EP1580404A2 - Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine - Google Patents
Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine Download PDFInfo
- Publication number
- EP1580404A2 EP1580404A2 EP05090065A EP05090065A EP1580404A2 EP 1580404 A2 EP1580404 A2 EP 1580404A2 EP 05090065 A EP05090065 A EP 05090065A EP 05090065 A EP05090065 A EP 05090065A EP 1580404 A2 EP1580404 A2 EP 1580404A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- bridge
- elements
- vanes
- arrangement according
- radially
- 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
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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
- 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
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
-
- 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
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
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- 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
- F01D25/26—Double casings; Measures against temperature strain in casings
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- 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
- F05D2240/11—Shroud seal segments
Definitions
- the invention relates to an arrangement for automatic - Passive - Run column setting in a two- or multi-stage turbine inside an outer casing at least first and second rotors and these upstream, intermediate and downstream vanes.
- the distance (running gap, blade gap) between the moving Blade tips and their neighbors fixed housing parts must be big enough to with the strain behavior prevailing under transition conditions a rubbing together of the fixed and movable Prevent parts. This distance is then during a continuous operating condition too big to be efficient To ensure use of the supplied energy.
- the well-known "active" solutions for adjusting the size of the running gap include the supply of cold compressor air or hot combustion gases to the housing or to the liner segments (intermediate layers) connected to these, about their stretching or contraction the Gap size can be set active or the expansion behavior the stator to the thermal and dynamic Strain behavior of the rotor in the different Operating phases can be adjusted.
- the invention is based on the object, on the basis the known from GB 2061396 radial adjustment the liner segments according to the elongation and Contraction behavior of the rotor a passive arrangement Setting one in different phases of operation constant gap width for two or more stages Specify turbines.
- the at least two Rotors each associated with at least one expansion ring whose Expansion and contraction behavior when changing the thermal load is matched with that of the rotors.
- the expansion rings are directly upstream of the turbine and downstream vanes connected, so that the upstream and downstream vanes accordingly be adjusted to the thermal load.
- the outer ones Platforms of upstream and downstream vanes are over a bridge that is axial and circumferential fixed and movable in the radial direction is guided, interconnected.
- the intermediary Vanes are each between the rotors the movable bridge is mounted integrally or separately.
- the rolling and tilting moments acting on these are from the axially and circumferentially secured bridge elements and optionally an additional axial attachment recorded on the free blade side.
- At the so formed bridge are also the separate or integral trained shroud segments attached.
- This bridge construction is also the first time two-stage or multi-stage turbines a passive, for all Rotor stages individually optimized gap width adjustment according to the thermal rotor movement possible, the also cheaper than the previous two-stage Turbines known active systems for gap width adjustment is.
- the bridge a first half bridge and one at this axially, radially and circumferentially held second Half bridge, at the intermediate vanes are integrally formed.
- the first half bridge forms segmented inner housing spaced from the circumference rigid support segments, each with a Radial angle-free connecting strut with one on the outer housing attached rigid ring are firmly connected.
- the first half bridge can also have a system out Pin and sleeve radially slidably guided on the outer housing be.
- the bridge can Full bridge elements exist where the interposed Guide vanes and the shroud segments separately held or integrally attached and the intermediate Guide vanes on the free side in a circumferential groove are held.
- the full bridge elements are radially by means of a guided in a guide sleeve guided guide pin.
- a full bridge In yet another embodiment of a full bridge are the individual full bridge elements over a radial angle-free connecting strut connected to the outer housing.
- the connecting struts are either with a Groove held on a mounting ring or immediately with a mounted on the outer housing via a flange connected rigid ring.
- this embodiment is on the bridge elements a support segment with integrated Guide vane and integrated shroud segment axially and fixed in the circumferential direction.
- the axial Storage of bridge elements, supporting elements or interposed Vanes with a one-off style Piston ring trained mounting ring in a engages the groove formed on the component to be fixed.
- the bridges or the half-bridge elements (support elements) and the Full bridge elements by stiffening elements (ribs) stiffened.
- the first and second rotors 1, 2 is in each case a first or second Leitschaufelkranz with respectively upstream of first and second vanes 5, 6.
- the principle of radial adjustment of the distance from the blade tips 3a, 4a located first and a second shroud forming the first and second shroud segments 8a, 8b is substantially with the construction described in GB-A-2061396 and is therefore not shown here.
