EP1861584A1 - Heat accumulation segment for sealing a flow channel of a turbine engine - Google Patents
Heat accumulation segment for sealing a flow channel of a turbine engineInfo
- Publication number
- EP1861584A1 EP1861584A1 EP06725191A EP06725191A EP1861584A1 EP 1861584 A1 EP1861584 A1 EP 1861584A1 EP 06725191 A EP06725191 A EP 06725191A EP 06725191 A EP06725191 A EP 06725191A EP 1861584 A1 EP1861584 A1 EP 1861584A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- contour
- joining
- sealing means
- flow channel
- recess
- 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
- 238000007789 sealing Methods 0.000 title claims description 60
- 238000009825 accumulation Methods 0.000 title description 8
- 238000000926 separation method Methods 0.000 claims abstract description 4
- 239000000565 sealant Substances 0.000 claims description 18
- 239000003566 sealing material Substances 0.000 claims description 5
- 239000007769 metal material Substances 0.000 claims description 4
- 230000017525 heat dissipation Effects 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims 1
- 230000000295 complement effect Effects 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 10
- 238000001816 cooling Methods 0.000 description 8
- 239000000463 material Substances 0.000 description 7
- 238000011084 recovery Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 238000005299 abrasion Methods 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000005338 heat storage Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 239000012812 sealant material Substances 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
-
- 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
- F01D11/005—Sealing means between non relatively rotating elements
-
- 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
Definitions
- the invention relates to a heat recovery segment for local separation of a flow channel within a flow rotating machine, in particular a gas turbine plant, opposite to a stator radially surrounding the stator housing, with two axially opposite joining contours, which are each engageable with two along the flow channel axially adjacent components, the to the joining contours each provide a gegenkonturrATOR receiving contour, of which at least one receiving contour has an axial play, along which the joined joining contour is axially displaceable, wherein between the axially displaceable joining contour and the receiving contour at least one sealing means is provided.
- 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.
- axially one behind the other arranged blades and vanes are acted upon directly with the resulting hot combustion gases in the combustion chamber.
- To prevent the hot gases flowing through the flow channel not Thermally load areas within the flow rotating machine, which are provided in the flow channel remote stator areas, provide so-called heat accumulation segments, which are provided on the stator side between each two axially adjacent vanes, for a possible gas-tight bridge-like seal between two axially adjacent arranged guide blade rows.
- Correspondingly designed heat accumulation segments can also be provided along the rotor unit, which are each mounted on the rotor side between two axially adjacent rotor blade rows in order to protect co-rotating rotor components from too high a heat input.
- FIG. 1 shows a schematic longitudinal section through a gas turbine stage, in the flow channel K of which stator blades 1 protrude radially from the outside with a stator housing S, the special design of which has no further significance in the following.
- a blade 2 which is spaced radially from the end face against a heat shield segment 3, which includes the smallest possible clearance gap 4 with the vane 2 to leakage losses with respect to flow components of the hot gas flow through avoid the intermediate gap 4 as possible.
- the blade tip Sealing structures 5, which are arranged freely rotating relative to so-called abrasion elements 6.
- the receiving contour 9 corresponds to a precisely matched to the joining contour 7 gegenkonturriert running groove-shaped recess which is incorporated in the foot region of the guide vane 1.
- the axially opposite joining contour 8 of the heat spreader segment 3 is likewise inserted into a receiving contour 10 which is counter-contoured corresponding to the outer contour of the joining contour 8 and is inserted in the foot region of the vane Y.
- the receiving contour 10 has an axial play 11, so that the joining contour 8 is axially slidably mounted with a corresponding operational thermal expansion of the heat shield segment 3.
- sealing means 12, 13 are provided between the joining contours 7, 8 and the associated receiving contours 9, 10.
- the sealing means 12, 13 are each in a groove-shaped recess 14 within the joining contours 7, 8 (see also detailed representation like Fig. 2b of the joining region between the joining contour 8 and the receiving contour 10).
- the sealing means 12, 13 are preferably made of an elastic sealing material in the form of a round rod, partially project beyond the radially outer boundary surface 16 and nestle flush, at least along a joint line to the surface portion 17 of the receiving contour 10 at.
