EP0761929A1 - Rotor für thermische Turbomaschinen - Google Patents

Rotor für thermische Turbomaschinen Download PDF

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Publication number
EP0761929A1
EP0761929A1 EP96810502A EP96810502A EP0761929A1 EP 0761929 A1 EP0761929 A1 EP 0761929A1 EP 96810502 A EP96810502 A EP 96810502A EP 96810502 A EP96810502 A EP 96810502A EP 0761929 A1 EP0761929 A1 EP 0761929A1
Authority
EP
European Patent Office
Prior art keywords
rotor
tubes
compressor
turbine
overlap
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Withdrawn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
EP96810502A
Other languages
German (de)
English (en)
French (fr)
Inventor
Claudio Pollini
Cornelis Striezenou
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0761929A1 publication Critical patent/EP0761929A1/de
Withdrawn legal-status Critical Current

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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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means

Definitions

  • the invention relates to a hollow hollow rotor for thermal turbomachinery.
  • rotors for steam and gas turbines, for compressors and for turbogenerators from individual rotating bodies with cavities.
  • rotors which are constructed from disc-shaped or hollow-cylindrical forgings, the individual disks or drums (hollow cylinders) preferably having a constant thickness in the central part of the rotor.
  • the disks or drums are connected to one another by means of low-volume weld seams.
  • the invention tries to avoid this disadvantage. It is based on the task of designing a rotor of a turbomachine in such a way that it reaches its operating state within a very short time and that it can be easily thermally regulated, i.e. can be heated or cooled with relatively little effort depending on requirements.
  • a further cylindrical cavity extending around the central axis of the rotor and extending from the downstream end of the rotor to the upstream last cavity is provided in that at least two tubes with different diameters and lengths, which at least partially overlap to a certain length, are placed in the cylindrical cavity, the tubes each at at least one fixed point are firmly anchored, the fixed points of the pipes are located at axially different locations and the pipes are provided with several holes distributed over the length, the holes of the different pipes overlapping at least partially.
  • the rotor can be optionally heated or cooled under different operating conditions, it reacts very quickly and the rotor cooling air can continue to be used in the machine, for example for cooling the turbine blade roots.
  • the rotor and, on the other hand, the tubes are made of different materials with the greatest possible difference in the coefficients of thermal expansion. Then the regulation can be carried out particularly well.
  • the holes are arranged distributed over the circumference of the tubes and the holes of the tube, which is smaller in circumference, are provided with grooves on the outside diameter. This means that no exact adjustment of the pipes is necessary when installing them in the rotor.
  • the diameter d H1 of the cylindrical cavity in the region between the first and the last cavity is larger than the outside diameter d 2a of the largest tube in the circumference, with a means for sealing the central part from the turbine part, for example a specially designed centering piece is arranged, which is only effective as a seal in the warm operating state. This ensures the flow of air in addition to the advantages mentioned above.
  • the rotor 1 shows a longitudinal section of a rotor 1 according to the invention of a single-shaft gas turbine with axial flow.
  • the rotor 1 consists of a compressor part 2, a middle part 3 and a turbine part 4. It is made up of individual rotating body-shaped disks by means of a low-volume weld seam according to DE 26 33 829 C2. These delimit several, in this exemplary embodiment eight, rotationally symmetrical cavities 5a to 5h in the interior of the rotor 1, the cavities 5a and 5b being in the turbine part 4, the cavity 5c in the middle part 3 and the cavities 5d to 5h in the compressor part 2.
  • the cylindrical cavity 7, which extends over the entire length of the rotor axis 6, has a larger diameter d H1 than in the area between the first and last cavities 5a, 5h, i.e. in the area between the first compressor disk and the second, here last turbine disk Range from the last turbine disc to the downstream end of rotor 1 (d H2 ).
  • Two tubes 8, 9 with different diameters and different lengths are arranged in the cylindrical cavity 7.
  • the shorter tube 8 with a length l 1 and an inner diameter d 1i is fixed at the compressor end of the cavity 7 on the compressor part 2 of the rotor 1, while the longer tube 9 with a length l 2 and an outer diameter d 2a at the other end of the cavity 7, that is to say fixed on the exhaust-side end of the turbine 4.
  • FIG. 2 shows the exhaust-side end of the rotor 1 in area A of FIG. 1.
  • the tube 9 is screwed on with the aid of a screw Flange 10 firmly connected to the rotor 1 by screws 11.
  • a screw Flange 10 firmly connected to the rotor 1 by screws 11.
  • this area there is only one tube, namely tube 9; inside the rotor 1.
  • the situation is different in area B (FIG. 3).
  • area B In this area (transition from the middle part 3 to the turbine part 4) the two pipes 8 and 9 overlap.
