EP1270874A1 - Turbine à gaz avec un compresseur d'air - Google Patents

Turbine à gaz avec un compresseur d'air Download PDF

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Publication number
EP1270874A1
EP1270874A1 EP01114599A EP01114599A EP1270874A1 EP 1270874 A1 EP1270874 A1 EP 1270874A1 EP 01114599 A EP01114599 A EP 01114599A EP 01114599 A EP01114599 A EP 01114599A EP 1270874 A1 EP1270874 A1 EP 1270874A1
Authority
EP
European Patent Office
Prior art keywords
combustion chambers
gas turbine
section
cross
turbine according
Prior art date
Legal status (The legal status 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 status listed.)
Granted
Application number
EP01114599A
Other languages
German (de)
English (en)
Other versions
EP1270874B1 (fr
Inventor
Robert Bland
Charles Ellis
Peter Tiemann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP01114599A priority Critical patent/EP1270874B1/fr
Priority to DE50107283T priority patent/DE50107283D1/de
Priority to JP2002172518A priority patent/JP2003042451A/ja
Priority to US10/172,016 priority patent/US6672070B2/en
Priority to CNB021233160A priority patent/CN1328492C/zh
Publication of EP1270874A1 publication Critical patent/EP1270874A1/fr
Application granted granted Critical
Publication of EP1270874B1 publication Critical patent/EP1270874B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal

