EP0636764B1 - Turbine à gaz avec refroidissement du rotor - Google Patents

Turbine à gaz avec refroidissement du rotor Download PDF

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Publication number
EP0636764B1
EP0636764B1 EP94108585A EP94108585A EP0636764B1 EP 0636764 B1 EP0636764 B1 EP 0636764B1 EP 94108585 A EP94108585 A EP 94108585A EP 94108585 A EP94108585 A EP 94108585A EP 0636764 B1 EP0636764 B1 EP 0636764B1
Authority
EP
European Patent Office
Prior art keywords
rotor
gas turbine
cooling air
turbine according
connecting openings
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
Application number
EP94108585A
Other languages
German (de)
English (en)
Other versions
EP0636764A1 (fr
Inventor
Eduard Primoschitz
Pavel Dr. Rihak
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 AG Germany
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 EP0636764A1 publication Critical patent/EP0636764A1/fr
Application granted granted Critical
Publication of EP0636764B1 publication Critical patent/EP0636764B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum 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
    • F01D5/02—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
    • F01D5/063—Welded rotors
    • 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
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Definitions

  • the essence of the invention is therefore that there are axial channels in the rotor periphery between the rotor surface and platforms formed by the rotor blades or heat exchanger segment plates, that one or more of the cavities are connected to the axial channels in the rotor periphery via the connection openings and that the at least one cavity between the rotor disks continuously tapers at least beyond a certain radial distance from the rotor axis towards the connection openings.
  • cooling air can be taken from the central part of the compressor, where it is still at a lower pressure and a lower temperature than at the compressor outlet.
  • the resulting low-pressure cooling is more effective and also manages with a lower cooling air flow. The losses are also lower and the efficiency is thereby improved.
  • the gas turbine shown in FIG. 1 has a compressor 1, a turbine 2, an exhaust gas housing 3 and an exhaust gas diffuser 4. 5 the combustion chamber and 6 the rotor.
  • the rotor 6 is welded together from a plurality of disks in its axial direction, with cavities remaining between the individual disks.
  • two disks are shown and designated 7 and 8 respectively.
  • the structure of the cavities between the rotor disks can be seen in the enlarged detail in FIG. 2. That one
  • the cavity shown between the rotor disks 7 and 8 is designated 9. It is narrow in its central area around the rotor axis 10 and widens outwards into a kind of annular chamber 11.
  • the rotor 6 is provided along its axis 10 with a central channel 20 extending from the end face 19 of its downstream end. Through the central channel 20, the cavities 9 and the connection openings 18, the axial channel 17 in the rotor periphery is fed with cooling air.
  • the cooling air is branched off in the central part of the compressor from the process air which has already been partially compressed there and is conducted via a line 21 to the end face 19 of the rotor end located downstream.
  • the line 21 passes through hollow ribs 22 between the outer ring 23 and the inner ring 24 of the exhaust gas diffuser or housing 3, 4.
  • the connecting openings 18 start in the cavities 9 on the very outside, ie where they have their greatest diameter or radial distance R1.
  • the annular chambers 11 of the hollow spaces 9 taper beyond the radius R2 each also continuously. This ensures that dirt carried in the cooling air cannot collect in the cavities 9 but is thrown out through the connecting openings 18. In addition to thermal insulation effects due to deposited dirt, this also prevents the imbalance of the rotor caused by dirt accumulation.
  • the weld seam 12 is arranged somewhat offset axially with respect to the connection openings 18. Its root 25 therefore comes to lie at a radial distance R3 from the rotor axis 10 which is somewhat smaller than the radial distance R1 from which the connection openings 18 originate.
  • the formation of pockets on both sides of the weld seam 12 on the outer zone of the cavities 9 in order to relieve the weld seam root 25, as was previously the case, is dispensed with for the aforementioned reasons of dirt ejection.