  • On the outer pipe 8 there is also a means 12 for sealing the middle part 3 from the turbine part 4; which is only effective in the warm operating state for the purpose of sealing.
  • the means 12 is a centering piece which is screwed together with the rotor 1 by means of screws 12. The centering piece also serves as a regulating piece by allowing air to pass through unhindered in the cold state and sealing the middle part 3 and the turbine part 4 from one another in the warm state.
  • the tubes 8, 9 have openings 13 distributed over the circumference, the openings 13 being in the cold state in the region B at different locations along the axial length, while in the warm state they overlap exactly and thus form a continuous opening 13.
  • Fig. 4 shows the two tubes 8, 9 each in the middle of the cavities 5c to 5g, that is in the area C.
  • the bores 13 in the tubes 8, 9 are made so that they lie exactly one above the other when the system is cold and so on form a continuous opening 13. In the warm state, however, the openings 13 are offset from one another.
  • the area D is shown in FIG. 5. This is the transition from the compressor part 2 to the middle part 3. In this area there are no bores 13 in the pipes 8, 9.
  • Another centering piece 14 was pushed over the pipes 8, 9, which is firmly connected to the compressor part 2 by means of screws 11. The centering piece 14 serves as a support for the tubes 8, 9.
  • FIG. 6 shows the area E, that is to say the area; in which the tube 8 with the larger diameter is attached to the compressor part 2.
  • the tube 8 is screwed to a stop with a flange 10 and fastened to the compressor rotor 2 with screws 11.
  • the fixing of the tubes (8, 9) can of course also be done in other ways in other embodiments, z. B. by welding, shrinking or clamping.
  • the thermal regulation works as follows:
  • the rotor 1 is now heated uniformly and expands, as are the tubes 8, 9 that act as regulating rods. Since the thermal expansion coefficients of the rotor 1 and the regulating rods 8, 9 should have a great difference for effective regulation, the material for the rotor 1 weldable steel and selected for tubes 8, 9 aluminum or plastic.
  • the air 15 is only conducted into the turbine part 4, so that it only has to cool the turbine region.
  • This regulation takes place thermally, because due to the thermal expansion of the two pipes 8, 9, which acts in the opposite direction due to the respective fixing at different points, the openings 13 in the two pipes 8, 9 in regions C and E are now offset from one another are, while in area B the openings 13 are one above the other, so that the air 15 easily passes through this through opening into the turbine part 4 (see FIG. 3, lower part).
  • the tubes 8, 9 do not have to be at an angle to one another, since the tubes are provided with grooves in the through holes.
  • heat-resistant seals which also serve to stabilize the tubes 8, 9, are arranged at various points not shown in the figures.
  • the invention has a number of advantages.
  • a simple thermal regulation of the rotor takes place, the cooling air in the turbine being used further, the air flowing through and the rotor reacting well.
  • Fig. 7 shows a further embodiment, the upper part of the drawing again showing the cold state of the rotor and the lower part of the warm state. It differs from the first exemplary embodiment only in that the outer tube 8 has only one opening 13 in the turbine part 4 and in the compressor part 2 and the inner tube 9 has only one opening 13 in the turbine part 4, only the opening 13 in the compressor part when cold 2 is permeable to the air 15, which then flows through the cavities 5 into the middle part 3 and then into the turbine part 4 and finally to the turbine blades (not shown).
  • the opening 13 in the compressor part 2 is closed by the thermal expansion that has taken place, while the openings 13 in the turbine part 4 overlap and thus form a passage for the cooling air.
  • the shut-off member 12 attached to the tube 8 prevents air flow in the warm state into the middle or compressor part (2, 3).
  • the embodiment variant shown in FIG. 8 has the disadvantage that the air in the middle part 3 and in the compressor part 2 of the rotor 1 is no longer passed on will (except in the 5h range). This is true can be removed from the rotor 1, for example through additional openings in the central part 3 and in the compressor part 2, but this leads to high losses.
  • turbomachinery for example steam turbines and turbochargers.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP96810502A 1995-08-25 1996-07-26 Rotor für thermische Turbomaschinen Withdrawn EP0761929A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19531290A DE19531290A1 (de) 1995-08-25 1995-08-25 Rotor für thermische Turbomaschinen
DE19531290 1995-08-25

Publications (1)

Publication Number Publication Date
EP0761929A1 true EP0761929A1 (de) 1997-03-12

Family

ID=7770364

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810502A Withdrawn EP0761929A1 (de) 1995-08-25 1996-07-26 Rotor für thermische Turbomaschinen

Country Status (5)

Country Link
US (1) US5639209A (ja)
EP (1) EP0761929A1 (ja)
JP (1) JPH09105306A (ja)
CN (1) CN1148134A (ja)
DE (1) DE19531290A1 (ja)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1013879A1 (de) 1998-12-24 2000-06-28 Asea Brown Boveri AG Flüssigkeitsgekühlte Turbomaschinenwelle
US6162018A (en) * 1997-12-27 2000-12-19 Asea Brown Boveri Ag Rotor for thermal turbomachines
US7267525B2 (en) 2003-11-28 2007-09-11 Alstomtechnology Ltd. Rotor for a steam turbine
CN102189349A (zh) * 2010-02-12 2011-09-21 通用电气公司 水平焊接方法及其接头结构