Definitions

  • the invention relates to a gas turbine with a compressor for air flowing in a variety of parallel flow switched combustion chambers is warmed up before over a transfer duct flows into a gas duct in a turbine.
  • Gas turbines are typically used to achieve an economical Power-density sucked air is initially compressed and then heated up in combustion chambers. The generated thereby Hot gas then drives a turbine.
  • FIG used arrangement In US Pat. No. 4,719,748 one of these is widespread in FIG used arrangement specified. With this arrangement lies a long connecting channel between a combustion chamber and a turbine inlet directly in an air duct the compressed air flows to a burner. With this arrangement no diffuser for air guidance is shown and the The air flow rate is when the connecting duct is reached sunk far. Correct cooling is consequently at most at relatively low temperatures Hot gas possible because higher temperatures are specific Flow rate for both the compressed air as well also for the hot gas and a specific duct height and - require alignment for the air duct.
  • Adequate Cooling is so far recognizable with this solution for neither Still accessible for the underside of the connecting channel, because on the one hand the volume of the air duct in this area is very large and because both the length of the to cooling channel section as well as that of the compressed Air to be returned after exiting a compressor Route is relatively long.
  • the invention is based on the object for a gas turbine to create an arrangement of the type mentioned at the beginning, in which an inevitable loss of pressure in the stream of compressed Air is further reduced.
  • a section of a rotor 1 of a gas turbine system rotates around an axis 2. Compressed in a compressor 3 Air leaves it through a ring of guide vanes 4 and flows in the direction of arrows 5 initially by an axially parallel in cross-section Channel section 6 of an air duct, which is inwardly through a Wall 38 and is limited to the outside by a wall 39.
  • the compressed passes Air webs 7.
  • the webs 7 have an annular cross section C-shaped deflector 8 and are over webs 7 in the end of the channel section 6 anchored.
  • One in the end of the canal section 6 lying leg 9 of the cross section of the deflector 8 with its upstream edge 9 forms one around wavy line 37 concentric to the axis 1 concentric circle.
  • the wall thickness of the deflector 8 increases, starting from the edge 9 to to its center, strongly to and is also in the circumferential direction of the Deflector 8 not constant, but increasing and decreasing like a wave.
  • Combustion chambers 10 for heating are located radially above the deflector 8 the compressed air.
  • a radially outside Cross-sectional leg of the deflector 8 is essentially adapted to the contour of the combustion chambers and forms its free end has a wavy edge 35.
  • This outer cross-sectional leg of the deflector 8 is moreover also designed in a wave shape, the so formed Waves opposed to the waves of the wave line 37 are, as can be seen particularly well from FIG. 3.
  • the special shape of the deflector 8 in its circumferential direction Waves 35 and 37 forming legs of his C-shaped Cross-section forces a division in its area of the air flow into a partial flow 5a to the top of the Combustion chambers 10 and in a partial flow 5b to the bottom of the Combustion chambers 10.
  • the top of the combustion chambers is located here 10, based on the gas turbine, radially outside and accordingly the bottom radially inside.
  • the distances of the partial flows 5a and 5b are approximately the same size, so that all parts of the cooling air from the compressor 3 to the entry into the combustion chambers 10 have to travel equally long distances.
  • Each of the combustion chambers 10 is supported via webs 11 from the inside on an outer casing 12, which at the same time the outer wall of an air duct 20 and a continuation of the air duct 6 for the air flowing in the direction of arrows 5.
  • the envelope 12 carries at its outer free end a cap 13 through which the air enters the interior of the combustion chamber 10 is performed.
  • the combustion chambers 10 are so close to one another in the circumferential direction arranged that the outer wrappers 12 on penetrate each other their end facing the runner 1 would.
  • the interior of the combustion chambers 10 is also by a Fuel nozzle, not shown, for example a combustible Supplied with gas or atomized liquid fuel, by burning the air in the combustion chamber 10 to a hot gas 34 is heated.
  • a Fuel nozzle not shown, for example a combustible Supplied with gas or atomized liquid fuel, by burning the air in the combustion chamber 10 to a hot gas 34 is heated.
  • the combustion chamber 10 and the outer casing 12 holding it are stored in a socket 14 in a housing shell 15 and via one firmly connected to the outer casing 12 Flange 16 fixed on the outer end of the nozzle 14.
  • On inner end 36 of the combustion chamber 10 is sealed in one Transfer channel 17, the output of the combustion chamber 10 with a in cross section annular gas channel 18 in one Turbine connects.
  • Around the gas channel 18 as far as possible on its circumference is one Variety of, for example, 10 to 30 combustion chambers 10 evenly distributed over the circumference of the turbine system and are their Junctions into the transfer duct 17 through one in the direction on the gas channel 18 open peripheral channel 19 with each other connected.
  • the transfer channel 17 is on by thin webs 21 anchored part 22 of the turbine.
  • the guide part 22 and a guide part 23 are in a housing shell 24 stored and are against each other by securing blocks 25 Rotation secured.
  • the guide parts 22 and 23 however, for example by hydraulic or pneumatic Motors 26 can be moved axially parallel over short distances, wherein a flange 27 is elastically deformed and with in it stored deformation energy to reset the guide part 22 or 23 serves.
  • One of the housing shells 15 and 24 enclosed volume is divided into compartments by partitions 28.
  • the guide parts 22 and 23 have a funnel-like shape and wear on their inner side in guide rings 29 fixed guide vanes 30, the ends opposite the guide rings 29 are firmly connected by rings 31. Between each other neighboring wreaths of guide vanes 30 are each one Ring of blades 32 wedged on rotor 1 is provided, whose free tips guide rings 33 are opposite. there the guide rings 29 and 33 form an outer ring and the rings 31, together with the feet of the blades 32, an inner boundary of the gas channel 18 for the hot gas 34 in the turbine.
  • Parts of the turbine plant immediately exposed to hot gas 34 are usually through channels not shown Bleed air from the compressor or from the duct section 6 cooled. In special cases, where necessary, also directly adjacent to the transfer duct 17, lying in a blind spot of the air flow near the deflector 8 Bags chilled this way. These bags are then Expediently by partition walls, not shown, from the air duct separated so that its free and effective cross-section is straight in the area of the transfer duct 17 more precisely to the cross section of the channel section 6 or the sum of the individual cross sections the channels 20 is customizable. This cross section is in addition by varying the wall thickness of the deflector 8 both in its circumferential direction and in its cross section exactly adjustable.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01114599A 2001-06-18 2001-06-18 Turbine à gaz avec un compresseur d'air Expired - Lifetime EP1270874B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP01114599A EP1270874B1 (fr) 2001-06-18 2001-06-18 Turbine à gaz avec un compresseur d'air
DE50107283T DE50107283D1 (de) 2001-06-18 2001-06-18 Gasturbine mit einem Verdichter für Luft
JP2002172518A JP2003042451A (ja) 2001-06-18 2002-06-13 空気圧縮機を備えたガスタービン
US10/172,016 US6672070B2 (en) 2001-06-18 2002-06-17 Gas turbine with a compressor for air
CNB021233160A CN1328492C (zh) 2001-06-18 2002-06-18 带有空气压缩机的燃气轮机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01114599A EP1270874B1 (fr) 2001-06-18 2001-06-18 Turbine à gaz avec un compresseur d'air

Publications (2)

Publication Number Publication Date
EP1270874A1 true EP1270874A1 (fr) 2003-01-02
EP1270874B1 EP1270874B1 (fr) 2005-08-31

Family

ID=8177741

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01114599A Expired - Lifetime EP1270874B1 (fr) 2001-06-18 2001-06-18 Turbine à gaz avec un compresseur d'air

Country Status (5)

