EP2310635A1 - Shroud seal segments arrangement in a gas turbine - Google Patents
Shroud seal segments arrangement in a gas turbineInfo
- Publication number
- EP2310635A1 EP2310635A1 EP09800032A EP09800032A EP2310635A1 EP 2310635 A1 EP2310635 A1 EP 2310635A1 EP 09800032 A EP09800032 A EP 09800032A EP 09800032 A EP09800032 A EP 09800032A EP 2310635 A1 EP2310635 A1 EP 2310635A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cooling
- gas turbine
- heat
- turbine according
- segment
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000001816 cooling Methods 0.000 claims abstract description 105
- 239000002826 coolant Substances 0.000 claims abstract description 23
- 238000009825 accumulation Methods 0.000 claims description 14
- 125000006850 spacer group Chemical group 0.000 claims description 8
- 238000011084 recovery Methods 0.000 claims description 6
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 230000017525 heat dissipation Effects 0.000 claims 2
- 230000004907 flux Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000012720 thermal barrier coating Substances 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 210000003746 feather Anatomy 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
-
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- 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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
Definitions
- the present invention relates to the field of thermal machines. It relates to a gas turbine according to the preamble of claim 1.
- Gas turbines as described, for example, in the document DE-A1-196 19 438, have in the turbine part a rotor blade provided with rows of blades, which is surrounded concentrically at a distance from a housing. On the housing rings are formed, carrying vanes, which - as well as the blades on the rotor - extend into the hot gas channel formed between the rotor and housing. In the axial direction or in the direction of the hot gas flow, vanes and blade rows alternate. Between adjacent guide blade rows are distributed over the periphery to the outer boundary of the hot gas channel
- Heat damper segments arranged at which the blades with their blade tips move past, and which are supplied from a surrounding the heat shield segments annular space (ring cavity) with cooling air or other cooling medium.
- a baffle cooling method is used, in which the cooling medium through variously mounted openings in an impingement cooling plate passes through the inside of the hot gas channel limiting wall of the heat exchanger segment.
- the heat shields behind the turbine's front stage vanes are exposed to high heat flux loads, high heat flux loads occur in the area where the blades rotate past, and high heat flux loads also occur in the area of the stator blade wake Caster pressure waves (31 in Fig. 1 1) reduce the pressure margin (Back Flow Margin BFM), ie the available pressure difference between the hot gas duct and annular cavity, against a hot gas.
- Back Flow Margin BFM Back Flow Margin BFM
- a "failsafe design" over rubbing cracks, inter heat shield feather seals, partload, environmental conditions (off-ISO design), impact damage (FOD) and manufacturing tolerances require a significant margin on BFM. which has a negative impact on performance under full load ISO conditions.
- the number of vanes in the ring in conventional solutions is independent of the number of associated heat shield segments. If possible, the number of parts is minimized. As the thermal and mechanical loads on the vanes are higher, a larger number of vanes is needed compared to the number of heat shield segments.
- FIGS. 1 to 3 illustrate, in a simplified representation, various impingement cooling schemes in a gas turbine 10 on the basis of the heat accumulation segments 1 1 arranged between the first guide vanes V1 and the second guide vanes V2 in relation to the first moving blades B1.
- hot gas flows with a mass flow density m HG from right to left, wherein at the leading edge (Leading Edge LE) of the blade B1, a pressure P SILE and at the trailing edge (Trailing Edge TE) there is a pressure P SiTE .
- the hot gas duct 29 is bounded in the region of the blade B1 on the outside by the heat spreader segment 11, which is fastened by means of hook-shaped fastening elements 12, 13, 14 to a housing (not shown).
- the heat shield segment 1 1 is externally surrounded by a ring cavity 30 from which a standing under pressure P 1 or P 2 cooling medium, usually cooling air, via perforated
- Impingement cooling plates 15, 16 flows into two corresponding impingement cooling cavities 17, 18, there cools the heat discharge segment by impingement cooling and then exits through cooling holes 19, 20 in the hot gas channel 29.
- Pi P 2 , so that the cooling medium with the same mass flow density m c flows into the two impingement cooling cavities.
- the invention aims to remedy this situation. It is therefore an object of the invention to provide a gas turbine with impingement-cooled heat accumulation segments, which avoids the disadvantages of known solutions and is characterized in particular by a reduction of the cooling medium consumption.
