EP0702129A2 - Refroidissement du rotor d'une turbine à gaz axiale - Google Patents

Refroidissement du rotor d'une turbine à gaz axiale Download PDF

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Publication number
EP0702129A2
EP0702129A2 EP95810542A EP95810542A EP0702129A2 EP 0702129 A2 EP0702129 A2 EP 0702129A2 EP 95810542 A EP95810542 A EP 95810542A EP 95810542 A EP95810542 A EP 95810542A EP 0702129 A2 EP0702129 A2 EP 0702129A2
Authority
EP
European Patent Office
Prior art keywords
rotor
turbine
cooling air
compressor
drum
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
EP95810542A
Other languages
German (de)
English (en)
Other versions
EP0702129A3 (fr
EP0702129B1 (fr
Inventor
Robert Marmilic
René Wälchli
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.)
Alstom SA
Original Assignee
ABB Management 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 ABB Management AG filed Critical ABB Management AG
Publication of EP0702129A2 publication Critical patent/EP0702129A2/fr
Publication of EP0702129A3 publication Critical patent/EP0702129A3/fr
Application granted granted Critical
Publication of EP0702129B1 publication Critical patent/EP0702129B1/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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • F05D2240/63—Glands for admission or removal of fluids from shafts

Definitions

  • the invention relates to an axially flow-through gas turbine according to the preamble of claim 1, consisting essentially of a multi-stage turbine which drives a compressor arranged on a common shaft, the shaft part lying between the turbine and the compressor being a drum.
  • Such gas turbines are known.
  • the entire rotor-side cooling air is z. B. removed from the compressor end. The majority of it flows through separate lines and through a swirl grille, which is usually on the same radius as the rotor cooling channels on the front side of the turbine rotor and e.g. is known from GB 2 189 845, in these rotor cooling channels.
  • the smaller proportion of cooling air is used to cool the last compressor disc, the drum and the first turbine disc.
  • the invention tries to avoid all of these disadvantages. It is based on the task of reducing the axial thrust in an axially flow-through gas turbine of the type mentioned at the outset, the effectiveness of the blade and disk cooling to improve and achieve a uniform temperature distribution.
  • this is achieved in an axially flow-through gas turbine according to the preamble of claim 1 in that at least one suction device for the leakage air and part of the cooling air is arranged in the region of the drum labyrinth.
  • the ring channel in the area of the suction device is expanded to a collecting space for the leakage or cooling air, because this ensures better suction.
  • the suction device consists of a line which is connected on one side to the collecting space for the leakage or cooling air and on the other side to the cooling air extraction ring space in the compressor housing.
  • the suction device is advantageously connected to the cooling air devices for the rear turbine stages, because as a result the extracted air is mixed with the cooling air for the rear turbine stages and is therefore usefully used for the process.
  • At least one feed to the ring channel is arranged in the part of the rotor drum on the compressor side for part of the cooling air, which feed has at least one swirl nozzle at its respective end.
  • the hot leakage air can also be mixed with cooling air, so that the air temperature in this area is reduced to the permissible level.
  • the cooling air pressure after the swirl grille is advantageously chosen so that the usual labyrinth seal between the turbine disk and the disk cover can be dispensed with, so that the pressure near the disk is determined by the pressure of the main turbine flow in the gas duct. If the rotor drum labyrinth is damaged, the disc labyrinth is eliminated and the enlarged leakage air is sucked out, which prevents a large increase in pressure on the turbine disc, so that the axial thrust of the rotor changes only slightly. The drum and disc temperatures also remain relatively stable in the case of an increase in the labyrinth clearance.
  • FIG. 1 shows that the turbine 1 through which the axial flow flows essentially consists of the rotor 3 equipped with moving blades 2 and the blade carrier 5 equipped with guide blades 4. In Fig. 1 only the first axially flow stage of the turbine 1 is shown.
  • the blade carrier 5 is suspended in the turbine housing 6.
  • the turbine housing 6 also includes the collecting space 7 for the compressed combustion air.
  • the combustion air passes from the collecting space 7 into the annular combustion chamber 8, which opens into the turbine inlet.
  • the compressed air flows from the diffuser 9 of the compressor 10 into the collecting space 7.
  • the rotor blades of the compressor 10 and the turbine 1 sit on a common shaft 13, the part of which is located between the turbine 1 and the compressor 10 is designed as a drum 14.
  • the drum 14 is surrounded by a drum cover 15 which is connected to the diffuser outer housing 17 via ribs 16.
  • the wheel side space 19 forms the end of an annular channel 20 which runs between the drum 14 and the drum cover 15.
  • a labyrinth seal 21 which seals against the drum cover 15 is arranged in this annular channel 20.
  • a line 22 coming from the compressor end for guiding the turbine rotor cooling air opens into the wheel side space 19.
  • Swirl nozzles 23 are arranged at their end.
  • the swirl nozzle 23 for the main turbine rotor cooling air is preferably arranged on the same radius as the rotor cooling channels 24 or the inlet opening of the rotor cooling channels 24, while one or more further swirl nozzles 23 are arranged at a smaller radial distance from the main turbine axis and for admixing cooling air for the end face 18 of the turbine rotor 3 serve.
  • two suction devices 25 for the leakage air and part of the cooling air are arranged in the region of the drum labyrinth 21.
  • FIG. 2 shows in detail a possible embodiment variant of the suction device 25.
  • the ring channel 20 is expanded to two collecting spaces 26 in the area of the suction devices 25.
  • the two suction devices 25 here are lines which are connected on the one hand to the collecting spaces 26 of the leakage air and on the other hand to the cooling air extraction ring spaces 28 in the compressor housing. Lines 22a lead from the cooling air extraction ring spaces 28 to the cooling system of the rear turbine stages.
  • the arrangement of the collecting spaces 26 in the drum labyrinth 21 is chosen such that the resulting pressure drop between the spaces 26 and 28 and the cross sections of the lines 25 result in the required amounts of suction air.
  • the suction device 25 can also be designed differently.
  • a feed 27 to the ring channel 20 can also be arranged in the compressor-side part of the rotor drum 14 for a small part of the cooling air, which also has at least one swirl nozzle 23 at its end facing the ring channel 20.
  • the swirl nozzles 23 are acceleration grids with a slight curvature of the skeleton line. The admixture of the cooling air into the hot leakage air mass flow leads to the fact that the air temperature in the compressor-side part of the rotor drum 14 is reduced to an admissible level.
  • FIG 3 shows that only one suction device 25 or more than two suction devices 25 for the leakage or cooling air can be arranged.
  • the cooling air required for the rotor cooling is removed at the end of the compressor.
  • the main part of the rotor cooling air flows via the line 22 and via the swirl nozzle 23 into the wheel side space 19.
  • Most of this swirling cooling air flows into the cooling channels 24 of the rotor 3 via the inlet openings located at the same height, while a small proportion between the turbine disk and the disk cover flows into the gas channel of the turbine 1.
  • the cooling air pressure after the swirl grille can now be selected so that the labyrinth seal normally arranged between the turbine disk and the disk cover can be dispensed with.
  • the pressure near the disc is determined by the pressure of the main turbine flow in the gas duct.