Country Link
US (1) US6672070B2 (fr)
EP (1) EP1270874B1 (fr)
JP (1) JP2003042451A (fr)
CN (1) CN1328492C (fr)
DE (1) DE50107283D1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1801356A2 (fr) 2005-12-22 2007-06-27 United Technologies Corporation Interface chambre de combustion-turbine
EP2428647A1 (fr) * 2010-09-08 2012-03-14 Alstom Technology Ltd Zone de dépassement pour une chambre de combustion d'une turbine à gaz
WO2014039247A1 (fr) * 2012-09-04 2014-03-13 Siemens Energy, Inc. Moteur de turbine à gaz ayant un diffuseur radial et une section intermédiaire raccourcie
US9453417B2 (en) 2012-10-02 2016-09-27 General Electric Company Turbine intrusion loss reduction system

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EP1423645B1 (fr) * 2001-09-07 2008-10-08 Alstom Technology Ltd Ensemble amortisseur concu pour reduire les pulsations d'une chambre de combustion dans une installation de turbine a gaz
US7047722B2 (en) * 2002-10-02 2006-05-23 Claudio Filippone Small scale hybrid engine (SSHE) utilizing fossil fuels
ATE403302T1 (de) * 2003-08-13 2008-08-15 Koninkl Philips Electronics Nv Kommunikationsnetzwerk
EP1508680A1 (fr) * 2003-08-18 2005-02-23 Siemens Aktiengesellschaft Diffuseur situé entre le compresseur et la chambre de combustion d'une turbine à gaz
US7043921B2 (en) * 2003-08-26 2006-05-16 Honeywell International, Inc. Tube cooled combustor
JP2005076982A (ja) * 2003-08-29 2005-03-24 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
US7047723B2 (en) * 2004-04-30 2006-05-23 Martling Vincent C Apparatus and method for reducing the heat rate of a gas turbine powerplant
US20080229749A1 (en) * 2005-03-04 2008-09-25 Michel Gamil Rabbat Plug in rabbat engine
US20060196189A1 (en) * 2005-03-04 2006-09-07 Rabbat Michel G Rabbat engine
US7870739B2 (en) * 2006-02-02 2011-01-18 Siemens Energy, Inc. Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions
US20070214792A1 (en) * 2006-03-17 2007-09-20 Siemens Power Generation, Inc. Axial diffusor for a turbine engine
US8499565B2 (en) * 2006-03-17 2013-08-06 Siemens Energy, Inc. Axial diffusor for a turbine engine
US7836677B2 (en) * 2006-04-07 2010-11-23 Siemens Energy, Inc. At least one combustion apparatus and duct structure for a gas turbine engine
US7600370B2 (en) 2006-05-25 2009-10-13 Siemens Energy, Inc. Fluid flow distributor apparatus for gas turbine engine mid-frame section
US7574870B2 (en) 2006-07-20 2009-08-18 Claudio Filippone Air-conditioning systems and related methods
US7631499B2 (en) * 2006-08-03 2009-12-15 Siemens Energy, Inc. Axially staged combustion system for a gas turbine engine
EP1892378A1 (fr) * 2006-08-22 2008-02-27 Siemens Aktiengesellschaft Turbine à gas
EP1950382A1 (fr) * 2007-01-29 2008-07-30 Siemens Aktiengesellschaft Entretoise avec élément de guidage de flux
KR101450867B1 (ko) * 2007-01-30 2014-10-14 제너럴 일렉트릭 캄파니 역류 분사 메카니즘을 구비한 가스 터빈 연소기
ITMI20071048A1 (it) * 2007-05-23 2008-11-24 Nuovo Pignone Spa Metodo per il controllo delle dinamiche di pressione e per la stima del ciclo di vita della camera di combustione di una turbina a gas
US8438855B2 (en) * 2008-07-24 2013-05-14 General Electric Company Slotted compressor diffuser and related method
US8397512B2 (en) * 2008-08-25 2013-03-19 General Electric Company Flow device for turbine engine and method of assembling same
US8474266B2 (en) * 2009-07-24 2013-07-02 General Electric Company System and method for a gas turbine combustor having a bleed duct from a diffuser to a fuel nozzle
FR2949810B1 (fr) * 2009-09-04 2013-06-28 Turbomeca Dispositif de support d'un anneau de turbine, turbine avec un tel dispositif et turbomoteur avec une telle turbine
US8516822B2 (en) * 2010-03-02 2013-08-27 General Electric Company Angled vanes in combustor flow sleeve
US8276390B2 (en) * 2010-04-15 2012-10-02 General Electric Company Method and system for providing a splitter to improve the recovery of compressor discharge casing
US20120031099A1 (en) * 2010-08-04 2012-02-09 Mahesh Bathina Combustor assembly for use in a turbine engine and methods of assembling same
US8667801B2 (en) * 2010-09-08 2014-03-11 Siemens Energy, Inc. Combustor liner assembly with enhanced cooling system
ES2427440T3 (es) * 2011-03-15 2013-10-30 Siemens Aktiengesellschaft Cámara de combustión de turbina de gas
US8938978B2 (en) * 2011-05-03 2015-01-27 General Electric Company Gas turbine engine combustor with lobed, three dimensional contouring
WO2013162982A1 (fr) 2012-04-27 2013-10-31 General Electric Company Joint métallique présentant la forme d'un demi-tube creux formé d'une seule pièce avec un tube
CN103334801A (zh) * 2013-05-31 2013-10-02 余泰成 涡轮燃具和涡轮轴承降温方法
US11732892B2 (en) 2013-08-14 2023-08-22 General Electric Company Gas turbomachine diffuser assembly with radial flow splitters
WO2015031796A1 (fr) 2013-08-29 2015-03-05 United Technologies Corporation Carter de diffuseur hybride pour chambre de combustion de moteur à turbine à gaz
US9134029B2 (en) * 2013-09-12 2015-09-15 Siemens Energy, Inc. Radial midframe baffle for can-annular combustor arrangement having tangentially oriented combustor cans
US20150159873A1 (en) * 2013-12-10 2015-06-11 General Electric Company Compressor discharge casing assembly
EP2977590B1 (fr) * 2014-07-25 2018-01-31 Ansaldo Energia Switzerland AG Ensemble compresseur pour turbine à gaz
WO2016181307A1 (fr) 2015-05-11 2016-11-17 Devcon Engineering Gerhard Schober Turbine
US10465907B2 (en) * 2015-09-09 2019-11-05 General Electric Company System and method having annular flow path architecture
CN110475948B (zh) * 2017-03-30 2022-05-10 三菱动力株式会社 燃气轮机
WO2020106431A2 (fr) 2018-11-02 2020-05-28 Chromalloy Gas Turbine Llc Aube directrice de diffuseur
US11021977B2 (en) * 2018-11-02 2021-06-01 Chromalloy Gas Turbine Llc Diffuser guide vane with deflector panel having curved profile
JP7777056B2 (ja) * 2022-09-29 2025-11-27 本田技研工業株式会社 ガスタービン

