EP1079070A2 - Wärmestaueinheit für eine Rotoranordnung - Google Patents
Wärmestaueinheit für eine Rotoranordnung Download PDFInfo
- Publication number
- EP1079070A2 EP1079070A2 EP00810682A EP00810682A EP1079070A2 EP 1079070 A2 EP1079070 A2 EP 1079070A2 EP 00810682 A EP00810682 A EP 00810682A EP 00810682 A EP00810682 A EP 00810682A EP 1079070 A2 EP1079070 A2 EP 1079070A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- heat accumulation
- accumulation unit
- rotor
- contour
- rotor disks
- 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
Images
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
- F01D11/001—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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
-
- 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
- F05D2240/40—Use of a multiplicity of similar components
Definitions
- the invention relates to a device for separating a hot Working area flowed through a preferably coolable, Space within a rotor arrangement of a turbomachine, preferably a gas turbine, with at least two axially one behind the other Rotor disks that can be firmly connected to one another via at least one connection area are and at least in the area of their radial peripheral edges from each other are spaced, and with a flat heat accumulation unit, which between two adjacent rotor disks are arranged and two connecting edges has, along which the heat accumulation unit in each case in the region of the peripheral edges the adjacent rotor disks can be brought into operative connection, and some Interspace extending between the two rotor disks on the rotor side covers.
- the heat accumulation units mainly serve to shape the interior a gas turbine provided hot gas channel on its facing the rotor Diameter and protects rotor structure parts against overheating.
- the heat accumulation units described above are part of axial turbomachines, flow through the gaseous working media for compression or targeted expansion and due to their high process temperatures, those with the hot working media subject the system components to direct thermal stress.
- rotating rotor components To protect a high heat input are known in the field the blade feet or the peripheral edges of the rotor disks are annular Heat accumulation units are provided, which are used for sealing the rotor with the Rotation shaft connected rotor disks opposite the hot flow channel to care.
- Figure 1 is a cross-sectional view through two adjacent rotor disks a screwed rotor shown, on the screw connection not in detail is received.
- the neighboring ones rotating about an axis of rotation A.
- Rotor disks 1, 2 see 3 receiving units on their peripheral peripheral edge for the connection of blades 4, 5 before. Here they open in the manner of a fir tree structure trained blade feet in corresponding counter contours in the rotor disks 1, 2.
- a guide vane 12 is introduced between the two adjacent rotor blades 4, 5 in the case of a gas turbine stage.
- Via screw connections 6, 7 is an annular between the two adjacent rotor disks 1, 2 Heat accumulation unit 8 firmly integrated.
- the heat accumulation unit 8 forms a closed one Contour with the outer radii of the rotor disks 1, 2 and enables in this way the separation of a cooling air fed into the rotor into the intermediate space 9 of the hot runner 10 located radially above the heat accumulation unit one is the heat accumulation unit 8 for reasons of its sealing function with the lowest possible Form sealing points, on the other hand, the construction of the heat accumulation unit 8 taking into account those acting on them due to the rotation Train centrifugal forces.
- FIG 2 shows the cross section through two rotor disks 1, 2 of a welded one Rotor arrangement shown.
- Welded Disc rotors require access after their preliminary assembly to the welds 11 between the rotor disks 1, 2.
- Da a closed ring-shaped heat accumulation unit 8 between the cavity 9 would close the rotor disks 1, 2, would be access to the Welded seams 11 of the rotor hindered.
- the invention has for its object to provide a device for separating a a hot working medium through which a room area flows within a rotor arrangement of a turbomachine in the form of a heat accumulation unit the above-mentioned genus in such a way that preferably in the case of completely pre-assembled rotor disc arrangements, the subsequent Integration of a heat accumulation unit is possible which is state of the art does not have the listed disadvantages.
- the heat accumulation unit should be possible to use the heat accumulation unit as a completely ring-shaped structure between two fixed pre-assembled rotor disks using an intimate but detachable joint bring in.
