WO2010108876A1 - Axialturbomaschine mit axial verschiebbarem leitschaufelträger - Google Patents
Axialturbomaschine mit axial verschiebbarem leitschaufelträger Download PDFInfo
- Publication number
- WO2010108876A1 WO2010108876A1 PCT/EP2010/053663 EP2010053663W WO2010108876A1 WO 2010108876 A1 WO2010108876 A1 WO 2010108876A1 EP 2010053663 W EP2010053663 W EP 2010053663W WO 2010108876 A1 WO2010108876 A1 WO 2010108876A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- adjusting ring
- axial turbomachine
- ring
- housing
- leitschaufeltrager
- Prior art date
Links
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
-
- 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
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
-
- 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
- F05D2260/50—Kinematic linkage, i.e. transmission of position
Definitions
- the invention relates to an axial turbomachine with an axially displaceable Leitschaufeltrager.
- radial gaps between blades and the housing lead to significant losses in thermal efficiency.
- the axial turbomachine is for example a
- the gas turbine When starting and stopping the gas turbine, the radial gaps change over time. In addition, the radial gaps change when switching from part-load operation to full-load operation of the gas turbine.
- the gas turbine is designed so that the radial gap for the operating case, in which the radial gaps set as the smallest, are sufficiently large, so that there is virtually no contact between the blades and the housing. This has the consequence that in continuous operation of the gas turbine unnecessarily large radial gaps must be kept for this operating condition, which is associated with a significant loss of efficiency.
- the temporal change of the radial gaps is the result of different thermal inertia behavior of the individual components of the gas turbine, in particular of the rotor, of the rotor blades and of the housing.
- the temporal change of the radial gap causes the centrifugal force expansion, in particular of the blades, a transverse contraction of the rotor, a possible clearance in the axial bearing of the rotor, in particular in connection with the reversal of axial thrust under corresponding operating conditions of the gas turbine, a possibly occurring ovalization of the housing due to montagebe- permanent pretension and uneven heating of the housing.
- Offenlegungssch ⁇ ft DE 1 426 818 discloses an adjustment mechanism for moving the Leitschaufeltragers in Radial ⁇ chtung.
- eight longitudinally extending I-shaped segment carriers are distributed over the circumference of the axial turbine, at the inner end of the Leitschaufeltrager is hooked form fit.
- the mutually contacting surfaces of the flanges of the segment carriers and the Leitschaufeltrager are formed like a saw tooth to synchronous Langsverschiebung all Segmenttrager in a radial displacement of
- Ubersch ⁇ ng is also internally conical. Between two conical surfaces cylindrical Walzkorper are provided, which are aligned obliquely relative to the axial direction. By a relative rotation of the coupling ring against the shroud, the radial gap between the blade tips of the blades and the shroud can be adjusted.
- the Ubersch ⁇ ng executed in a relatively thick wall thickness deforms the in a relatively thin wall running executed collar ring in terms of elastic deformation, so adapted by turning the diameter of the shroud and thus the gap between the shroud and the blade ring can be adjusted. It is disadvantageous that the shroud is elastically deformed. Even over the circumference uniform gap setting is only partially possible due to the spaced apart with each other rolling body.
- the object of the invention is to provide a Axialturbomaschme with a high thermal efficiency, the device for Radialspaltem ein is relatively simple, reliable and accurate.
- the axial-turbomachinery has a rotor blade grille formed by rotor blades each having a radially outer, free-standing blade tip extending obliquely to the axis of the axial turbine cylinder, a housing in which the rotor blade grille is installed and which with its inner side forms the main flow channel of the axial flow belt. Bine defined, and the blade shroud enclosing and m the inside of the housing integrated Leitschaufel- carrier with a radially inner ring inside lying on the inside of the housing, the main flow channel is continued and the Leitschaufeltrager immediately adjacent to the blade tips to form a
- Radial gap between the envelope of the blade tips and the ring inner side is arranged, wherein the Rmgmnen- side substantially parallel to the blade tip and the Leitschaufeltrager is slidably mounted in the housing parallel to the axis of the Axialturbomaschme and has a collar which on the housing and on the Leitschau- feltrager truncated on contact surfaces and is rotatable about the axis of Axialturbomaschme, wherein the contact surfaces of the adjusting ring and of the housing and / or of the Leitsch Kirs are so employed to a plane perpendicular to the axis of the axial turbomachine plane, that when the adjusting ring is rotated about the axis of the axial turbomachine, the Leitschaufeltrager is axially displaceable by the adjusting ring.
