EP0028217A1 - Rotor pour turbomachine thermique - Google Patents

Rotor pour turbomachine thermique Download PDF

Info

Publication number
EP0028217A1
EP0028217A1 EP80890125A EP80890125A EP0028217A1 EP 0028217 A1 EP0028217 A1 EP 0028217A1 EP 80890125 A EP80890125 A EP 80890125A EP 80890125 A EP80890125 A EP 80890125A EP 0028217 A1 EP0028217 A1 EP 0028217A1
Authority
EP
European Patent Office
Prior art keywords
rotor
elastic
disks
discs
pieces
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.)
Withdrawn
Application number
EP80890125A
Other languages
German (de)
English (en)
Inventor
Herbert Prof.Dr.Dipl.Ing. Jericha
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.)
Andritz Hydro GmbH Austria
Original Assignee
Andritz Hydro GmbH Austria
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 Andritz Hydro GmbH Austria filed Critical Andritz Hydro GmbH Austria
Publication of EP0028217A1 publication Critical patent/EP0028217A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D5/02—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
    • F01D5/02—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
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps

Definitions

  • the invention relates to a rotor for a thermal turbomachine, in particular for an industrial exhaust gas turbine utilizing the exhaust gases of chemical or petrochemical processes, which is constructed from individual disks and two shaft ends and is clamped together by axial clamping bolts.
  • the problem with the design of rotors and gas turbines is that individual parts of the rotor remain almost cold at the cooling air temperature, such as the compensating piston and the low-pressure outlet side, while other parts are heated almost to the hot gas temperature. It is especially the first disc of the gas turbine with the highest temperature.
  • the disks can reach different temperatures depending on their environmental conditions, such as the compensating piston at the cooling air temperature, the first disk at the highest gas temperature, the last disk at the lowest gas temperature and the outlet-side shaft end again at cooling air temperature.
  • the middle disks are then at a temperature of 500 - 600 ° C while the cold parts of the rotor reach about 200 ° C.
  • the corresponding strain difference for a medium rotor is in the order of magnitude of 0.5-2 mm radial expansion.
  • the clamping bolts must be dimensioned in such a way that when the axial expansions of the washers are absorbed, they do not come into the plastic range in accordance with their temperature increase, but retain their elastic prestress.
  • this arrangement above has the disadvantage that there is no perfect centering of the individual disks, since small movements in the Hirth toothing are always possible due to the necessary play and therefore eccentricities of the individual disks occur during their expansion.
  • welded rotors for gas turbines are known in which a plurality of disks, which are shaped in the form of a disk of the same strength, are connected to one another by a deep tulip-shaped weld seam with a rim that is very wide in the radial direction.
  • no axial clamping bolts are required, since the washers are directly connected to one another by welds.
  • there are different temperatures between the individual disks which causes radial expansion differences at the welding point. These differences in elongation must now be absorbed by elastic deformation of the intermediate piece.
  • this intermediate piece is made much thicker than the intermediate pieces of the constructions with Hirth toothing, so that the absorption of the radial displacements causes great bending forces in this intermediate piece.
  • these high bending forces have to be absorbed by the weld seams, which requires a particularly careful design of the weld seams and thus a correspondingly expensive production.
  • this construction can only be made from disks of the same material, since the welding of high-temperature materials and low-temperature materials causes metallurgical difficulties.
  • certain high-temperature materials, especially austenites are difficult to weld.
  • dumbbell rings of the Ljungström turbine which compensate for radial expansion differences by movement in the double spherical (torus) seat of the dumbbell-shaped elements by means of a joint effect.
  • the disadvantage here is that a sliding movement occurs in the ball seats and the barbell ring deforms as in a joint. Since a turning moment can not be transmitted by positive locking but only by frictional forces and because the manufacture of a ball seat is correspondingly inaccurate or expensive and there is only slight pretensioning by caulking, in contrast to high pretensioning of the clamping bolts, can also be brought up: only low torques, in each case those of a vane grille but not of an entire rotor, are transmitted.
  • the object of the present invention is to provide a rotor which does not have any of the above disadvantages and which is also assembled with lower pretensioning forces.
  • the rotor described in the introduction is characterized according to the invention in that the individual disks, which are preferably made of different materials, are spaced apart by elastic intermediate pieces and that at least one connection of the elastic intermediate pieces to one another or to the disks is positively under axial prestress.
  • the invention makes it possible for the first time to produce a rotor for a thermal turbomachine, in which disks of different materials can also be used and in which the large temperature differences between the disks and, accordingly, the large relative radial expansions are mastered.
  • These radial expansions are absorbed by elastic deformation of the intermediate pieces, with no sliding and therefore no wear occurring at the fastening points.
  • the torques of the gas forces are preferably transmitted by friction in these fastening points.
  • these frictional forces are used to make do with lower pretensioning forces, i.e. with weaker and more elastic axial clamping bolts.
  • the elastic intermediate piece has the shape of a ring and the outer peripheral surface of this ring has the intermediate bottom to the guide vanes of the turbine.
  • this embodiment of the elastic intermediate rings according to the invention also has the advantages of an intermediate base.
  • an intermediate disk is arranged between the disks carrying the blades and is connected to the disks by elastic intermediate rings.
  • the positive connection takes place by means of a double cone or a cylinder seat with a cone or a double cylinder seat.
  • This solution according to the invention is an advantage over conventional constructions where axial end faces abut one another and thus only the simple amount of prestress comes into effect, since under the effect of the increased frictional forces a considerable reduction in the necessary prestress and thus the size of the tensioning bolts is achieved, as a result of which the clamping bolts become more elastic and can absorb the axial thermal expansion more easily.
