EP1163427B1 - Gasturbinenrotor mit innenraumgekühlter gasturbinenschaufel - Google Patents
Gasturbinenrotor mit innenraumgekühlter gasturbinenschaufel Download PDFInfo
- Publication number
- EP1163427B1 EP1163427B1 EP00920496A EP00920496A EP1163427B1 EP 1163427 B1 EP1163427 B1 EP 1163427B1 EP 00920496 A EP00920496 A EP 00920496A EP 00920496 A EP00920496 A EP 00920496A EP 1163427 B1 EP1163427 B1 EP 1163427B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- disc
- recess
- blade
- turbine rotor
- 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.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
-
- 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
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
Definitions
- the invention relates to a gas turbine rotor with an interior-cooled Gas turbine blade that has a blade root and has a blade platform, and with a disc, has the disc transverse grooves in which the blade root is inserted is, the blade platform outside an outer circumference the disc is arranged and on an end wall portion one long side has a recess into which a Insert strip is inserted into a corresponding one Recess of a blade platform of a second gas turbine blade engages and a space between the two Bucket platforms bridged and sealed.
- sealing plate for a Gas turbine blade known. If cooling air, that of the gas turbine blade is fed into the high-temperature fuel gas channel escapes, this leads among other things to a belittling the performance of the gas turbine.
- the sealing plate which in the gas turbine blade is used to exit prevent cooling air.
- the seal is made except by the named sealing plate by different sealing pins, built between the platforms of two blades are. A variety of sealing elements are required to the desired sealing function against the escape of cooling air manufacture.
- DE-B-1 258 662 discloses a deck device for the Guiding the cooling gas of gas turbine disks, which consist of several individual segments, which are interlinked with sealing strips are sealed. Sealing takes place in one additional device in front of the gas turbine disc and the gas turbine blades inserted therein is. This increases the number of elements required to build the Seal are needed.
- US-A-4 523 890 discloses sealing elements for the foot areas the turbine blades.
- the seal is used for reduction the loss of cooling air at the bottom of the feet.
- the sealing elements must hold grooves in the turbine disk be introduced into which the sealing elements are inserted are. So there are complex manufacturing steps necessary.
- the object of the invention is to provide a gas turbine rotor Specify indoor-cooled gas turbine blade, where both the seal against hot gas entry as well Cooling air outlet and securing the gas turbine blade to produce with little effort and at the same time very reliable are.
- the object is achieved in that the recess up to one disc-side base of the blade platform is sufficient and the insert strip against axial displacement in Safeguarding the direction of use of the gas turbine blade Has positive locking on the disc.
- the seal leaves easy to manufacture and is made by a single element done that in its form individually to different Platform configurations can be adapted.
- the gas turbine blade is sealed and fixed accordingly with a single element, the insert strip.
- a single insert strip also makes it easy to handle and the ability to quickly replace it to clean or repair.
- Insert strips It is preferably highly heat-resistant and resistant to chemical attacks stable material to use, so that the inflowing Hot gas does not deform the insert strip, respectively destroyed corrosively.
- the proposed training of the Insert strips can be made with these materials due to their simple shape can be easily produced and also exhibit great durability with brittle materials.
- each gas turbine blade secured by four insert strips two strips each ensure security in one direction. In this way, the gas turbine blade itself is closed a failure or loss of a deployment strip in the Disk transverse groove non-displaceable through the remaining three Stripes held. Two gas turbine blades each share the one between them in the long side of the bucket platform seated two insert strips.
- the insert strips can thus be attached with little effort and held particularly securely in the recess that the recess obliquely in the direction of a longitudinal axis of the rotor Gas turbine rotor runs and at its disc end into a chamfer on the disc head corresponding to the recess empties.
- the hot gases are due to the inclination of the insert strip used in the direction of the gas turbine wing distracted and thus optimally used without too to be swirled heavily by the bucket platform respectively the blade platform too strong with high temperatures to charge.
