WO2006100237A1 - Wärmestausegment - Google Patents
Wärmestausegment Download PDFInfo
- Publication number
- WO2006100237A1 WO2006100237A1 PCT/EP2006/060905 EP2006060905W WO2006100237A1 WO 2006100237 A1 WO2006100237 A1 WO 2006100237A1 EP 2006060905 W EP2006060905 W EP 2006060905W WO 2006100237 A1 WO2006100237 A1 WO 2006100237A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- joining
- radially
- contour
- axially
- heat
- 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
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
-
- 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
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
Definitions
- the invention relates to a heat spreader for local limitation of a flow channel within a flow rotating machine, in particular a gas turbine plant, opposite to a radially surrounding the flow channel stator housing, with two axially opposite joining contours, which are respectively engageable with two along the flow channel axially adjacent components.
- Heat accumulation segments of the type described above are part of axial flow-through turbomachines through which flow for compression or targeted expansion gaseous working media and due to their high process temperatures, the thermally heavily loaded with the hot working fluids system components.
- the guide vanes arranged axially one after the other in the rows of rotor blades and vanes are acted upon directly by the combustion gases produced in the combustion chamber.
- so-called heat accumulation segments which are provided on the stator side between two guide vanes arranged axially adjacent to one another, ensure a gas-tight bridge-like seal between the two axially adjacent one another arranged guide blade rows.
- Correspondingly designed heat accumulation segments can also be used along the rotor unit. These are each to be mounted on the rotor side between two axially adjacent rows of blades in order to protect rotor-internal areas from excessive heat input.
- FIG. 2 shows a partial longitudinal section through a gas turbine stage, in which a flow channel K is bounded radially inwardly by a rotor unit 1 and radially outside by a stator unit 2. Rotationally fixed to the rotor unit 1, blades 3 protrude radially in the flow channel K, which is flowed through axially in the rest of hot gases with the direction of arrow oriented flow direction.
- the flow channel K is bounded by stator vanes 4 attached to the stator, whose guide vanes 41 protrude radially into the flow channel K from the outside.
- the guide vanes 4 have for the gas-tight separation of the flow channel K relative to the stator-mounted components on a platform 42 which covers both the axial region immediately around the vane blade 41 as a one-piece component in the form of a balcony-like overhang 42 ', the area between two rows of vanes spans and radially opposite the blade tips.
- the guide vanes 4 are arranged in the circumferential direction of the gas turbine in each row of guide blades, it is true that within a row of guide vanes in the circumferential direction immediately adjacent arranged vanes 4 along their axial side edges 5 to connect gas-tight with each other. This purpose is served over the entire extent of the side edge 5 extending belt seal 6, which opens on both sides in corresponding grooves along the side edges of two adjacent vanes.
- the band seal 6 ensures, in particular, that the platform 42 cooling air supplied to the stator can not escape into the flow channel K and is therefore available through appropriate cooling channels within the guide vane for effective cooling of all the vane areas exposed to the hot gases.
- the object of the invention is to effectively counteract the above-described wear phenomena due to mechanical vibrations on the band seals provided between two guide vanes. It should be ensured that the maintenance intervals required to inspect these seals are considerably extended. Consequently, the assembly and disassembly effort, which is required for the inspection and, where appropriate, for the replacement of appropriate sealing materials, should be significantly reduced. In particular, it should not be necessary for the removal of individual guide vanes from the composite of a row of guide vanes to dismantle the entire number of vanes or at least segment regions of the number of vanes.
- the idea underlying the invention is fundamentally based on a separation of the guide vane platform 42 and the balcony-like platform section 42 ', which are integrally formed according to image representation in Figure 2. It is proposed that between two rows of blades axially extending portion separated by means of a separate, bridge-like heat dam segment, ie between each two axially adjacent vanes extends a heat shield segment and adjacent on both sides as possible gas-tight on the vanes. Corresponding to the number of vanes within a row of vanes, correspondingly many heat accumulation segments are provided in the circumferential direction, which accordingly form a series of heat stacks, along the axial extent of which the blades of a blade row circulate radially inward.
- Such a heat dissipation segment which basically serves for the local separation of a flow channel within a flow-rotating machine, in particular a gas turbine plant, with respect to a stator housing radially surrounding the flow channel, with two axially opposite joining contours, each in engagement with two axially adjacent components along the flow channel, in particular two Guide vanes, can be brought, according to the solution is designed such that a first of the two joining contours has a radially oriented recess with a conically shaped contour surface, to the radially a fastening pin with a conical outer contour from the side of a force adjacent to the first joining contour adjacent component is force applied.