- the heat accumulation unit should also be of the highest degree Tightness between the flow channel and the space facing the rotor allow to have minimal seal gaps and a mechanical stable and stress-optimized shape and geometry.
- the invention is based on a device for separating one with a hot one Working medium flowing through a room area from a room area within a rotor arrangement of a fluid flow machine, preferably a gas turbine, the provides at least two rotor disks arranged axially one behind the other.
- the rotor disks are firmly connected to one another via at least one connection area, for example by a welded joint, being in the area of their radial peripheral edges are spaced apart.
- the flat heat accumulation unit has a toothed contour with web-shaped connecting elements and the connecting elements spaced spaces.
- the heat accumulation unit (8) roughly corresponding toothed counter contour (13, 14) is provided such that the connecting elements (17) with the toothed counter contour can be brought into a form-fitting, releasably firm connection.
- each individual connecting element is seen to be form-fitting Connect at least one molding section before that of the rest of the contour of the connecting element protrudes.
- the mold section can be as Dovetail extension or in the simplest sense transverse to Be longitudinal extension of the connecting element bent.
- each is in the area of the peripheral edge of the rotor disks, to the toothed contour the connecting edges of the heat accumulation unit approximately corresponding toothed Counter contour provided, with raised teeth, which each provide recesses, the exact fit of a counter contour corresponding to the shaped sections correspond.
- the one based on the construction according to the invention can be used Use the joining mechanism for segmented heat accumulation units that are in angular series in a row around the circumferential edge of the rotor disks complete annular heat accumulation unit can be assembled.
- the counter contour provided in the area of the peripheral edge of the rotor disks into which the connecting edges of the heat accumulation unit designed according to the invention can be used can either be worked directly into the material of the rotor disks be, but also in the foot area to be inserted in the peripheral edge of the rotor disks Blades are provided.
- the heat accumulation unit has an axially circumferential counter contour corresponding curvature, the inner radius of which is approximately the outer radius the radially circumferential counter contour in the area of the peripheral edge of the rotor disk corresponds.
- the tooth elements of the heat accumulation unit are axially aligned with the interdental spaces within the counter contours located in the area of the peripheral edges - via the Slide rotor disks and at a certain axial position in which the Formed sections of the tooth elements on the connecting edges of the heat accumulation unit angular with the recesses in the raised teeth within the counter contour align, by interlocking with the counter contour by rotating in the circumferential direction.
- the shaped sections move precisely into the corresponding recesses the teeth contained in the opposite contour.
- the heat accumulation unit is secured radially.
- the heat accumulation unit can also provide additional fastening measures a further rotation in the circumferential direction are hindered, whereby the heat accumulation unit is securely fixed within the counter contour.
- Locking pins prevent twisting in the circumferential direction of the heat accumulation unit help.
- Figure 3 shows a schematic longitudinal section of a rotor arrangement through two Rotor disks 1, 2 are provided on their radial peripheral edge 3 rotor blades 4, 5 are.
- a guide vane 12 protrudes between the rotor blades 4, 5.
- Both rotor disks 1, 2 are permanently connected to one another via a weld seam 11 and rotate together around the axis of rotation A. In the peripheral area, close to their Circumferential edges see the rotor disks 1, 2 on opposite sides of the opposite contours 13, 14, into which the connecting edges 15, 16 protrude.
- the counter contours are 13, 14 incorporated into the material of the rotor disks 1, 2, but it is also possible as mentioned above, that the counter contours are part of the blade roots. Combinations of both configurations are nevertheless also possible.
- the rotor blade feet are positively connected to the rotor via an essentially axial Connection, e.g. fir tree connection, dovetail connection, connected.
- an essentially axial Connection e.g. fir tree connection, dovetail connection
- the counter contours 13, 14 and the connecting edges 15, 16 each have one serrated contour, which is designed to correspond to each other. So engages in illustrated case according to Figure 3, the connecting element 17 with its dovetail-like formed shaped section 18 into the corresponding recess 19th of the tooth 20 in the counter contour 13.