  • the solution according to the invention is much cheaper to manufacture than a Hirth toothing.
  • FIG. 1 shows the central connection of two adjacent disks with an elastic intermediate piece
  • FIGS. 2 to 5 different possible elastic connections
  • FIG. 6 an elastic intermediate ring which is supported by an intermediate disk
  • FIG. 7 a deformed intermediate piece
  • FIG 8 shows the deformation of the intermediate disk due to the deformation of the intermediate ring
  • FIG. 9 shows an overall arrangement of the rotor
  • FIG. 10 shows a clamping bolt with a clamping sleeve
  • FIGS. 11 and 12 show details of the torque transmission in the intermediate ring.
  • This elastic intermediate piece can form the mating surface for an intermediate guide vane 9 Fig. 1, wherein cooling air channels 40 pass through in the known manner under the blade feet and feed this intermediate floor.
  • the clamping bolts 6 are preferably located radially further inwards, but can also be arranged radially outside the elastic intermediate piece.
  • the double-cone connection 5 of the two elastic rings 13 and 14 belonging to the disks 1 and 2 does not necessarily have to be arranged in the middle between the two disks 1 and 2, it can also be located directly at the fastening point of a disk or it can even have a separate intermediate ring two double cone attachment points can be arranged on each layer.
  • the elastic, annular intermediate pieces 13 and 14 of the rotor not only have to absorb the relative expansion of the disks, but are also subject to the centrifugal forces of the rotating rotor. As a result, they get an elongation in their middle part between the disks which is generally higher than that of the disks, since the radial expansion of a ring at the same speed is much higher than that of a disc. This means that the elastic intermediate ring bends outwards in the middle and is only held at the fastening points on the disks.
  • an intermediate disk 20 is switched on.
  • this washer 20 is connected to the adjacent washers 10 and 11 with two double-cone connections.
  • the profile and the temperature profile of the intermediate plate 20 should preferably be selected so that the extension of the intermediate plate 20 lies in the middle between the extensions of the adjacent plates 10 and 11 (half relative extension).
  • This intermediate disk 20 is also advantageously suitable for receiving an annular groove 12 provided with a tripping edge in which the guide vane 9, which lies between the two rotor blades belonging to the disks 10 and 11, runs and at which the gap flow is throttled.
  • This tripping edge 12 should be welded with hard metal and this can conveniently be done on a closed ring.
  • the intermediate disk 20 must be made thin in the axial direction at the point of connection with the elastic intermediate ring or the intermediate ring pieces 21 and 22, or it must extend as a thin disk sufficiently radially outside and inside so that it shaped deformation of the elastic intermediate piece, see FIG. 7, does not provide a high resistance and does not oppose high turning moments of this deformation. This deformation is indicated in Fig. 8.
  • the intermediate disk 20 can have a corresponding thickening 15 for absorbing the centrifugal forces.
  • FIG. 9. 23 forms the left stub shaft with the transverse bearing 24 and with the disk of the compensating piston, on which the elastic intermediate ring 25 is forged in one piece. This is in connection with the corresponding conical connection 23 with the first disk 34. This carries blades with a fir tree foot and in the known manner running under these feet through the cooling channel 40, which is supplied from the cooling air feed 31.
  • the first disk 34 is connected to the second disk 37 via elastic intermediate pieces 35 and 36, the double cone connection 33 according to the invention being provided in the middle.
  • the platform created in this way serves as a sealing surface for the intermediate floor 39 of the corresponding guide vanes 38, which is only indicated.
  • connection for an intermediate base 39 of the guide vane 38 is therefore established between the disks 34 and 37.
  • the washer 30 is provided with a double cone connection 33, the washer 30 producing a surface for a corresponding tripping edge.
  • the elastic intermediate rings 26, 27 are fastened to the left and right-hand disks 37 and 32, respectively.
  • Two double-cone connections 33 on the intermediate disk 30 are necessary. Since the cooling air has to be passed from the disk 37 to the disk 32, corresponding bores 28 must be provided in the intermediate disk 30.
  • the disk 32 is, for example, the last disk of the rotor, a double-cone connection 33 connects to it again, followed by the elastic intermediate ring 41 to the right bearing stub 42, in which a transverse bearing 43 and the coupling seat 29 are arranged again.
  • the entire rotor is held together in the axial direction by several offset clamping bolts 6, which are clamped together by nuts 7.
  • the clamping bolts 6 are fastened in the bores of the disks by corresponding clamping sleeves 44 Fig. 10, which have an axial movement allow the clamping bolt 6, but achieve a fastening in the radial direction, namely to absorb the centrifugal forces on the one hand and on the other hand to ensure the effect of the clamping bolts in the bending stress by corresponding radial displacement during the deflection of the rotor.
  • only axial frictional forces which are low compared to the bolt preload should act on the clamping sleeves 44. This is achieved by a corresponding elasticity of the clamping sleeve according to FIG. 10.
  • the pretensioning by the clamping bolts can namely be lower by the amount caused by the frictional forces R in the cone seat without the cone seats gaping.
  • the rotor bolts 6 must be long enough that they can absorb the thermal expansion of the disks 34, 37, 32 which become hot without exceeding the yield strength, the hot disks coming to about 500-600 ° C., while the cooled parts of the rotor to 200 C. remain, and the clamping bolts assume an average temperature.
  • the preload must be maintained taking this heating of the bolts into account.
  • radial bolts 45 Corresponding arrangements are indicated in Fig. 12.
  • the radial bolts can be purely cylindrical, light or strongly conical and are drilled or rubbed into the prestressed seat, whereby the two elastic intermediate pieces 46, 47, which are indicated with the respective disks, are connected in a torque-proof manner.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP80890125A 1979-10-25 1980-10-24 Rotor pour turbomachine thermique Withdrawn EP0028217A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AT6935/79 1979-10-25
AT693579A AT378575B (de) 1979-10-25 1979-10-25 Rotor fuer eine thermische turbomaschine