- the adjusted bevels provide an even, one-sided Applying the deployment strip to the recess or the chamfer of the disc head, whereby attacking forces to Example shear forces caused by a relative displacement the gas turbine blade compared to another gas turbine blade or the gas turbine blade opposite the disk transverse groove arise without too much selective stress of the deployment strip can be safely intercepted.
- the insert strip is inserted after insertion thereby, for example, through the closed wing-side End of the recess or held by his disc-side end is widened and a Undercut of the recess, so that a Form fit against the attacking centrifugal forces.
- Forces acting on the insert strips can be effective without interruption of the emergency lane is prevented, that it is between the disc-side end of the recess and the outer circumference of the disk a relative movements between the gap and the blade platform allowing gap gives.
- Attacking forces are, for example, shear forces that due to relative movements between the disc and the blade platform or by the relative to each other in the disc transverse grooves shifting gas turbine blades arise.
- the Dimensions of the gap will be at the bottom of the recess designed so that the attacking people of different sizes Forces due to appropriate elastic deformations of the attached Insert strips can be intercepted so that a kind of "springback effect" is achieved.
- the end of the insert strip is in the direction of use of the gas turbine blade as well as possible perpendicular to it, depending on which of the attacking forces are intercepted particularly strongly Need to become.
- the axially displacing forces in particular Shear forces particularly large, it makes sense to leave a gap to choose with a very low height so that the insert strip has sufficient rigidity to the axial To be able to exercise security reliably.
- the insert strip is preferably made of a material that has sufficient elastic deformation properties.
- the recess is designed as a groove.
- the groove is preferably characterized by at least three surrounding them Walls that have a positive connection to prevent the Form the deployment strip. It also provides the sealing strip surrounding groove a better seal against inflowing Hot gas or cooling air flowing out.
- the groove can be designed so that they are close to the Insert strips and thus without additional sealing materials seals.
- Another form of training are on the groove attached cutting edges which engage in the insert strip.
- the groove continues to provide increased security against Effects of forces on the deployment strip, for example shear forces caused by relative displacements the platforms with each other or the platforms relative to the disc.
- the groove is open on the side, which is closest to the neighboring platform. To this The insert strip can easily be placed in the two opposite one another Grooves are inserted and sits there very sure.
- a slip of a deployment strip in the event of attacks by Centrifugal forces can easily be prevented by the Recess at its disc-side end is wider than at their remaining part. In this way, a positive connection is against a slipping of the deployment strip, which by the disc-side end of the recess can be used prevented without simultaneously closing the groove at the top have to be.
- a secure hold of the insert strip with the gas turbine stopped results from the fact that the insert strip in its Insert position is fixed on the disc. In this way is the insert strip slipping out of the recess even when stationary, if not due to the centrifugal force is pushed out due to the rotational movement, prevented.
- the fixation on the disc is still an improved hold against axial slippage. she can be done for example by a screw or a bolt be present below the deployment strip is and does not have to intervene in the latter. This especially simple type of fixation can be made quickly and undo quickly even if corrosion occured.
- a screw part is used to fix the insert strip, which engages in a recess of the insert strip and which is supported under centrifugal force on the insert strip.
- the screwed part secures the insert strip against slipping out when the gas turbine is stopped.
- the insert strip prevents the screw part from slipping out due to the fact that the screw part is supported on the insert strip by centrifugal force. Accordingly, the two elements secure each other. This reduces the number of elements required.
- the insert strip can in turn be easily removed if, for example, gas turbine blades are to be replaced.
- a fall protection of the deployment strip and / or a Protection against ejection of the deployment strip Centrifugal attack, with no additional parts required are achieved in that the insert strip on a disc-side end in a safety recess Engages the face of the disc.
- the insert strip can be used for intervening in the safety recess, for example already have a bent end after insertion or after be inserted into the securing recess. Another possibility is that the insert strip one has a projection that is in the inserted position corresponds to the safety recess.
- the insert strip for any Maintenance purposes or in the event of a failure of the gas turbine blade without additional tools or without the danger caking of the securing element with the material due to a diffusive or corrosive attack at high Easy to remove operating temperatures.
- the part of the Insert strip designed almost any dimension be, so that the fuse even with large external forces is given reliably.
