EP2229507A2 - Gasturbine - Google Patents
GasturbineInfo
- Publication number
- EP2229507A2 EP2229507A2 EP08868596A EP08868596A EP2229507A2 EP 2229507 A2 EP2229507 A2 EP 2229507A2 EP 08868596 A EP08868596 A EP 08868596A EP 08868596 A EP08868596 A EP 08868596A EP 2229507 A2 EP2229507 A2 EP 2229507A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- cooling
- arrangement
- hot gas
- gas turbine
- guide vanes
- 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
Links
- 238000001816 cooling Methods 0.000 claims abstract description 58
- 238000002485 combustion reaction Methods 0.000 claims abstract description 24
- 238000011010 flushing procedure Methods 0.000 claims description 5
- 238000011144 upstream manufacturing Methods 0.000 claims description 5
- 238000010926 purge Methods 0.000 claims description 4
- 230000002000 scavenging effect Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 claims 2
- 239000007789 gas Substances 0.000 description 27
- 230000000694 effects Effects 0.000 description 6
- 230000007704 transition Effects 0.000 description 4
- 238000009826 distribution Methods 0.000 description 3
- 102100031118 Catenin delta-2 Human genes 0.000 description 2
- 101000922056 Homo sapiens Catenin delta-2 Proteins 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009828 non-uniform distribution Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- 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
- 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
- F05B2240/00—Components
- F05B2240/80—Platforms for stationary or moving blades
- F05B2240/801—Platforms for stationary or moving blades cooled platforms
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
Definitions
- the present invention relates to the field of gas turbine technology. It relates to a gas turbine according to the preamble of claim 1.
- Gas turbines have long been firmly established in power generation in their stationary form. These are high performance machines whose efficiency is constantly improving.
- An example of the achieved state of development is Applicant's type GT24 / GT26 gas turbines equipped with a 2-stage sequential combustion and described, for example, in the article F. Joos et al., Field Experience with the Sequential Combustion System of the GT24 / GT26 gas turbine family ", ABB review 5, pp.
- the first burner arrangement consists of premix burners, which have also become known in professional circles as EV-AEV burners, for example, EP-0321809 A1 or EP-0704657 A1, these publications as well as other publications relating to this technology form an integral part of this application.
- EV-AEV burners for example, EP-0321809 A1 or EP-0704657 A1
- SEV burners second burner arrangement
- the hot gas from the SEV burners is then relaxed in a low pressure turbine.
- the exhaust gases are then finally used for example to generate steam in a heat recovery steam generator.
- the hot gas flow hits the first row of the vanes of the low-pressure turbine.
- This configuration is e.g. in US-B1 -6, 751, 962 or EP-A2-1 505 254 and is shown in fragmentary detail in Fig. 1 of the present description, said references are an integral part of the present description.
- the hot gas 12 flowing out of the combustion chamber outlet 11 is incident on the leading edge of the vanes 15 of the first vane ring disposed at the entrance of the turbine.
- the Brennschauslass 1 1 is bounded laterally by a limiting element 19. Between the end of the limiting element 19 and the first row of guide vanes (15) there is a gap 16, which is sealed to the outside by an annular seal 17.
- cooling air is also injected through cooling holes 20, 21 in the limiting element, as in the o.g. US-B1 -6,751, 962 is described.
- the rapidly flowing hot gas produces various effects at the transition to the turbine.
- a rearward bow wave 13 is created, which faces the pressure gradient upstream of the suction side 24a, 24b, 24c, 24d towards the pressure side 25a, 25b, 25c. 25d is superimposed.
- a characteristic pressure distribution is generated by the complicated flow conditions in the burners or combustion chambers with swirling elements which are usually present at the combustion chamber outlet 11, which can be referred to as burner shaft 14.
- the object is solved by the entirety of the features of claim 1.
- Essential for the solution found is that the cooling holes are divided into first cooling hole groups and second cooling hole groups, that the arrangement of the first cooling hole groups corresponds to the arrangement of the guide vanes, and that the arrangement of the second cooling hole groups corresponds to the regular arrangement of the burners.