- FIG 4 is a section of a perspective view of a section through the rotor disks 1 and 2 are shown, which are fixed to one another via a weld seam 11 are connected.
- the rotor disk 1 has the counter contour 13 on the peripheral edge, which have a plurality of teeth 20 arranged side by side with teeth in between Interdental spaces 21 provides. The same applies to the counter contour 14 in the Rotor disc 2.
- the teeth 20 have recesses 19, which are shown in the Provide a dovetail cutout example.
- the heat accumulation unit is already in the assembled state between the rotor disks 1, 2 8 introduced, which has a curved flat shape.
- Your connecting edges 15, 16 have toothed elements 17 which have a shaped section in the lower region 18 provide, which is designed in the manner of a dovetail.
- the mold sections 18 sit in the cutouts 19 and secure on the basis their shape, the heat accumulation unit 8 radial direction.
- the tooth elements 17 are axially opposite placed between the teeth 21 of the counter contours 13, 14 and in Axial direction between the rotor disks 1, 2 shifted.
- the mold sections 18 are brought into register with the recesses 19, the heat accumulation unit 8 moved radially in the circumferential direction until the state shown in Figure 4 is reached.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- Figur 1
- schematisierte Längsschnittdarstellung durch einen geschraubten Rotor (Stand der Technik)
- Figur 2
- schematisierte Längsschnittdarstellung durch einen geschweißten Rotor (Stand der Technik),
- Figur 3
- schematisierte Längsschnittdarstellung durch zwei Rotorscheiben mit erfindungsgemäß ausgebildeter Wärmestaueinheit sowie
- Figur 4
- perspektivische Querschnittsdarstellung durch die Verzahnung der Wärmestaueinheit mit zwei sich gegenüberstehenden Rotorscheiben.
- A
- Rotationsachse
- 1
- Rotorscheibe
- 2
- Rotorscheibe
- 3
- Umfangsrand
- 4
- Laufschaufel
- 5
- Laufschaufel
- 6, 7
- Schraubverbindung
- 8
- Wärmestaueinheit
- 9
- Zwischenraum
- 10
- Heißgaskanal
- 11
- Schweißnaht
- 12
- Leitschaufel
- 13, 14
- Gegenkontur
- 15, 16
- Verbindungskante
- 17
- Verbindungselement
- 18
- Formabschnitt
- 19
- Aussparung
- 20
- Zahn
- 21
- Zahnzwischenraum
- 22
- Axialrichtung
Claims (16)
- Vorrichtung zur Abtrennung eines mit einem heißen Arbeitsmedium durchströmten Raumbereiches (10) von einem Raumbereich (9) innerhalb einer Rotoranordnung einer Strömungsmaschine, vorzugsweise einer Gasturbine, mit wenigstens zwei axial hintereinander angeordneten Rotorscheiben (1, 2), die über wenigstens einen Verbindungsbereich fest miteinander verbindbar sind und wenigstens im Bereich ihrer radialen Umfangsränder voneinander beabstandet sind, und mit einer flächig ausgebildeten Wärmestaueinheit (8), die zwischen zwei benachbarten Rotorscheiben (1, 2) angeordnet ist und zwei Verbindungskanten (15, 16) aufweist, entlang derer die Wärmestaueinheit (8) jeweils im Bereich der Umfangsränder der benachbarten Rotorscheiben in Wirkverbindung bringbar ist, und die einen rotorseitig sich zwischen beiden Rotorscheiben (1, 2) erstreckenden Zwischenraum (9) abdeckt,