- the insert strip which engages in the securing recess, possible so that thermal expansions respectively attacking gravity without failure respectively damage to the deployment strip is more easily intercepted can be.
- a fuse independent of the disc can be supplied that a security strip under the bucket platform through two insert strips and on its ends are bent.
- the anti-slip device is open given this way regardless of the disc. This is beneficial when large shear forces occur, Put a lot of strain on the attached panel and possibly would detach. This additional security aspect is particularly with high temperature fluctuations respectively strongly changing attacking forces important.
- Figure 1 is a schematic and not to scale a principle Construction of part of the gas turbine rotor, namely a outer part - the head part 6 - the disc 4 shown.
- the disc 4 has circumferential, open to its periphery 7 Disk transverse grooves 3, which are substantially parallel to the longitudinal axis of the rotor 16 run, but also inclined to it can wine.
- the disc transverse grooves 3 are with undercuts 15 equipped.
- a disc transverse groove 3 is one Gas turbine blade 1 with its blade root 2 along the Direction of use 30 of the disc transverse groove 3 used.
- the Blade root 2 is supported with longitudinal ribs 41 on the undercuts 15 of the disc transverse groove 3.
- the gas turbine blade has above the blade root 2 1 a broadened area, the so-called Bucket platform 5.
- Bucket platform 5 On a disc-side base 13 the outside of the blade platform 5 43 of the Blade platform 5 is a wing 40 of the gas turbine blade 1.
- On the wing 40 flow to operate the Gas turbine blade 1 required hot gases to pass and generate a torque of the disc 1.
- an internal cooling system which is not complete here is shown. Only the supply lines are shown 55 to the internal cooling system through which the Cooling air is introduced into the internal cooling system.
- the cooling air is through a supply line, not shown through the disc 4 in the blade root 2 of the gas turbine blade 1 passed and from there to the supply lines 55 of the internal cooling system. To leave early the cooling air in the area of the blade root 2 or the blade platform 5 are to be prevented Insert strips 11 available.
- hot gas will be prevented from between two gas turbine rotor blades 1 in the blade platform 5 or the internal cooling system penetrates and this Areas damaged.
- a second, in an adjacent disc transverse groove used gas turbine blade 1 is dashed shown.
- the long sides 9 of the two gas turbine blades 1 have a space 12.
- the long sides 9 have recesses 10 into which an insert strip 11 is used.
- the recess 10 is up to the disc-side base 13 of the blade platform 5 is designed to be sufficient.
- the Insert strip 11 in turn extends over the disc side End 14 of the recess 10 and lies on its disc-side End 34 on a chamfer 17 on the end face 22 of the Disc 4.
- the insert strip 11 thus has one against axial displacement of the gas turbine blade 1 in the direction of use 30 of the gas turbine blade 1 securing positive engagement the disc 4.
- the insert strip 11 fulfills in this way by the tight Bearing in the recess 10 as well as on the chamfer 17 sealing against both hot gas and cooling air leaks Function, as well as one against slipping of the gas turbine blade 1 in the disk transverse groove 3 respectively function in the direction of use 30.
- the insert strip 11 is preferably a highly heat-resistant material related, for example a nickel-based alloy.
- each a recess 10 is present, and one each Insert strip 11 is inserted into a recess 10 and on one of the two opposite disc ends 22 is present, the gas turbine blade 1 in both possible directions of use 30 secured relative to the disc 4.
- the opposite long side 9 of the blade platform 5 in turn has 8 at its end wall sections the long side 9 recesses 10, in the insert strips 11th are used.
- a gas turbine blade 1 is thus through secured a total of four insert strips 11.
- the seal is a sealing strip in the groove 35 of the Longitudinal sides 9 inserted lengthways.
- Figure 2 shows a side view of the gas turbine blade 1 with an inserted insert strip 11.
- the recess 10 runs obliquely, inclined in the direction of a longitudinal axis of the rotor 16 of the gas turbine rotor and opens at its disc-side End 14 in one of the recess 10 beveled accordingly Chamfer 17 of the disc head 6.