- the critical operating state with regard to the radial gap during hot start is. If the axial turbomachine at ⁇ play, a Axialturbme, the critical operating condition is in terms of radial gaps during cold starts. Until the components of the housing have warmed up properly after starting and thermally expanded to a larger diameter, there is a risk that the blades will touch the housing with their blade tips. The critical phase of operation, which can be expected with small radial gaps, is about 5 to 10 minutes. To remedy the erfmdungsgeINE axially slidably provided in the axial turbomachine Leitschaufeltrager, which is axially displaceable by means of the adjusting ring.
- Characterized in that the ring inner side and the blade tips are arranged inclined to the axis of the axial ⁇ turbomachinery, can be produced by a corresponding axial displacement of the Leitschaufeltragers a change of the radial gap.
- the measure of the radial gap can be adapted to the correspondingly prevailing operating state of the axial turbomachine for a short time, whereby the smallest possible radial gap is always desired.
- the thermal efficiency is high in all operating states of the axial turbomachine.
- the axial turbomachine according to the invention may additionally have a known device for adjusting the radial gaps during operation of the axial turbomachine, so that the The device and the actuation of the adjusting ring according to the invention for the suitable axial displacement of the vane carrier can be operated simultaneously at the same time.
- After overcoming the starting phase of the axial turbomachine can be brought by appropriate actuation of the adjusting ring in its original starting position after the components have been thoroughly heated by the Leitschaufeltra ⁇ ger. Only during critical operating phases, for example, the Leitschaufeltrager can be moved accordingly.
- the Leitschaufeltrager has an outwardly radially extending, rotating Leitschaufeltragersteg with an outwardly open annular groove, m engages a radially inwardly extending, circumferential Gehausesteg, wherein in the annular groove between the Leitschaufeltragersteg and the
- the collar is arranged.
- the adjusting ring is preferably located at the bottom of the annular groove, whereby the adjusting ring is mounted radially from the annular groove during rotation. It is preferred that a fixing ring is provided between the adjusting ring and the Gehausesteg, which is attached to the Gehausesteg and is in axial motion for the Leitschaufeltragers with the adjusting ring in interaction.
- the fixing ring has on its side facing the adjusting ring side a first sawtooth profile and the adjustment ring preferably has, on its side facing the fixing ring side a second sawtooth profile, wherein the sawtooth profile in such a can nested grei ⁇ fen and slide against each other that when the adjusting ring is rotated axially is moved axially, the Leitschaufeltrager.
- the sawtooth profile in such a can nested grei ⁇ fen and slide against each other that when the adjusting ring is rotated axially is moved axially, the Leitschaufeltrager.
- the fixing ring is preferably fixed form fit to the Gehausesteg.
- the form gleichige fixing of the fixing ring for example, by a radially extending groove in the Gehausesteg is provided and engages in a corresponding pas ⁇ send trained nose of the fixing ring.
- the fixing ring is fixed to the Gehausesteg in memoris ⁇ chtung.
- the adjusting ring is mounted on the fixing ring with a roller bearing provided between the sawtooth profiles.
- the axes of rotation of the rolling bearings are in Radial ⁇ chtung the turbomachine. Due to the rolling bearings, the friction and wear on the sawtooth profiles during actuation of the adjusting ring is minimized, as a result of which the adjusting ring and the fixing ring have a long service life.
- a biasing device is preferably provided, which is truncated on the housing and acting on the Leitschaufeltragersteg counteracting the adjusting ring, so that is printed by the biasing device, the Leitschaufeltragersteg always on the adjusting ring.
- the biasing means is preferably a coil spring.
- the inside of the ring preferably curves, and preferably the upstream side of the ring
- Adjusting ring arranged on the Gehausesteg As a result, a compressive force can be exerted in the main flow direction when the guide blade carrier is displaced into the main flow direction by the adjusting ring.
- the biasing device is preferably arranged on the Gehausesteg.
- Adjusting the adjusting ring are preferably provided an adjusting rod and / or a hydraulic ram.
- FIG. 2 shows a longitudinal section through a conventional axial turbomaschme.
- a conventional Axialturbomaschme 101 ge ⁇ shows.
- the Axialturbomaschme 101 has a housing 2 with an inner side 3, with a main flow channel 4 is defined.
- a blade ring is arranged which is formed from a plurality of rotor blades 5 arranged distributed over the circumference.
- Each of the rotor blades 5 has upstream of a front edge 6 and downstream of a trailing edge 7. Radially outward, the blade 5 is bounded by a blade tip 8.
- the main flow channel 4 is traversed in Figure 2 from left to right in the main flow direction, wherein the main flow channel 4 expands in the main flow direction.
- the inner side 3 of the housing 2 is arranged inclined relative to the axis 22 of the Axialturbomaschme 101.
