EP2379846A1 - Leitschaufelsystem für eine strömungsmaschine mit segmentiertem leitschaufelträger - Google Patents
Leitschaufelsystem für eine strömungsmaschine mit segmentiertem leitschaufelträgerInfo
- Publication number
- EP2379846A1 EP2379846A1 EP10700394A EP10700394A EP2379846A1 EP 2379846 A1 EP2379846 A1 EP 2379846A1 EP 10700394 A EP10700394 A EP 10700394A EP 10700394 A EP10700394 A EP 10700394A EP 2379846 A1 EP2379846 A1 EP 2379846A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine
- vane
- segments
- guide
- gas turbine
- 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
- 239000000969 carrier Substances 0.000 title 1
- 238000002485 combustion reaction Methods 0.000 claims description 39
- 238000007789 sealing Methods 0.000 claims description 16
- 238000001816 cooling Methods 0.000 description 9
- 238000013461 design Methods 0.000 description 5
- 238000000576 coating method Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 230000011218 segmentation Effects 0.000 description 4
- 238000005266 casting Methods 0.000 description 3
- 239000011248 coating agent Substances 0.000 description 3
- 230000002028 premature Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 238000003466 welding 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
- 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
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F05D2230/80—Repairing, retrofitting or upgrading methods
Definitions
- a number of rotor blades which are usually combined into blade groups or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium.
- For flow guidance of the working medium are also usually connected between adjacent rows of blades with the turbine housing, too
- the invention is therefore based on the object of specifying a turbine guide vane carrier, in particular for a gas turbine, which, while maintaining a particularly high efficiency, enables a particularly simple exchange of individual vanes and is therefore designed for a particularly short repair duration.
- the vane of the first turbine stage ie the vane, which is the combustor chamber is closest to these highest temperatures and subject to the greatest wear. Accordingly, premature replacement as a result of damage caused by clogging of the cooling air bores (eg by inwardly oxidizing cooling air bores) is to be expected in particular in the case of this turbine guide vane.
- the vane support should therefore advantageously be segmented multiple times in the section of the vane row closest to a combustion chamber of the gas turbine.
- the upstream side portion of the turbine vane carrier should have more segments than the remaining portion of the turbine vane carrier.
- the guide blade fixation of a gas turbine should be provided in a meaningful manner such that undisturbed disassembly of an arbitrarily circumferentially located segment is ensured, so that, depending on the Position of the blade to be replaced only the affected, radially further outwardly disposed segment must be dismantled.
- the guide vane of the respective vane row with one of the segments of the remaining portion releasably connected. Thereby, after removal of the affected segment, the vane can be disassembled by releasing the connection with the segment of the section.
- the segments arranged in the inflow-side section thus do not serve for fastening guide vanes, but only for producing or maintaining the integrity of the gas turbine and possibly for separating spaces for cooling air with different pressures and / or temperatures.
- such a turbine guide vane carrier is used in a gas turbine.
- an outer housing of the gas turbine advantageously comprises a manhole through which easy access to the segments of the vane support for the installation personnel is possible.
- FIG. 9 shows a section through two adjacent vanes perpendicular to the turbine axis with clamping elements fixed sealing elements, and 10 shows a half section through a gas turbine.
- the vanes 6, 8 each comprise a blade root 10, 12 and a blade head 14, 16, via which their attachment to the other components takes place.
- the guide vanes 6, 8 of the first and second turbine stages are fastened to the guide blade carrier 1 with their blade roots 10, 12 and fixed to inner rings 18, 20 at their respective blade heads 14, 16.
- both the inner ring 20 and the vane support 1 include a plurality of cooling systems 22, which provide a cooling air supply to the vane support 1, the vanes 6, 8 and the inner ring 22 to sufficiently cool these components due to the high hot gas temperatures.
- the guide vane carrier 1 is segmented in many cases in the region of the first vane row.
- the guide blade carrier 1 comprises a number (in this case 12 pieces, see FIG. 3) of segments 24 in an inflow-side portion 23 and a guide-blade carrier 1 segmented in only one half 25 in a remaining portion 25. All segments 24, 26 are detachably connected to one another.
- the rest of the vane carrier is understood to be an upper and a lower half of a ring-shaped vane carrier which is annular in cross-section, as is already known in stationary gas turbines. In this case, two
- FIG. 3 shows a section perpendicular to the turbine axis through the guide vane carrier 1 at the level of the segments 24.
- a total of twelve segments 24 are provided, which are connected via flanges 52, for example with a screw connection.
- flanges 52 for example with a screw connection.
- the segmentation can also be done in other ways and adapted to the handling of the machine.
- the blade root 14 comprises a spring 36 which is inserted into a groove 38 of the inner ring 18.
- the guide vane of the first turbine stage 6 is fixed by means of a pin 60.
- the inner ring 18 is then inserted into the groove 56 of the combustion chamber hub 54.
- the blade root 14 a groove 62 for receiving a sealing plate 64, which is also located in the groove 58 of the combustion chamber hub 54.
- a plurality of guide vanes 6 are first to be unlocked and displaced in the circumferential direction, so that a guide Schaufei 6 comes out of engagement of the sealing plates 70 and can be expanded radially.
