EP2984295A1 - Segment de bague d'étanchéité destiné à un stator de turbine - Google Patents
Segment de bague d'étanchéité destiné à un stator de turbineInfo
- Publication number
- EP2984295A1 EP2984295A1 EP14734785.0A EP14734785A EP2984295A1 EP 2984295 A1 EP2984295 A1 EP 2984295A1 EP 14734785 A EP14734785 A EP 14734785A EP 2984295 A1 EP2984295 A1 EP 2984295A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sealing ring
- ring segment
- turbine
- stator
- segment
- 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
- 238000007789 sealing Methods 0.000 title claims abstract description 53
- 238000002485 combustion reaction Methods 0.000 description 5
- 239000012530 fluid Substances 0.000 description 4
- 239000002775 capsule Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 229910016347 CuSn Inorganic materials 0.000 description 1
- 229910000990 Ni alloy Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 229910001026 inconel Inorganic materials 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 1
- 229910001235 nimonic Inorganic materials 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000012720 thermal barrier coating Substances 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
-
- 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
-
- 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
- F05D2260/30—Retaining components in desired mutual position
Definitions
- the invention relates to a sealing ring segment for a stator of a turbine, which essentially has the shape of a cylinder jacket segment and on its outer side has a groove for fixing a plurality of guide vanes.
- a turbine is a turbomachine, which is the inner one
- Blades and shaft are parts of the movable rotor or rotor of the turbine, which is arranged within a housing.
- Blades mounted on the axle are mounted on the axle. Blades mounted in a plane each form a paddle wheel or impeller. The blades are slightly curved profiled, similar to an aircraft wing.
- ⁇ wheel is usually a stator. These Leitschau ⁇ feln protrude from the housing into the flowing medium and put it in a twist. The swirl generated in the stator (kinetic energy) is used in the following impeller to set the shaft on which the impeller blades are mounted in rotation.
- the stator and the impeller together are called stages. Often several such stages are connected in series. Since the stator is stationary, and the vanes are attached to the housing exterior, a seal must be made to the shaft of the impeller to minimize losses as possible.
- the guide vanes are held on the rotor side by cylinder-jacket-shaped sealing rings. These consist übli ⁇ ch note of a plurality, normally ten segments. These are pushed onto an entanglement at the head of the guide vanes (tongue and groove connection) and thus seal off the hot gas duct in relation to the rotor.
- the sealing ring segments are individually fixed by bolts, each of which projects radially into one of the guide vanes.
- a disadvantage of the known sealing ring segments is that when using sheet or large disc springs always a large-scale bias is applied to a plurality of vanes. This complicates the assembly of the Leitschau- fine.
- the strength of the restoring force is not individu ⁇ ell adjustable or readjusted. It is therefore an object of the invention to provide a sealing ring segment of the type mentioned above, which allows a higher life ⁇ life and a lower repair cost for a turbine with a simple installation and high optimization.
- sealing ⁇ ring segment for each of the sealing ring segment fixable Leit ⁇ shovel in each case at least one force acting on the respective Leitschau ⁇ fel means of a restoring force pressure pin up has formed as a cylindrical element, wel ⁇ ches in compresses axial direction.
- the invention proceeds from the consideration that the Le ⁇ service life of the turbine is increased and the repair cost of the turbine could be reduced when the wear could be reduced by the relative movement of individual vanes and the sealing ring segment. For this, the relative ⁇ movement would have to be limited. However, consideration must be given to the thermal expansion during operation, so that a fixed form-locking fixation is eliminated.
- the remedy is a frictional fixation by means of a pressure ⁇ bolt, which ensures a kraftschlüs ⁇ sige fixation of the guide vane by its restoring force, while by the elasticity thermal expansion remains possible.
- a pressure pin is a substantially cylindrical element, which can be compressed in the axial direction, for example by an internal structure in the manner of a Kol ⁇ bens.
- the pressure pin z. B self-resetting by appropriate Fe ⁇ deran angel configured.
- the pressure pin can be fixed by a corresponding opening in the sealing ring segment and aligned accordingly.
- the vane is fixable in each case at least ⁇ provided a pressure acting on the respective guide vane by means of a restoring force for each pressure pin on the sealing ring segment.
- the sealing ring segment is particularly securely fixed, as a force ⁇ locking connection is created by a plunger with each vane. Therefore, none of the vanes can perform a wear-producing relative movement.
- the groove for fixing the guide vanes advantageously extends in the circumferential direction and / or the restoring force of the respective elastic element advantageously acts in the radial direction. This allows a simple assembly of the sealing ⁇ ring segment, which can be easily pushed onto the entanglement of the guide vanes. Due to the radial orientation of the elastic element this can be biased from the inside after insertion of the die ring.
