RU2008140723A - METHOD FOR INSTALLING A MIXING CHAMBER OF A GAS TURBINE, COMBUSTION CHAMBER AND A GAS TURBINE - Google Patents

METHOD FOR INSTALLING A MIXING CHAMBER OF A GAS TURBINE, COMBUSTION CHAMBER AND A GAS TURBINE Download PDF

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Publication number
RU2008140723A
RU2008140723A RU2008140723/06A RU2008140723A RU2008140723A RU 2008140723 A RU2008140723 A RU 2008140723A RU 2008140723/06 A RU2008140723/06 A RU 2008140723/06A RU 2008140723 A RU2008140723 A RU 2008140723A RU 2008140723 A RU2008140723 A RU 2008140723A
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Russia
Prior art keywords
mixing chamber
combustion chamber
gas turbine
bolt
relative
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RU2008140723/06A
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Russian (ru)
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RU2444681C2 (en
Inventor
Петер ДИТРИХ (DE)
Петер ДИТРИХ
Милан ШМАЛЬ (DE)
Милан ШМАЛЬ
Мартин ШТАППЕР (DE)
Мартин ШТАППЕР
Original Assignee
Сименс Акциенгезелльшафт (DE)
Сименс Акциенгезелльшафт
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Publication of RU2008140723A publication Critical patent/RU2008140723A/en
Application granted granted Critical
Publication of RU2444681C2 publication Critical patent/RU2444681C2/en

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Classifications

    • 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
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • 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
    • 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
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
    • 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
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • 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
    • F05D2250/40—Movement of components
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/42—Movement of components with two degrees of freedom

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)
  • Gas Burners (AREA)

Abstract

1. Способ монтажа смесительной камеры газовой турбины с жаровой трубой (2) и внутренним корпусом (8), причем смесительная камера (4) расположена между жаровой трубой (2) и внутренним корпусом (8), отличающийся тем, что при монтаже происходит регулировка смесительной камеры (4) относительно жаровой трубы (2) и внутреннего корпуса (8). !2. Способ по п.1, отличающийся тем, что содержит расположенное между смесительной камерой (4) и внутренним корпусом (8) и закрепленное на смесительной камере (4) кольцо (6) системы воздушного охлаждения, причем кольцо (6) системы воздушного охлаждения выравнивают относительно положения внутреннего корпуса. ! 3. Камера сгорания для газовой турбины со смесительной камерой (4), окружающим смесительную камеру (4) внешним корпусом (18), причем смесительная камера (4) выполнена с возможностью регулировки относительно внешнего корпуса (18), а также с регулировочным устройством для регулировки смесительной камеры (4) относительной внешнего корпуса (18). ! 4. Камера сгорания по п.3, отличающаяся тем, что регулировочное устройство для регулировки смесительной камеры (4) содержит болт (12), прижимной лист (13) и косую шайбу (14). ! 5. Камера сгорания по п,4, отличающаяся тем, что контактные поверхности (15) между болтом (12) и косой шайбой (14), а также между болтом (12) и прижимным листом (13) выполнены сферическими. ! 6. Камера сгорания по п.4 или 5, отличающаяся тем, что болты (12) выполнены с возможностью эксцентричной установки относительно трубы (20) с фланцем. ! 7. Камера сгорания по п.6, отличающаяся тем, что болты (12) имеют на головке, соответственно, отверстие (26) для установки монтажной тяги. ! 8. Камера сгорания по п.7, отличающаяся тем, что б� 1. A method of mounting a mixing chamber of a gas turbine with a flame tube (2) and an inner case (8), wherein the mixing chamber (4) is located between the flame tube (2) and the inner case (8), characterized in that the mixer is adjusted during installation chamber (4) relative to the flame tube (2) and the inner casing (8). ! 2. The method according to claim 1, characterized in that it comprises a ring (6) of the air cooling system located between the mixing chamber (4) and the inner housing (8) and fixed to the mixing chamber (4), the ring (6) of the air cooling system being aligned with position of the inner case. ! 3. The combustion chamber for a gas turbine with a mixing chamber (4) surrounding the mixing chamber (4) by an external housing (18), the mixing chamber (4) being made with the possibility of adjustment relative to the external housing (18), as well as with an adjustment device for adjustment a mixing chamber (4) of the relative outer casing (18). ! 4. The combustion chamber according to claim 3, characterized in that the adjusting device for adjusting the mixing chamber (4) contains a bolt (12), a pressure sheet (13) and an oblique washer (14). ! 5. The combustion chamber according to claim 4, characterized in that the contact surfaces (15) between the bolt (12) and the oblique washer (14), as well as between the bolt (12) and the pressure sheet (13) are made spherical. ! 6. The combustion chamber according to claim 4 or 5, characterized in that the bolts (12) are made with the possibility of eccentric installation relative to the pipe (20) with a flange. ! 7. The combustion chamber according to claim 6, characterized in that the bolts (12) have a hole (26) on the head, respectively, for installing the mounting rod. ! 8. The combustion chamber according to claim 7, characterized in that