dadurch gekennzeichnet, daß die Verbindungskanten (15, 16) der Wärmestaueinheit (8) jeweils eine gezahnte Kontur mit stegartig ausgebildeten Verbindungselementen (17) mit dazwischenbefindlichen Zwischenräumen (16) aufweisen, daß jeweils im Bereich des Umfangsrandes der Rotorscheiben (1, 2) eine, zu der gezahnten Kontur der Verbindungskanten (15, 16) der Wärmestaueinheit (8) in etwa korrespondierende gezahnte Gegenkontur (13, 14) vorgesehen ist, und daß die Verbindungselemente (17) mit der gezahnten Gegenkontur in eine formschlüssige, lösbar feste Verbindung bringbar sind. - Vorrichtung nach Anspruch 1,
dadurch gekennzeichnet, daß die Verbindungselemente jeweils wenigstens einen Formabschnitt (18) aufweisen, der die übrige Kontur des Verbindungselementes (17) überragt, und
daß die Gegenkontur (13, 14) Zähne (20) mit Aussparungen (19) aufweist, die der Ausbildung der Formabschnitte (18) entsprechen. - Vorrichtung nach Anspruch 2,
dadurch gekennzeichnet, daß die Formabschnitte (18) paßgenau in die Aussparungen (19) einführbar sind und eine formschlüssige Verbindung darstellen. - Vorrichtung nach Anspruch 2 oder 3,
dadurch gekennzeichnet, daß die Formabschnitte (18) an den Verbindungselementen (17) sowie die korrespondierenden Ausnehmungen (19) in Art einer Schwalbenschwanz-Verbindung ausgebildet sind. - Vorrichtung nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, daß die flächig ausgebildete Wärmestaueinheit (8) eine Flächenkrümmung aufweist, die in etwa der Krümmung des radialen Umfangsrand der Rotorscheiben (1, 2) entspricht. - Vorrichtung nach einem der Ansprüche 1 bis 4,
dadurch gekennzeichnet, daß die Verbindungskanten (15, 16) der flächig ausgebildeten Wärmestaueinheit (8) parallel zueinander verlaufen, und
daß die Wärmestaueinheit (8) senkrecht zu den Verbindungskanten (15, 16) gekrümmt ausgebildet ist. - Vorrichtung nach einem der Ansprüche 1 bis 6,
dadurch gekennzeichnet, daß die Wärmestaueinheit (8) aus einzelnen Wärmestausegmenten zusammengesetzt ist, die einzeln aneinandergrenzend die Rotorscheiben (1, 2) vollständig umschließen. - Vorrichtung nach Anspruch 7,
dadurch gekennzeichnet, daß die einzelnen Wärmestausegmenten radial oder axial montierbar sind. - Vorrichtung nach einem der Ansprüche 1 bis 8,
dadurch gekennzeichnet, daß die Wärmestaueinheit (8) aus einem einzigen zusammenhängenden ringförmigen Gebilde besteht. - Vorrichtung nach einem der Ansprüche 1 bis 9,
dadurch gekennzeichnet, daß die Formgebung wenigstens einer Rotorscheibe an der äußeren Peripherie ein axiales Überstreifen einer ringförmig ausgebildeten Wärmestaueinheit ermöglicht. - Vorrichtung nach Anspruch 10,
dadurch gekennzeichnet, daß die Zähne (20) an der Rotorscheibe (1, 2) bei Überstreifen der ringförmigen Wärmestaueinheit (8) über die Rotorscheibe (1, 2) in die Zahnzwischenräume (21) der Wärmestaueinheit (8) hineinragen. - Vorrichtung nach einem der Ansprüche 1 bis 9,
dadurch gekennzeichnet, daß die Rotorscheiben (1, 2) geschweißt, geschraubt, genietet oder anderweitig fest gegeneinander verfügt oder einstückig gearbeitet sind. - Vorrichtung nach einem der Ansprüche 1 bis 12,
