RU2016142340 A RU 2016142340A RU 2016142340 A RU2016142340 A RU 2016142340A RU 2016142340 A RU2016142340 A RU 2016142340A RU 2016142340 A RU2016142340 A RU 2016142340A
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RU
Russia
Prior art keywords
installation according
bypass line
annular
combustion chamber
annular groove
Prior art date
Application number
RU2016142340A
Other languages
English (en)
Other versions
RU2016142340A3 (ru
Inventor
Андреас БЁТЧЕР
Схарцад ЮНКЕ
Андре КЛУГЕ
Борис Фердинанд КОК
Тобиас КРИГЕР
Original Assignee
Сименс Акциенгезелльшафт
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Сименс Акциенгезелльшафт filed Critical Сименс Акциенгезелльшафт
Publication of RU2016142340A publication Critical patent/RU2016142340A/ru
Publication of RU2016142340A3 publication Critical patent/RU2016142340A3/ru

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Classifications

    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/606—Bypassing the fluid
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/08—Purpose of the control system to produce clean exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/06041—Staged supply of oxidant
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
    • 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]

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (8)

1. Газотурбинная установка (2) электростанции с компрессором (4), а также с содержащей горелку (14) кольцевой камерой (10) сгорания и с турбиной (6), которая соединена с компрессором (4), а также с обводной линей (16) для сжатого воздуха, шунтирующей горелку (14) и подключенной аэродинамически параллельно ей, причем обводная линия (16) впадает в кольцевой паз (42, 48, 60), отличающаяся тем, что кольцевой паз (42, 48, 60) покрыт жаропрочными плитками (56).
2. Установка по п. 1, отличающаяся тем, что кольцевой паз (42, 48, 60) покрыт металлическим листом (44, 50, 62), содержащим заданное количество отверстий (46).
3. Установка по п. 1 или 2, отличающаяся тем, что кольцевой паз (42, 48, 60) выполнен в кольцевой камере (10) сгорания.
4. Установка по п. 1 или 2, отличающаяся тем, что обводная линия (16) содержит аксиальный зазор (54), выполненный на стороне ступицы кольцевой камеры (10) сгорания.
5. Установка по п. 1 или 2, отличающаяся тем, что содержит по меньшей мере, два указанного рода кольцевых паза (42, 48, 60).
6. Установка по п. 5, отличающаяся тем, что кольцевая камера (10) сгорания содержит наружную оболочку (24) и расположенную на стороне ступицы внутреннюю оболочку (26), причем каждая оболочка (24, 26) содержит один из кольцевых пазов (42, 48, 60).
7. Установка по п. 1 или 2, отличающаяся тем, что обводная линия (16) содержит клапан (18), соединенный в соответствии с техникой передачи сигналов со схемой (22) управления.
8. Способ (64) эксплуатации газотурбинной установки (2) по п. 7, при котором в зависимости от требований к производительности обводную линию (16) нагружают воздухом, отличающийся тем, что в частности на клапан (18) передают команду управления.
RU2016142340A 2014-03-31 2015-03-19 Газотурбинная установка RU2016142340A (ru)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102014206018.4A DE102014206018A1 (de) 2014-03-31 2014-03-31 Gasturbinenanlage
DE102014206018.4 2014-03-31
PCT/EP2015/055765 WO2015150088A1 (de) 2014-03-31 2015-03-19 Gasturbinenanlage

Publications (2)

Publication Number Publication Date
RU2016142340A true RU2016142340A (ru) 2018-05-03
RU2016142340A3 RU2016142340A3 (ru) 2018-05-03

Family

ID=52737089

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2016142340A RU2016142340A (ru) 2014-03-31 2015-03-19 Газотурбинная установка

Country Status (6)

Country Link
US (1) US20170130655A1 (ru)
EP (1) EP3126650B1 (ru)
CN (1) CN106164446B (ru)
DE (1) DE102014206018A1 (ru)
RU (1) RU2016142340A (ru)
WO (1) WO2015150088A1 (ru)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102020116245B4 (de) * 2020-06-19 2024-03-07 Man Energy Solutions Se Baugruppe einer Gasturbine mit Brennkammerluftbypass

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0489193B1 (de) * 1990-12-05 1997-07-23 Asea Brown Boveri Ag Gasturbinen-Brennkammer
EP0660046B1 (en) * 1993-12-22 1999-12-01 Siemens Westinghouse Power Corporation Combustor bybass system for a gas turbine
EP0731316A1 (en) * 1995-02-24 1996-09-11 R. Jan Mowill Star-shaped single stage low emission combustion system
JP2002317650A (ja) * 2001-04-24 2002-10-31 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
US20060016195A1 (en) * 2003-09-16 2006-01-26 Catalytica Energy Systems, Inc. Bypass and injection method and apparatus for gas turbines
EP1724526A1 (de) * 2005-05-13 2006-11-22 Siemens Aktiengesellschaft Brennkammerschale, Gasturbinenanlage und Verfahren zum An- oder Abfahren einer Gasturbinenanlage
US20080113163A1 (en) * 2006-11-14 2008-05-15 United Technologies Corporation Thermal barrier coating for combustor panels
EP1967717A1 (en) * 2007-03-07 2008-09-10 Siemens Aktiengesellschaft Gas turbine with a bypass conduit system
US20100095680A1 (en) * 2008-10-22 2010-04-22 Honeywell International Inc. Dual wall structure for use in a combustor of a gas turbine engine
US8281601B2 (en) * 2009-03-20 2012-10-09 General Electric Company Systems and methods for reintroducing gas turbine combustion bypass flow
GB2484254A (en) * 2010-08-04 2012-04-11 Combined Cycle Enhancements Ltd Gas turbine apparatus with energy recovery heat exchange system
DE102012204103A1 (de) * 2012-03-15 2013-09-19 Siemens Aktiengesellschaft Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer
US9181813B2 (en) * 2012-07-05 2015-11-10 Siemens Aktiengesellschaft Air regulation for film cooling and emission control of combustion gas structure
EP2711633A1 (de) * 2012-09-21 2014-03-26 Siemens Aktiengesellschaft Halteelement zum Halten eines Hitzeschildsteines und Verfahren zum Kühlen der Tragstruktur eines Hitzeschildes
WO2014052965A1 (en) * 2012-09-30 2014-04-03 United Technologies Corporation Interface heat shield for a combustor of a gas turbine engine
US10309314B2 (en) * 2013-02-25 2019-06-04 United Technologies Corporation Finned ignitor grommet for a gas turbine engine
US8984896B2 (en) * 2013-08-23 2015-03-24 Pratt & Whitney Canada Corp. Interlocking combustor heat shield panels

Also Published As

Publication number Publication date
US20170130655A1 (en) 2017-05-11
CN106164446A (zh) 2016-11-23
DE102014206018A1 (de) 2015-10-01
EP3126650A1 (de) 2017-02-08
EP3126650B1 (de) 2018-10-10
WO2015150088A1 (de) 2015-10-08
CN106164446B (zh) 2017-09-29
RU2016142340A3 (ru) 2018-05-03

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Effective date: 20180718