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US2479573A (en) * 1943-10-20 1949-08-23 Gen Electric Gas turbine power plant
US2765620A (en) * 1951-06-23 1956-10-09 Gen Motors Corp Flow deflector for combustion chamber apparatus
FR1110063A (fr) * 1953-10-23 1956-02-06 Licentia Gmbh Diffuseur annulaire placé avant la chambre d'échappement de la vapeur ou du gaz d'une turbine à vapeur ou à gaz
US3353351A (en) * 1964-12-02 1967-11-21 Rolls Royce Aerofoil-shaped fluid-cooled blade for a fluid flow machine
US3657882A (en) * 1970-11-13 1972-04-25 Westinghouse Electric Corp Combustion apparatus
US3652181A (en) * 1970-11-23 1972-03-28 Carl F Wilhelm Jr Cooling sleeve for gas turbine combustor transition member
US4195474A (en) * 1977-10-17 1980-04-01 General Electric Company Liquid-cooled transition member to turbine inlet
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FR2757210A1 (fr) * 1996-12-12 1998-06-19 Hispano Suiza Sa Echappement centrifuge de turbine a deflecteur cambre

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1801356A2 (fr) 2005-12-22 2007-06-27 United Technologies Corporation Interface chambre de combustion-turbine
EP1801356A3 (fr) * 2005-12-22 2011-01-26 United Technologies Corporation Interface chambre de combustion-turbine
US7934382B2 (en) 2005-12-22 2011-05-03 United Technologies Corporation Combustor turbine interface
EP2428647A1 (fr) * 2010-09-08 2012-03-14 Alstom Technology Ltd Zone de dépassement pour une chambre de combustion d'une turbine à gaz
US9097118B2 (en) 2010-09-08 2015-08-04 Alstom Technology Ltd. Transitional region for a combustion chamber of a gas turbine
WO2014039247A1 (fr) * 2012-09-04 2014-03-13 Siemens Energy, Inc. Moteur de turbine à gaz ayant un diffuseur radial et une section intermédiaire raccourcie
US9127554B2 (en) 2012-09-04 2015-09-08 Siemens Energy, Inc. Gas turbine engine with radial diffuser and shortened mid section
US9453417B2 (en) 2012-10-02 2016-09-27 General Electric Company Turbine intrusion loss reduction system

Also Published As

Publication number Publication date
US20030010014A1 (en) 2003-01-16
US6672070B2 (en) 2004-01-06
JP2003042451A (ja) 2003-02-13
CN1328492C (zh) 2007-07-25
CN1392331A (zh) 2003-01-22
EP1270874B1 (fr) 2005-08-31
DE50107283D1 (de) 2005-10-06

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