EP3194725A1 - Rotor, compresseur axial, procédé de montage - Google Patents

Rotor, compresseur axial, procédé de montage

Info

Publication number
EP3194725A1
EP3194725A1 EP15788071.7A EP15788071A EP3194725A1 EP 3194725 A1 EP3194725 A1 EP 3194725A1 EP 15788071 A EP15788071 A EP 15788071A EP 3194725 A1 EP3194725 A1 EP 3194725A1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade
shaft
cover
rbs
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
Application number
EP15788071.7A
Other languages
German (de)
English (en)
Other versions
EP3194725B1 (fr
Inventor
Viktor Hermes
Rosario Montante
Erich Muranyi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP3194725A1 publication Critical patent/EP3194725A1/fr
Application granted granted Critical
Publication of EP3194725B1 publication Critical patent/EP3194725B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • 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
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/053—Shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings

Definitions

  • Rotor, axial compressors, method for mounting The invention relates to a rotor of a multi-stage axial compressor, which extends along a rotational axis, the rotor having a shaft, said shaft having drive vane ⁇ , wherein adjacently arranged in peripheral direction and at the Laufschaufelnuten each case by means of a blade root attached to the rotor blades of the rotor depending ⁇ wells form a blade stage, said axial rear reinan ⁇ the at least two blade stages are provided and which extends in the peripheral direction
  • the rotor comprises an interspace cover which surrounds the intermediate blades raumnuten covers, wherein the space cover is formed segmented in the circumferential direction in space cover segments, wherein the space cover segments are positively
  • the invention also relates to an axial compressor and a method for mounting the axial compressor with the above Ro ⁇ tor.
  • Shaft of an axial compressor provides that an extending in the circumferential direction groove with undercuts on the shaft is provided and the rotating blades with a corresponding also undercut trained foot at a certain circumferential position radially into this circumferential groove at a threading point in a certain scope - Position are introduced and then to the ready for the assembled shaft or for the fully assembled rotor intended circumferential end position to be moved.
  • the feet of the blades are hereby regularly formed as Hammerkopffuß and the connection of the shaft with the blade is positively.
  • a less reliable connection can also take place by means of non-undercut trained blade feet on the shaft, for example by means of locking pins, which plug in the axial direction connect a shaft shoulder with a drilled in the axial direction blade foot positively.
  • Such training is for example from the
  • Axially between the two blade stages of a compressor of the above type is regularly seen before ⁇ a guide blade stage, which aligns the process of the axial compressor through the process fluid for entry into the downstream run ⁇ blade stage accordingly.
  • the advantage of a blade which is fastened in a circumferential groove extending in the circumferential direction lies in the low production expenditure , since the bypass groove can be produced by a simple turning operation.
  • the foot geometry as a hammer head which is regularly provided for positive fastening in higher-loaded axial compressors, in conjunction with the circumferential groove in the shaft and the orientation of the blade on the rotor in such a way that only a limited contact surface between the shaft material and the Blade ⁇ foot material for transmitting forces from the blade to the shaft is available.
  • each is an individual ⁇ blade only to the number of running blades of a stage above the circumferential small circumferential segment is available, the power to the undercut in the circumferential groove to übertra ⁇ gene.
  • This is by means of the undercut of the foot in the geometry of the hammer head foot established that the width in the circumferential direction of the izoflä ⁇ surfaces of the undercut can not go beyond the width of the circumferential segment.
  • Demen Schemeend acts for the transmission of forces available geometry of the circumferential groove with the Hammerkopffuß limiting the rotational speed and the diameter of the rotor at a certain mass of the blade.
  • the insertion direction runs obliquely to a rotation axis of the rotor at an angle which is particularly advantageous mechanically for the alignment of the blade leaf and the blade root.
  • the fastening ⁇ grooves of such a blade attachment is not incorporated by means of a rotary process in the shaft son ⁇ countries are milled in the shaft or generated in a different way.
  • integrally formed shaft that is not single
  • the attachment groove opens into the circumferential groove.
  • a circumferential groove can also a wave heel be provided.
  • the separate for each blade mounting grooves are also designed as Tannbaumnuten. Tannbaumnuten already be ⁇ known from US 2014/0037396 Al.
  • the circumferential groove is characterized by the invention as a gap groove ⁇ and affects aerodynamically loss-enhancing at a flow through the Axialver.
  • the raumnut intermediate ⁇ is also therefore covered by means of a guide blade to the flow channel out.
  • the guide vane cover strip is fastened here as a stationary component of circumferentially extending individual segments at the radially inner tips of the guide vanes.
  • the invention has set itself the task of creating a rotor of an axial compressor, which avoids the aforementioned disadvantages of the prior art.
  • an axial compressor is proposed with such a rotor according to the invention.
  • the invention proposes a method for manufacturing an axial compressor with a rotor according to the invention.
  • a multi-stage axial compressor according to the invention is of a process fluid flows axially substantially in the compression ⁇ gradually and there is from the last stage of sealing Ver ⁇ a substantially axial outflow.
  • the individual compression stages typically include a vane stage and a blade stage.