- Heat dam segments and adjacent vanes in the rings is the same. As a result, maximum loads occurring locally, ie local cooling, are addressed. Margins and total Coolant consumption can be reduced considerably. This allows higher temperatures and lower cooling medium requirements for better performance and flatter temperature profiles for smaller emissions.
- An embodiment of the invention is characterized in that two impact cooling cavities, in which the cooling medium flows from the annular cavity, are arranged in the heat accumulation segment in each case in the axial direction, that the downstream impingement cooling cavity is separated from the annular cavity and both annular cavities with the cooling medium at the same pressure
- the heat accumulation segments each have a central, hook-shaped fastening element, the two impingement cooling cavities are separated from one another by the middle fastening element, and the downstream impingement cooling cavity is separated from the annular cavity by a cover plate arranged between impingement cooling cavity and annular cavity.
- Another embodiment is characterized in that in the impingement cooling cavities to increase the heat transfer, a plurality of posts is arranged distributed, wherein the plurality of posts spacers for the impingement cooling plates and cooling pins for increasing the heat transfer between the cooling medium and heat shield segment comprises, and wherein the posts in the Impeller cooling cavities are housed in at least partially regular arrangements, and the spacers and cooling pins are arranged offset to one another.
- a further embodiment is characterized in that the heat accumulation segments in relation to the flow of the hot gas each have a leading edge, a trailing edge and two side regions, and that cooling holes are provided for film cooling of the edges and side portions of the heat termination, which starting from the impingement cooling cavities, the heat rejection segment enforce on all sides and end in the outside space.
- the cooling bores ending at the opposite side regions of the heat termination segment are thus in this case arranged offset to each other that the exiting cooling medium does not prevent each other at the exit in adjoining michstausegmenten.
- the coolant holes at the leading edge and in the side regions set back in a recess end for unimpeded leakage of the cooling medium, and when the cooling holes are formed spread in the corners of the heat shield segment for improved cooling of the edge regions.
- each heat shield segment and the associated upstream vane are positioned relative to one another in the circumferential direction so that the wake pressure wave generated by the vane can be compensated by a corresponding arrangement and supply of the affected cooling holes, preferably those in Open the region of the trailing pressure wave cooling holes above the impingement cooling plates in the impingement cooling cavities.
- Fig. 1 -3 in a simplified representation in longitudinal section the detail of a gas turbine with a arranged between the first and second row of guide vanes heat accumulation segments, which by means of a simple (Figure 1) of a sequential ( Figure 2) and a countercurrent impingement cooling scheme cooled become; Fig. 4 in a to Fig. 1 -3 comparable representation
- Impingement cooling scheme according to an embodiment of the invention
- Fig. 5 is a suitable for the arrangement of Figure 4 heat recovery segment with the arrangement of the various cooling holes and recesses in the plan view from the outside.
- FIG. 6 in a representation comparable to FIG. 4, the built-in thermal segment according to FIG. 5;
- Fig. 7 shows the arrangement of posts in the impingement cooling cavities of
- FIG. 9 in longitudinal section another of the possible posts of Figure 7, which is provided as a cooling pin with additional heat transfer surface.
- Fig. 10 shows a preferred distribution of the posts of Fig. 8 and 9 in the
- Fig. 1 1 seen in the radial direction, the important for the pressure margin relative positioning of the vane and heat recovery segment in the circumferential direction and
- Fig. 12 shows an example of the local reduction of the wall thickness by means of a groove where the cooling holes open into the impingement cooling cavities. Ways to carry out the invention
- FIG. 4 An embodiment of the invention is shown in FIG. 4 in a representation comparable to FIGS. 1 to 3: assuming the same number of parts in the ring for the guide vanes V1 and the heat accumulation segments 1 1.
- the heat staging segment 1 1 has two impingement cooling cavities 17 and 18 on, which are separated from each other by the middle hook-shaped fastening element 13 and operated at the same pressure P 1 .
- the second impingement cooling cavity 17 positioned downstream is isolated from the annular cavity 30 by a cover plate 21.
- the pressure margin for the impingement cooling and pressure margin for the spring seals between adjacent segments can be adjusted independently of each other. A loss of seal no longer causes the cooling medium pressure to drop.
- the margin of the cooling medium pressure can be reduced.
- the pressure above the cover plate 21 (P 2 ) can be adjusted so that the passing of the
- Blade B1 causes no vibration of the seal and thus no seal failure occurs.