- the disc head is Area of the blade platform 5 very well against Secured entry of hot gas.
- the cooling air through access 29 to the internal cooling system in the gas turbine blade cannot be initiated before reaching the Wing tip of the blade wing 40 through the space 12 escape.
- FIG. 3 shows an end 14 of the recess 10 on the disk side with insert strip 11.
- the gap 19 enables lateral forces to be applied elastic deformation of the insert strip used 11, so that a kind of "springback effect" is achieved.
- the Recess 10 is here, as in the previous illustrations, formed as a groove. In this way the insert strip sits 11 held securely and well sealed in the recess 10th
- the insert strip 11 is in its insertion position on the Disc 4 fixed. In this way, the Prevention strip under the action of gravity and the securing effect of the insert strip 11 against axial Displacements of the gas turbine blade 1 are increased.
- a screw part 20 is used to fix the insert strip 11.
- the screw 20 is in the chamfer 17 in the washer head 6 used.
- the screw part 20 has a head 36 and circumferential shoulders 37. The head 36 protrudes into a recess 60 of the deployment strip 11 and the shoulders 37 support itself on the inside 38 of the insert strip 11.
- the Shoulders 37 lie close to the inside 38 of the insert strip 11 on, so that the insert strip 11 slipping out of the screw part 20 is prevented in the case of attacking centrifugal forces and at the same time the insert strip 11 through the Head 36 of the screw 20 against slipping out stationary gas turbine rotor is secured.
- Figure 4a shows another possible formation of the disc side End 34 of the deployment strip 11.
- the deployment strip 11 engages at its disc-side end 34 in a securing recess 70 of the disc end face 22.
- the safety recess 70 supports the insert strip 11 against Fall out, as well as against slipping sideways.
- the End 14 is preferably after inserting the insert strip 11 bent into the recess 70.
- the insert strip 11 can also in front of its disc-side end 34 be bent and inserted before insertion. requirement this is sufficient resilience of the Strip 11 and / or a sufficient bevel of the recess 70th
- Figure 4b shows the disk-side securing of the insert strip 11 from Fig.4a, however, the securing recess 70 has a flatter bevel. In this way the insert strip 11 is used even with light axial displacements kept captive.
- Figure 5 shows a further security option in the area of the disc-side end 34 of the insert strip 11.
- a Security strip 24 engages under the blade platform 5 and leads through a passage opening 56 in each case in two opposing insert strips 11 and is bent 80 at its ends. That way is a Prevents the insert strips 11 from slipping out.
- the disc 4 is not in this way with holes or openings for Securing the deployment strips 11 affected.
- This type of backup offers increased durability against attacking Shear forces, since such an insert strip 11 has some play to move. Furthermore, securing easily without permanent damage to the Disk 4 can be removed again. Removing the fuse is also easier because such a backup generally not undesirable even at high temperatures material connection with the surrounding material received or if necessary easier to detach from this is.
- the security strip 24 should accordingly as well as the insert strips 11 made of highly heat-resistant material consist.
- the openings 56 should if possible on the security strips 24 be well adjusted so that no hot gas in the Blade platform 5 penetrates.
- the width of the security strip 24 can be adapted to the strength of the attacking forces ends 80 can also be placed under the insert strips 11 reach through and possibly wider than their Width 25.
- Figures 6a, 6b show an exemplary embodiment of a Insert strip 11, the 34 at its disc end has an enlarged width 25 compared to the rest of the part.
- the recess 10 is on its disc side End 14 formed wider than the rest of its part. It has undercuts 85. This is a Slipping out of the insert strip 11 when attacking Centrifugal forces even with an open wing end 75 the recess 10 prevented. No gap 19 is provided and the distance of the blade platform 5 from the disk circumference 7 kept small. This way one can go through strong gas turbine blade acting in the direction of use 30 loads 1 be kept safe.
- the width 25 of the insert strip 11 can be in an alternative Training also from its disc-side end 34 to steadily decrease to its wing-side end 75.
- a screw part 100 or a bolt below the insert strip 11 be arranged on the disc end face 22.