- each one-piece expansion ring (not shown) is associated with its expansion behavior corresponds to the adjacent rotor 1 and 2 respectively.
- the first rotor 1 associated with the expansion ring (not shown) is with the over the respective outer Platform 9 of the radial to the outer housing 10 of the turbine movably held first vanes 5 on the upstream side connected to the turbine while near the second rotor 2 arranged expansion ring (not shown) to an also radially movably mounted outer Platform 11 for a vane ring (not shown) connected to the downstream side of the turbine is.
- the radial movement of the vanes 5 on the inflow side and the downstream vanes 7 the downstream side is in each case by a double arrow 12th or 13 marked.
- the release of a first and a second Running gap 14, 15 the blade tips 3a, 4a opposite Shroud segments 8a, 8b are according to the from the expansion rings (not shown) on the one hand movable first vanes 5 and the outer Platform 9 and the other on the outer platforms 11 of the downstream vanes 7 of the rear Vane ring and from these on a bridge 16 transmitted movement relative to the blade tips 3a, 4a adjusted.
- the second half bridge 18 is integral with the intermediate vanes 6 and connected to the second shroud segments 8b.
- the first shroud segments 8a are in the present Embodiment made separately and at the bottom the first half bridge 17 and the outer platforms 9 of the first vanes 5 held.
- the first half bridge 17 consists of in the circumferential direction arranged, rigid by stiffening elements 30 trained support elements 19. Between the support elements 19 remains in each case a circumferential gap 20.
- a on the Support member 19 provided carrier 21 serves on the one hand for receiving or holding each of the first shroud segments 7 and on the other hand for axial and radial support the upstream end of the second half-bridge 18 each with integrated shroud segments 8 and second Guide vanes 6.
- the circumferentially of half-bridge elements 18 a existing second half-bridge 18, at which the second rotor 2 upstream second guide vanes 6 of the turbine and the second shroud segments 8b are fixed at the downstream end radially to the outer platforms 11 of the subsequent to the second rotor 2 (downstream) Guides (not shown) held.
- the second half bridge 18 is fixed to one with each Half-bridge element 18a connected web 25 the downstream side End of the circumferentially spaced support members 19 of the half-bridge 17 axially with a one-piece, Slotted mounting ring 26, radially with a Stop piece 27 and in the circumferential direction with retaining pins 28th
- any thermal expansion of the bridge 16 is defined by the circumferential column 20 between the Support elements 19 and the radial gap 24 was added. While the radial angle-free connecting struts 22nd any relative movement between the support elements 19th and the mounting ring 23 of the half bridge 17th balance between, allows the remaining between them Radial gap 24 thermal compensation.
- the half bridge 17 takes the rolling and tilting moments in the Half-bridge elements 18a of the second half-bridge 18 integrated second guide vanes 6, wherein the radial angle-free connecting struts 22 to the second (intermediate) blades 6 acting axial and Circumferential forces over the support element 19 by the Radial gap 24 separate rigid mounting ring 23 in lead the outer housing 10.
- Fig. 3 describes another embodiment of one two half bridges 17, 18 existing bridge 16, with their Help the rotors 1 and 2 of a two-stage turbine immediately upstream and downstream vanes 5, 7th Mounted together, to a passive, to the thermal Loading clearance adapted to the rotors to ensure.
- the release of circumferential gaps (not shown) arranged, stiffened support elements 19 of the first half bridge 17 are each with a separately manufactured first shroud segment 8a, that on the outer platform 9 of the first vane 5 is held.
- Half-bridge elements 18a of the second half-bridge 18, each integrally formed second rotor blades 6 and second shroud segments 8b are on the outer platform 11 of the downstream vanes 7 and on the respective support member 19 of the first half-bridge 17 held axially and radially.
- Guide sleeve 32 is the half bridge 17 and thus the bridge 16 (17, 18) a total of radially slidably guided and additionally also held axially and in the circumferential direction.
- a retaining ring 34 ( Figure 4) prevents rotation of the Bridge around the guide pin 31.
- FIGs 4, 5 and 6 show embodiments of the invention Assembly of vanes on vanes with the help of one of the vanes 5, 7 connecting Bridge 16 for passive run gap control in a two-stage Turbine in which the arranged in the circumferential direction Bridge elements a one-piece bridge 16 (full bridge) form and the individual full bridge elements 16a - As in the embodiment of FIG. 3 - by means of a from the housing 10 outgoing guide pin 31 and a formed on the full bridge elements 16a guide sleeve 32 are guided in the radial direction.