- the sealing effect of the sealing means 12, 13 can be avoided on the one hand, that hot gases from the flow channel K in the radially remote from the flow channel K regions to the heat shield segment 3, also prevents stator-fed cooling air L can pass through appropriate leakage points in the flow channel K.
- the clearance 11 provided in the recess 11 serves for a thermally induced material expansion along the heat shield segment 3, whereby the joining contour 8 together with the sealing means 12 provided in it is displaced to a right position shown in the illustration. If, on the other hand, the gas turbine stage is switched off and the individual components cool down, the joining contour 8, together with the sealing means 12 provided in it, returns to the original starting position.
- sealing means 12 is subject by the thermally induced relative movements between the receiving contour 8 and the surface region 17 Materialabrieberscheinungen that leads to a wear-related reduction of the sealing function of the sealant when exceeding a maximum allowable limit, so that cooling air L through the adjusting or existing intermediate gaps between the joining contour 8 and the receiving contour 10 can escape.
- This not only leads to a considerable loss of cooling air, whereby the cooling effect is drastically reduced, however, there is the danger that hot gases can also enter areas that are located facing away from the flow channel K to the heat shield segment 3.
- sealing means are used, which consist of a fabric material which can be thinned at high mechanical rubbing stress, whereby the sealing effect of the sealant decreases with increasing operating time.
- the invention is based on the object, a heat dissipation segment for local separation 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, the each in engagement with two along the flow channel axially adjacent components can be brought, which provide for the joining contours each have a gegenkonturrATOR receiving contour, of which at least one receiving contour has an axial play, along which the joining contour is axially slidably mounted therein, wherein between the axially displaceable Joining contour and the receiving contour at least one sealing means is provided to form such that the sealant should experience no or significantly lower Abriebeigenschaften caused by the thermally induced material expansion and shrinkage caused relative movements between the joining contour and the receiving contour.
- a heat spreader segment according to the features of the preamble of claim 1 is designed such that the sealing means is movably mounted within the receiving contour or the joining contour such that the sealing means can be deflected against a surface area of the receiving contour or the joining contour.
- the sealing means which is preferably made of a metallic material, preferably of an incompressible material, as it were introduced in the prior art within a recess along the receiving contour or joining contour, but additionally subjected to a force, Preferably spring-loaded against a surface area of the receiving contour or joining contour to deflect or press.
- a force Preferably spring-loaded against a surface area of the receiving contour or joining contour to deflect or press.
- the following considerations provide for integrating the sealing means in the joining contour of the heat spreader segment, so that the sealing means is pressed against a surface area of the receiving contour by a spring force.
- 1a is a schematic partial longitudinal section through a joining region between a heat recovery segment and an axially adjacent vane
- FIG. 2a, b longitudinal sectional view of a heat spreader with axially adjacent vanes and detailed illustration of this according to the prior art.
- FIG. 1a shows a partial view through a longitudinal section of a heat shield segment 3 in the region of the joining contour 8, which opens into a corresponding groove-shaped receiving contour 10 of an axially adjacent foot of a guide vane V.
- the axial depth of the receiving contour 10 is dimensioned so to speak to the prior art described above such that in thermally induced material expansion of the heat shield segment 3, the joining contour 8 along the axially oriented game 11 is slidably mounted.
- the joining contour 8 consequently carries out a translational movement indicated in the direction of the arrow B.
- the joining contour 8 has a radially outer joining surface 16, in which a groove-shaped recess 14 is incorporated.
- the depth of the groove-shaped recess 14, measured from the joining surface 16 corresponds at least to the maximum radial extent of the sealing means 12, whose shape is adapted to the inner contour of the groove-shaped recess 14, so that the sealing means 14 can be completely inserted into the recess 14. Furthermore, a spring element 18 is provided within the groove-shaped recess 14, which is introduced between the groove bottom of the recess 14 and the spring element 12, so that the spring element 18 is able to drive the sealing means 12 radially upwards.
- the spring element 18 and the groove-shaped recess 14 within the joining contour 8 reference is made to the perspective view according to Figure 1 b, the consideration of which will be made in the following together with Figure 1a.
- the sealing means 12 is formed rod-shaped in the manner shown in Figure 1 b in perspective and preferably made of an incompressible metallic material which has substantially no Abriebeigenschaften.