dadurch gekennzeichnet, daß in den Umfangsrand der Rotorscheiben (1, 2) Laufschaufelfüße hineinragen, an denen die Gegenkontur (13, 14) vorgesehen ist, in die die gezahnte Kontur der Verbindungskanten (15, 16) eingreift oder
daß am Umfangsrand der Rotorscheiben (1, 2) selbst die Gegenkontur (13, 14) vorgesehen ist, in die die gezahnte Kontur der Verbindungskanten (15, 16) eingreift. - Vorrichtung nach Anspruch 7 oder 8,
dadurch gekennzeichnet, daß die Wärmestausegmente derart ausgebildet sind, daß ein axiales oder radiales Einführen in die Gegenkontur der Rotorscheibe (1, 2) möglich ist. - Vorrichtung nach Anspruch 9,
dadurch gekennzeichnet, daß die ringförmige Wärmestaueinheit (8) axialwärts in die Gegenkontur (13,14) der Rotorscheibe (1, 2) fügbar ist. - Vorrichtung nach einem der Ansprüche 1 bis 15,
dadurch gekennzeichnet, daß die formschlüssige, lösbar feste Verbindung zwischen der Wärmestaueinheit und der Rotorscheibe durch Verdrehen der Wärmestaueinheit in Umfangsrichtung erfolgt.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19940525A DE19940525A1 (de) | 1999-08-26 | 1999-08-26 | Wärmestaueinheit für eine Rotoranordnung |
DE19940525 | 1999-08-26 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1079070A2 true EP1079070A2 (de) | 2001-02-28 |
EP1079070A3 EP1079070A3 (de) | 2004-01-14 |
EP1079070B1 EP1079070B1 (de) | 2005-03-16 |
Family
ID=7919697
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00810682A Expired - Lifetime EP1079070B1 (de) | 1999-08-26 | 2000-07-31 | Wärmestaueinheit für eine Rotoranordnung |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP1079070B1 (de) |
DE (2) | DE19940525A1 (de) |
Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1264964A1 (de) * | 2001-06-07 | 2002-12-11 | Snecma Moteurs | Anordung für einen Turbomachinenrotor mit zwei durch einen Abstandshalter getrennten Scheiben |
WO2007023158A1 (de) * | 2005-08-23 | 2007-03-01 | Alstom Technology Ltd | Vorrichtung zur einbausicherung und fixierung eines hitzeschildelementes für eine rotoreinheit einer strömungsmaschine |
EP1898054A1 (de) * | 2006-08-25 | 2008-03-12 | ALSTOM Technology Ltd | Gasturbine |
CN101845996A (zh) * | 2009-01-14 | 2010-09-29 | 通用电气公司 | 用于在燃气轮机中减少二次空气流的装置和系统 |
CN101852100A (zh) * | 2009-03-24 | 2010-10-06 | 通用电气公司 | 用于涡轮级间密封环的方法和设备 |
CN101858257A (zh) * | 2009-04-02 | 2010-10-13 | 通用电气公司 | 燃气涡轮机内部流径遮盖件 |
WO2012056161A1 (fr) * | 2010-10-28 | 2012-05-03 | Snecma | Ensemble de disques de rotor pour une turbomachine |
EP2218879A3 (de) * | 2009-02-13 | 2012-12-05 | General Electric Company | Rotoranordnung mit Dichtung zwischen den Stufen |
EP2832952A1 (de) | 2013-07-31 | 2015-02-04 | ALSTOM Technology Ltd | Turbinenschaufel und Turbine mit verbesserter Abdichtung |
EP2930304A1 (de) * | 2014-04-11 | 2015-10-14 | United Technologies Corporation | Hitzeschildvorrichtung und -system für hochdruckverdichter |
EP3168205A1 (de) | 2015-11-12 | 2017-05-17 | General Electric Technology GmbH | Gasturbinenteil und verfahren zur herstellung solch eines gasturbinenteils |
FR3057016A1 (fr) * | 2016-09-30 | 2018-04-06 | Safran Aircraft Engines | Procede de conception d'un organe de rotor et organe de rotor ameliore |