- the first and second shroud segments 8a, 8b and the second (intermediate) Guide vanes 6 integral part of the full bridge element 16a are for receiving the second vanes 6th outgoing tilting and rolling moments at the ends in the outer Platform 9 of the first vanes 5 and the outer Platform 11 of the second rotor 2 downstream Guides 7 held.
- the in the full bridge elements 16a integral second vanes 6 indicate its inner platform 6a a holding web 33 which in an annular groove of a circumferential retaining ring 34 received is to the respective second vanes 6 against Twisting to secure.
- Figures 7 and 8 show still other embodiments of the inventive design with mounted on vanes Guide vanes using a full bridge element 16a. It is with a separate first Shroud segment 8a formed full bridge element 16a the outer platform 9 of the first vane 5 and at the outer platform 11 of the downstream vanes 7 held. Between the outer housing 10 and the Full bridge elements 16a seals 35 are provided.
- stiffening elements 29 rigidly executed full bridge elements 16a - as in the embodiment with a half-bridge according to Fig. 1 - via a radial angle-free connecting strut 22 either by means of a fastening ring 26 (FIG. 7) or as in the embodiment of Fig. 1 - one on the outer housing 10 fixed rigid ring 23 (Fig.
- a transmission element 37 is provided in the case of axial attachment over the mounting ring 26 is for the derivation of the bridge perimeter load on the housing 10.
- the second vane 6 and the second shroud segment 8b form a one-piece - in the connection region 36a between the vane and shroud segment flexible Component 36, which on the bridge element 16a axially, radially and is fixed in the circumferential direction and also at the outer platform 11 is held axially.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- Fig. 1
- eine Teilansicht einer zweistufigen Turbine mit einer sich entsprechend dem Dehnungsverhalten der Rotoren selbsttätig einstellenden zweiteiligen Brücke und an dieser gehaltenen Deckbandsegmenten sowie einer zwischengeschalteten Leitschaufel;
- Fig. 2
- eine isometrische Ansicht einer in Richtung des Pfeils A in Fig. 1 gesehenen, ein segmentiertes Innengehäuse bildenden Halbbrücke der zweiteiligen Brücke;
- Fig. 3
- eine andere Ausführungsform einer aus Halbbrückenelementen gebildeten Brücke, die radial gleitend gelagert ist;
- Fig. 4
- eine aus radial gleitend geführten Vollbrückenelementen bestehende einstückige Vollbrücke mit in diese integrierten Deckbandsegmenten und zwischengeschalten Leitschaufeln;
- Fig. 5
- eine Vollbrücke nach Fig. 4, jedoch mit separat an dem jeweiligen Vollbrückenelement angebrachter Leitschaufel;
- Fig. 6
- eine Vollbrücke nach Fig. 4, bei der die Deckbandsegmente der ersten Stufe separat gefertigt und an dem Vollbrückenelement angebracht sind;
- Fig. 7
- eine Vollbrücke mit an den Vollbrückenelementen separat montierten Tragelementen und in diese integrierter Leitschaufel und Deckbandsegment, wobei die Vollbrückenelemente über einen Befestigungsring und mit diesem verbundener radial winkelfreier Verbindungsstrebe am Außengehäuse gehalten sind; und
- Fig. 8
- eine Vollbrücke gemäß Fig. 7, bei der die radial winkelfreien Verbindungsstreben mit einem am Außengehäuse befestigten steifen Ring fest verbunden sind.