Claims (13)

1. Способ монтажа смесительной камеры газовой турбины с жаровой трубой (2) и внутренним корпусом (8), причем смесительная камера (4) расположена между жаровой трубой (2) и внутренним корпусом (8), отличающийся тем, что при монтаже происходит регулировка смесительной камеры (4) относительно жаровой трубы (2) и внутреннего корпуса (8).1. A method of mounting a mixing chamber of a gas turbine with a flame tube (2) and an inner case (8), the mixing chamber (4) being located between the flame tube (2) and the inner case (8), characterized in that the mixer is adjusted during installation chamber (4) relative to the flame tube (2) and the inner casing (8). 2. Способ по п.1, отличающийся тем, что содержит расположенное между смесительной камерой (4) и внутренним корпусом (8) и закрепленное на смесительной камере (4) кольцо (6) системы воздушного охлаждения, причем кольцо (6) системы воздушного охлаждения выравнивают относительно положения внутреннего корпуса.2. The method according to claim 1, characterized in that it contains a ring (6) of the air cooling system located between the mixing chamber (4) and the inner housing (8) and fixed to the mixing chamber (4), the ring (6) of the air cooling system align with the position of the inner case. 3. Камера сгорания для газовой турбины со смесительной камерой (4), окружающим смесительную камеру (4) внешним корпусом (18), причем смесительная камера (4) выполнена с возможностью регулировки относительно внешнего корпуса (18), а также с регулировочным устройством для регулировки смесительной камеры (4) относительной внешнего корпуса (18).3. A combustion chamber for a gas turbine with a mixing chamber (4) surrounding the mixing chamber (4) by an external housing (18), the mixing chamber (4) being made with the possibility of adjustment relative to the external housing (18), as well as with an adjustment device for adjustment a mixing chamber (4) of the relative outer casing (18). 4. Камера сгорания по п.3, отличающаяся тем, что регулировочное устройство для регулировки смесительной камеры (4) содержит болт (12), прижимной лист (13) и косую шайбу (14).4. The combustion chamber according to claim 3, characterized in that the adjusting device for adjusting the mixing chamber (4) contains a bolt (12), a pressure sheet (13) and an oblique washer (14). 5. Камера сгорания по п,4, отличающаяся тем, что контактные поверхности (15) между болтом (12) и косой шайбой (14), а также между болтом (12) и прижимным листом (13) выполнены сферическими.5. The combustion chamber according to claim 4, characterized in that the contact surfaces (15) between the bolt (12) and the oblique washer (14), as well as between the bolt (12) and the pressure sheet (13) are made spherical. 6. Камера сгорания по п.4 или 5, отличающаяся тем, что болты (12) выполнены с возможностью эксцентричной установки относительно трубы (20) с фланцем.6. The combustion chamber according to claim 4 or 5, characterized in that the bolts (12) are made with the possibility of eccentric installation relative to the pipe (20) with a flange. 7. Камера сгорания по п.6, отличающаяся тем, что болты (12) имеют на головке, соответственно, отверстие (26) для установки монтажной тяги.7. The combustion chamber according to claim 6, characterized in that the bolts (12) have a hole (26) on the head, respectively, for installing the mounting rod. 8. Камера сгорания по п.7, отличающаяся тем, что болты (12) выполнены с возможностью параллельного, перпендикулярного и горизонтального перемещения относительно внешнего корпуса.8. The combustion chamber according to claim 7, characterized in that the bolts (12) are made with the possibility of parallel, perpendicular and horizontal movement relative to the outer casing. 9. Камера сгорания по п.4, отличающаяся тем, что смесительная камера (4) выполнена с возможностью поворота вокруг оси болта.9. The combustion chamber according to claim 4, characterized in that the mixing chamber (4) is rotatable around the axis of the bolt. 10. Камера сгорания по п.4, отличающаяся тем, что она содержит трубу (20) с фланцем, которая расположена во внешнем корпусе и в которой находится болт (12), причем труба (20) с фланцем расширена до продольного паза.10. The combustion chamber according to claim 4, characterized in that it contains a pipe (20) with a flange, which is located in the outer casing and in which there is a bolt (12), and the pipe (20) with the flange is expanded to a longitudinal groove. 11. Камера сгорания по п.3, отличающаяся тем, что она содержит регулировочное устройство, образованного системой управления и системой шин.11. The combustion chamber according to claim 3, characterized in that it contains an adjustment device formed by the control system and the tire system. 12. Газовая турбина с камерой сгорания (1) по одному из пп.3-11.12. Gas turbine with a combustion chamber (1) according to one of claims 3-11. 13. Газовая турбина по п.12, отличающаяся тем, что камера сгорания содержит закрепленное на смесительной камере (4) и обращенное к внутреннему корпусу (8) кольцо (6) системы воздушного охлаждения, и среднее значение зазора между внутренним корпусом (8) и кольцом (6) системы воздушного охлаждения составляет от 3 до 3,5 мм. 13. A gas turbine according to claim 12, characterized in that the combustion chamber comprises a ring (6) of the air cooling system mounted on the mixing chamber (4) and facing the inner case (8), and the average gap between the inner case (8) and the ring (6) of the air cooling system is from 3 to 3.5 mm.
RU2008140723/06A 2006-03-15 2007-01-09 Gas turbine combustion chamber and gas turbine RU2444681C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP06005259 2006-03-15
EP06005259.4 2006-03-15