- the insert strip 11 provides for the narrow space 12 a particularly small contact surface compared to hot gases, or is well sealed against the ingress of hot gases.
- the insert strip 11 engages with a predetermined one Depth of engagement 95 in the recess 10 of the blade platform 5 of depth 90 a.
- the depth of engagement 95 of Insert strip 11 in the recess 10 is larger than that Gap 12 between two adjacent blade platforms 5. This enables the insert strip to be held very securely 11 in the recess 10.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Dies reduziert die Zahl der benötigten Elemente. Gleichzeitig läßt sich der Einsatzstreifen wiederum leicht entfernen, wenn zum Beispiel Gasturbinenschaufeln ausgetauscht werden sollen.
- FIG 1
- eine perspektivische Ansicht eines Ausschnitts der Scheibe mit eingesetzter Gasturbinenschaufel,
- FIG 2
- eine Seitenansicht einer Gasturbinenschaufel mit Einsatzstreifen,
- FIG 3
- eine Seitenansicht einer Schraubfixierung des Einsatzstreifens,
- FIG 4a,b
- Sicherungsnutfixierungen des Einsatzstreifens,
- FIG 5
- eine perspektivische Ansicht einer Gasturbinenschaufel mit eingesetzten Sicherungsstreifen,
- FIG 6a
- eine Aufsicht auf einen scheibenseitig verbreiterten Einsatzstreifen und
- FIG 6b
- eine perspektivische Ansicht eines verbreiterten Einsatzstreifens.
Claims (13)
- Gasturbinenrotor, mit einer innenraumgekühlten Gasturbinenschaufel (1), die einen Schaufelfuß (2) und eine Schaufelplattform (5) aufweist, und mit einer Scheibe (4), die Scheibenquernuten (3) besitzt, in die der Schaufelfuß (2) eingesetzt ist, wobei die Schaufelplattform (5) außerhalb eines Außenumfangs (7) der Scheibe (4) angeordnet ist und an einem Endwandabschnitt (8) einer Längsseite (9) eine Ausnehmung (10) besitzt, in die ein Einsatzstreifen (11) eingesetzt ist, der in eine entsprechende Ausnehmung (10) einer Schaufelplattform (5) einer zweiten Gasturbinenschaufel (1) eingreift und einen Zwischenraum (12) zwischen den beiden Schaufelplattformen (5) überbrückt und abdichtet,
dadurch gekennzeichnet, daß die Ausnehmung (10) bis an eine scheibenseitige Basis (13) der Schaufelplattform (5) reicht und der Einsatzstreifen (11) einen gegen axiale Verschiebung in einer Einsatzrichtung (30) der Gasturbinenschaufel (1) absichernden Formschluß an der Scheibe (4) aufweist. - Gasturbinenrotor nach Anspruch 1,
dadurch gekennzeichnet, daß an den Endwandabschnitten (8) einer Längsseite (9) der Schaufelplattform (5) jeweils eine Ausnehmung (10) vorhanden ist, und daß deren Einsatzstreifen (11) an zwei einander gegenüberliegenden Scheibenstirnseiten (22) anliegen und gegen axiale Verschiebungen der Gasturbinenschaufel (1) relativ zur Scheibe (4) absichern. - Gasturbinenrotor nach einem oder mehreren der Ansprüche 1 oder 2,
dadurch gekennzeichnet, daß die Ausnehmung (10) schräg in Richtung einer Rotorlängsachse (16) des Gasturbinenrotors verläuft und an ihrem scheibenseitigen Ende (14) in eine der Ausnehmung (10) entsprechend schräge Fase (17) des Scheibenkopfes (6) mündet. - Gasturbinenrotor nach einem oder mehreren der Ansprüche 1 bis 3,
dadurch gekennzeichnet, daß der Einsatzstreifen (11) bei in die Scheibenquernut (3) eingesetzter Gasturbinenschaufel (1) scheibenseitig in die Ausnehmung (10) einzuschieben und gegen Fliehkräfte formschlüssig an der Scheibe und/oder an der Schaufelplattform gesichert ist. - Gasturbinenrotor nach einem oder mehreren der Ansprüche 1 bis 4,