- the flows at the combustor outlet are non-uniform because of the configuration of the combustors with their fluid flows, local wall cooling effects, and leakage air.
- the invention relates to the interface of burner and turbine in gas turbines with 1 or 2 burner assemblies resp. Combustion chambers.
- the number of burners used, in particular, in the abovementioned combustion chambers is often not equal to the number of guide vanes, in particular smaller than the number of vanes.
- the burners are arranged in the second stage of a gas turbine with two-stage or sequential combustion.
- a further embodiment is characterized in that the cooling openings of the first cooling opening groups have an undefined position with respect to the leading edges of the guide vanes, typically slightly upstream from the leading edge, and the cooling openings of the second cooling opening groups are aligned transversely to the hot gas flow.
- a particularly preferred embodiment of the invention is characterized in that between the Brennschauslässen and the first row of guide vanes of the turbine, a circumferential gap is provided, which is flushed by circumferentially spaced flushing holes flushed with purging air, and that the flushing holes are divided into groups whose arrangement the arrangement of the vanes and / or the regular arrangement of the burner corresponds.
- Fig. 1 in a section a transition between the Brennschauslässen and the first row of guide vanes
- Fig. 2 is a schematic representation of the different periodicity of vanes and burners, according to which the arrangement of the cooling port groups according to the invention.
- FIG. 2 is a schematic representation of the different periodicity of vanes 15 a, b, c, d and burners 22 a, b, c reproduced, according to which the arrangement of the cooling holes 18, 20 and 21 is directed according to the invention.
- the cooling holes 20 according to FIG. 1, which are directed onto the guide vanes 15, are, as shown in FIG. 2, subdivided into cooling-opening groups 20a, b, c, and d, which form a series of cooling openings A distributed over the circumference. 2, each vane 15a, b, c, d is associated with a cooling port group 20a, b, c, d, the periodicity of the cooling port groups 20a, b, c, d being equal to the periodicity of the vanes 15a , b, c, d.
- the cooling port groups 20a, b, c, d are associated with the leading edges of the vanes 15a, b, c, d at which the bow shaft 13 is formed, as shown in FIG.
- the cooling holes are typically arranged somewhat on the pressure side of the front edges in order to even out the pressure difference from the pressure side to the suction side.
- the cooling openings 21, which inject cooling air transversely into the combustion chamber outlet 11, are likewise combined into cooling-opening groups, of which only one cooling-opening group 21 'is shown in FIG. 2 and indicates a series of cooling openings B.
- the periodicity of the cooling port groups 21 ' is equal to the periodicity of the burners 22a, b, c. In the example of FIG.
- the cooling opening groups 21 ' are arranged directly in the middle of the combustion chamber outlets and thus aligned with the burner lances 23 a, b lying in the middle.
- Other arrangements of the same periodicity are conceivable and depend on the specific flow conditions at the combustion chamber outlet.
- the cooling air openings 20, 21 can not only be provided cumulatively, but also be used as an alternative to each other, or be arranged alternately. The same considerations, cumulative, alternative or alternating, also applies with respect to the flushing openings 18.
- Opening groups can be introduced, which can be aligned either on the periodicity of the guide vanes 15a, b, c, d or the burner 22a, b, c or both.
- unequal distributions in the gap region which result from the superposition of bow waves 13 and burner waves 12, can be directly compensated.
- an embodiment not shown in the figures described is briefly commented. With reference to FIG. 1, embodiments are possible within the hot gas flow channel, in which not only an inner circumferential gap 16 is present in the circumferential direction, but also on the outer circumferential side of this hot gas flow channel also an outer circumferential gap is present, which largely fulfills the same attributes.