- 1
- erster Rotor
- 2
- zweiter Rotor
- 3
- Rotorschaufel v. 1
- 3a
- Schaufelspitzen
- 4
- Rotorschaufel von 2
- 4a
- Schaufelspitzen
- 5
- erste (vorgeschaltete) Leitschaufeln
- 6
- zweite (zwischengeschaltete) Leitschaufeln
- 6a
- Innenplattform
- 7
- nachgeschaltete Leitschaufeln
- 8a, 8b
- erste/zweite Deckbandsegmente
- 9
- äußere Plattform v. 5
- 10
- Außengehäuse
- 11
- äußere Plattform v. 7
- 12
- Doppelpfeil (Radialbewegung)
- 13
- Doppelpfeil (Radialbewegung)
- 14
- erster Laufspalt
- 15
- zweiter Laufspalt
- 16
- Brücke
- 16a
- Vollbrückenelement
- 17
- erste Halbbrücke
- 18
- zweite Halbbrücke
- 17a, 18a
- Halbbrückenelement
- 19
- Tragelemente v. 17
- 20
- Umfangsspalt v. 17
- 21
- Träger v. 19
- 22
- radial winkelfreie Verbindungsstrebe
- 23
- steifer Ring v. 17
- 23a
- Befestigungsflansch
- 23b
- Bohrung
- 24
- Radialspalt v. 17
- 25
- Steg v. 18a
- 26
- Befestigungsring
- 27
- Anschlagstück
- 28
- Haltestifte
- 29
- Versteifungselemente v. 18
- 30
- Versteifungselemente v. 17
- 31
- Führungsstift
- 32
- Führungshülse
- 33
- Haltesteg
- 34
- Haltering
- 35
- Dichtung
- 36
- einstückiges Bauteil (Tragelement)
- 36a
- flexibler Verbindungsbereich
- 37
- Übertragungselement
Claims (15)
- Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine, die innerhalb eines Außengehäuses mindestens erste und zweite Rotoren sowie diesen vor-, zwischen- und nachgeschaltete Leitschaufeln umfasst, dadurch gekennzeichnet, dass den Rotoren (1, 2) jeweils ein Dehnring zugeordnet ist, der jeweils mit radial beweglichen vorgeschalteten Leitschaufeln (5) und mit radial beweglichen nachgeschalteten Leitschaufeln (7) verbunden ist und dessen thermisches Dehnungsverhalten dem der Rotoren (1, 2) entspricht, wobei die vor- und nachgeschalteten Leitschaufeln (5, 7) an ihren äußeren Plattformen (9, 11) über eine axial und in Umfangsrichtung fixierte und radial winkelfrei am Außengehäuse (10) der Turbine geführte Brücke (16, 17, 18) verbunden sind, an der die zwischengeschalteten Leitschaufeln (6) und die über den Rotoren (1, 2) angeordneten Deckbandsegmente (8a, 8b) befestigt sind.
- Anordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Brücke (16) eine erste Halbbrücke (17) und eine zweite Halbbrücke (18), die axial, radial und in Umfangsrichtung an der ersten Halbbrücke (17) gehalten ist, umfasst, wobei die zwischengeschalteten zweiten Leitschaufeln (6) integral mit der zweiten Halbbrücke (18) verbunden sind.
- Anordnung nach Anspruch 2, dadurch gekennzeichnet, dass die erste Halbbrücke (17) eine Mehrzahl jeweils unter Freilassung eines Umfangsspaltes (20) im Kreisumfang angeordnete biegesteife Tragelemente (19) und einen am Außengehäuse der Turbine befestigten steifen Ring (23) umfasst, mit dem die Tragelemente (19) über radial winkelfreie Verbindungsstreben (22) verbunden sind, wobei zwischen den freien Enden des Ringes und der Tragelemente ein Radialspalt (24) verbleibt.
- Anordnung nach Anspruch 2, dadurch gekennzeichnet, dass die erste Halbbrücke (17) und die zweite Halbbrücke (18) aus einer Mehrzahl im Kreisumfang angeordneter Halbbrückenelemente (17a, 18a) besteht und die ersten Halbbrückenelemente (17a) mittels einer an diesen jeweils angebrachten Führungshülse (32) und einem von dem Außengehäuse (10) ausgehenden Führungsstift (31) oder einer Nut-Federverbindung radial gleitend geführt sind.
- Anordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Brücke (16) aus einer Mehrzahl im Kreisumfang angeordneter Vollbrückenelemente (16a) besteht, die an den freien Enden in den äußeren Plattformen (9, 11) der vorgeschalteten und der nachgeschalteten Leitschaufeln (5, 7) gelagert sind.
- Anordnung nach Anspruch 5, dadurch gekennzeichnet, dass die zwischengeschalteten Leitschaufeln ((6) integral mit den Vollbrückenelementen (16a) verbunden sind.
- Anordnung nach Anspruch 5, dadurch gekennzeichnet, dass die zwischengeschalteten Leitschaufeln (6) separat gefertigt und axial, radial und in Umfangsrichtung an den Vollbrückenelementen (16a) fixiert sind.