Publications (1)

Publication Number Publication Date
EP0028217A1 true EP0028217A1 (fr) 1981-05-06

Family

ID=3591183

Family Applications (1)

Application Number Title Priority Date Filing Date
EP80890125A Withdrawn EP0028217A1 (fr) 1979-10-25 1980-10-24 Rotor pour turbomachine thermique

Country Status (2)

Country Link
EP (1) EP0028217A1 (fr)
AT (1) AT378575B (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1998019081A1 (fr) * 1996-10-30 1998-05-07 Siemens Aktiengesellschaft Arbre de transmission et transmission pour vitesses de rotation elevees
EP0893576A2 (fr) * 1997-07-03 1999-01-27 Asea Brown Boveri AG Connexion d' éléments rotatifs
EP0936350A3 (fr) * 1998-02-17 2000-12-13 Mitsubishi Heavy Industries, Ltd. Turbine à gaz refroidie par de la vapeur
EP1378629A1 (fr) * 2002-07-01 2004-01-07 ALSTOM (Switzerland) Ltd Rotor de moteur thermique rotatif, ainsi que procédé de fabrication d'un tel rotor
JP2010265896A (ja) * 2009-05-15 2010-11-25 General Electric Co <Ge> 回転部品用の継手
WO2012037347A1 (fr) * 2010-09-15 2012-03-22 Wilson Solarpower Corporation Procédé et appareil pour accoupler des rotors de turbine
FR3025559A1 (fr) * 2014-09-08 2016-03-11 Snecma Ensemble d’elements pour une turbomachine
DE102020004151A1 (de) 2020-07-09 2022-01-13 MTU Aero Engines AG Turbomaschinen-Rotor
DE102021126427A1 (de) 2021-10-12 2023-04-13 MTU Aero Engines AG Rotoranordnung für eine Gasturbine mit an Rotorsegmenten ausgebildeten, geneigten axialen Kontaktflächen, Gasturbine und Fluggasturbine
CN117722235A (zh) * 2024-02-18 2024-03-19 中国航发四川燃气涡轮研究院 双辐板涡轮盘