- the sealing means 12 has a rectangular design in the middle Projection 19, which engages in a corresponding rectangular recess 20 in the inserted state within the groove-shaped recess 14.
- the sealing means 12 is forced radially linearly by the projection 19, so that slippage of the sealing means 12 in the circumferential direction along the groove-shaped recess 14 is avoided.
- a swung formed spring element 18 is introduced, which is capable of pressing the sealing means 12 radially upward Federkraftbeetzschlagt.
- the curved spring element section 18 'facing the groove bottom opens into a recess (not shown) inserted correspondingly in the groove bottom.
- the rectangular shaped recess 20 axially opposite boundary wall 21 within the groove-shaped recess 14 is made of a sealing material and is able to produce in this way in a fluid-tight contact with the sealant 12.
- FIG. 1 a shows the inserted state of the joining contour 8 within the receiving contour 10, wherein the spring element 18 presses the sealing element 12 radially outwards against a surface region 17 of the receiving contour 10 and thus seals the heat-releasing segment 3 in a fluid-tight manner Receiving contour 10 within the foot of the vane Y presses.
- the radially lower side edge of the sealant 12 is formed inclined, so that the spring element 18, the sealant 12 also axially against the rear Limiting surface 21 can press fluid-tight.
- the side edge 12 'of the sealing means facing the surface area 17 is contoured to the surface area 17.
- the sealing system according to the invention can not avoid the longitudinal axial movement of the heat accumulation segment 3 due to the thermal material expansion or shrinkage, the material abrasion completely disappears with a suitable choice of the sealant material, especially as the sealant 12 is made of an incompressible, wear-free, preferably metallic material is selected, which ensures a fluid-tight seal due to the spring-loaded pressure.
- cooling air L flowing in under high pressure can exert a high contact pressure on the axially directed surface 23 of the projection 19 within the cooling volume V enclosed by the thermal damper segment 3, so that the sealing means is pressed in the axial direction in addition to the spring force component against the sealing side 21 consisting of sealing material ,
- spring element 18 In addition to the illustrated in Figures 1a and b specific embodiment of the spring element 18 and other spring element designs are conceivable, such as a plurality of individual coil spring elements, helically shaped or coiled spring elements and suitably shaped flat springs.
- the heat discharge segment shown in FIGS. 1a and b is in a ring-like manner
- Multiple arrangement limits the entire circumferential area between two adjacent rows of vane.
- two heat accumulation segments arranged adjacent to one another in the circumferential direction engage via a common strip band seal 24, by means of which a possible loss of cooling air along two circumferentially adjacent heat accumulation segments can be avoided.
- the tightness of the cooling air volume, which is separated by the heat discharge segment from the flow channel is significantly improved due to the wear-free sealant, especially since the sealing effect is guaranteed despite thermal expansion and shrinkage phenomena by the spring-loaded contact pressure of the sealant to the respective surface area opposite the sealant.
- the spring-pressure of the sealant ensures at any time a sealing of the joining area with respect to its radially upper and lower boundary surfaces, especially since the radially upper sealing means 12 by the force exerted on the joint counterforce and the radially lower boundary surface of the joining region against the boundary surface 22 of the receiving contour 10 can press fluid-tight. If the sealing means be provided in the region of the boundary surface 22, the same applies accordingly.