  • the invention means the axis about which the rotor of the axial compressor is rotatably formed. Unless stated otherwise, this data refers to all data relating to an axis, such as axial, radial, circumferential direction, tangential.
  • the individual blades of a rotor blade stage of the rotor are fastened by means of a blade root to the shaft of the rotor, wherein the blade root is attributable to the rotor blade.
  • each blade stage is assigned at least one in the circumferential direction extending gap groove in the shaft.
  • This gap groove is covered according to the invention by means of a space cover radially outward.
  • Another expedient development of the invention provides that a clearance groove two adjacent Laufschau ⁇ felmen are assigned, so that the blade stages for mounting the blades on each blade grooves on pointing, which open for both blade stages in the same circumferential groove.
  • a clearance groove two adjacent Laufschau ⁇ fel caren are assigned, so that the blade stages for mounting the blades on each blade grooves on pointing, which open for both blade stages in the same circumferential groove.
  • it is possible in this way only in every second space between blade stages provide a clearance groove for mounting the run ⁇ blades. In this way, it is conceivable that intermediate spaces between blade stages in alternating sequence each have a clearance groove and have no clearance groove.
  • a cover of the space groove by means of the space covers such that a substantially continuous radial transition in the axial direction of the radially outer surface between the upstream run ⁇ blade stage and the space cover and the space cover and the downstream Schaufelstu ⁇ fe results.
  • the advantages of the invention come to the fore, because between the space cover and the shaft main body or the shaft no movement gaps are provided, since the space cover with the shaft forms a firm connection and is mounted with-rotating.
  • the shaft is formed over at least the axial Ab ⁇ section of two blade stages and a clearance groove as a one-piece component.
  • the shaft is formed as a one-piece axially undivided component on the axial compressor.
  • the application of the invention is not to the same extent is beneficial because the slice-wise composition of the rotor offers ⁇ greater opportunities to cover the gap.
  • Preferred is therefore an axially at least partially unge ⁇ divided, in particular massive one-piece shaft design over several blade stages.
  • a further advantageous embodiment provides that the interspace cover is arranged and designed such that the rotor blades are secured in the axial end position in the blade groove against displacement by means of the interspace cover.
  • the space cover fulfills not only the aerodynamic function of the flow guidance but also the mechanical function of securing the rotor blade in the intended axial position on the rotor. In this case, it is conceivable for the blade feet of the rotor blade to rest against the intermediate space cover or to come into contact with the respective space cover with play. A corresponding axial clearance fit or
  • Press fit may be provided constructively for this purpose. While the blade feet are positively anchored to a radial disengagement on the shaft, a positive obstruction of an axial movement of the blades results through the gap cover. Particularly useful is a design of the blade feet as so-called Tannenbaumfpune, so that in comparison to a Hammerkopffuß radial successively arranged several surfaces of the Christmas tree root abut against corresponding contact surfaces of the sliding fine.
  • each septum space cover segments form fit to the shaft are attached.
  • each septraumabdeckungsseg ⁇ ment be equipped with a hammer foot, which can be used in a ent ⁇ speaking extending in the circumferential direction shaping the gap.
  • An expedient development of the invention provides that at least one gap lock ⁇ piece is provided for each insectsnut that at a particular first circumferential position of insects is arranged at the Eisenraumnut for the purpose of the radial insertion of the interim ⁇ rule space cover segments is different designed as over the remaining circumference of the shaft.
  • the intermediate raumnut at least partially extending having over the circumference a first undercut which is provided with a second undercut of the gap cover segment form ⁇ conclusively ⁇ sammenhabilitd formed blocking in the radial direction movement.
  • the space lock piece is used to cover the gap at this circumferential position and at the same time set the respective circumferential position of all insectsraumabde ⁇ ckungssegmente, which are arranged in this space groove.
  • the interspace lock piece can in this case be fastened by means of a screw connection against a radial disengagement on the shaft.
  • the gap groove advantageously has no first undercut.
  • the axial compressor according to the invention provides that radially opposite the Eisenraumnut and the axially adjacent to at least a moving blade stage arranged guide vane stage ⁇ the local guide vanes are formed as free-standing Leitschau ⁇ feln without a shroud.
  • the invention also proposes a method for mounting this rotor, which is particularly applicable for the inventive design of the rotor. sector.
  • a wave is thereby provided ⁇ which is fitted in a second step with the rotor blades to be inserted with the blade roots radially into the interim ⁇ schenraumnuten and then vane means of single-shifting of the blade roots of the rotor blades in the running ⁇ be attached.
  • the axial position of the blade feet or blades on the shaft of the rotor is then secured by means of mounting the space cover segments form fit to the shaft.
  • Figure 1 is a schematic three-dimensional view of two adjacent blade stages and a clearance groove with clearance cover
  • Figure 2 is a schematic three-dimensional view of two adjacent blade stages with intermediate therebetween gutter and a space cover in a further embodiment
  • FIG. 3 shows a schematic sectional view of second adjacent blade stages of an axial compressor with a guide blade stage located therebetween in the region of the intermediate space with a clearance groove and a clearance cover.