- the first joining contour has a collar portion with a radially upper and lower collar surface, which is available in a counter-contoured receiving contour within the axially adjacent component by a joining force acting between the mounting pin and the conically shaped contour surface.
- the heat recovery segment according to the invention is releasably fixedly connected to a guide vane arranged axially adjacent only over a single joining region.
- the second joining region of the heat recovery segment which is axially opposite this joining region is loosely pressed against a radially oriented joining surface on a stator-supporting structure. If it is necessary to remove the heat release segment, the guide vane, which is in contact with the heat discharge segment via the loose press connection, can be separated by mere axial removal.
- the heat spreader segment can be easily separated from the other vane by loosening the joint by removing the respective vane in the circumferential direction from the stator supporting structure carrying the vane, whereby the joint connection to the heat spreader is automatically released. Since that is according to the solution according to the invention design features with respect to the joint structure, the solution according to the invention heat recovery segment will be described below with reference to a preferred embodiment.
- FIG. 2 shows a longitudinal section of a guide vane suspension within a gas turbine stage according to the prior art.
- FIG. 1 shows a partial longitudinal section through the stator-side suspension of a stator blade 4 and a heat shield segment 12 formed separately from the stator blade 4.
- the exemplary embodiment described in connection with FIG. 2, to the description of which reference is made to the introduction to the description, can also accommodate the stator blade 4 shown in FIG and the axially adjacent heat shield segment 12 to separate the flow channel K in a gastight manner with respect to the components 2 arranged on the stator side.
- a band-shaped sealing means 6, 14 which is respectively engaged with a circumferentially adjacent arranged heat spreader and a guide vane and in this way for a gas-tight seal between the flow channel K and the stator side arranged components 2 provides.
- the guide vane 4 is likewise supplied with cooling air, which is supplied to it via the cooling channel 16.
- the cooling air supplied in this area also has to be sealed off from the flow channel K, which is ensured by the band seal 6.
- the band seals 6 and 14 of the separately executed vane and heat dissipation segment 13 only one half the length, whereby the wear due to the unchanged occurring vibrations due to material abrasion occur significantly less in appearance. This makes it possible to extend the maintenance and possibly replacement intervals for the band seal significantly.
- the thermal damper segment 12 formed in accordance with the invention has two axially opposite joining contours 17, 18, of which the joining contour 18 is pressed against a surface region 20 of the stator-side support structure 7 only by force, via a radially oriented joining surface 19.
- a groove-shaped recess is provided within the radially oriented joining surface 19, within which a sealing means 21 is introduced.
- the second joining region 18 adjoins an axially adjacent guide blade 4 1 via a further axial joining surface 22, which, when appropriately assembled or disassembled, passes through Exclusive axial approach or removal (see arrow representations according to G and D) can be mounted or dismounted on the heat spreader segment 12.
- the first joining region 17 is provided, which is inscribed in the illustration according to FIG. 1 a by a circle A, and which is shown enlarged in accordance with the illustration in FIG. 1 b.
- the further embodiments thus refer to both FIGS. 1a and 1b.
- the joining region 17 of the heat spreader segment 12 has a collar section 23, which provides a radially upper and radially lower collar surface 24, 25.
- the collar portion 23 protrudes axially into a corresponding counter-contoured receiving contour 26 within the axially adjacent guide vane 4.
- the joining between the collar portion 23 and the receiving contour 26, which is more precisely provided in the foot region of the guide vane 4, takes place precisely, so that the joint at least in Radial direction has no clearance or tolerance. This is necessary in particular for a gas-tight and force-loaded pressing of the joining contour 18 against the support structure 7 in the surface region 20.
- the joining contour 17 has a radially oriented recess 27, which has a conically shaped contour surface 28.
- the radially oriented recess 27 is formed as a half-mold, wherein the conically shaped contour surface 28 axially facing the collar portion 23 is attached.
- the joining region 17 is also covered radially on the outside by an overhanging region 29 of the guide blade 4, with which the guide blade 4 is fastened in a stator-side support structure 7.
- an opening 30 is provided, in which a fastening pin 31, a spring element 32 and a helically shaped support member 33 are provided in the arrangement shown in the detailed illustration according to Figure 1 b.
- the mounting pin 31 has a conical outer contour 34 which, by radially lowering the mounting pin 31 in engagement with the conically shaped Contour surface 28 of the first joining contour 17 occurs.
- Radially outwardly lying, the mounting pin 31 has a cylindrically shaped portion 35 which abuts the radial guide within the opening 30 of the overhanging region 29.