- the spring element 18 Due to the spring-loaded contact pressure of the sealant 12 against the surface portion 16 of the receiving contour 10, the spring element 18 contributes due to its inherent elasticity to a certain ability of shock or vibration absorption, so that occurring mechanical shocks can be absorbed within the joint area by the spring element 18 and thus the Do not subject the joining area to excessive mechanical stress.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
- Heating, Cooling, Or Curing Plastics Or The Like In General (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SI200631029T SI1861584T1 (en) | 2005-03-24 | 2006-03-21 | Heat accumulation segment for sealing a flow channel of a turbine engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102005013798A DE102005013798A1 (en) | 2005-03-24 | 2005-03-24 | Heat release segment for sealing a flow channel of a flow rotary machine |
PCT/EP2006/060903 WO2006100235A1 (en) | 2005-03-24 | 2006-03-21 | Heat accumulation segment for sealing a flow channel of a turbine engine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1861584A1 true EP1861584A1 (en) | 2007-12-05 |
EP1861584B1 EP1861584B1 (en) | 2011-03-09 |
Family
ID=36593051
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06725191A Not-in-force EP1861584B1 (en) | 2005-03-24 | 2006-03-21 | Heat accumulation segment for sealing a flow channel of a turbine engine |
Country Status (10)
Country | Link |
---|---|
US (1) | US7665957B2 (en) |
EP (1) | EP1861584B1 (en) |
KR (1) | KR101287408B1 (en) |
AT (1) | ATE501341T1 (en) |
BR (1) | BRPI0609723A2 (en) |
CA (1) | CA2602458C (en) |
DE (2) | DE102005013798A1 (en) |
MX (1) | MX2007011589A (en) |
SI (1) | SI1861584T1 (en) |
WO (1) | WO2006100235A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110332023A (en) * | 2019-07-16 | 2019-10-15 | 中国航发沈阳发动机研究所 | A kind of end face seal structure with refrigerating function |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SI2173974T1 (en) | 2007-06-28 | 2012-03-30 | Alstom Technology Ltd | Heat shield segment for a stator of a gas turbine |
DE102007031711A1 (en) | 2007-07-06 | 2009-01-08 | Rolls-Royce Deutschland Ltd & Co Kg | Housing shroud segment suspension |
EP2098688A1 (en) * | 2008-03-07 | 2009-09-09 | Siemens Aktiengesellschaft | Gas turbine |
FR2954400B1 (en) * | 2009-12-18 | 2012-03-09 | Snecma | TURBINE STAGE IN A TURBOMACHINE |
CN104471197B (en) * | 2012-04-27 | 2016-05-11 | 通用电气公司 | Suspension bracket and the axially movable system and method for radome fairing inter-module in restriction turbine assembly |
US9771818B2 (en) | 2012-12-29 | 2017-09-26 | United Technologies Corporation | Seals for a circumferential stop ring in a turbine exhaust case |
US10458268B2 (en) * | 2016-04-13 | 2019-10-29 | Rolls-Royce North American Technologies Inc. | Turbine shroud with sealed box segments |
EP3412871B1 (en) | 2017-06-09 | 2021-04-28 | Ge Avio S.r.l. | Sealing arrangement for a turbine vane assembly |
US10858953B2 (en) * | 2017-09-01 | 2020-12-08 | Rolls-Royce Deutschland Ltd & Co Kg | Turbine casing heat shield in a gas turbine engine |
US11248705B2 (en) * | 2018-06-19 | 2022-02-15 | General Electric Company | Curved seal with relief cuts for adjacent gas turbine components |
US11047248B2 (en) * | 2018-06-19 | 2021-06-29 | General Electric Company | Curved seal for adjacent gas turbine components |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
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US4576548A (en) * | 1984-01-17 | 1986-03-18 | Westinghouse Electric Corp. | Self-aligning static seal for gas turbine stator vanes |
US5188506A (en) * | 1991-08-28 | 1993-02-23 | General Electric Company | Apparatus and method for preventing leakage of cooling air in a shroud assembly of a gas turbine engine |
US5188507A (en) * | 1991-11-27 | 1993-02-23 | General Electric Company | Low-pressure turbine shroud |
US5333995A (en) * | 1993-08-09 | 1994-08-02 | General Electric Company | Wear shim for a turbine engine |