- a gas turbine 101 has a compressor 102 for combustion air, a combustion chamber 2 and a turbine unit 106 for driving the compressor 102 and a generator or a working machine (not shown).
- the turbine unit 106 and the compressor 102 are arranged on a common turbine shaft 108, also referred to as a turbine rotor, to which the generator or the working machine is also connected, and which is rotatably mounted about its turbine axis 109.
- the running in the manner of an annular combustion chamber 2 is equipped with a number of burners 110 for the combustion of a liquid or gaseous fuel.
- the turbine unit 106 has a number of rotatable blades 112 connected to the turbine shaft 108.
- the blades 112 are annularly disposed on the turbine shaft 108 and thus form a number of blade rows.
- the turbine unit 106 includes a number of stationary vanes 6, 8, 114, which are also attached in a donut-like manner to a vane support 1 of the turbine unit 106 to form rows of vanes.
- the blades 112 serve to drive the turbine shaft 108 by momentum transfer from the turbine unit 106 flowing through the working medium M.
- the vanes 6, 8, 114 serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
- a successive pair of a ring of vanes 114 or a row of guide vanes and of a ring of rotor blades 112 or a row of revolutions is also referred to as a turbine stage.
- Each vane 114 has a blade root 118, which is arranged to fix the respective vane 114 on a vane support 1 of the turbine unit 106 as a wall element.
- Each rotor blade 112 is fastened to the turbine shaft 108 in a similar manner via a blade root 119.
- each ring segment 121 is arranged on the guide blade carrier 1 of the turbine unit 106.
- the outer surface of each ring segment 121 is spaced apart in the radial direction from the outer end of the blades 112 lying opposite it by a gap. The between adjacent
- the combustion chamber 2 is configured in the exemplary embodiment as a so-called annular combustion chamber, in which a plurality of burners 110 arranged around the turbine shaft 108 in the circumferential direction open into a common combustion chamber space.
- the combustion chamber 2 is configured in its entirety as an annular structure, which is positioned around the turbine shaft 108 around.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10700394.9A EP2379846B1 (de) | 2009-01-21 | 2010-01-05 | Leitschaufelträger einer strömungsmaschine |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09000797A EP2211023A1 (de) | 2009-01-21 | 2009-01-21 | Leitschaufelsystem für eine Strömungsmaschine mit segmentiertem Leitschaufelträger |
EP10700394.9A EP2379846B1 (de) | 2009-01-21 | 2010-01-05 | Leitschaufelträger einer strömungsmaschine |
PCT/EP2010/050024 WO2010084028A1 (de) | 2009-01-21 | 2010-01-05 | Leitschaufelsystem für eine strömungsmaschine mit segmentiertem leitschaufelträger |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2379846A1 true EP2379846A1 (de) | 2011-10-26 |
EP2379846B1 EP2379846B1 (de) | 2019-11-06 |
Family
ID=40942519
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09000797A Withdrawn EP2211023A1 (de) | 2009-01-21 | 2009-01-21 | Leitschaufelsystem für eine Strömungsmaschine mit segmentiertem Leitschaufelträger |
EP10700394.9A Active EP2379846B1 (de) | 2009-01-21 | 2010-01-05 | Leitschaufelträger einer strömungsmaschine |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09000797A Withdrawn EP2211023A1 (de) | 2009-01-21 | 2009-01-21 | Leitschaufelsystem für eine Strömungsmaschine mit segmentiertem Leitschaufelträger |
Country Status (5)
Country | Link |
---|---|
US (1) | US9238976B2 (de) |
EP (2) | EP2211023A1 (de) |
JP (1) | JP5357270B2 (de) |
CN (1) | CN102282340B (de) |
WO (1) | WO2010084028A1 (de) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2442033A1 (de) * | 2010-10-12 | 2012-04-18 | Siemens Aktiengesellschaft | Brennkammerverhakungssegment und Brennkammeraußenschale |
EP2644833A1 (de) * | 2012-03-26 | 2013-10-02 | Alstom Technology Ltd | Trägerring |
EP2692995B1 (de) * | 2012-07-30 | 2017-09-20 | Ansaldo Energia IP UK Limited | Stationäre Gasturbinenmotor und Verfahren zur Durchführung von Instandhaltungsarbeit |
FR3008912B1 (fr) * | 2013-07-29 | 2017-12-15 | Snecma | Carter de turbomachine et procede de fabrication |
US10072516B2 (en) | 2014-09-24 | 2018-09-11 | United Technologies Corporation | Clamped vane arc segment having load-transmitting features |