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE352282C (de) * 1919-04-20 1922-04-24 Rudolf Wagner Dr Turbinenlaeufer, insbesondere fuer schnellaufende leichte Dampf- oder Gasturbinen
CH226091A (de) * 1937-07-07 1943-03-15 Es Erteke Talalmanykifejleszto Läufer mit Scheiben, insbesondere für Gas- und Dampfturbinen und umlaufende Verdichter.
CH257836A (de) * 1947-08-07 1948-10-31 Sulzer Ag Läufer für Kreiselmaschinen, insbesondere für Gasturbinen.
CH324825A (de) * 1952-11-18 1957-10-15 Svenska Turbinfab Ab Rotor von Axialströmungsmaschinen für kompressibles Fluidum
GB836920A (en) * 1957-05-15 1960-06-09 Napier & Son Ltd Rotors for multi-stage axial flow compressors or turbines
CH367353A (de) * 1957-11-13 1963-02-15 Gen Electric Axialströmungsmaschine
GB1148339A (en) * 1966-10-20 1969-04-10 Rolls Royce Compressors or turbines for gas turbine engines
DE1953710A1 (de) * 1968-10-28 1970-04-30 Elin Union Ag Erosionsschutz fuer die Beschaufelung von Gasturbinen,insbesondere Abgasturbinen
US3868197A (en) * 1973-10-26 1975-02-25 Westinghouse Electric Corp Spacer rings for a gas turbine rotor

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE352282C (de) * 1919-04-20 1922-04-24 Rudolf Wagner Dr Turbinenlaeufer, insbesondere fuer schnellaufende leichte Dampf- oder Gasturbinen
CH226091A (de) * 1937-07-07 1943-03-15 Es Erteke Talalmanykifejleszto Läufer mit Scheiben, insbesondere für Gas- und Dampfturbinen und umlaufende Verdichter.
CH257836A (de) * 1947-08-07 1948-10-31 Sulzer Ag Läufer für Kreiselmaschinen, insbesondere für Gasturbinen.
CH324825A (de) * 1952-11-18 1957-10-15 Svenska Turbinfab Ab Rotor von Axialströmungsmaschinen für kompressibles Fluidum
GB836920A (en) * 1957-05-15 1960-06-09 Napier & Son Ltd Rotors for multi-stage axial flow compressors or turbines
CH367353A (de) * 1957-11-13 1963-02-15 Gen Electric Axialströmungsmaschine
GB1148339A (en) * 1966-10-20 1969-04-10 Rolls Royce Compressors or turbines for gas turbine engines
DE1953710A1 (de) * 1968-10-28 1970-04-30 Elin Union Ag Erosionsschutz fuer die Beschaufelung von Gasturbinen,insbesondere Abgasturbinen
AT290926B (de) * 1968-10-28 1971-06-25 Elin Union Ag Erosionsschutz für die Beschaufelung von Gasturbinen, insbesondere Abgasturbinen
US3868197A (en) * 1973-10-26 1975-02-25 Westinghouse Electric Corp Spacer rings for a gas turbine rotor