- the respective elastic element in particular the pressure pin comprises a plate spring.
- a diaphragm spring is understood to mean a conical annular shell which can be loaded in the axial direction and thus can be stressed in both stationary and oscillating (dynamic). The power ⁇ introduction is normally done on the upper inner edge of the lower outer edge.
- the diaphragm spring can be used as a single spring or as a spring column. In a column, either individual plate springs or consisting of several springs spring assemblies can interact intimately layered ⁇ to.
- the diaphragm spring has in comparison with other types of springs a number of advantageous properties, it may, for. B. accommodate very large forces in a small installation space.
- the diaphragm spring has a long service life under dynamic load, as z. B. occurs in a turbine.
- Suitable materials include spring steels, also stainless and heat-resistant as well as copper (CuSn 8, CuBe 2) and nickel alloys (Nimonic, Inconel, Duratherm).
- the respective elastic element in particular the pressure pin by means of a screwing on Dichtringseg- fixed.
- a detachable connection which thus enables subsequent replacement in the course of an inspection, on the other hand is easy to mount laubt ⁇ .
- the restoring force on the entanglement of the guide blade is precisely adjusted by the depth of the screwing.
- an anti-rotation is provided, for example by a side hooking Vermosetechnisch- rungsbolzen.
- the respective elastic element for the circumferential fixation of the Dichtringseg ⁇ Mentes is arranged such that it fixes the respective guide vane in the circumferential direction positively.
- the guide vane has a corresponding recess into which the correspondingly executed elastic element is inserted.
- a stator for a turbine with a number of vanes is advantageously a majority of Leitschau ⁇ blades arranged at its radially inwardly directed head by means of a spring in a groove of a sealing ring segment described.
- a turbine advantageously comprises such a stator .
- the turbine is set as the gas turbine from ⁇ .
- the thermal, mechanical and dynamic loads are particularly high, so that the described embodiment of the sealing ring segment offers particular advantages with regard to the minimization of wear.
- a power plant advantageously comprises a derar ⁇ term turbine.
- the advantages achieved by the invention are, in particular, that by introducing a cup spring design for the defined fixed bias of the sealing ring and the vane, an avoidance of relative movements between the two parts is achieved. At the same time a thermal mobility is hereby ensured despite fixed bias.
- a defined tension between blades and sealing ring segments can be applied, which minimizes or prevents the relative movement, in particular under dynamic loads between the components. The material wear can thus be reduced or avoided.
- FIG. 1 shows a turbine 100, here a gas turbine, in a longitudinal partial section.
- the gas turbine 100 has inside a rotatably mounted around a rotation axis 102 (axial direction) rotor 103, which is also referred to as a turbine runner.
- a suction housing 104 Along the rotor 103 follow one another a suction housing 104, a compressor 105, a combustion chamber 110, shown here as an annular combustion chamber 106, with a plurality of coaxial ⁇ order burners 107, a turbine 108 and the Abgasgepatu ⁇ se 109th
- the combustion chamber 106 communicates with an annular hot gas channel 111.
- Each turbine stage 112 is formed from two blade rings. Seen in Strö ⁇ direction of flow of a working medium 113, in the hot ⁇ gas channel 111 a vane ring 115 is a ring formed from rotor acting ⁇ feln 120 125.
- the guide vanes 130 are secured to the stator 143, where ⁇ other hand, the rotor blades 120 of a ring 125 by means of a turbine disk 133 are attached to the rotor 103.
- the run ⁇ blades 120 thus form components of the rotor or Läu ⁇ fers 103. Coupled to the rotor 103 is a generator or a working machine (not shown).
- the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
- the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the highest thermal load in addition to the heat shield stones lining the combustion chamber 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
- Each vane 130 has a vane root (not shown) facing the housing 138 of the turbine 108 and a vane head opposite the vane root.
- the vane head faces the rotor 103 and is fixed in a sealing ring 140.
- Each sealing ring 140 of a turbine stage encloses the shaft of the rotor 103. It is advantageously formed from ten similar sealing ring segments 144.
- pressure bolts 146 are provided in the sealing ring segments 144, which are shown in cross section in FIG.
- the pressure ⁇ bolt 146 is aligned in a radial direction, through hole 148 with a thread 150 by screwing them fixed.