- a Leitschaufeltrager 10 Radially in the region of the blade tip 8, a Leitschaufeltrager 10 is provided in the housing 2.
- the Leitschaufeltrager 10 facing the axis 22 of the Axialturbomaschme 101 facing a ring inner side 11, which runs parallel to the blade tip 8. Between the ring inner side 11 and the blade tip 8, a radial gap 12 is formed.
- the Leitschaufeltrager 10 has a radially outwardly extending Leitschaufeltragersteg 13, which has an outwardly opening, circumferential annular groove 9.
- a Gehausesteg 14 is provided on the housing 2, which extends radially inwardly and is circumferential.
- the vane trolley 10 is secured to the housing ridge 14 with fasteners such that the vane carrier 10 is stationary.
- 1 shows a section of a Erflndungsgeclaren Axialtur- bomaschine shown.
- the inventive axial flow turbomachine is different from the conventional axial flow turbomachine 101, as shown in FIG 2, is that the guide vane is axially slidably feltrager ⁇ arranges the Gehausesteg 14 10th
- the annular groove 9 is of an axially wider design, with an additional annular groove 9 upstream of the housing web 14
- the fixing ring 15 has, on its annular ring-shaped side facing the adjusting ring 16, a first saw tooth profile 17, the edges of which extend radially.
- a second sawtooth profile 18 is formed as the correspondence to the first sawtooth profile 17.
- the adjusting ring 16 has on its side facing away from the second sawtooth profile 18 a flat annular surface which lies flat against a side wall of the annular groove 9.
- the fixing ring 15 has at its the
- the adjusting ring 16 is rotatably mounted relative to the fixing ring 15 in the annular groove 9.
- the second sawtooth profile 18 is joined to the first sawtooth profile 17. puts. Due to the obliquely set flanks of the saw tooth profile 17 and 18, a changing axial position of the fixing ring 15 relative to the adjusting ring 16 results when the adjusting ring 16 is rotated.
- the compressive force serves as a restoring force for the Leitschaufeltrager 10, so that when the axial extent of the fixing ring 15 is reduced together with the adjusting ring 16 by the rotation of the adjusting ring 16, the Leitschaufeltrager 13 may follow the adjusting ring 16.
- the Leitschaufeltrager 10 is moved in the Hauptstromungs ⁇ chtung and the radial gap 12 verklemert.
- the base of the annular groove 9 is formed parallel to the axis of the axial bomax 1 and the radially inner edge of the housing web 14 rests against the bottom of the annular groove 9, so that when the Leitschaufeltrager 10 caused by an adjustment of the adjusting ring 16 axially back and forth is shifted, the Leitschaufeltrager 10 is mounted radially on the Gehausesteg 14.
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)
- Control Of Turbines (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2012501266A JP5346118B2 (ja) | 2009-03-26 | 2010-03-22 | 軸方向に変位可能なガイドベーンキャリアを有する軸流ターボ機械 |
US13/260,406 US9057281B2 (en) | 2009-03-26 | 2010-03-22 | Axial turbomachine having an axially displaceable guide-blade carrier |
PL10713598T PL2411632T3 (pl) | 2009-03-26 | 2010-03-22 | Osiowa maszyna wirnikowa z przemieszczalnym osiowo wspornikiem łopatki kierowniczej |
EP10713598.0A EP2411632B1 (de) | 2009-03-26 | 2010-03-22 | Axialturbomaschine mit axial verschiebbarem leitschaufelträger |
CN201080013989.XA CN102365426B (zh) | 2009-03-26 | 2010-03-22 | 具有可轴向移动的导向叶片支架的轴流式涡轮机 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09004409.0 | 2009-03-26 | ||
EP09004409A EP2233701A1 (de) | 2009-03-26 | 2009-03-26 | Axialturbomaschine mit axial verschiebbarem Leitschaufelträger |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2010108876A1 true WO2010108876A1 (de) | 2010-09-30 |
Family
ID=41327688
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2010/053663 WO2010108876A1 (de) | 2009-03-26 | 2010-03-22 | Axialturbomaschine mit axial verschiebbarem leitschaufelträger |