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1998019081A1 (fr) * 1996-10-30 1998-05-07 Siemens Aktiengesellschaft Arbre de transmission et transmission pour vitesses de rotation elevees
EP0893576A2 (fr) * 1997-07-03 1999-01-27 Asea Brown Boveri AG Connexion d' éléments rotatifs
EP0893576A3 (fr) * 1997-07-03 1999-12-08 Asea Brown Boveri AG Connexion d' éléments rotatifs
US6126357A (en) * 1997-07-03 2000-10-03 Asea Brown Boveri Ag Friction- and form-grip connection of rotating components
US6276863B1 (en) 1997-07-03 2001-08-21 Asea Brown Boveri Ag Friction- and form-grip connection of rotating components
EP0936350A3 (fr) * 1998-02-17 2000-12-13 Mitsubishi Heavy Industries, Ltd. Turbine à gaz refroidie par de la vapeur
US6224327B1 (en) 1998-02-17 2001-05-01 Mitsubishi Heavy Idustries, Ltd. Steam-cooling type gas turbine
EP1378629A1 (fr) * 2002-07-01 2004-01-07 ALSTOM (Switzerland) Ltd Rotor de moteur thermique rotatif, ainsi que procédé de fabrication d'un tel rotor
JP2010265896A (ja) * 2009-05-15 2010-11-25 General Electric Co <Ge> 回転部品用の継手
WO2012037347A1 (fr) * 2010-09-15 2012-03-22 Wilson Solarpower Corporation Procédé et appareil pour accoupler des rotors de turbine
FR3025559A1 (fr) * 2014-09-08 2016-03-11 Snecma Ensemble d’elements pour une turbomachine
DE102020004151A1 (de) 2020-07-09 2022-01-13 MTU Aero Engines AG Turbomaschinen-Rotor
DE102021126427A1 (de) 2021-10-12 2023-04-13 MTU Aero Engines AG Rotoranordnung für eine Gasturbine mit an Rotorsegmenten ausgebildeten, geneigten axialen Kontaktflächen, Gasturbine und Fluggasturbine
US11795822B2 (en) 2021-10-12 2023-10-24 MTU Aero Engines AG Rotor arrangement for a gas turbine with inclined axial contact surfaces formed on rotor segments, gas turbine and aircraft gas turbine
CN117722235A (zh) * 2024-02-18 2024-03-19 中国航发四川燃气涡轮研究院 双辐板涡轮盘
CN117722235B (zh) * 2024-02-18 2024-05-17 中国航发四川燃气涡轮研究院 双辐板涡轮盘

Also Published As

Publication number Publication date
AT378575B (de) 1985-08-26
ATA693579A (de) 1985-01-15

Similar Documents

Publication Publication Date Title
DE69226208T2 (de) Kombiniertes Schraubenscherungs- und Hitzeschildelement für Zusammensetzungsschraube einer Turbine
DE3219615C2 (de) Gasturbinenstrahltriebwerk mit gegenläufigen Laufschaufelgittern
DE69403027T2 (de) Rotierender Turbinenrahmen
DE69629332T2 (de) Gasturbinenrotor mit Trägerringen
DE3510230C2 (de) Brennkammer für ein Gasturbinentriebwerk
DE3724210A1 (de) Dichtungsanordnung
EP1780376A1 (fr) Turbine à vapeur
DE69818406T2 (de) Dichtungsstruktur zwischen gasturbinenscheiben
DE3008889C2 (de) Beschaufelter Rotor für ein Gasturbinentriebwerk
EP0028217A1 (fr) Rotor pour turbomachine thermique
EP2173972B1 (fr) Rotor pour turbomachine à flux axial
DE102005033362A1 (de) Axialdampfturbinenanordnung
WO2008043663A1 (fr) Rotor pour une turbomachine
DE950100C (de) Zusammengesetzter Trommellaeufer fuer Kreiselmaschinen, insbesondere fuer Gasturbinen mit axialer Durchstroemrichtung
DE3406071A1 (de) Einrichtung zur kuehlung der rotoren von dampfturbinen
WO2001016467A1 (fr) Turbine et procede pour evacuer du fluide de fuite
DE102005033364A1 (de) Axialdampfturbinenanordnung
EP2284426B1 (fr) Turbomachine
DE68912606T2 (de) Struktur einer hochtemperaturgasturbine.
DE69018088T2 (de) Dichten von lufterwärmern durch deformierung von sektorplatten.
DE60024921T2 (de) Axialdichtungssystem für einen dampfgekühlten Gasturbinenrotor
DE972310C (de) Aus Scheiben und Ringen zusammengesetzter Turbinenlaeufer
DE854604C (de) Laufrad fuer axialdurchstroemte Kreiselradmaschinen, insbesondere Gasturbinen
EP2352909B1 (fr) Support d&#39;aubes directrices
CH350836A (de) Verfahren zur Kühlung eines Gasturbinenrotors

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Designated state(s): CH DE FR GB SE

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

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 19820412

RIN1 Information on inventor provided before grant (corrected)

Inventor name: JERICHA, HERBERT, PROF.DR.DIPL.ING.