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)
EP95810542A 1994-09-19 1995-09-01 Refroidissement du rotor d'une turbine à gaz axiale Expired - Lifetime EP0702129B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4433289A DE4433289A1 (de) 1994-09-19 1994-09-19 Axialdurchströmte Gasturbine
DE4433289 1994-09-19

Publications (3)

Publication Number Publication Date
EP0702129A2 true EP0702129A2 (fr) 1996-03-20
EP0702129A3 EP0702129A3 (fr) 1998-11-11
EP0702129B1 EP0702129B1 (fr) 2002-06-05

Family

ID=6528562

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810542A Expired - Lifetime EP0702129B1 (fr) 1994-09-19 1995-09-01 Refroidissement du rotor d'une turbine à gaz axiale

Country Status (5)

Country Link
US (1) US5575617A (fr)
EP (1) EP0702129B1 (fr)
JP (1) JPH08105330A (fr)
CN (1) CN1056909C (fr)
DE (2) DE4433289A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19632038A1 (de) * 1996-08-08 1998-02-12 Asea Brown Boveri Vorrichtung zur Abscheidung von Staubpartikeln
EP2011963A1 (fr) * 2007-07-04 2009-01-07 ALSTOM Technology Ltd Turbine à gaz à poussée axiale compensée

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5738488A (en) * 1996-11-12 1998-04-14 General Electric Co. Gland for transferring cooling medium to the rotor of a gas turbine
JP3310907B2 (ja) * 1997-06-12 2002-08-05 三菱重工業株式会社 ガスタービンフランジ接合面のシール構造
JP3567065B2 (ja) * 1997-07-31 2004-09-15 株式会社東芝 ガスタービン
US6968696B2 (en) * 2003-09-04 2005-11-29 Siemens Westinghouse Power Corporation Part load blade tip clearance control
US7096673B2 (en) * 2003-10-08 2006-08-29 Siemens Westinghouse Power Corporation Blade tip clearance control
US7743613B2 (en) * 2006-11-10 2010-06-29 General Electric Company Compound turbine cooled engine
US7934901B2 (en) * 2006-12-20 2011-05-03 General Electric Company Air directing assembly and method of assembling the same
US8277170B2 (en) * 2008-05-16 2012-10-02 General Electric Company Cooling circuit for use in turbine bucket cooling
US8192151B2 (en) * 2009-04-29 2012-06-05 General Electric Company Turbine engine having cooling gland
US9540945B2 (en) 2013-03-01 2017-01-10 Siemens Energy, Inc. Active bypass flow control for a seal in a gas turbine engine
EP3006668A1 (fr) * 2014-10-07 2016-04-13 Siemens Aktiengesellschaft Turbine à gaz dotée de deux alimentations en vortex destinées au refroidissement du rotor
JP6554736B2 (ja) * 2015-10-23 2019-08-07 三菱日立パワーシステムズ株式会社 ガスタービンロータ、ガスタービン、及びガスタービン設備
WO2018165455A1 (fr) 2017-03-09 2018-09-13 Johnson Controls Technology Company Systèmes d'étanchéité de palier de dos à dos
US10669893B2 (en) * 2017-05-25 2020-06-02 General Electric Company Air bearing and thermal management nozzle arrangement for interdigitated turbine engine
US10941664B2 (en) * 2019-03-18 2021-03-09 General Electric Company Turbine engine component and method of cooling
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2189845A (en) 1986-04-30 1987-11-04 Gen Electric Gas turbine cooling air transferring apparatus
EP0447886A1 (fr) 1990-03-23 1991-09-25 Asea Brown Boveri Ag Turbine à gaz avec flux axiale