Landscapes

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

Claims (7)

  1. Turbine à gaz stationnaire, à un seul arbre, pour la production de courant avec un rotor à aubes (6) composé de plusieurs disques (7, 8) assemblés par
    soudage, dans laquelle il existe des espaces creux (9) entre les disques (7, 8), dans laquelle un ou plusieurs des espaces creux (9) se trouve en communication avec la périphérie du rotor par des ouvertures de communication (18) et lesdites ouvertures de communication (18) se placent dans ledit au moins un espace creux (9) à un endroit où l'espace creux (9) présente sa plus grande distance radiale (R1) par rapport à l'axe (10) du rotor, caractérisée en ce que des canaux axiaux (17) sont présents dans la périphérie du rotor entre la surface (15) du rotor et des plates-formes (16) formées par les aubes (13) du rotor ou des plaques segmentées d'accumulation de chaleur, en ce qu'un ou plusieurs des espaces creux (9) est en communication avec les canaux axiaux (17) dans la périphérie du rotor par les ouvertures de communication (18) et en ce que ledit au moins un espace creux (9) entre les disques (7, 8) du rotor se rétrécit de façon continue depuis l'axe (10) du rotor vers les ouvertures de communication (18) au moins au-delà d'une certaine distance radiale (R2).
  2. Turbine à gaz suivant la revendication 1, caractérisée en ce qu'il est prévu un canal central (20) d'amenée d'air de refroidissement le long de l'axe (10) du rotor (6).
  3. Turbine à gaz suivant la revendication 2, caractérisée en ce que le canal central (20) d'amenée d'air de refroidissement part de la face frontale (19) située à l'extrémité aval du rotor et en ce que l'air de refroidissement lui est fourni en cet endroit.
  4. Turbine à gaz suivant la revendication 3 et avec un diffuseur des gaz d'échappement (4), qui présente un anneau intérieur (24) recevant l'extrémité aval du rotor, un anneau extérieur (23) ainsi que des nervures creuses (22) reliant l'un à l'autre l'anneau intérieur et l'anneau extérieur, caractérisée en ce que l'air de refroidissement est conduit à l'extrémité aval du rotor dans au moins une conduite d'air de refroidissement (21) à travers au moins une des nervures creuses (22).
  5. Turbine à gaz suivant l'une des revendications 2 à 4, caractérisée en ce que l'air de refroidissement est soutiré dans la partie centrale du compresseur (1).
  6. Turbine à gaz suivant l'une des revendications 1 à 4 et dans laquelle les différents disques (7, 8) du rotor sont soudés l'un à l'autre dans leurs zones de bord au moyen d'un cordon de soudure (12) réalisé en anneau, caractérisée en ce que le cordon de soudure (12) est légèrement décalé en direction axiale par rapport aux ouvertures de communication (18) respectives.
  7. Turbine à gaz suivant les revendications 1 et 6, caractérisée en ce que la distance radiale (R1) à partir de l'axe (10) du rotor, d'où partent les ouvertures de communication (18), est plus grande que la distance radiale (R3) à laquelle est disposée la racine du cordon de soudure (12).
EP94108585A 1993-07-17 1994-06-04 Turbine à gaz avec refroidissement du rotor Expired - Lifetime EP0636764B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4324034A DE4324034A1 (de) 1993-07-17 1993-07-17 Gasturbine mit gekühltem Rotor
DE4324034 1993-07-17

Publications (2)

Publication Number Publication Date
EP0636764A1 EP0636764A1 (fr) 1995-02-01
EP0636764B1 true EP0636764B1 (fr) 1997-03-19

Family

ID=6493082

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94108585A Expired - Lifetime EP0636764B1 (fr) 1993-07-17 1994-06-04 Turbine à gaz avec refroidissement du rotor

Country Status (5)