  • Figures 1 and 2 each show different variants of the invention with reference to two adjacent blade stages RBS in a schematic three-dimensional view.
  • 3 shows a schematic longitudinal section through two adjacent blade stages RBS of an axial compressor ACO, which is only partially shown here.
  • the blade stages RBS are each represented only as a single blade RB, along a circumferential direction CD actually several blades arranged side by side result in a blade stage RBS.
  • a shaft SH of a rotor R of an axial compressor ACO he ⁇ extends along a rotational axis X.
  • jeweili ⁇ gen representations is shown in each case listed in axial sequence: a rotor blade stage RBS, a gap with egg ⁇ ner amraumnut and a gap cover IC and another Blade level RBS.
  • the blade stages is reproduced radially opposite the IG bacteriaraumnut a vane stage comprising vanes GVS GV.
  • the guide vanes GV are formed without a circumferentially extending radially inside the guide vane befindliches shroud and accordingly ⁇ freestanding.
  • the blades RB are each connected positively in the blade grooves RBG with the shaft SH.
  • blade roots RBF are introduced into the blade grooves RBG, which prevent a radial disengagement of the blades RB from the shaft SH of the rotor R.
  • the Laufschaufel Stahl- SSE RBF are formed in the shape of a hammer head and korres ⁇ pondieren in the mold with the Laufschaufelnut in the shaft SH, so that the undercuts of the hammer head foot with which the Laufschaufelnut a positive connection ge ⁇ gen form an axial disengagement.
  • the blade root can also be designed as a fir tree root or have another shape with undercuts. Between the two blade stages RBS is a gap groove IG in the shaft SH, which extends in the direction CD.
  • the blade grooves wherein a blade groove RBG is provided for each blade RB, Mün ⁇ all in this insectraumnut IG.
  • a single breeding knife IG is provided for mounting the Laufschaufein RB for two blade stages RBS, on both sides of the gap groove IG.
  • the rotor blades are radially inserted RB ⁇ leads with its blade root in the RBF pregnantraumnut IG and then inserted axially substantially in the running ⁇ blade groove RBG. After all the are positioned in their final position in the rotor R and the shaft SH, the gap cover IC for Ab ⁇ cover the insectsnut IG radially outward to the Wel ⁇ le SH and the rotor R is mounted.
  • individual intermediate space cover segments of the falraumabde ⁇ ckung IC can be mounted in the areas where the blades RB have already been introduced using the Eisenraumnut IG and demenschend secured in Endpositi ⁇ on against axial displacement by means of the gap cover segments ICS.
  • the Swissraumabde ⁇ ckungssegmente ICS close the septraumnut IG of the ⁇ art, that a substantially smooth and continuous transition in the axial direction between the upstream blade stage RBS and the insectsnut IG or the intermediate compartment cover IC and the downstream moving blade stage RBS is given.
  • the space cover segments ICS are positively attached to the shaft SH.
  • Undercut LI of the space groove IG can be introduced in the circumferential direction.
  • the clearance groove has no first undercut LI, so that a radial insertion of the hammerhead foot of the clearance cover segments ICS is possible.
  • An alternative to the hammerhead feet of Figure 1 shows a reproduced in Figure 2 variant of the invention, where the insectsabde ⁇ ckungssegmente ICS have an omega shape and the second undercut L2 extends beyond the axial region of the Eisenraumnut IG addition.
  • the corresponding first circumferential position is not shown in FIG. 2, but for the purpose of radial insertion, the interstice cover segment must be provided.
  • Have ICS recesses extending axially into the region of the blade stages RBS.
  • FIG. 3 shows one way in which a gap cover segment ICS may be formed at the first circumferential position as a gap lock piece ICL and fastened to the shaft SH.
  • the gap lock piece ICSL is secured radially by means of a screw SR and against displacement in the circumferential direction. In this way, all gap cover segments ISC are positively fixed in the circumferential position.
  • all clearance Cover ⁇ ICS segments are fixed by a screw on the shaft SH SR ⁇ to additionally or exclusively, in a particular embodiment of the invention without further form closure against radial disengagement.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un rotor (R) d'un compresseur axial multi-étagé (ACO) qui s'étend le long d'un axe de rotation (X), le rotor (R) comportant un arbre (SH), l'arbre (SH) comportant des rainures de pales (RBG). Des pales (RB) du rotor (R) disposées les unes derrière les autres dans la direction de maniement (CD) et fixées sur les rainures de pales (RBG), chacune au moyen d'une patte (RBF), forment chacune un étage de pale (RBS) et au moins deux étages de pales (RBS) sont prévus axialement les uns derrière les autres et une rainure d'espace intermédiaire (IG) s'étendant dans la direction de maniement est prévue axialement dans l'arbre (SH) entre les deux étages de pale (RBS). Selon l'invention, les rainures de pale (RBG) débouchent dans les rainures d'espace intermédiaire (IG) et cet agencement est configuré de telle sorte que des pattes (RBF) des pales de rotor (RB) peuvent être introduites radialement dans les rainures d'espace intermédiaire (IG) et, de là, peuvent être insérées dans les rainures (RBG) des pales. Pour améliorer l'aérodynamique et pour simplifier le montage, l'invention propose que le rotor (R) comprenne un couvercle d'espace intermédiaire (IC) qui recouvre les rainures d'espace intermédiaire (IG), le couvercle d'espace intermédiaire (IC) étant configuré de manière segmentée dans la direction circonférentielle (CD) dans des segments de couvercle d'espace intermédiaire (ICS).
EP15788071.7A 2014-12-04 2015-11-03 Rotor, compresseur axial, procédé de montage Not-in-force EP3194725B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014224844.2A DE102014224844A1 (de) 2014-12-04 2014-12-04 Rotor, Axialverdichter, Verfahren zur Montage
PCT/EP2015/075575 WO2016087153A1 (fr) 2014-12-04 2015-11-03 Rotor, compresseur axial, procédé de montage