- the pressure pin consists of a cylindrical portion 152 with a corresponding thread for screwing with the sealing ring segment, an adjoining piston 154 with a smaller diameter, on which a movable in the axial direction of the pressure pin 146 Kap ⁇ sel 156 sits, the piston 154 at the Lace encloses. As a result, it is fixed positively in the radial direction of the pressure pin 146.
- the piston 154 between section 152 and capsule 156 enclosing a total of eight mutually arranged Tel ⁇ lerfedern 158 are positioned, which exert a restoring force at an axial compression of the pressure pin 146. Since the
- Pressure bolt 146 in the radial direction with respect to the axis of rotation of the gas turbine 102 in the sealing ring segment 144 is screwed ⁇ a , it exerts so a defined force on the Ver hooking of the guide vane 130, so that relative movements are prevented, but thermal expansion remains possible.
- the restoring force can set ⁇ .
- FIG. 3 shows a longitudinal section through the sealing ring segment 144.
- the sealing ring 144 has two grooves 160, both axially and radially spaced, which extend in the circumferential direction and are opened in the radial, respectively identical direction.
- the respective groove 160 is surrounded by a longitudinal cut ⁇ L-shaped portion of the sealing ring segment 144 environmentally whose first leg extending in the radial direction, and the second leg in the axial direction of the turbine 100th
- the sealing ring segment 144 can be pushed during assembly so on the Leit ⁇ blade ring.
- the pressure pin 146 is arranged in the region of the radially outer groove 160 such that the capsule 156 opens into an opening in the radially inner wall of the groove 160. Since the pressure pin 146 exerts a radial ⁇ ale restoring force which acts on the spring 162 in the groove 160, the spring 162 is thus tringsegments in the groove 160 against the radially-oriented leg of the L-shaped part of the dense 144 pressed. The vane 130 is thus elastically fixed in the grooves 160.
- the pressure pin 146 is secured against rotation by means of a bolt 164.
- the bolt 164 is inserted through a axially extending bore which meets the bore 148 of the pressure bolt 146 and screwed. As a result, it exerts a lateral force on the thread of the pressure bolt 146 and fixes it non-positively. 4 finally shows a partial section through the
- the pressure pin 146 exercise as described a restoring force on the Leit ⁇ blades 130 from.
- One of the push pins 146 is additional designed as circumferential fixing bolt 166. It is longer than the remaining pressure pin 146 and protrudes into a depression 168 of a foot of a guide blade 130 which is molded onto it. Since ⁇ by the sealing ring segment 144 is fixed on the guide vane 130 in the circumferential direction.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14734785.0A EP2984295B1 (fr) | 2013-06-28 | 2014-06-25 | Élément de bague d'étanchéité pour le stator d'une turbine |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13174357.7A EP2818642A1 (fr) | 2013-06-28 | 2013-06-28 | Elément de bague d'étanchéité pour le stator d'une turbine |
EP14734785.0A EP2984295B1 (fr) | 2013-06-28 | 2014-06-25 | Élément de bague d'étanchéité pour le stator d'une turbine |
PCT/EP2014/063432 WO2014207058A1 (fr) | 2013-06-28 | 2014-06-25 | Segment de bague d'étanchéité destiné à un stator de turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2984295A1 true EP2984295A1 (fr) | 2016-02-17 |
EP2984295B1 EP2984295B1 (fr) | 2017-05-03 |
Family
ID=48700406
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13174357.7A Withdrawn EP2818642A1 (fr) | 2013-06-28 | 2013-06-28 | Elément de bague d'étanchéité pour le stator d'une turbine |
EP14734785.0A Active EP2984295B1 (fr) | 2013-06-28 | 2014-06-25 | Élément de bague d'étanchéité pour le stator d'une turbine |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13174357.7A Withdrawn EP2818642A1 (fr) | 2013-06-28 | 2013-06-28 | Elément de bague d'étanchéité pour le stator d'une turbine |