- first and / or second cooling opening groups (20, 21) are also provided in the region of this outer circumferential gap, which fulfill the same final purpose as in the region of the gap 16 shown.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH232008 | 2007-12-29 | ||
PCT/EP2008/067739 WO2009083456A2 (de) | 2007-12-29 | 2008-12-17 | Gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2229507A2 true EP2229507A2 (de) | 2010-09-22 |
EP2229507B1 EP2229507B1 (de) | 2017-02-08 |
Family
ID=39358154
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08868596.1A Not-in-force EP2229507B1 (de) | 2007-12-29 | 2008-12-17 | Gasturbine |
Country Status (3)
Country | Link |
---|---|
US (1) | US8783044B2 (de) |
EP (1) | EP2229507B1 (de) |
WO (1) | WO2009083456A2 (de) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2483529B1 (de) * | 2009-09-28 | 2013-08-28 | Siemens Aktiengesellschaft | Gasturbinendüsenanordnung und gasturbine |
EP2341217A1 (de) * | 2009-12-30 | 2011-07-06 | Siemens Aktiengesellschaft | Turbine zur Umwandlung von Energie und Verfahren zu ihrem Betrieb |
CN102667068A (zh) * | 2009-12-30 | 2012-09-12 | 西门子公司 | 用于转换能量的涡轮机及其操作方法 |
US10337404B2 (en) * | 2010-03-08 | 2019-07-02 | General Electric Company | Preferential cooling of gas turbine nozzles |
CH703105A1 (de) | 2010-05-05 | 2011-11-15 | Alstom Technology Ltd | Gasturbine mit einer sekundärbrennkammer. |
EP2754858B1 (de) * | 2013-01-14 | 2015-09-16 | Alstom Technology Ltd | Anordnung zum Abdichten eines offenen Hohlraums gegen Heißgaseinschluss |
JP6263365B2 (ja) | 2013-11-06 | 2018-01-17 | 三菱日立パワーシステムズ株式会社 | ガスタービン翼 |
WO2015130425A2 (en) * | 2014-02-03 | 2015-09-03 | United Technologies Corporation | Gas turbine engine cooling fluid composite tube |
US9752447B2 (en) * | 2014-04-04 | 2017-09-05 | United Technologies Corporation | Angled rail holes |
JP6546481B2 (ja) * | 2015-08-31 | 2019-07-17 | 川崎重工業株式会社 | 排気ディフューザ |
EP3141702A1 (de) * | 2015-09-14 | 2017-03-15 | Siemens Aktiengesellschaft | Gasturbinenleitschaufelsegment und verfahren zur herstellung |
DE102016217320A1 (de) * | 2016-09-12 | 2018-03-15 | Siemens Aktiengesellschaft | Gasturbine mit getrennter Kühlung für Turbine und Abgasgehäuse |
DE102019211418A1 (de) * | 2019-07-31 | 2021-02-04 | Siemens Aktiengesellschaft | Verfahren zur Modernisierung einer Gasturbinenanlage sowie Gasturbinenanlage |
Family Cites Families (31)
Publication number | Priority date | Publication date | Assignee | Title |
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GB980363A (en) | 1961-12-04 | 1965-01-13 | Jan Jerie | Improvements in or relating to gas turbines |
DE1252470B (de) * | 1964-08-14 | 1967-10-19 | Bordes Joseph Szydlowski (Frankreich) | Ringförmige Brennkammer, insbesondere für Gasturbinentriebwerke |
US3608310A (en) * | 1966-06-27 | 1971-09-28 | Gen Motors Corp | Turbine stator-combustor structure |
GB1488481A (en) * | 1973-10-05 | 1977-10-12 | Rolls Royce | Gas turbine engines |
US3965066A (en) * | 1974-03-15 | 1976-06-22 | General Electric Company | Combustor-turbine nozzle interconnection |
GB1492049A (en) * | 1974-12-07 | 1977-11-16 | Rolls Royce | Combustion equipment for gas turbine engines |
US4012167A (en) * | 1975-10-14 | 1977-03-15 | United Technologies Corporation | Turbomachinery vane or blade with cooled platforms |
US4026659A (en) * | 1975-10-16 | 1977-05-31 | Avco Corporation | Cooled composite vanes for turbine nozzles |