DE102015224988A1 (de) * | 2015-12-11 | 2017-06-14 | Rolls-Royce Deutschland Ltd & Co Kg | Verfahren zur Montage einer Brennkammer eines Gasturbinentriebwerks |
DE102016201766A1 (de) * | 2016-02-05 | 2017-08-10 | MTU Aero Engines AG | Leitschaufelsystem für eine Strömungsmaschine |
JP6763157B2 (ja) * | 2016-03-11 | 2020-09-30 | 株式会社Ihi | タービンノズル |
US20180106155A1 (en) * | 2016-10-13 | 2018-04-19 | Siemens Energy, Inc. | Transition duct formed of a plurality of segments |
DE102017204953A1 (de) | 2017-03-23 | 2018-09-27 | MTU Aero Engines AG | Strömungsmaschine, Verfahren und Leitschaufelreihensystem |
Family Cites Families (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2766963A (en) * | 1952-11-01 | 1956-10-16 | Gen Motors Corp | Turbine stator assembly |
US2851246A (en) * | 1956-10-24 | 1958-09-09 | United Aircraft Corp | Turbine or compressor construction and method of assembly |
US3300180A (en) * | 1964-11-17 | 1967-01-24 | Worthington Corp | Segmented diaphragm assembly |
US3302926A (en) * | 1965-12-06 | 1967-02-07 | Gen Electric | Segmented nozzle diaphragm for high temperature turbine |
US3963368A (en) * | 1967-12-19 | 1976-06-15 | General Motors Corporation | Turbine cooling |
US4011718A (en) * | 1975-08-01 | 1977-03-15 | United Technologies Corporation | Gas turbine construction |
DE3110098C2 (de) * | 1981-03-16 | 1983-03-17 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Turbinenleitschaufel für Gasturbinentriebwerke |
US4511306A (en) * | 1982-02-02 | 1985-04-16 | Westinghouse Electric Corp. | Combustion turbine single airfoil stator vane structure |
CA2031085A1 (en) * | 1990-01-16 | 1991-07-17 | Michael P. Hagle | Arrangement for sealing gaps between adjacent circumferential segments of turbine nozzles and shrouds |
DE19821889B4 (de) * | 1998-05-15 | 2008-03-27 | Alstom | Verfahren und Vorrichtung zur Durchführung von Reparatur- und/oder Wartungsarbeiten im Innengehäuse einer mehrschaligen Turbomaschine |
US6503051B2 (en) * | 2001-06-06 | 2003-01-07 | General Electric Company | Overlapping interference seal and methods for forming the seal |
EP1288574A1 (de) | 2001-09-03 | 2003-03-05 | Siemens Aktiengesellschaft | Brennkammeranordnung |
FR2831615B1 (fr) * | 2001-10-31 | 2004-01-02 | Snecma Moteurs | Redresseur fixe sectorise pour compresseur d'une turbomachine |
CN100406684C (zh) * | 2001-11-20 | 2008-07-30 | 阿尔斯通技术有限公司 | 气体涡轮组件 |
US6910854B2 (en) * | 2002-10-08 | 2005-06-28 | United Technologies Corporation | Leak resistant vane cluster |
US7094025B2 (en) * | 2003-11-20 | 2006-08-22 | General Electric Company | Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction |
FR2871844B1 (fr) * | 2004-06-17 | 2006-09-29 | Snecma Moteurs Sa | Montage etanche d'un distributeur de turbine haute pression sur une extremite d'une chambre de combustion dans une turbine a gaz |
EP1840337A1 (de) * | 2006-03-31 | 2007-10-03 | Siemens Aktiengesellschaft | Nut-Feder-Verbindung zwischen zwei Turbinenkomponenten einer Turbine |
WO2008012195A1 (de) * | 2006-07-24 | 2008-01-31 | Siemens Aktiengesellschaft | Verfahren zum herausdrehen einer ringhälfte eines insgesamt ringförmigen leitapparats aus einer unteren gehäusehälfte einer axial durchströmbaren, stationären strömungsmaschine, montagevorrichtung, montagevorrichtungsverbund und hilfshalbring hierfür |
US7824152B2 (en) * | 2007-05-09 | 2010-11-02 | Siemens Energy, Inc. | Multivane segment mounting arrangement for a gas turbine |
EP2199544B1 (de) * | 2008-12-22 | 2016-03-30 | Techspace Aero S.A. | Aufbau einer Leitschaufelstufe |
-
2009
- 2009-01-21 EP EP09000797A patent/EP2211023A1/de not_active Withdrawn
-
2010
- 2010-01-05 CN CN201080004513.XA patent/CN102282340B/zh not_active Expired - Fee Related
- 2010-01-05 EP EP10700394.9A patent/EP2379846B1/de active Active
- 2010-01-05 US US13/145,353 patent/US9238976B2/en not_active Expired - Fee Related
- 2010-01-05 WO PCT/EP2010/050024 patent/WO2010084028A1/de active Application Filing
- 2010-01-05 JP JP2011545707A patent/JP5357270B2/ja not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2010084028A1 * |
Also Published As
Publication number | Publication date |
---|---|
CN102282340A (zh) | 2011-12-14 |
US9238976B2 (en) | 2016-01-19 |
US20120039716A1 (en) | 2012-02-16 |
EP2379846B1 (de) | 2019-11-06 |
JP5357270B2 (ja) | 2013-12-04 |
EP2211023A1 (de) | 2010-07-28 |
JP2012515869A (ja) | 2012-07-12 |
CN102282340B (zh) | 2016-01-20 |
WO2010084028A1 (de) | 2010-07-29 |
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