Country Status (6)
Country | Link |
---|---|
US (1) | US9057281B2 (de) |
EP (2) | EP2233701A1 (de) |
JP (1) | JP5346118B2 (de) |
CN (1) | CN102365426B (de) |
PL (1) | PL2411632T3 (de) |
WO (1) | WO2010108876A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104105844A (zh) * | 2012-02-02 | 2014-10-15 | 西门子公司 | 用于轴流式涡轮机的叶片环和用于调整叶片环的最大流率的方法 |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102012215413B4 (de) * | 2012-08-30 | 2020-04-02 | Rolls-Royce Deutschland Ltd & Co Kg | Baugruppe einer Axialturbomaschine |
EP2711504A1 (de) * | 2012-09-19 | 2014-03-26 | Siemens Aktiengesellschaft | Vorrichtung zum Überbrücken eines Spiels |
WO2015069328A2 (en) * | 2013-09-27 | 2015-05-14 | United Technologies Corporation | Gas turbine engine rapid response clearance control system |
US10323536B2 (en) * | 2015-04-09 | 2019-06-18 | United Technologies Corporation | Active clearance control for axial rotor systems |
US20190178159A1 (en) * | 2016-08-10 | 2019-06-13 | In2Rbo, Inc. | Multistage radial compressor and turbine |
KR102047328B1 (ko) * | 2017-12-21 | 2019-11-21 | 두산중공업 주식회사 | 가스터빈의 블레이드 팁 간극 제어장치 |
CN110374685A (zh) * | 2019-07-17 | 2019-10-25 | 中国航发沈阳发动机研究所 | 锯齿冠转子叶片非工作面侧向间隙控制方法及航空发动机 |
CN111980969B (zh) * | 2020-08-07 | 2022-09-23 | 中国人民解放军63837部队 | 用于超低温轴流压缩机的双层壳体 |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1426818A1 (de) | 1963-07-26 | 1969-03-13 | Licentia Gmbh | Einrichtung zur Radialverstellung von Segmenten eines Ringes einer Axialturbomaschine,insbesondere -gasturbine,der Leitschaufeln traegt und/oder Laufschaufeln umgibt |
US4932835A (en) * | 1989-04-04 | 1990-06-12 | Dresser-Rand Company | Variable vane height diffuser |
US6158956A (en) * | 1998-10-05 | 2000-12-12 | Allied Signal Inc. | Actuating mechanism for sliding vane variable geometry turbine |
EP1249577A1 (de) | 2001-04-12 | 2002-10-16 | Siemens Aktiengesellschaft | Gasturbine mit axial verschiebbaren Gehäuseteilen |
EP1900907A2 (de) * | 2006-09-08 | 2008-03-19 | Siemens Power Generation, Inc. | System zur Turbinenschaufelspitzen-Abstandsreduktion für einen Turbinenmotor |
US20080131270A1 (en) * | 2006-12-04 | 2008-06-05 | Siemens Power Generation, Inc. | Blade clearance system for a turbine engine |
DE102007003028A1 (de) | 2007-01-20 | 2008-07-24 | Mtu Aero Engines Gmbh | Turbomaschine |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3227418A (en) * | 1963-11-04 | 1966-01-04 | Gen Electric | Variable clearance seal |
CA1262033C (en) | 1983-12-05 | 1989-10-03 | EXTRA-EFFICIENT CRYSTALLIZATION COLUMN | |
JPS60187302U (ja) * | 1984-05-22 | 1985-12-12 | 株式会社東芝 | 蒸気タ−ビン |
JP2003286992A (ja) * | 2002-03-28 | 2003-10-10 | Mitsubishi Heavy Ind Ltd | ターボ分子ポンプ及びその調整方法 |
JP3907635B2 (ja) * | 2004-04-16 | 2007-04-18 | ファナック株式会社 | 電動機 |
-
2009
- 2009-03-26 EP EP09004409A patent/EP2233701A1/de not_active Withdrawn
-
2010
- 2010-03-22 EP EP10713598.0A patent/EP2411632B1/de not_active Not-in-force
- 2010-03-22 PL PL10713598T patent/PL2411632T3/pl unknown
- 2010-03-22 JP JP2012501266A patent/JP5346118B2/ja not_active Expired - Fee Related
- 2010-03-22 US US13/260,406 patent/US9057281B2/en not_active Expired - Fee Related
- 2010-03-22 WO PCT/EP2010/053663 patent/WO2010108876A1/de active Application Filing
- 2010-03-22 CN CN201080013989.XA patent/CN102365426B/zh not_active Expired - Fee Related
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1426818A1 (de) | 1963-07-26 | 1969-03-13 | Licentia Gmbh | Einrichtung zur Radialverstellung von Segmenten eines Ringes einer Axialturbomaschine,insbesondere -gasturbine,der Leitschaufeln traegt und/oder Laufschaufeln umgibt |
US4932835A (en) * | 1989-04-04 | 1990-06-12 | Dresser-Rand Company | Variable vane height diffuser |
US6158956A (en) * | 1998-10-05 | 2000-12-12 | Allied Signal Inc. | Actuating mechanism for sliding vane variable geometry turbine |