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
PT991850E (pt) 1997-06-27 2002-07-31 Siemens Ag Eixo de uma turbina a vapor com refrigeracao interna bem como um processo para a refrigeracao de um eixo de turbina
GB9716494D0 (en) 1997-08-05 1997-10-08 Gozdawa Richard J Compressions
US6324831B1 (en) * 2000-01-25 2001-12-04 Hamilton Sundstrand Corporation Monorotor for a gas turbine engine
US7473475B1 (en) 2005-05-13 2009-01-06 Florida Turbine Technologies, Inc. Blind weld configuration for a rotor disc assembly
EP1970533A1 (de) * 2007-03-12 2008-09-17 Siemens Aktiengesellschaft Turbine mit mindestens einem Rotor bestehend aus Rotorscheiben und einen Zuganker
US8944761B2 (en) * 2011-01-21 2015-02-03 General Electric Company Welded rotor, a steam turbine having a welded rotor and a method for producing a welded rotor
US20170350597A1 (en) * 2016-06-07 2017-12-07 General Electric Company Heat transfer device, turbomachine casing and related storage medium
US20210067023A1 (en) * 2019-08-30 2021-03-04 Apple Inc. Haptic actuator including shaft coupled field member and related methods

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2837893A (en) * 1952-12-12 1958-06-10 Phillips Petroleum Co Automatic primary and secondary air flow regulation for gas turbine combustion chamber
US3031132A (en) * 1956-12-19 1962-04-24 Rolls Royce Gas-turbine engine with air tapping means
US3814313A (en) * 1968-10-28 1974-06-04 Gen Motors Corp Turbine cooling control valve
EP0266235A1 (fr) * 1986-10-01 1988-05-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbomachine munie d'un dispositif de commande automatique des débits de ventilation de turbine
EP0318026A1 (en) * 1987-11-25 1989-05-31 Hitachi, Ltd. Warming structure of gas turbine rotor
EP0468782A2 (en) * 1990-07-27 1992-01-29 General Electric Company Gas turbine rotor and operation thereof

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10538C (de) * W. GÜLZOW in Hamburg Uhrenaufzug für Remontoir- und Schlüsseluhren zur Verhütung des Federabdrehens
DE953566C (de) * 1954-04-26 1956-12-06 Napier & Son Ltd Brennkraftturbine mit Einrichtung zum Ausgleich des Axialschubes
CH594471A5 (ja) * 1976-07-02 1978-01-13 Bbc Brown Boveri & Cie
DE3606597C1 (de) * 1986-02-28 1987-02-19 Mtu Muenchen Gmbh Schaufel- und Dichtspaltoptimierungseinrichtung fuer Verdichter von Gasturbinentriebwerken
US5020932A (en) * 1988-12-06 1991-06-04 Allied-Signal Inc. High temperature ceramic/metal joint structure
US5271711A (en) * 1992-05-11 1993-12-21 General Electric Company Compressor bore cooling manifold

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2837893A (en) * 1952-12-12 1958-06-10 Phillips Petroleum Co Automatic primary and secondary air flow regulation for gas turbine combustion chamber
US3031132A (en) * 1956-12-19 1962-04-24 Rolls Royce Gas-turbine engine with air tapping means
US3814313A (en) * 1968-10-28 1974-06-04 Gen Motors Corp Turbine cooling control valve
EP0266235A1 (fr) * 1986-10-01 1988-05-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbomachine munie d'un dispositif de commande automatique des débits de ventilation de turbine
EP0318026A1 (en) * 1987-11-25 1989-05-31 Hitachi, Ltd. Warming structure of gas turbine rotor
EP0468782A2 (en) * 1990-07-27 1992-01-29 General Electric Company Gas turbine rotor and operation thereof

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6162018A (en) * 1997-12-27 2000-12-19 Asea Brown Boveri Ag Rotor for thermal turbomachines
DE19757945B4 (de) * 1997-12-27 2006-11-30 Alstom Rotor für thermische Turbomaschine
EP1013879A1 (de) 1998-12-24 2000-06-28 Asea Brown Boveri AG Flüssigkeitsgekühlte Turbomaschinenwelle
US7267525B2 (en) 2003-11-28 2007-09-11 Alstomtechnology Ltd. Rotor for a steam turbine
CN102189349A (zh) * 2010-02-12 2011-09-21 通用电气公司 水平焊接方法及其接头结构

Also Published As

Publication number Publication date
US5639209A (en) 1997-06-17
CN1148134A (zh) 1997-04-23
DE19531290A1 (de) 1997-02-27
JPH09105306A (ja) 1997-04-22

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