Publications (2)

Publication Number Publication Date
EP3194725A1 true EP3194725A1 (fr) 2017-07-26
EP3194725B1 EP3194725B1 (fr) 2019-04-10

Family

ID=54365273

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15788071.7A Not-in-force EP3194725B1 (fr) 2014-12-04 2015-11-03 Rotor, compresseur axial, procédé de montage

Country Status (6)

Country Link
US (1) US10830253B2 (fr)
EP (1) EP3194725B1 (fr)
CN (1) CN107002493B (fr)
DE (1) DE102014224844A1 (fr)
RU (1) RU2678865C2 (fr)
WO (1) WO2016087153A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113606186B (zh) * 2021-08-24 2023-11-03 中国联合重型燃气轮机技术有限公司 一种压气机双级转子叶片锁紧装置、压气机及燃气轮机
CN113586519B (zh) * 2021-08-24 2023-09-26 中国联合重型燃气轮机技术有限公司 锁紧装置及包括该锁紧装置的压气机、燃气轮机
CN113586520B (zh) * 2021-08-24 2023-09-01 中国联合重型燃气轮机技术有限公司 锁紧装置及包括该锁紧装置的压气机、燃气轮机

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB612097A (en) 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors
BE496713A (fr) 1949-07-01
US3603702A (en) * 1969-05-01 1971-09-07 Carrier Corp Rotor assembly
DE2620762C2 (de) 1976-05-11 1977-11-17 Motoren- und Turbinen-Union München GmbH, 8000 München Spaltdichtung für Strömungsmaschinen, insbesondere Gasturbinenstrahltriebwerke
JPS57168005A (en) * 1981-04-10 1982-10-16 Hitachi Ltd Rotor structue for axial machines
GB2293628B (en) * 1994-09-27 1998-04-01 Europ Gas Turbines Ltd Turbines
DE19615549B8 (de) * 1996-04-19 2005-07-07 Alstom Vorrichtung zum thermischen Schutz eines Rotors eines Hochdruckverdichters
ITMI20012783A1 (it) 2001-12-21 2003-06-21 Nuovo Pignone Spa Sistema di connessione e bloccaggio di pale rotoriche di un compressore assiale
US8567059B2 (en) 2009-07-10 2013-10-29 Pratt & Whitney Canada Corp. Process for forming a firtree slot in a disc of a rotor of a gas turbine engine
US8376689B2 (en) 2010-04-14 2013-02-19 General Electric Company Turbine engine spacer
FR2964692B1 (fr) 2010-09-13 2012-11-09 Snecma Dispositif de blocage circonferentiel d'aubes marteau pour turbomachine, a deploiement radial ameliore
US9528376B2 (en) * 2012-09-13 2016-12-27 General Electric Company Compressor fairing segment