EP1249577A1 (de) | 2001-04-12 | 2002-10-16 | Siemens Aktiengesellschaft | Gasturbine mit axial verschiebbaren Gehäuseteilen |
EP1900907A2 (de) * | 2006-09-08 | 2008-03-19 | Siemens Power Generation, Inc. | System zur Turbinenschaufelspitzen-Abstandsreduktion für einen Turbinenmotor |
US20080131270A1 (en) * | 2006-12-04 | 2008-06-05 | Siemens Power Generation, Inc. | Blade clearance system for a turbine engine |
DE102007003028A1 (de) | 2007-01-20 | 2008-07-24 | Mtu Aero Engines Gmbh | Turbomaschine |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104105844A (zh) * | 2012-02-02 | 2014-10-15 | 西门子公司 | 用于轴流式涡轮机的叶片环和用于调整叶片环的最大流率的方法 |
Also Published As
Publication number | Publication date |
---|---|
JP2012521511A (ja) | 2012-09-13 |
JP5346118B2 (ja) | 2013-11-20 |
EP2233701A1 (de) | 2010-09-29 |
US20120076638A1 (en) | 2012-03-29 |
EP2411632A1 (de) | 2012-02-01 |
US9057281B2 (en) | 2015-06-16 |
EP2411632B1 (de) | 2013-06-19 |
CN102365426A (zh) | 2012-02-29 |
PL2411632T3 (pl) | 2013-11-29 |
CN102365426B (zh) | 2015-09-02 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2411632A1 (de) | Axialturbomaschine mit axial verschiebbarem leitschaufelträger | |
DE3941174C2 (de) | Spitzenspalt-Einstellvorrichtung für die Turbinenrotorschaufeln eines Gasturbinentriebwerks | |
DE69321776T2 (de) | Gasturbine | |
DE69509884T2 (de) | Leitschaufelanordnung für einen axialkompressor | |
DE69605045T2 (de) | Gehäuse einer gasturbine mit einer wärmedämmenden schicht, die die grösse des axialspaltes zwischen leuf-und leitschaufel reduziert | |
EP2723991B1 (de) | Schaufelanordnung | |
EP2304186B1 (de) | Axialturbomaschine mit geringen spaltverlusten | |
DE112016004554T5 (de) | Betätigungsvorrichtung für variable Statorschaufeln | |
EP3152407B1 (de) | Leitschaufelkranz, innenring und strömungsmaschine | |
WO2010112421A1 (de) | Axialturbomaschine mit passiver spaltkontrolle | |
CH703872A2 (de) | Befestigungsbolzen für eine verstellbare Leitschaufelanordnung. | |
EP1653049B1 (de) | Leitschaufelring einer Strömungsmaschine und zugehöriges Modifikationsverfahren | |
EP3324001B1 (de) | Dichtungsanordnung für eine leitschaufelanordnung einer gasturbine | |
EP2344723B1 (de) | Gasturbine mit dichtplatten an der turbinenscheibe | |
EP2520769A1 (de) | Innenring zur Bildung eines Leitschaufelkranzes, Leitschaufelkranz und Strömungsmaschine | |
EP1914388A1 (de) | Dichtelement zur Abdichtung eines Leckagespalts zwischen einem Rotor und einem Stator einer thermischen Strömungsmaschine. | |
EP2411631A1 (de) | Dichtplatte und laufschaufelsystem | |
EP2984295A1 (de) | Dichtringsegment für einen stator einer turbine | |
WO2009109430A1 (de) | Dichtungsanordnung und gasturbine | |
EP2526263A2 (de) | Gehäusesystem für eine axialströmungsmaschine | |
EP1731715A1 (de) | Übergangsbereich zwischen einer Brennkammer und einer Turbineneinheit | |
EP1731711A1 (de) | Übergang zwischen Brennkammer und Turbineneinheit, Hitzeschild und Turbinenleitschaufel für eine Gasturbine | |
DE10352789B4 (de) | Gasturbine | |
EP2982834B1 (de) | Wälzlager, insbesondere nadellager, zur anordnung an einem drehzapfen einer variablen leitschaufel einer strömungsmaschine | |
EP1965035B1 (de) | Minimierung der axialen Spalte an verstellbaren Leitgittern und am Konturring für Heissgasexpander |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WWE | Wipo information: entry into national phase |
Ref document number: 201080013989.X Country of ref document: CN |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 10713598 Country of ref document: EP Kind code of ref document: A1 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2010713598 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 3901/KOLNP/2011 Country of ref document: IN |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2012501266 Country of ref document: JP |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 13260406 Country of ref document: US |