dadurch gekennzeichnet, daß es zwischen dem scheibenseitigen Ende (14) der Ausnehmung (10) und dem Außenumfang (7) der Scheibe (4) einen Relativbewegungen zwischen der Scheibe (4) und der Schaufelplattform (5) zulassenden Spalt (19) gibt. - Gasturbinenrotor nach einem oder mehreren der Ansprüche 1 bis 5,
dadurch gekennzeichnet, daß die Ausnehmung (10) als Nut ausgebildet ist. - Gasturbinenrotor nach einem oder mehreren der Ansprüche 1 bis 6,
dadurch gekennzeichnet, daß die Ausnehmung (10) an ihrem scheibenseitigen Ende (14) breiter ist als in ihrem restlichen Teil. - Gasturbinenrotor nach einem oder mehreren der Ansprüche 1 bis 7,
dadurch gekennzeichnet, daß der Einsatzstreifen (11) in seiner Einschubstellung an der Scheibe (4) fixiert ist. - Gasturbinenrotor nach einem oder mehreren der Ansprüche 1 bis 8,
dadurch gekennzeichnet, daß zur Fixierung des Einsatzstreifens (11) ein Schraubteil (20) dient, das in eine Ausnehmung (60) des Einsatzstreifens (11) eingreift und das sich unter Fliehkrafteinwirkung am Einsatzstreifen (11) abstützt. - Gasturbinenrotor nach einem oder mehreren der Ansprüche 1 bis 9,
dadurch gekennzeichnet, daß der Einsatzstreifen (11) an einem scheibenseitigen Ende (14) in eine Sicherungsausnehmung (70) der Scheibenstirnseite (22) eingreift. - Gasturbinenrotor nach einem oder mehreren der Ansprüche 1 bis 10,
dadurch gekennzeichnet, daß ein Sicherungsstreifen (24) unter der Schaufelplattform (5) durch zwei Einsatzstreifen (11) hindurchführt und an seinen Enden (80) umgebogen ist. - Gasturbinenrotor nach einem oder mehreren der Ansprüche 1 bis 11,
dadurch gekennzeichnet, daß der Einsatzstreifen (11) draht- oder blechförmig ausgebildet ist. - Gasturbinenrotor nach einem oder mehreren der Ansprüche 1 bis 12,
dadurch gekennzeichnet, daß der Einsatzstreifen (11) mit einer vorbestimmten Eingriffstiefe (95) in die Ausnehmung (10) der Schaufelplattform (5) eingreift und daß die Eingriffstiefe (95) des Einsatzstreifens (11) in die Ausnehmung (10) größer ist, als der Zwischenraum (12) zwischen zwei benachbarten Schaufelplattformen (5).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00920496A EP1163427B1 (de) | 1999-03-19 | 2000-03-13 | Gasturbinenrotor mit innenraumgekühlter gasturbinenschaufel |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP99105683 | 1999-03-19 | ||
EP99105683 | 1999-03-19 | ||
EP00920496A EP1163427B1 (de) | 1999-03-19 | 2000-03-13 | Gasturbinenrotor mit innenraumgekühlter gasturbinenschaufel |
PCT/EP2000/002209 WO2000057031A1 (de) | 1999-03-19 | 2000-03-13 | Gasturbinenrotor mit innenraumgekühlter gasturbinenschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1163427A1 EP1163427A1 (de) | 2001-12-19 |
EP1163427B1 true EP1163427B1 (de) | 2003-12-10 |
Family
ID=8237822
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00920496A Expired - Lifetime EP1163427B1 (de) | 1999-03-19 | 2000-03-13 | Gasturbinenrotor mit innenraumgekühlter gasturbinenschaufel |
Country Status (5)
Country | Link |
---|---|
US (1) | US6561764B1 (de) |
EP (1) | EP1163427B1 (de) |
JP (1) | JP2003526039A (de) |
DE (1) | DE50004724D1 (de) |
WO (1) | WO2000057031A1 (de) |