US4126405A (en) * | 1976-12-16 | 1978-11-21 | General Electric Company | Turbine nozzle |
US4733538A (en) * | 1978-10-02 | 1988-03-29 | General Electric Company | Combustion selective temperature dilution |
US4739621A (en) * | 1984-10-11 | 1988-04-26 | United Technologies Corporation | Cooling scheme for combustor vane interface |
US4821522A (en) * | 1987-07-02 | 1989-04-18 | United Technologies Corporation | Sealing and cooling arrangement for combustor vane interface |
CH674561A5 (de) | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
JPH03213602A (ja) * | 1990-01-08 | 1991-09-19 | General Electric Co <Ge> | ガスタービンエンジンの当接セグメントを連結する自己冷却式ジョイント連結構造 |
GB9305010D0 (en) * | 1993-03-11 | 1993-04-28 | Rolls Royce Plc | A cooled turbine nozzle assembly and a method of calculating the diameters of cooling holes for use in such an assembly |
GB9305012D0 (en) * | 1993-03-11 | 1993-04-28 | Rolls Royce Plc | Sealing structures for gas turbine engines |
DE4435266A1 (de) | 1994-10-01 | 1996-04-04 | Abb Management Ag | Brenner |
EP0902164B1 (de) * | 1997-09-15 | 2003-04-02 | ALSTOM (Switzerland) Ltd | Plattformkühlung für Gasturbinen |
DE19813779B4 (de) * | 1998-03-27 | 2005-04-14 | Rolls-Royce Deutschland Ltd & Co Kg | Anordnung zur Kühlung der Plattformen von Leitschaufeln einer Gasturbine |
JP4031590B2 (ja) | 1999-03-08 | 2008-01-09 | 三菱重工業株式会社 | 燃焼器の尾筒シール構造及びその構造を用いたガスタービン |
DE50109870D1 (de) * | 2001-03-26 | 2006-06-29 | Siemens Ag | Gasturbine |
FR2833035B1 (fr) * | 2001-12-05 | 2004-08-06 | Snecma Moteurs | Plate-forme d'aube de distributeur pour moteur a turbine a gaz |
US6758651B2 (en) * | 2002-10-16 | 2004-07-06 | Mitsubishi Heavy Industries, Ltd. | Gas turbine |
US7234304B2 (en) * | 2002-10-23 | 2007-06-26 | Pratt & Whitney Canada Corp | Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine |
DE10336432A1 (de) * | 2003-08-08 | 2005-03-10 | Alstom Technology Ltd Baden | Gasturbine und zugehöriges Kühlverfahren |
US7004720B2 (en) * | 2003-12-17 | 2006-02-28 | Pratt & Whitney Canada Corp. | Cooled turbine vane platform |
DE102004029696A1 (de) * | 2004-06-15 | 2006-01-05 | Rolls-Royce Deutschland Ltd & Co Kg | Plattformkühlanordnung für den Leitschaufelkranz einer Gasturbine |
US20060032233A1 (en) * | 2004-08-10 | 2006-02-16 | Zhang Luzeng J | Inlet film cooling of turbine end wall of a gas turbine engine |
US7806650B2 (en) * | 2006-08-29 | 2010-10-05 | General Electric Company | Method and apparatus for fabricating a nozzle segment for use with turbine engines |
US7857580B1 (en) * | 2006-09-15 | 2010-12-28 | Florida Turbine Technologies, Inc. | Turbine vane with end-wall leading edge cooling |
US8171634B2 (en) * | 2007-07-09 | 2012-05-08 | Pratt & Whitney Canada Corp. | Method of producing effusion holes |
-
2008
- 2008-12-17 WO PCT/EP2008/067739 patent/WO2009083456A2/de active Application Filing
- 2008-12-17 EP EP08868596.1A patent/EP2229507B1/de not_active Not-in-force
-
2010
- 2010-06-28 US US12/824,630 patent/US8783044B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2009083456A3 * |
Also Published As
Publication number | Publication date |
---|---|
WO2009083456A3 (de) | 2009-09-17 |
US20100313571A1 (en) | 2010-12-16 |
US8783044B2 (en) | 2014-07-22 |
WO2009083456A2 (de) | 2009-07-09 |
EP2229507B1 (de) | 2017-02-08 |
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