Publications (2)

Publication Number Publication Date
RU2008140723A true RU2008140723A (en) 2010-04-20
RU2444681C2 RU2444681C2 (en) 2012-03-10

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RU2008140723/06A RU2444681C2 (en) 2006-03-15 2007-01-09 Gas turbine combustion chamber and gas turbine

Country Status (4)

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EP (1) EP1994260B1 (en)
CN (1) CN101548135B (en)
RU (1) RU2444681C2 (en)
WO (1) WO2007104587A2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2993315B8 (en) * 2014-09-05 2017-07-19 Ansaldo Energia Switzerland AG Apparatus for an assembly tool for mounting or dismantling, replacement and maintenance of a component of an engine
FR3038699B1 (en) * 2015-07-08 2022-06-24 Snecma BENT COMBUSTION CHAMBER OF A TURBOMACHINE

Family Cites Families (10)

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Publication number Priority date Publication date Assignee Title
GB701099A (en) * 1950-05-22 1953-12-16 Lucas Ltd Joseph Improvements to combustion chambers
US3759038A (en) * 1971-12-09 1973-09-18 Westinghouse Electric Corp Self aligning combustor and transition structure for a gas turbine
DE2523449C3 (en) * 1975-05-27 1981-03-26 Kraftwerk Union AG, 45473 Mülheim Combustion chamber for gas turbines
IT1216611B (en) * 1988-04-21 1990-03-08 Nuovo Pignone Spa DEVICE FOR KEEPING THE ANNULAR OUTLET MOUTH OF THE GAS CONVEYOR ALWAYS CENTERED COMPARED TO THE NOZZLE GROUP OF AN AGAS TURBINE.
FR2671857B1 (en) * 1991-01-23 1994-12-09 Snecma COMBUSTION CHAMBER, ESPECIALLY FOR A GAS TURBINE, WITH A DEFORMABLE WALL.
DE4223733C2 (en) * 1992-07-18 1995-05-18 Gutehoffnungshuette Man Connection of mixing tube and flame tube of a gas turbine
RU2100705C1 (en) * 1993-02-03 1997-12-27 Акционерное общество открытого типа "Самарский научно-технический комплекс "Двигатели НК" Device for securing flame tube in combustion chamber housing
RU2112181C1 (en) * 1994-06-10 1998-05-27 Ставропольское высшее авиационное инженерное училище противовоздушной обороны им.Маршала авиации Судца В.А. Gas-turbine engine combustion chamber
US6442946B1 (en) * 2000-11-14 2002-09-03 Power Systems Mfg., Llc Three degrees of freedom aft mounting system for gas turbine transition duct
DE10348447B4 (en) * 2003-10-17 2014-04-03 Siemens Aktiengesellschaft Assembly and maintenance aid for a gas turbine

Also Published As

Publication number Publication date
CN101548135A (en) 2009-09-30
EP1994260B1 (en) 2017-09-20
EP1994260A2 (en) 2008-11-26
CN101548135B (en) 2011-06-08
WO2007104587A2 (en) 2007-09-20
WO2007104587A3 (en) 2009-01-22
RU2444681C2 (en) 2012-03-10

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