- the tolerance-free joints of the upper and lower collar surfaces 24, 25 within the counter-contoured receiving contour 26 ensures a force-loaded seal in the region of the second joining region 18, as already described above. Even a reassembly of the vane 4 'is not hindered by the presence of the heat spreader segment 12. Rather, it is possible to bring the guide vane 4 'by axial approach according to the motion vector G with the second joining region 18 in contact.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Thermotherapy And Cooling Therapy Devices (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
- Materials For Medical Uses (AREA)
- Central Heating Systems (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP06725192A EP1861585B1 (de) | 2005-03-24 | 2006-03-21 | Wärmestausegment |
MX2007011754A MX2007011754A (es) | 2005-03-24 | 2006-03-21 | Segmento de acumulacion termica. |
DE502006005786T DE502006005786D1 (de) | 2005-03-24 | 2006-03-21 | Wärmestausegment |
BRPI0609313A BRPI0609313A8 (pt) | 2005-03-24 | 2006-03-21 | Segmento de retenção de calor |
AT06725192T ATE453780T1 (de) | 2005-03-24 | 2006-03-21 | Wärmestausegment |
AU2006226334A AU2006226334B8 (en) | 2005-03-24 | 2006-03-21 | Heat accumulation segment |
US11/859,984 US7658593B2 (en) | 2005-03-24 | 2007-09-24 | Heat accumulation segment |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102005013797A DE102005013797A1 (de) | 2005-03-24 | 2005-03-24 | Wärmestausegment |
DE102005013797.0 | 2005-03-24 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/859,984 Continuation US7658593B2 (en) | 2005-03-24 | 2007-09-24 | Heat accumulation segment |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2006100237A1 true WO2006100237A1 (de) | 2006-09-28 |
Family
ID=36599084
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2006/060905 WO2006100237A1 (de) | 2005-03-24 | 2006-03-21 | Wärmestausegment |
Country Status (9)
Country | Link |
---|---|
US (1) | US7658593B2 (de) |
EP (1) | EP1861585B1 (de) |
AT (1) | ATE453780T1 (de) |
AU (1) | AU2006226334B8 (de) |
BR (1) | BRPI0609313A8 (de) |
DE (2) | DE102005013797A1 (de) |
MX (1) | MX2007011754A (de) |
SI (1) | SI1861585T1 (de) |
WO (1) | WO2006100237A1 (de) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20180347399A1 (en) * | 2017-06-01 | 2018-12-06 | Pratt & Whitney Canada Corp. | Turbine shroud with integrated heat shield |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB721453A (en) * | 1951-10-19 | 1955-01-05 | Vickers Electrical Co Ltd | Improvements relating to gas turbines |
DE19619438A1 (de) * | 1996-05-14 | 1997-11-20 | Asea Brown Boveri | Wärmestausegment für eine Turbomaschine |
EP0844369A1 (de) * | 1996-11-23 | 1998-05-27 | ROLLS-ROYCE plc | Zusammenbau eines Schaufelrotors und dessen Gehäuses |
EP1099826A1 (de) * | 1999-11-10 | 2001-05-16 | Snecma Moteurs | Sicherungsvorrichtung für ein Turbinendeckband |
EP1293644A1 (de) * | 2001-09-12 | 2003-03-19 | ALSTOM (Switzerland) Ltd | Träger für Leitschaufel und Wärmestausegment |
Family Cites Families (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3362160A (en) * | 1966-09-16 | 1968-01-09 | Gen Electric | Gas turbine engine inspection apparatus |
US3391904A (en) * | 1966-11-02 | 1968-07-09 | United Aircraft Corp | Optimum response tip seal |
US3558237A (en) * | 1969-06-25 | 1971-01-26 | Gen Motors Corp | Variable turbine nozzles |
BE756582A (fr) * | 1969-10-02 | 1971-03-01 | Gen Electric | Ecran circulaire et support d'ecran avec dispositif de reglage de la temperature pour turbomachine |
US3825364A (en) * | 1972-06-09 | 1974-07-23 | Gen Electric | Porous abradable turbine shroud |
US3864056A (en) * | 1973-07-27 | 1975-02-04 | Westinghouse Electric Corp | Cooled turbine blade ring assembly |
US3892497A (en) * | 1974-05-14 | 1975-07-01 | Westinghouse Electric Corp | Axial flow turbine stationary blade and blade ring locking arrangement |
FR2416345A1 (fr) * | 1978-01-31 | 1979-08-31 | Snecma | Dispositif de refroidissement par impact des segments d'etancheite de turbine d'un turboreacteur |