Country Status (7)
Country | Link |
---|---|
US (1) | US10215041B2 (fr) |
EP (2) | EP2818642A1 (fr) |
JP (1) | JP6067942B2 (fr) |
CN (1) | CN105392966B (fr) |
RU (1) | RU2657390C2 (fr) |
SA (1) | SA515370314B1 (fr) |
WO (1) | WO2014207058A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP4053381A1 (fr) | 2021-03-01 | 2022-09-07 | ANSALDO ENERGIA S.p.A. | Dispositif de segment annulaire pour aubes de turbine d'une centrale électrique et ensemble turbine à gaz correspondant pour centrale électrique |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2018090307A1 (fr) * | 2016-11-18 | 2018-05-24 | Air Liquide (China) Holding Co., Ltd. | Buse d'entrée à faible frottement pour un turbo-détendeur |
FR3059041B1 (fr) * | 2016-11-21 | 2020-05-08 | Safran Aircraft Engines | Dispositif de pilotage rotor/stator avec lechette a ressort |
CN107882599B (zh) * | 2017-11-01 | 2021-02-09 | 中国航发湖南动力机械研究所 | 整体式涡轮外环连接结构及涡轮发动机 |
CN113294214B (zh) * | 2021-06-24 | 2022-07-22 | 上海万仞动力技术有限公司 | 一种装备有拼装隔板的冲动式汽轮机 |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB142924A (en) * | 1919-02-12 | 1920-05-12 | Samuel Hough | Improvements in adjustable rotary cutting heads for lathes |
US3501246A (en) * | 1967-12-29 | 1970-03-17 | Westinghouse Electric Corp | Axial fluid-flow machine |
US4576548A (en) | 1984-01-17 | 1986-03-18 | Westinghouse Electric Corp. | Self-aligning static seal for gas turbine stator vanes |
US4897021A (en) | 1988-06-02 | 1990-01-30 | United Technologies Corporation | Stator vane asssembly for an axial flow rotary machine |
DE19513457A1 (de) | 1995-04-08 | 1996-10-10 | Abb Management Ag | Rotor einer elektrischen Maschine |
US7291946B2 (en) * | 2003-01-27 | 2007-11-06 | United Technologies Corporation | Damper for stator assembly |
DE102004006706A1 (de) * | 2004-02-11 | 2005-08-25 | Mtu Aero Engines Gmbh | Dämpfungsanordnung für Leifschaufeln |
ES2344059T3 (es) | 2004-12-23 | 2010-08-17 | Siemens Aktiengesellschaft | Disposicion para la obturacion de un intersticio entre un primer componente y un segundo componente. |
JP4918263B2 (ja) * | 2006-01-27 | 2012-04-18 | 三菱重工業株式会社 | 軸流圧縮機の静翼環 |
US7645117B2 (en) * | 2006-05-05 | 2010-01-12 | General Electric Company | Rotary machines and methods of assembling |
US8001790B2 (en) * | 2008-08-11 | 2011-08-23 | Mitsubishi Heavy Industries, Ltd. | Gas turbine |
WO2010073783A1 (fr) * | 2008-12-25 | 2010-07-01 | 三菱重工業株式会社 | Aube de turbine et turbine à gaz |
JP5501609B2 (ja) | 2008-12-25 | 2014-05-28 | 三菱重工業株式会社 | タービン翼およびガスタービン |
US8454023B2 (en) * | 2011-05-10 | 2013-06-04 | General Electric Company | Retractable seal system |
-
2013
- 2013-06-28 EP EP13174357.7A patent/EP2818642A1/fr not_active Withdrawn
-
2014
- 2014-06-25 RU RU2016102766A patent/RU2657390C2/ru active
- 2014-06-25 EP EP14734785.0A patent/EP2984295B1/fr active Active
- 2014-06-25 US US14/898,135 patent/US10215041B2/en active Active
- 2014-06-25 CN CN201480035984.5A patent/CN105392966B/zh active Active
- 2014-06-25 JP JP2016522477A patent/JP6067942B2/ja not_active Expired - Fee Related
- 2014-06-25 WO PCT/EP2014/063432 patent/WO2014207058A1/fr active Application Filing
-
2015
- 2015-12-24 SA SA515370314A patent/SA515370314B1/ar unknown
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP4053381A1 (fr) | 2021-03-01 | 2022-09-07 | ANSALDO ENERGIA S.p.A. | Dispositif de segment annulaire pour aubes de turbine d'une centrale électrique et ensemble turbine à gaz correspondant pour centrale électrique |
Also Published As
Publication number | Publication date |
---|---|
WO2014207058A1 (fr) | 2014-12-31 |
US20160208630A1 (en) | 2016-07-21 |
RU2016102766A (ru) | 2017-08-01 |
SA515370314B1 (ar) | 2020-03-15 |
CN105392966A (zh) | 2016-03-09 |
JP6067942B2 (ja) | 2017-01-25 |
RU2016102766A3 (fr) | 2018-04-04 |
EP2984295B1 (fr) | 2017-05-03 |
US10215041B2 (en) | 2019-02-26 |
RU2657390C2 (ru) | 2018-06-13 |
JP2016523342A (ja) | 2016-08-08 |
EP2818642A1 (fr) | 2014-12-31 |
CN105392966B (zh) | 2018-03-20 |
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