US5423659A (en) * | 1994-04-28 | 1995-06-13 | United Technologies Corporation | Shroud segment having a cut-back retaining hook |
DE4442157A1 (en) | 1994-11-26 | 1996-05-30 | Abb Management Ag | Method and device for influencing the radial clearance of the blades in compressors with axial flow |
US5901787A (en) * | 1995-06-09 | 1999-05-11 | Tuboscope (Uk) Ltd. | Metal sealing wireline plug |
US5609469A (en) * | 1995-11-22 | 1997-03-11 | United Technologies Corporation | Rotor assembly shroud |
US6315519B1 (en) * | 1998-09-28 | 2001-11-13 | General Electric Company | Turbine inner shroud and turbine assembly containing such inner shroud |
DE19938274A1 (en) | 1999-08-12 | 2001-02-15 | Asea Brown Boveri | Device and method for drawing the gap between the stator and rotor arrangement of a turbomachine |
FR2800797B1 (en) | 1999-11-10 | 2001-12-07 | Snecma | ASSEMBLY OF A RING BORDING A TURBINE TO THE TURBINE STRUCTURE |
US20030039542A1 (en) * | 2001-08-21 | 2003-02-27 | Cromer Robert Harold | Transition piece side sealing element and turbine assembly containing such seal |
US6514041B1 (en) | 2001-09-12 | 2003-02-04 | Alstom (Switzerland) Ltd | Carrier for guide vane and heat shield segment |
JP2004036443A (en) * | 2002-07-02 | 2004-02-05 | Ishikawajima Harima Heavy Ind Co Ltd | Gas turbine shroud structure |
GB0308147D0 (en) * | 2003-04-09 | 2003-05-14 | Rolls Royce Plc | A seal |
EP1515003A1 (en) * | 2003-09-11 | 2005-03-16 | Siemens Aktiengesellschaft | Gas turbine and sealing means for a gas turbine |
FR2859762B1 (en) * | 2003-09-11 | 2006-01-06 | Snecma Moteurs | REALIZATION OF SEALING FOR CABIN TAKEN BY SEGMENT SEAL |
US7435049B2 (en) * | 2004-03-30 | 2008-10-14 | General Electric Company | Sealing device and method for turbomachinery |
US7207771B2 (en) * | 2004-10-15 | 2007-04-24 | Pratt & Whitney Canada Corp. | Turbine shroud segment seal |
-
2005
- 2005-03-24 DE DE102005013798A patent/DE102005013798A1/en not_active Withdrawn
-
2006
- 2006-03-21 DE DE502006009054T patent/DE502006009054D1/en active Active
- 2006-03-21 SI SI200631029T patent/SI1861584T1/en unknown
- 2006-03-21 CA CA2602458A patent/CA2602458C/en not_active Expired - Fee Related
- 2006-03-21 BR BRPI0609723-5A patent/BRPI0609723A2/en not_active Application Discontinuation
- 2006-03-21 KR KR1020077021795A patent/KR101287408B1/en not_active IP Right Cessation
- 2006-03-21 WO PCT/EP2006/060903 patent/WO2006100235A1/en not_active Application Discontinuation
- 2006-03-21 EP EP06725191A patent/EP1861584B1/en not_active Not-in-force
- 2006-03-21 AT AT06725191T patent/ATE501341T1/en active
- 2006-03-21 MX MX2007011589A patent/MX2007011589A/en active IP Right Grant
-
2007
- 2007-09-24 US US11/859,963 patent/US7665957B2/en active Active
Non-Patent Citations (1)
Title |
---|
See references of WO2006100235A1 * |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110332023A (en) * | 2019-07-16 | 2019-10-15 | 中国航发沈阳发动机研究所 | A kind of end face seal structure with refrigerating function |
CN110332023B (en) * | 2019-07-16 | 2021-12-28 | 中国航发沈阳发动机研究所 | End face sealing structure with cooling function |
Also Published As
Publication number | Publication date |
---|---|
US20080260524A1 (en) | 2008-10-23 |
KR101287408B1 (en) | 2013-07-19 |
SI1861584T1 (en) | 2011-07-29 |
DE502006009054D1 (en) | 2011-04-21 |
US7665957B2 (en) | 2010-02-23 |
DE102005013798A1 (en) | 2006-09-28 |
CA2602458C (en) | 2010-07-20 |
EP1861584B1 (en) | 2011-03-09 |
ATE501341T1 (en) | 2011-03-15 |
MX2007011589A (en) | 2007-12-06 |
BRPI0609723A2 (en) | 2010-04-20 |
KR20070115997A (en) | 2007-12-06 |
CA2602458A1 (en) | 2006-09-28 |
WO2006100235A1 (en) | 2006-09-28 |
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Legal Events
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RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: BURMISTROV, ALEXANDER Inventor name: KHANIN, ALEXANDER Inventor name: SLOUTSKI, EDOUARD |
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GRAS | Grant fee paid |
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