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EP2551453A1 - Dispositif de refroidissement d'un compresseur d'un turbomoteur - Google Patents

Dispositif de refroidissement d'un compresseur d'un turbomoteur Download PDF

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Publication number
EP2551453A1
EP2551453A1 EP11175451A EP11175451A EP2551453A1 EP 2551453 A1 EP2551453 A1 EP 2551453A1 EP 11175451 A EP11175451 A EP 11175451A EP 11175451 A EP11175451 A EP 11175451A EP 2551453 A1 EP2551453 A1 EP 2551453A1
Authority
EP
European Patent Office
Prior art keywords
ring
rotor
compressor
cooling medium
compressor rotor
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Withdrawn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
EP11175451A
Other languages
German (de)
English (en)
Inventor
Christian Dombek
Mauro Corradi
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP11175451A priority Critical patent/EP2551453A1/fr
Priority to DE102012014646A priority patent/DE102012014646A1/de
Priority to US13/556,722 priority patent/US9382802B2/en
Publication of EP2551453A1 publication Critical patent/EP2551453A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • 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

Definitions

  • the present invention relates to the field of turbomachinery. It relates to a compressor rotor according to the preamble of claim 1 and a gas turbine comprising such a rotor and a method for cooling a gas turbine with such a rotor.
  • Fig. 1 shows the basic scheme of a gas turbine, as used for example as a stationary industrial turbine for the production of energy.
  • the gas turbine 10 of Fig. 1 comprises a compressor 12 which sucks and compresses combustion air through an air inlet 11. The compressed air is introduced into a combustion chamber 13 and used there for the combustion of a fuel 14. The resulting hot gases are in a subsequent Relaxed turbine 15 under work and discharged as exhaust 16 to the outside or used in a heat recovery steam generator.
  • the blades required for the compressor 12 and the turbine 15 are usually mounted on a rotor 17 having corresponding rotor disks.
  • compression air temperatures at the compressor end of several 100 ° C arise during the compression of the combustion air. Cooling of the rotor in this area on the one hand reduces the thermal load on the materials used, but on the other hand can also contribute to improving the overall efficiency of the gas turbine.
  • a part of the compressed air can be branched off, in a cooling device 18 (in Fig. 1 dashed) cooled down and then fed to the cooling in the end region of the compressor 12.
  • the cooling air is used here for flushing the cavity 22 between the compressor rotor end and the middle section 19 and as cooling air for the rotor disk 25 'in the region of the compressor rotor end.
  • the aim is to use the cooling air to lower the rotor temperature in this area.
  • the rotor according to the invention which is intended in particular for use in a gas turbine, comprises a rotor, which has at least one groove into which a plurality of rotor blades can be inserted and held on the rotor, and furthermore a device for cooling the rotor in the area of the compressor rotor end.
  • the invention is characterized in that the rotor in the region of the compressor rotor end has a ring which is pushed concentrically and at a distance with formation of a gap over a rotor disk of the rotor and attached to the rotor disk, that the blades in the region of the compressor rotor end in corresponding grooves on Ring are used and held there, that first means for axially flowing through the ring are provided with a cooling medium from Kompressorrotorende forth, and in that second means for deflecting the emerging from the ring cooling medium are provided, such that the cooling medium through the gap between the Ring and the rotor disc enclosed by the ring flows back in the axial direction.
  • the gap between the ring and the rotor disc enclosed by the ring for example, has the shape of an annular gap, which may be interrupted by fastening elements which connect the ring with the rotor disk.
  • An embodiment of the compressor according to the invention is characterized in that the first means comprises a plurality of distributed over the circumference of the ring arranged axial bores through which the cooling medium flows.
  • Another embodiment of the compressor according to the invention is characterized in that the second means comprise an annular deflection region formed in the rotor disk, which communicates with the first means or axial bores and the gap between the ring and the rotor disk, and a reversal of the flow direction of the cooling medium causes.
  • the ring is fastened by a positive connection between the inner circumferential surface of the ring and the outer circumferential surface of the rotor disk on the rotor disk.
  • the positive engagement is in the nature of circumferentially distributed, radially aligned hammerhead connections or fir tree root connections.
  • a further embodiment of the invention is characterized in that the ring with the upstream end face abuts against an annular abutment surface of the rotor disk, and that the ring and the rotor disk are connected to one another in this region.
  • connection between ring and rotor disk can be effected by a positive connection.
  • connection between the ring and the rotor disk by a material bond, in particular by welding, is effected.
  • compressor rotor In addition to the compressor rotor is a gas turbine comprising a compressor, a combustion chamber, a turbine and a rotor subject of the invention, wherein the rotor (34) comprises a compressor rotor (17) according to one of the embodiments described above.
  • An embodiment of the gas turbine according to the invention is characterized in that the ring is arranged in the installed state at the downstream end side next to stationary structural parts, and that the cooling medium for cooling the compressor rotor end is brought over the structural parts.
  • deflecting elements are arranged at the transition between the structural parts and the ring, which impart a twist in the direction of rotation of the compressor to the cooling medium emerging from the structural parts.
  • the deflecting elements may be formed as baffles.
  • the deflection elements are designed as swirl nozzles.
  • At least one seal is arranged between the structural parts and the ring.
  • the seal may be formed as a labyrinth seal or brush seal.
  • such a seal is mounted on a radius which is smaller than the distance from the center of the rotor to the first means for axially flowing through the ring with a cooling medium. This seal prevents a bypass of the cooling medium around the ring.
  • such a seal is mounted on a radius which is greater than the distance from the center of the rotor to the first means for axially flowing through the ring with a cooling medium. This seal prevents backflow of the cooling medium into the main flow of the compressor.
  • the gas turbine comprises a compressor, a combustion chamber and a turbine.
  • the compressor itself has a plurality of blades, which are inserted into corresponding grooves on a compressor rotor and held there.
  • the compressor rotor in the region of the compressor rotor end has a ring which is pushed concentrically and with the formation of a gap over a rotor disk of the compressor rotor and attached to the rotor disk, wherein the rotor blades are inserted into corresponding grooves on the ring in the region of the compressor rotor end and held there ,
  • first means are provided for axially flowing through the ring with a cooling medium from the Kompressorotorende forth and second means for deflecting the emerging from the ring cooling medium is provided.
  • the method is characterized in that a cooling medium from the compressor end is passed through the first means of the ring, the cooling medium is subsequently deflected by second means, and the cooling medium is finally returned through the gap between the ring and the ring surrounded by the rotor disc in the axial direction ,
  • cooling medium is subjected to a twist before it is introduced into the first means of the ring.
  • the compressor rotor described by way of example of a gas turbine having a compressor, a combustor, and a turbine may be used for gas turbines with sequential combustion, ie, gas turbines containing one or more compressors, a first combustor, a high pressure turbine, a second combustor (sequential combustor ) and a low pressure turbine.
  • gas turbines with sequential combustion ie, gas turbines containing one or more compressors, a first combustor, a high pressure turbine, a second combustor (sequential combustor ) and a low pressure turbine.
  • gas turbine with sequential combustion and the rotor according to the invention and a method for cooling a compressor rotor for a gas turbine with sequential combustion included in the invention.
  • a cooling circuit is produced below the high-pressure compressor or compressor rotor end with the aid of a separate ring.
  • the ring 26 is pushed onto the rotor disk 25 during manufacture.
  • the connection between ring 26 and rotor disk 25 can be made in different ways.
  • a positive fit 30 between the opposite lateral surfaces of the ring 26 and the rotor disk 25 are used, which in particular has the form of a distributed over the circumference, radially oriented hammer head connection.
  • the cooling air 24 is guided through the structural parts 23 of the middle part to the cavity at the end of the compressor 17. From the cavity, the cooling air passes into distributed over the circumference of the ring 26 arranged axial bores 27 in the ring 46. At the upstream end of the ring 26, the exiting the ring 26 cooling air is deflected in a deflection (180 °) and passes through the gap 29 between the rotor disk 25 and the ring 26 again towards the turbine.
  • a seal 32 is preferably provided between the ring 26 and the structural parts 23 of the middle part 19, in order to minimize the slight leakage. This can e.g. a conventional labyrinth seal or brush seal.
  • deflecting elements 33 in particular in the form of a swirl nozzle or baffles, can be provided at the outlet of the cooling air from the structural parts 23, which impart a twist in the direction of rotation of the compressor to the cooling air emerging from the structural parts 23 ,