- a film cooling is preferably provided for the front edge LE, the trailing edge TE and the side regions SW according to FIGS. 5 and 6. Lead to this
- Cooling bores 19, 19 ', 20, 20', 25 and 26 from the impingement cooling cavities 17, 18 to the outside and open into the outside space.
- the cooling bores 20, 20 'and 25, 26 are arranged offset back by corresponding recesses 22, 23 and 24 on the end faces, so that when touching the component with the adjacent component, the air can still escape unhindered .
- the cooling holes 19 ', 20' are spread in the region of the corners of the heat spreader segment 1 1 (flared cooling holes) in order to optimally cool the edge regions.
- the impingement cooling can be further improved if, according to FIG. 7, additional cone-shaped posts 28 are provided in the impingement cooling cavities 17, 18, which are arranged so as to be distributed with the holes 27 in the impingement cooling plates.
- One type of post ( Figure 8) is formed as a spacer 28a for the impingement cooling plates 15, 16.
- the other type of post ( Figure 9) serves as a cooling pin 28b to increase turbulence, heat flow and heat transfer area.
- Both types of posts, the spacers 28a and the cooling pins 28b may be arranged offset to increase the heat transfer according to FIG.
- the trailing pressure wave 31 is positioned by projecting or resting the components 1 1, V1 in the parting plane relative to each other on the heat spreader segment 11 (displacement arrows in FIG. 11), that the pressure margin of the cooling bores in the leading edges and in the side region, and the annular gap and the total cooling air consumption are optimally adjusted.
- the size of the impingement cooling cavities 17, 18 is chosen so that optimum cooling occurs.
- the thermal damper segment 1 1 is preferably provided with a thermal barrier coating (TBC), wherein different thicknesses and tolerances are selected in the regions upstream of the forward rotation of the blade B1 and at the location where the blade B1 passes.
- TBC thermal barrier coating
- the cooling bores 19, 19 ', 20, 20', 25, 26 are positioned as close as possible to the hot gas in the hot gas duct 29. Manufacturing tolerances, global wall thicknesses for rubbing and oxidation are subject to minimal criteria. Therefore, locally, where the cooling holes open into the impingement cooling cavities, the wall thickness is preferably reduced by means of a groove 32 (FIG. 12).
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH01146/08A CH699232A1 (en) | 2008-07-22 | 2008-07-22 | Gas turbine. |
PCT/EP2009/058895 WO2010009997A1 (en) | 2008-07-22 | 2009-07-13 | Shroud seal segments arrangement in a gas turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2310635A1 true EP2310635A1 (en) | 2011-04-20 |
EP2310635B1 EP2310635B1 (en) | 2018-01-24 |
Family
ID=39876635
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09800032.6A Active EP2310635B1 (en) | 2008-07-22 | 2009-07-13 | Shroud seal segments arrangement in a gas turbine |
Country Status (6)
Country | Link |
---|---|
US (1) | US8353663B2 (en) |
EP (1) | EP2310635B1 (en) |
KR (1) | KR101584974B1 (en) |
CH (1) | CH699232A1 (en) |
MX (1) | MX2011000711A (en) |
WO (1) | WO2010009997A1 (en) |
Families Citing this family (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB0910177D0 (en) * | 2009-06-15 | 2009-07-29 | Rolls Royce Plc | A cooled component for a gas turbine engine |
US8684662B2 (en) * | 2010-09-03 | 2014-04-01 | Siemens Energy, Inc. | Ring segment with impingement and convective cooling |
US9151179B2 (en) * | 2011-04-13 | 2015-10-06 | General Electric Company | Turbine shroud segment cooling system and method |
US9719362B2 (en) | 2013-04-24 | 2017-08-01 | Honeywell International Inc. | Turbine nozzles and methods of manufacturing the same |
GB201308602D0 (en) | 2013-05-14 | 2013-06-19 | Rolls Royce Plc | A Shroud Arrangement for a Gas Turbine Engine |
US8814507B1 (en) | 2013-05-28 | 2014-08-26 | Siemens Energy, Inc. | Cooling system for three hook ring segment |
WO2014204574A2 (en) * | 2013-06-21 | 2014-12-24 | United Technologies Corporation | Seals for gas turbine engine |
EP2860358A1 (en) | 2013-10-10 | 2015-04-15 | Alstom Technology Ltd | Arrangement for cooling a component in the hot gas path of a gas turbine |
US10690055B2 (en) * | 2014-05-29 | 2020-06-23 | General Electric Company | Engine components with impingement cooling features |
EP3026219B1 (en) * | 2014-11-27 | 2017-07-26 | Ansaldo Energia Switzerland AG | Support segment for a transition piece between combustor and turbine |