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EP1284339A1 (de) * | 2001-08-14 | 2003-02-19 | Siemens Aktiengesellschaft | Abdeckringsystem für Schaufelscheiben von Gasturbinen |
JP2005009382A (ja) * | 2003-06-18 | 2005-01-13 | Ishikawajima Harima Heavy Ind Co Ltd | タービンロータ、タービンディスク、及びタービン |
US7334331B2 (en) * | 2003-12-18 | 2008-02-26 | General Electric Company | Methods and apparatus for machining components |
DE102004037331A1 (de) | 2004-07-28 | 2006-03-23 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenrotor |
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EP1914386A1 (de) * | 2006-10-17 | 2008-04-23 | Siemens Aktiengesellschaft | Turbinenschaufelanordnung |
US7566201B2 (en) * | 2007-01-30 | 2009-07-28 | Siemens Energy, Inc. | Turbine seal plate locking system |
ATE466169T1 (de) | 2007-04-05 | 2010-05-15 | Alstom Technology Ltd | Spaltdichtung für schaufeln einer turbomaschine |
US8469656B1 (en) | 2008-01-15 | 2013-06-25 | Siemens Energy, Inc. | Airfoil seal system for gas turbine engine |
US8096758B2 (en) * | 2008-09-03 | 2012-01-17 | Siemens Energy, Inc. | Circumferential shroud inserts for a gas turbine vane platform |
GB2467582B (en) * | 2009-02-10 | 2011-07-06 | Rolls Royce Plc | Vibration damper assembly |
US8696320B2 (en) * | 2009-03-12 | 2014-04-15 | General Electric Company | Gas turbine having seal assembly with coverplate and seal |
US20100232939A1 (en) * | 2009-03-12 | 2010-09-16 | General Electric Company | Machine Seal Assembly |
GB0906342D0 (en) * | 2009-04-15 | 2009-05-20 | Rolls Royce Plc | Apparatus and method for simulating lifetime of and/or stress experienced by a rotor blade and rotor disc fixture |
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GB699582A (en) * | 1950-11-14 | 1953-11-11 | Rolls Royce | Improvements in or relating to gas-turbine engines |
GB779059A (en) * | 1954-07-15 | 1957-07-17 | Rolls Royce | Improvements in or relating to axial-flow fluid machines, for example compressors orturbines of gas-turbine engines |
BE540433A (de) * | 1954-08-12 | |||
GB905582A (en) * | 1960-05-26 | 1962-09-12 | Rolls Royce | Improvements relating to the sealing of blades in a bladed rotor |
DE1258662B (de) | 1964-10-28 | 1968-01-11 | Goerlitzer Maschb Veb | Deckscheibe fuer die Kuehlgasfuehrung von Gasturbinenlaeufern |
US3748060A (en) * | 1971-09-14 | 1973-07-24 | Westinghouse Electric Corp | Sideplate for turbine blade |
GB2010404B (en) * | 1977-12-17 | 1982-02-10 | Rolls Royce | Gas turbine engines |
US4523890A (en) | 1983-10-19 | 1985-06-18 | General Motors Corporation | End seal for turbine blade base |
JP3462695B2 (ja) | 1997-03-12 | 2003-11-05 | 三菱重工業株式会社 | ガスタービン動翼シール板 |
-
2000
- 2000-03-13 DE DE50004724T patent/DE50004724D1/de not_active Expired - Fee Related
- 2000-03-13 WO PCT/EP2000/002209 patent/WO2000057031A1/de active IP Right Grant
- 2000-03-13 EP EP00920496A patent/EP1163427B1/de not_active Expired - Lifetime
- 2000-03-13 JP JP2000606876A patent/JP2003526039A/ja not_active Withdrawn
- 2000-03-13 US US09/936,990 patent/US6561764B1/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
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US6561764B1 (en) | 2003-05-13 |
JP2003526039A (ja) | 2003-09-02 |
EP1163427A1 (de) | 2001-12-19 |
DE50004724D1 (de) | 2004-01-22 |
WO2000057031A1 (de) | 2000-09-28 |
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