FR2574473B1 (fr) * | 1984-11-22 | 1987-03-20 | Snecma | Anneau de turbine pour une turbomachine a gaz |
US5071313A (en) * | 1990-01-16 | 1991-12-10 | General Electric Company | Rotor blade shroud segment |
GB2245316B (en) * | 1990-06-21 | 1993-12-15 | Rolls Royce Plc | Improvements in shroud assemblies for turbine rotors |
US5169287A (en) * | 1991-05-20 | 1992-12-08 | General Electric Company | Shroud cooling assembly for gas turbine engine |
US5165847A (en) * | 1991-05-20 | 1992-11-24 | General Electric Company | Tapered enlargement metering inlet channel for a shroud cooling assembly of gas turbine engines |
US5593277A (en) * | 1995-06-06 | 1997-01-14 | General Electric Company | Smart turbine shroud |
GB2310255B (en) * | 1996-02-13 | 1999-06-16 | Rolls Royce Plc | A turbomachine |
FR2766517B1 (fr) * | 1997-07-24 | 1999-09-03 | Snecma | Dispositif de ventilation d'un anneau de turbomachine |
US5993150A (en) * | 1998-01-16 | 1999-11-30 | General Electric Company | Dual cooled shroud |
US6139257A (en) * | 1998-03-23 | 2000-10-31 | General Electric Company | Shroud cooling assembly for gas turbine engine |
FR2780443B1 (fr) * | 1998-06-25 | 2000-08-04 | Snecma | Anneau de stator de turbine haute pression d'une turbomachine |
US6183192B1 (en) * | 1999-03-22 | 2001-02-06 | General Electric Company | Durable turbine nozzle |
US6412149B1 (en) * | 1999-08-25 | 2002-07-02 | General Electric Company | C-clip for shroud assembly |
FR2803871B1 (fr) * | 2000-01-13 | 2002-06-07 | Snecma Moteurs | Agencement de reglage de diametre d'un stator de turbine a gaz |
US6726448B2 (en) * | 2002-05-15 | 2004-04-27 | General Electric Company | Ceramic turbine shroud |
US6902371B2 (en) * | 2002-07-26 | 2005-06-07 | General Electric Company | Internal low pressure turbine case cooling |
US7367776B2 (en) * | 2005-01-26 | 2008-05-06 | General Electric Company | Turbine engine stator including shape memory alloy and clearance control method |
US7438520B2 (en) * | 2005-08-06 | 2008-10-21 | General Electric Company | Thermally compliant turbine shroud mounting assembly |
FR2899274B1 (fr) * | 2006-03-30 | 2012-08-17 | Snecma | Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine d'une turbomachine |
FR2914350B1 (fr) * | 2007-03-30 | 2011-06-24 | Snecma | Enveloppe externe etanche pour une roue de turbine de turbomachine |
-
2005
- 2005-03-24 DE DE102005013797A patent/DE102005013797A1/de not_active Withdrawn
-
2006
- 2006-03-21 BR BRPI0609313A patent/BRPI0609313A8/pt active Search and Examination
- 2006-03-21 DE DE502006005786T patent/DE502006005786D1/de active Active
- 2006-03-21 AU AU2006226334A patent/AU2006226334B8/en not_active Ceased
- 2006-03-21 WO PCT/EP2006/060905 patent/WO2006100237A1/de not_active Application Discontinuation
- 2006-03-21 SI SI200630599T patent/SI1861585T1/sl unknown
- 2006-03-21 EP EP06725192A patent/EP1861585B1/de not_active Not-in-force
- 2006-03-21 MX MX2007011754A patent/MX2007011754A/es active IP Right Grant
- 2006-03-21 AT AT06725192T patent/ATE453780T1/de active
-
2007
- 2007-09-24 US US11/859,984 patent/US7658593B2/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB721453A (en) * | 1951-10-19 | 1955-01-05 | Vickers Electrical Co Ltd | Improvements relating to gas turbines |
DE19619438A1 (de) * | 1996-05-14 | 1997-11-20 | Asea Brown Boveri | Wärmestausegment für eine Turbomaschine |
EP0844369A1 (de) * | 1996-11-23 | 1998-05-27 | ROLLS-ROYCE plc | Zusammenbau eines Schaufelrotors und dessen Gehäuses |
EP1099826A1 (de) * | 1999-11-10 | 2001-05-16 | Snecma Moteurs | Sicherungsvorrichtung für ein Turbinendeckband |
EP1293644A1 (de) * | 2001-09-12 | 2003-03-19 | ALSTOM (Switzerland) Ltd | Träger für Leitschaufel und Wärmestausegment |
Also Published As
Publication number | Publication date |
---|---|
ATE453780T1 (de) | 2010-01-15 |
AU2006226334B2 (en) | 2009-09-10 |
DE502006005786D1 (de) | 2010-02-11 |
SI1861585T1 (sl) | 2010-04-30 |