Country Link
US (1) US5507620A (fr)
EP (1) EP0636764B1 (fr)
JP (1) JP3853383B2 (fr)
DE (2) DE4324034A1 (fr)
RU (1) RU94026895A (fr)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6217280B1 (en) 1995-10-07 2001-04-17 Siemens Westinghouse Power Corporation Turbine inter-disk cavity cooling air compressor
JP2000502775A (ja) * 1996-01-11 2000-03-07 シーメンス アクチエンゲゼルシヤフト 内部冷却形蒸気タービンのタービン軸
DE19613472A1 (de) * 1996-04-04 1997-10-09 Asea Brown Boveri Vorrichtung zur Wärmedämmung
CN1106496C (zh) * 1996-06-21 2003-04-23 西门子公司 涡轮轴及其冷却方法
US5628621A (en) * 1996-07-26 1997-05-13 General Electric Company Reinforced compressor rotor coupling
US5704764A (en) * 1996-10-07 1998-01-06 Westinghouse Electric Corporation Turbine inter-disk cavity cooling air compressor
DE19648185A1 (de) * 1996-11-21 1998-05-28 Asea Brown Boveri Geschweisster Rotor einer Strömungsmaschine
JP4162724B2 (ja) * 1997-06-27 2008-10-08 シーメンス アクチエンゲゼルシヤフト 内部冷却形蒸気タービンのタービン軸並びにタービン軸の冷却方法
DE59710425D1 (de) * 1997-12-24 2003-08-14 Alstom Switzerland Ltd Rotor einer Strömungsmaschine
DE19852604A1 (de) * 1998-11-14 2000-05-18 Abb Research Ltd Rotor für eine Gasturbine
EP1008722B1 (fr) * 1998-12-10 2003-09-10 ALSTOM (Switzerland) Ltd Procédé de fabrication par soudage d'un rotor de turbomachine
EP1705339B1 (fr) * 2005-03-23 2016-11-30 General Electric Technology GmbH Arbre de rotor, particulièrement pour une turbine à gaz
US8277170B2 (en) * 2008-05-16 2012-10-02 General Electric Company Cooling circuit for use in turbine bucket cooling
CH702191A1 (de) * 2009-11-04 2011-05-13 Alstom Technology Ltd Geschweisster Rotor.
US9091172B2 (en) 2010-12-28 2015-07-28 Rolls-Royce Corporation Rotor with cooling passage
US9206693B2 (en) * 2011-02-18 2015-12-08 General Electric Company Apparatus, method, and system for separating particles from a fluid stream
CN104929692A (zh) * 2014-03-19 2015-09-23 阿尔斯通技术有限公司 带有冷却孔入口的转子轴
EP3342979B1 (fr) 2016-12-30 2020-06-17 Ansaldo Energia Switzerland AG Turbine à gaz comportant des disques de rotor refroidis
CN111927561A (zh) * 2020-07-31 2020-11-13 中国航发贵阳发动机设计研究所 一种用于涡轮叶片冷却的旋转增压结构

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GB512301A (en) * 1937-12-27 1939-08-31 Bayerische Motoren Werke Ag An arrangements for cooling solid blades for exhaust gas turbines
GB612097A (en) * 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors
US2868500A (en) * 1949-02-15 1959-01-13 Boulet George Cooling of blades in machines where blading is employed
US2791091A (en) * 1950-05-15 1957-05-07 Gen Motors Corp Power plant cooling and thrust balancing systems
DE943328C (de) * 1951-01-20 1956-05-17 Maschf Augsburg Nuernberg Ag Waermeschutzeinrichtung fuer den staehlernen Laeufer einer Gasturbine mit hohen Treibmitteltemperaturen
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DE2042478C3 (de) * 1970-08-27 1975-08-14 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Gasturbinentriebwerk, vorzugsweise Strahltriebwerk für Flugzeuge, mit Kühlluft- und gegebenenfalls Sperrluftentnahme
US3742706A (en) * 1971-12-20 1973-07-03 Gen Electric Dual flow cooled turbine arrangement for gas turbine engines
CA1034510A (fr) * 1975-10-14 1978-07-11 Westinghouse Canada Limited Appareil refroidisseur pour turbine a gaz a arbre divise
DE2633222A1 (de) * 1976-07-23 1978-01-26 Kraftwerk Union Ag Gasturbinenanlage mit kuehlung der turbinenteile
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Also Published As

Publication number Publication date
US5507620A (en) 1996-04-16
EP0636764A1 (fr) 1995-02-01
JPH0754602A (ja) 1995-02-28
RU94026895A (ru) 1997-04-27
JP3853383B2 (ja) 2006-12-06
DE59402122D1 (de) 1997-04-24
DE4324034A1 (de) 1995-01-19

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