EP3318724A1 (de) * | 2016-11-04 | 2018-05-09 | Siemens Aktiengesellschaft | Dichtsegment eines rotors sowie rotor |
DE102017220336A1 (de) * | 2017-11-15 | 2019-05-16 | Siemens Aktiengesellschaft | Dichtsegment eines Rotors sowie Rotor |
EP3078809B1 (de) | 2015-04-10 | 2019-07-03 | United Technologies Corporation | Rotierende m-förmige labyrinthdichtung |
WO2020025406A1 (de) * | 2018-08-02 | 2020-02-06 | Siemens Aktiengesellschaft | Rotor mit zwischen zwei rotorscheiben angeordnetem rotorbauteil |
US10612382B2 (en) | 2015-11-12 | 2020-04-07 | Ansaldo Energia Ip Uk Limited | Method for manufacturing gas turbine part |
FR3120894A1 (fr) * | 2021-03-19 | 2022-09-23 | Safran Aircraft Engines | Rotor de turbomachine, comprenant un anneau de joint a labyrinthe monte sur des viroles de disque |
CN117722235A (zh) * | 2024-02-18 | 2024-03-19 | 中国航发四川燃气涡轮研究院 | 双辐板涡轮盘 |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE950100C (de) * | 1955-04-10 | 1956-10-04 | Maschf Augsburg Nuernberg Ag | Zusammengesetzter Trommellaeufer fuer Kreiselmaschinen, insbesondere fuer Gasturbinen mit axialer Durchstroemrichtung |
GB848465A (en) * | 1957-06-14 | 1960-09-14 | Napier & Son Ltd | Rotors of multi-stage axial flow compressors or turbines |
JPS57168005A (en) * | 1981-04-10 | 1982-10-16 | Hitachi Ltd | Rotor structue for axial machines |
US5236302A (en) * | 1991-10-30 | 1993-08-17 | General Electric Company | Turbine disk interstage seal system |
JP2941698B2 (ja) * | 1995-11-10 | 1999-08-25 | 三菱重工業株式会社 | ガスタービンロータ |
EP0921273B1 (de) * | 1997-06-11 | 2003-12-03 | Mitsubishi Heavy Industries, Ltd. | Rotor für gasturbinen |
-
1999
- 1999-08-26 DE DE19940525A patent/DE19940525A1/de not_active Withdrawn
-
2000
- 2000-07-31 DE DE50009768T patent/DE50009768D1/de not_active Expired - Fee Related
- 2000-07-31 EP EP00810682A patent/EP1079070B1/de not_active Expired - Lifetime
Non-Patent Citations (1)
Title |
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None |
Cited By (37)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1264964A1 (de) * | 2001-06-07 | 2002-12-11 | Snecma Moteurs | Anordung für einen Turbomachinenrotor mit zwei durch einen Abstandshalter getrennten Scheiben |
FR2825748A1 (fr) * | 2001-06-07 | 2002-12-13 | Snecma Moteurs | Agencement de rotor de turbomachine a deux disques aubages separes par une entretoise |
US6655920B2 (en) | 2001-06-07 | 2003-12-02 | Snecma Moteurs | Turbomachine rotor assembly with two bladed-discs separated by a spacer |
WO2007023158A1 (de) * | 2005-08-23 | 2007-03-01 | Alstom Technology Ltd | Vorrichtung zur einbausicherung und fixierung eines hitzeschildelementes für eine rotoreinheit einer strömungsmaschine |
US7722319B2 (en) | 2005-08-23 | 2010-05-25 | Alstom Technology Ltd | Locking and fixing device for a heat shield element for a rotor unit of a turbomachine |
EP1898054A1 (de) * | 2006-08-25 | 2008-03-12 | ALSTOM Technology Ltd | Gasturbine |
US8182211B2 (en) | 2006-08-25 | 2012-05-22 | Alstom Technology Ltd. | Turbo machine |
CN101845996A (zh) * | 2009-01-14 | 2010-09-29 | 通用电气公司 | 用于在燃气轮机中减少二次空气流的装置和系统 |