AU2006226334A1 (en) | 2006-09-28 |
BRPI0609313A2 (pt) | 2010-03-09 |
US20080050224A1 (en) | 2008-02-28 |
DE102005013797A1 (de) | 2006-09-28 |
MX2007011754A (es) | 2007-12-05 |
AU2006226334B8 (en) | 2010-01-07 |
US7658593B2 (en) | 2010-02-09 |
BRPI0609313A8 (pt) | 2017-07-25 |
EP1861585A1 (de) | 2007-12-05 |
EP1861585B1 (de) | 2009-12-30 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1456506B1 (de) | Gasturbinenanordnung | |
DE102005045459B4 (de) | Mechanische Lösung zur Schienenhalterung von Turbinendüsen | |
DE102005017148B4 (de) | Drehdichtungsanordnung für Kühlkreisläufe von Turbinenschaufeln | |
EP1180196B1 (de) | Strömungsmaschine mit einem dichtsystem für einen rotor | |
EP3152407B1 (de) | Leitschaufelkranz, innenring und strömungsmaschine | |
EP2918913B1 (de) | Brennkammer einer Gasturbine mit äusserer und innerer Brennkammerwand | |
EP1183444B1 (de) | Strömungsmaschine sowie dichtelement für einen rotor einer strömungsmaschine | |
WO2000070191A1 (de) | Dichtsystem für einen rotor einer strömungsmaschine | |
EP3409897B1 (de) | Dichtungsanordnung für eine strömungsmaschine, verfahren zur herstellung einer dichtungsanordnung sowie strömungsmaschine | |
EP2728122B1 (de) | Dichtungsträgerfixierung für eine Strömungsmaschine | |
EP1848904B1 (de) | Dichtungselement zur verwendung in einer strömungsmaschine | |
DE60117337T2 (de) | Anordnung der Leitschaufelplattformen in einer Axialturbine zur Verminderung der Spaltverluste | |
EP1861583B1 (de) | Wärmestausegment | |
CH708764A2 (de) | Verriegelnde Abstandshalteranordnung zur Einführung in einen umlaufenden Befestigungsschlitz zwischen Plattformen benachbarter Laufschaufeln. | |
EP2960555A1 (de) | Bürstendichtungssystem zum abdichten eines spalts zwischen relativ zueinander bewegbaren bauteilen einer strömungsmaschine | |
EP1413715A1 (de) | Prallkühlung der Plattform einer Gasturbinenlaufschaufel | |
EP2173972A1 (de) | Rotor für eine axial durchströmbare strömungsmaschine | |
EP3287611A1 (de) | Gasturbine und verfahren zum aufhängen eines turbinen-leitschaufelsegments einer gasturbine | |
EP1861585B1 (de) | Wärmestausegment | |
WO2009095402A1 (de) | Kombination von bürstendichtung mit kolbenring für grosse dichtspalte | |
EP0945597A1 (de) | Turbinenleitschaufelanordnung für eine Gasturbinenanlage | |
EP0943785A1 (de) | Anordnung zur Befestigung einer Turbinenschaufel | |
DE102013109271A1 (de) | Ersetzbare Dichtungen für Turbomaschinenbaugruppen und Verfahren zum Einbau derselben | |
DE102019206432A1 (de) | Turbomaschinenschaufel | |
EP3256783A1 (de) | Heissgasführendes gehäuse |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
DPE1 | Request for preliminary examination filed after expiration of 19th month from priority date (pct application filed from 20040101) | ||
WWE | Wipo information: entry into national phase |
Ref document number: 2006725192 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: MX/a/2007/011754 Country of ref document: MX Ref document number: 2006226334 Country of ref document: AU Ref document number: 11859984 Country of ref document: US |
|
WWE | Wipo information: entry into national phase |
Ref document number: 07104194 Country of ref document: CO |
|
ENP | Entry into the national phase |
Ref document number: 2006226334 Country of ref document: AU Date of ref document: 20060321 Kind code of ref document: A |
|
WWP | Wipo information: published in national office |
Ref document number: 2006226334 Country of ref document: AU |
|
NENP | Non-entry into the national phase |
Ref country code: RU |
|
WWW | Wipo information: withdrawn in national office |
Ref document number: RU |
|
WWP | Wipo information: published in national office |
Ref document number: 2006725192 Country of ref document: EP |
|
WWP | Wipo information: published in national office |
Ref document number: 11859984 Country of ref document: US |
|
ENP | Entry into the national phase |
Ref document number: PI0609313 Country of ref document: BR Kind code of ref document: A2 |