Also Published As

Publication number Publication date
RU2678865C2 (ru) 2019-02-04
CN107002493A (zh) 2017-08-01
EP3194725B1 (fr) 2019-04-10
RU2017123340A (ru) 2019-01-10
RU2017123340A3 (fr) 2019-01-10
CN107002493B (zh) 2019-10-08
DE102014224844A1 (de) 2016-06-09
WO2016087153A1 (fr) 2016-06-09
US20170268536A1 (en) 2017-09-21
US10830253B2 (en) 2020-11-10

Similar Documents

Publication Publication Date Title
DE602004006323T2 (de) Verfahren zur Herstellung einer Turbine mit Turbinenschaufeln unterschiedlicher Resonanzfrequenzen samt einer solchen Turbine
EP2877701B1 (fr) Rotor d'un turbocompresseur
EP2647795B1 (fr) Système d'étanchéité pour turbomachine
EP2302174A2 (fr) Turbine à gaz avec un joint à labyrinthe de la virole
EP2478186B1 (fr) Rotor de turbomachine
EP2824282A1 (fr) Turbine à gaz avec système de refroidissement de turbine à haute pression
CH704105B1 (de) Mehrstufige Gasturbine.
EP2505851B1 (fr) Aubage de stator pour un compresseur axial dans une turbomachine
EP2818724B1 (fr) Turbomachine et procédé
EP3404210A1 (fr) Segment de grille d'aubes d'une turbomachine avec paroi de plateforme non-axisymétrique , grille d'aubes, canal d'aube, plateforme, turbomachine associés
WO2016087153A1 (fr) Rotor, compresseur axial, procédé de montage
EP3388626B1 (fr) Contournage d'une plate-forme de grille d'aube
EP2647796A1 (fr) Système d'étanchéité pour turbomachine
EP2410131B1 (fr) Rotor d'une turbomachine
EP1706595B1 (fr) Turbomachine comprenant un canal en spirale dans la partie mediane du carter
EP3312388B1 (fr) Pièce de rotor, compresseur, turbine et procédé de fabrication associés
WO2015074912A1 (fr) Garniture d'étanchéité d'arbre et procédé pour la fabriquer
EP2878773B1 (fr) Turbine à gaz avec anneau fendu de fixation
DE102014226195A1 (de) Radialturbofluidenergiemaschine
EP3636880B1 (fr) Roue de turbine
EP2294285A2 (fr) Grille d'aubes pour une turbomachine et turbomachine comportant une telle grille
CH714391B1 (de) Turbinenleitapparat.
WO2021083442A1 (fr) Ensemble aube directrice de turbomachine
EP3369892B1 (fr) Contournage d'une plate-forme de grille d'aube
EP3536913A1 (fr) Bague intérieure pour une turbomachine et procédé de fabrication de cette bague intérieure

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20170419

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL 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 RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190104

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL 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 RS 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

Ref country code: AT

Ref legal event code: REF

Ref document number: 1118893

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190415

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: 502015008671

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190410

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: 20190410

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

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: 20190410

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: 20190910

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: 20190410

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: 20190410

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: 20190410

Ref country code: AL

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: 20190410

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: 20190710

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: 20190410

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

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: 20190711

Ref country code: RS

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: 20190410

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: 20190710

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: 20190410

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: 20190410

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

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: 20190810

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502015008671

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: 20190410

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: 20190410

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: 20190410

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: 20190410

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: 20190410

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

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

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: 20190410

Ref country code: IT

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: 20190410

26N No opposition filed

Effective date: 20200113

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: 20190410

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: 20190410

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191130

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: 20190410

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191130

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191103

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20191130

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20191103

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191103

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191103

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191130

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: 20191130

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502015008671

Country of ref document: DE

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG, DE

Free format text: FORMER OWNER: SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

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: 20190410

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20210119

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

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: 20151103

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: 20190410

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1118893

Country of ref document: AT

Kind code of ref document: T

Effective date: 20201103

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: 20201103

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502015008671

Country of ref document: DE

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190410

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220601