- Anordnung nach Anspruch 6 oder 7, dadurch gekennzeichnet, dass die Vollbrückenelemente (16a) eine Führungshülse (32) aufweisen und an einem am Außengehäuse (10) angebrachten Führungsstift (31) radial gleitend geführt sind, und dass die zwischengeschalteten Leitschaufeln (6) jeweils einen Haltesteg (33) aufweisen, der in eine umlaufende Nut eines Halteringes (34) eingreift.
- Anordnung nach Anspruch 5, dadurch gekennzeichnet, dass die Vollbrückenelemente (16a) jeweils über radial winkelfreie Verbindungsstreben (22), die ein segmentiertes Innengehäuse bilden, am Außengehäuse (10) gehalten sind, wobei ein separates Tragelement (36), das radial, axial und in Umfangsrichtung an jedem Vollbrückenelement (16a) fixiert ist, integral mit der jeweiligen zwischengeschalteten Leitschaufel (6) und dem zweiten Deckbandsegment (8b) verbunden ist.
- Anordnung nach Anspruch 9, dadurch gekennzeichnet, dass die radial winkelfreien Verbindungsstreben (22) mittels einer an deren freiem Ende ausgebildeten Nut über einen Befestigungsring (26) am Außengehäuse (10) gehalten sind und die Vollbrückenelemente (16a) in Umfangsrichtung am Außengehäuse (10) gehalten sind.
- Anordnung nach Anspruch 9, dadurch gekennzeichnet, dass die radial winkelfreien Verbindungsstreben (22) mit einem am Außengehäuse (10) befestigten steifen Ring (23) fest verbunden sind.
- Anordnung nach Anspruch 9, dadurch gekennzeichnet, dass das Tragelement (36) für die zwischengeschaltete Leitschaufel (7) und das Deckbandsegment (8a) einen flexiblen Verbindungsbereich (36a) aufweist.
- Anordnung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass zwischen der äußeren Plattform (11) der nachgeschalteten Leitschaufeln (7) und dem Außengehäuse (10) und/oder dem Vollbrückenelement (16a) und dem Außengehäuse (10) Dichtungen angeordnet sind.
- Anordnung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass zur axialen Fixierung zwischen den Tragelementen (19) und den Halbbrückenelementen (18a) oder den Vollbrückenelementen (16a) und den separat ausgebildeten zwischengeschalteten Leitschaufeln (6) oder den Vollbrückenelementen (16a) und den Tragelementen (36) ein nach Art eines Kolbenringes ausgebildeter Befestigungsring (26) vorgesehen ist.
- Anordnung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Tragelemente (19), die Halbbrückenelemente (17a, 18a) und die Vollbrückenelemente (16a) durch Versteifungselemente (29, 30) versteift sind.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004016222A DE102004016222A1 (de) | 2004-03-26 | 2004-03-26 | Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine |
DE102004016222 | 2004-03-26 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1580404A2 true EP1580404A2 (de) | 2005-09-28 |
EP1580404A3 EP1580404A3 (de) | 2008-10-01 |
EP1580404B1 EP1580404B1 (de) | 2011-10-05 |
Family
ID=34854112
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05090065A Expired - Fee Related EP1580404B1 (de) | 2004-03-26 | 2005-03-16 | Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine |
Country Status (3)
Country | Link |
---|---|
US (2) | US7524164B2 (de) |
EP (1) | EP1580404B1 (de) |
DE (1) | DE102004016222A1 (de) |
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WO2008017681A1 (de) * | 2006-08-07 | 2008-02-14 | Abb Turbo Systems Ag | Axialturbine mit geschlitztem abdeckring |
EP1739309B1 (de) | 2005-06-29 | 2017-01-11 | Snecma | Mehrstufiger Turbomaschinenkompressor |
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DE102007031711A1 (de) | 2007-07-06 | 2009-01-08 | Rolls-Royce Deutschland Ltd & Co Kg | Gehäusedeckbandsegment-Aufhängung |
EP2184445A1 (de) * | 2008-11-05 | 2010-05-12 | Siemens Aktiengesellschaft | Axial segmentierter Leitschaufelträger für einen Gasturbine |
DE102008060706A1 (de) * | 2008-12-05 | 2010-06-10 | Man Turbo Ag | Düsensegment für eine Dampfturbine |