CN101845996B (zh) * | 2009-01-14 | 2015-04-01 | 通用电气公司 | 用于在燃气轮机中减少二次空气流的装置和系统 |
EP2208860A3 (de) * | 2009-01-14 | 2012-12-05 | General Electric Company | Dichtung zwischen Stufen einer Gasturbine und zugehörige Gasturbine |
EP2218879A3 (de) * | 2009-02-13 | 2012-12-05 | General Electric Company | Rotoranordnung mit Dichtung zwischen den Stufen |
CN101852100A (zh) * | 2009-03-24 | 2010-10-06 | 通用电气公司 | 用于涡轮级间密封环的方法和设备 |
EP2236769A3 (de) * | 2009-03-24 | 2014-02-19 | General Electric Company | Verfahren und Vorrichtung für Turbinenzwischendichtungsringe |
CN101858257A (zh) * | 2009-04-02 | 2010-10-13 | 通用电气公司 | 燃气涡轮机内部流径遮盖件 |
EP2236767A3 (de) * | 2009-04-02 | 2014-04-23 | General Electric Company | Abdeckteil eines Innenströmungspfades einer Gasturbine |
WO2012056161A1 (fr) * | 2010-10-28 | 2012-05-03 | Snecma | Ensemble de disques de rotor pour une turbomachine |
FR2966867A1 (fr) * | 2010-10-28 | 2012-05-04 | Snecma | Ensemble de disques de rotor pour une turbomachine |
US9371742B2 (en) | 2010-10-28 | 2016-06-21 | Snecma | Set of rotor disks for a turbine engine |
GB2498321A (en) * | 2010-10-28 | 2013-07-10 | Snecma | Set of rotor discs for a turbomachine |
GB2498321B (en) * | 2010-10-28 | 2017-07-05 | Snecma | A set of rotor disks for a turbine engine |
EP2832952A1 (de) | 2013-07-31 | 2015-02-04 | ALSTOM Technology Ltd | Turbinenschaufel und Turbine mit verbesserter Abdichtung |
US9816393B2 (en) | 2013-07-31 | 2017-11-14 | Ansaldo Energia Ip Uk Limited | Turbine blade and turbine with improved sealing |
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US10612382B2 (en) | 2015-11-12 | 2020-04-07 | Ansaldo Energia Ip Uk Limited | Method for manufacturing gas turbine part |
FR3057016A1 (fr) * | 2016-09-30 | 2018-04-06 | Safran Aircraft Engines | Procede de conception d'un organe de rotor et organe de rotor ameliore |
WO2018082907A1 (de) * | 2016-11-04 | 2018-05-11 | Siemens Aktiengesellschaft | Dichtsegment eines rotors sowie rotor |
EP3318724A1 (de) * | 2016-11-04 | 2018-05-09 | Siemens Aktiengesellschaft | Dichtsegment eines rotors sowie rotor |
DE102017220336A1 (de) * | 2017-11-15 | 2019-05-16 | Siemens Aktiengesellschaft | Dichtsegment eines Rotors sowie Rotor |
WO2020025406A1 (de) * | 2018-08-02 | 2020-02-06 | Siemens Aktiengesellschaft | Rotor mit zwischen zwei rotorscheiben angeordnetem rotorbauteil |
US11339662B2 (en) | 2018-08-02 | 2022-05-24 | Siemens Energy Global GmbH & Co. KG | Rotor comprising a rotor component arranged between two rotor disks |
FR3120894A1 (fr) * | 2021-03-19 | 2022-09-23 | Safran Aircraft Engines | Rotor de turbomachine, comprenant un anneau de joint a labyrinthe monte sur des viroles de disque |
CN117722235A (zh) * | 2024-02-18 | 2024-03-19 | 中国航发四川燃气涡轮研究院 | 双辐板涡轮盘 |
CN117722235B (zh) * | 2024-02-18 | 2024-05-17 | 中国航发四川燃气涡轮研究院 | 双辐板涡轮盘 |
Also Published As
Publication number | Publication date |
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DE19940525A1 (de) | 2001-03-01 |
EP1079070B1 (de) | 2005-03-16 |
EP1079070A3 (de) | 2004-01-14 |
DE50009768D1 (de) | 2005-04-21 |
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