US20180023404A1 (en) * | 2015-02-16 | 2018-01-25 | Siemens Aktiengesellschaft | Ring segment system for gas turbine engines |
US10837300B2 (en) | 2016-11-01 | 2020-11-17 | General Electric Company | Seal pressurization in box shroud |
US10641174B2 (en) | 2017-01-18 | 2020-05-05 | General Electric Company | Rotor shaft cooling |
US10677084B2 (en) | 2017-06-16 | 2020-06-09 | Honeywell International Inc. | Turbine tip shroud assembly with plural shroud segments having inter-segment seal arrangement |
US10900378B2 (en) | 2017-06-16 | 2021-01-26 | Honeywell International Inc. | Turbine tip shroud assembly with plural shroud segments having internal cooling passages |
CN108443236A (en) * | 2018-03-05 | 2018-08-24 | 清华大学 | A kind of compressor stator corner separation control device and its control method |
US10989068B2 (en) | 2018-07-19 | 2021-04-27 | General Electric Company | Turbine shroud including plurality of cooling passages |
US10982559B2 (en) | 2018-08-24 | 2021-04-20 | General Electric Company | Spline seal with cooling features for turbine engines |
US10822986B2 (en) * | 2019-01-31 | 2020-11-03 | General Electric Company | Unitary body turbine shrouds including internal cooling passages |
US10830050B2 (en) | 2019-01-31 | 2020-11-10 | General Electric Company | Unitary body turbine shrouds including structural breakdown and collapsible features |
US10927693B2 (en) | 2019-01-31 | 2021-02-23 | General Electric Company | Unitary body turbine shroud for turbine systems |
US11035251B2 (en) * | 2019-09-26 | 2021-06-15 | General Electric Company | Stator temperature control system for a gas turbine engine |
US11098612B2 (en) * | 2019-11-18 | 2021-08-24 | Raytheon Technologies Corporation | Blade outer air seal including cooling trench |
EP4001593B1 (en) * | 2020-11-13 | 2023-12-20 | Doosan Enerbility Co., Ltd. | A gas turbine vane comprising an impingement cooled inner shroud |
CN114320488A (en) * | 2021-10-20 | 2022-04-12 | 中国航发四川燃气涡轮研究院 | Sealing structure of aeroengine turbine guider blade flange plate |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4573865A (en) * | 1981-08-31 | 1986-03-04 | General Electric Company | Multiple-impingement cooled structure |
US5538393A (en) * | 1995-01-31 | 1996-07-23 | United Technologies Corporation | Turbine shroud segment with serpentine cooling channels having a bend passage |
DE19619438B4 (en) | 1996-05-14 | 2005-04-21 | Alstom | Heat release segment for a turbomachine |
US6146091A (en) * | 1998-03-03 | 2000-11-14 | Mitsubishi Heavy Industries, Ltd. | Gas turbine cooling structure |
EP1124039A1 (en) * | 2000-02-09 | 2001-08-16 | General Electric Company | Impingement cooling apparatus for a gas turbine shroud system |
US6354795B1 (en) * | 2000-07-27 | 2002-03-12 | General Electric Company | Shroud cooling segment and assembly |
US6779597B2 (en) * | 2002-01-16 | 2004-08-24 | General Electric Company | Multiple impingement cooled structure |
US6702550B2 (en) * | 2002-01-16 | 2004-03-09 | General Electric Company | Turbine shroud segment and shroud assembly |
FR2852053B1 (en) * | 2003-03-06 | 2007-12-28 | Snecma Moteurs | HIGH PRESSURE TURBINE FOR TURBOMACHINE |
US7306424B2 (en) * | 2004-12-29 | 2007-12-11 | United Technologies Corporation | Blade outer seal with micro axial flow cooling system |
CA2644099C (en) * | 2006-03-02 | 2013-12-31 | Ihi Corporation | Impingement cooled structure |
US9133715B2 (en) * | 2006-09-20 | 2015-09-15 | United Technologies Corporation | Structural members in a pedestal array |
US7740444B2 (en) * | 2006-11-30 | 2010-06-22 | General Electric Company | Methods and system for cooling integral turbine shround assemblies |
-
2008
- 2008-07-22 CH CH01146/08A patent/CH699232A1/en not_active Application Discontinuation
-
2009
- 2009-07-13 KR KR1020117001661A patent/KR101584974B1/en not_active IP Right Cessation
- 2009-07-13 WO PCT/EP2009/058895 patent/WO2010009997A1/en active Application Filing
- 2009-07-13 EP EP09800032.6A patent/EP2310635B1/en active Active
- 2009-07-13 MX MX2011000711A patent/MX2011000711A/en not_active Application Discontinuation
-
2011
- 2011-01-21 US US13/011,203 patent/US8353663B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2010009997A1 * |
Also Published As
Publication number | Publication date |
---|---|
US20110171013A1 (en) | 2011-07-14 |
KR20110042172A (en) | 2011-04-25 |
EP2310635B1 (en) | 2018-01-24 |
MX2011000711A (en) | 2011-03-21 |
CH699232A1 (en) | 2010-01-29 |
WO2010009997A1 (en) | 2010-01-28 |
KR101584974B1 (en) | 2016-01-13 |