US8876458B2 (en) * | 2011-01-25 | 2014-11-04 | United Technologies Corporation | Blade outer air seal assembly and support |
JP5665724B2 (ja) * | 2011-12-12 | 2015-02-04 | 株式会社東芝 | 静翼翼列、静翼翼列の組立方法および蒸気タービン |
US9500095B2 (en) * | 2013-03-13 | 2016-11-22 | Pratt & Whitney Canada Corp. | Turbine shroud segment sealing |
EP2853685A1 (de) * | 2013-09-25 | 2015-04-01 | Siemens Aktiengesellschaft | Einsatzelement und Gasturbine |
US9266618B2 (en) | 2013-11-18 | 2016-02-23 | Honeywell International Inc. | Gas turbine engine turbine blade tip active clearance control system and method |
GB201507647D0 (en) * | 2015-05-05 | 2015-06-17 | Rolls Royce Plc | Casing assembly |
FR3045717B1 (fr) | 2015-12-22 | 2020-07-03 | Safran Aircraft Engines | Dispositif de pilotage de jeu en sommets d'aubes rotatives de turbine |
DE102016213810A1 (de) | 2016-07-27 | 2018-02-01 | MTU Aero Engines AG | Verkleidungselement für ein Turbinenzwischengehäuse |
US10641129B2 (en) * | 2017-11-08 | 2020-05-05 | United Technologies Corporation | Support rail truss for gas turbine engines |
US11174742B2 (en) | 2019-07-19 | 2021-11-16 | Rolls-Royce Plc | Turbine section of a gas turbine engine with ceramic matrix composite vanes |
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FR2548733B1 (fr) * | 1983-07-07 | 1987-07-10 | Snecma | Dispositif d'etancheite d'aubages mobiles de turbomachine |
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US5165850A (en) * | 1991-07-15 | 1992-11-24 | General Electric Company | Compressor discharge flowpath |
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DE19807247C2 (de) * | 1998-02-20 | 2000-04-20 | Mtu Muenchen Gmbh | Strömungsmaschine mit Rotor und Stator |
FR2794816B1 (fr) * | 1999-06-10 | 2001-07-06 | Snecma | Stator de compresseur a haute pression |
US6340285B1 (en) * | 2000-06-08 | 2002-01-22 | General Electric Company | End rail cooling for combined high and low pressure turbine shroud |
FR2835563B1 (fr) * | 2002-02-07 | 2004-04-02 | Snecma Moteurs | Agencement d'accrochage de secteurs en arc de cercle de distributeur porteur d'aubes |
GB2388407B (en) * | 2002-05-10 | 2005-10-26 | Rolls Royce Plc | Gas turbine blade tip clearance control structure |
US20040219011A1 (en) * | 2003-05-02 | 2004-11-04 | General Electric Company | High pressure turbine elastic clearance control system and method |
-
2004
- 2004-03-26 DE DE102004016222A patent/DE102004016222A1/de not_active Withdrawn
-
2005
- 2005-03-16 EP EP05090065A patent/EP1580404B1/de not_active Expired - Fee Related
- 2005-03-25 US US11/088,840 patent/US7524164B2/en not_active Expired - Fee Related
-
2009
- 2009-04-27 US US12/453,010 patent/US20090269190A1/en not_active Abandoned
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GB886626A (en) | 1958-09-04 | 1962-01-10 | Bristol Siddeley Engines Ltd | Improvements in or relating to axial flow turbines or compressors |
GB2061396A (en) | 1979-10-24 | 1981-05-13 | Rolls Royce | Turbine blade tip clearance control |
GB2226365A (en) | 1988-12-22 | 1990-06-27 | Rolls Royce Plc | Turbomachine clearance control |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1739309B1 (de) | 2005-06-29 | 2017-01-11 | Snecma | Mehrstufiger Turbomaschinenkompressor |
WO2008017681A1 (de) * | 2006-08-07 | 2008-02-14 | Abb Turbo Systems Ag | Axialturbine mit geschlitztem abdeckring |
EP1890011A1 (de) * | 2006-08-07 | 2008-02-20 | ABB Turbo Systems AG | Axialturbine mit geschlitztem Abdeckring |
Also Published As
Publication number | Publication date |
---|---|
EP1580404B1 (de) | 2011-10-05 |
US20050254939A1 (en) | 2005-11-17 |
US7524164B2 (en) | 2009-04-28 |
US20090269190A1 (en) | 2009-10-29 |
DE102004016222A1 (de) | 2005-10-06 |
EP1580404A3 (de) | 2008-10-01 |
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