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE585101C (de) * 1930-07-25 1933-09-28 Wilhelm Beyer Dipl Ing Labyrinthdichtung gegen unter UEberdruck stehenden Sattdampf, insbesondere bei Hochdruckdampfanlagen
DE974790C (de) * 1952-11-19 1961-04-27 Kuehnle Ag Mit einem Geblaese zusammenarbeitende Gasturbine
NL105688C (fr) * 1958-10-01
CH443821A (de) * 1966-01-14 1967-09-15 Escher Wyss Ag Vorrichtung zur Abdichtung der Welle einer Turbomaschine für Wärmekraftanlagen, deren gasförmiges Arbeitsmittel in einem Atomkern-Reaktor erhitzt wird
AT290927B (de) * 1968-10-28 1971-06-25 Elin Union Ag Kühlung des Trommelrotors von Gasturbinen
US3602605A (en) * 1969-09-29 1971-08-31 Westinghouse Electric Corp Cooling system for a gas turbine
US3826084A (en) * 1970-04-28 1974-07-30 United Aircraft Corp Turbine coolant flow system
CA939521A (en) * 1970-04-28 1974-01-08 Bruce R. Branstrom Turbine coolant flow system
US4296599A (en) * 1979-03-30 1981-10-27 General Electric Company Turbine cooling air modulation apparatus
JPS5951109A (ja) * 1982-09-17 1984-03-24 Hitachi Ltd 蒸気原動所の復水器真空保持装置
US4574584A (en) * 1983-12-23 1986-03-11 United Technologies Corporation Method of operation for a gas turbine engine
US4645415A (en) * 1983-12-23 1987-02-24 United Technologies Corporation Air cooler for providing buffer air to a bearing compartment
DE3627306A1 (de) * 1986-02-28 1987-09-03 Mtu Muenchen Gmbh Einrichtung zur belueftung von rotorbauteilen fuer verdichter von gasturbinentriebwerken
US4666368A (en) * 1986-05-01 1987-05-19 General Electric Company Swirl nozzle for a cooling system in gas turbine engines
CA1309873C (fr) * 1987-04-01 1992-11-10 Graham P. Butt Methode de refroidissement par connection forcee du conduit de transition d'uneturbine a gaz
FR2690482B1 (fr) * 1992-04-23 1994-06-03 Snecma Circuit de ventilation des disques de compresseurs et de turbines.
DE4225625A1 (de) * 1992-08-03 1994-02-10 Asea Brown Boveri Abgasturbolader

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2189845A (en) 1986-04-30 1987-11-04 Gen Electric Gas turbine cooling air transferring apparatus
EP0447886A1 (fr) 1990-03-23 1991-09-25 Asea Brown Boveri Ag Turbine à gaz avec flux axiale

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19632038A1 (de) * 1996-08-08 1998-02-12 Asea Brown Boveri Vorrichtung zur Abscheidung von Staubpartikeln
US5837019A (en) * 1996-08-08 1998-11-17 Asea Brown Boveri Ag Device for separating dust particles
EP2011963A1 (fr) * 2007-07-04 2009-01-07 ALSTOM Technology Ltd Turbine à gaz à poussée axiale compensée
US8092150B2 (en) 2007-07-04 2012-01-10 Alstom Technology Ltd. Gas turbine with axial thrust balance

Also Published As

Publication number Publication date
CN1056909C (zh) 2000-09-27
EP0702129A3 (fr) 1998-11-11
DE59510224D1 (de) 2002-07-11
DE4433289A1 (de) 1996-03-21
JPH08105330A (ja) 1996-04-23
EP0702129B1 (fr) 2002-06-05
CN1129278A (zh) 1996-08-21
US5575617A (en) 1996-11-19

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