US8353663B2 (en) | 2013-01-15 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2310635B1 (en) | Shroud seal segments arrangement in a gas turbine | |
DE69205889T2 (en) | Cooling for a gas turbine stator ring. | |
DE69517306T2 (en) | TURBINE BLADE WITH SEALING ELEMENT AND AN INTEGRAL HEAT SHIELD | |
EP1048822B1 (en) | Heat shield for a gas turbine | |
DE60128865T2 (en) | Cooling for a turbine shroud ring | |
DE69409332T2 (en) | Seal in a gas turbine | |
EP1789654B1 (en) | Turbine engine vane with fluid cooled shroud | |
DE2837123C2 (en) | Turbomachinery blade | |
CH708795A2 (en) | Segment for an annular rotary machine Leitradbauteil. | |
EP2300686B1 (en) | Gas turbine comprising a guide vane | |
DE102008002890A1 (en) | Alternately cooled turbine stator | |
EP1276972B1 (en) | Turbine | |
EP1834066A1 (en) | Turbine blade for a gas turbine, use of a turbine blade and method for cooling a turbine blade | |
DE4102033A1 (en) | NOZZLE COOLING | |
EP3093447B1 (en) | Rotor of a turbine of a gas turbine with improved cooling air conduction | |
DE102008037501A1 (en) | Gas turbines with flexible tendon joint seals | |
CH701041A2 (en) | A turbine with sidewall cooling plenum. | |
EP2881541A1 (en) | Tip cooling of a turbine rotor blade of a gas turbine | |
EP2084368B1 (en) | Turbine blade | |
DE102014100087A1 (en) | Interior structure of a turbine blade | |
EP3336313A1 (en) | Turbine rotor blade arrangement for a gas turbine and method for the provision of sealing air in a turbine rotor blade arrangement | |
EP1409926A1 (en) | Baffle cooling device | |
DE1601563B2 (en) | Air-cooled blade | |
EP2428647B1 (en) | Transitional Region for a Combustion Chamber of a Gas Turbine | |
EP2092164A1 (en) | Turbomachine, particularly a gas turbine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20110112 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA RS |
|
RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: SCHNIEDER, MARTIN Inventor name: ARZEL, TANGUY Inventor name: HEINZ-SCHWARZMAIER, THOMAS |
|
DAX | Request for extension of the european patent (deleted) | ||
17Q | First examination report despatched |
Effective date: 20130311 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: ANSALDO ENERGIA IP UK LIMITED |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
INTG | Intention to grant announced |
Effective date: 20170814 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 965912 Country of ref document: AT Kind code of ref document: T Effective date: 20180215 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: LANGUAGE OF EP DOCUMENT: GERMAN |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 502009014709 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20180124 |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG4D |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180424 Ref country code: CY Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: HR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180425 Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180424 Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180524 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502009014709 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: SM Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20181025 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20180713 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180713 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20180731 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: MM4A |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180731 Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180731 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180731 Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180713 Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180713 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180731 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MM01 Ref document number: 965912 Country of ref document: AT Kind code of ref document: T Effective date: 20180713 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180713 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180124 Ref country code: HU Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO Effective date: 20090713 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MK Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180124 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20231228 Year of fee payment: 15 Ref country code: DE Payment date: 20231214 Year of fee payment: 15 |
|
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20240430 |