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP11175451A 2011-07-26 2011-07-26 Dispositif de refroidissement d'un compresseur d'un turbomoteur Withdrawn EP2551453A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP11175451A EP2551453A1 (fr) 2011-07-26 2011-07-26 Dispositif de refroidissement d'un compresseur d'un turbomoteur
DE102012014646A DE102012014646A1 (de) 2011-07-26 2012-07-24 Kompressorrotor
US13/556,722 US9382802B2 (en) 2011-07-26 2012-07-24 Compressor rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11175451A EP2551453A1 (fr) 2011-07-26 2011-07-26 Dispositif de refroidissement d'un compresseur d'un turbomoteur

Publications (1)

Publication Number Publication Date
EP2551453A1 true EP2551453A1 (fr) 2013-01-30

Family

ID=44651048

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11175451A Withdrawn EP2551453A1 (fr) 2011-07-26 2011-07-26 Dispositif de refroidissement d'un compresseur d'un turbomoteur

Country Status (3)

Country Link
US (1) US9382802B2 (fr)
EP (1) EP2551453A1 (fr)
DE (1) DE102012014646A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8668439B2 (en) * 2011-03-24 2014-03-11 General Electric Company Inserts for turbine cooling circuit
CH705840A1 (de) * 2011-12-06 2013-06-14 Alstom Technology Ltd Hochdruck-Verdichter, insbesondere in einer Gasturbine.

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0313826A1 (fr) * 1987-10-30 1989-05-03 BBC Brown Boveri AG Turbine à gaz avec flux axial
EP0690202A2 (fr) * 1994-06-30 1996-01-03 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Arrangement pour la séparation des particules de poussière de l'air de refroidissement des aubes de turbine
GB2350408A (en) 1999-03-29 2000-11-29 Abb Alstom Power Ch Ag Turbomachine rotor heat shield
EP0799971B1 (fr) 1996-04-04 2002-11-13 Alstom Barrière thermique pour rotor de turbine
US20050163612A1 (en) * 2002-07-01 2005-07-28 Martin Reigl Steam turbine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2633222A1 (de) 1976-07-23 1978-01-26 Kraftwerk Union Ag Gasturbinenanlage mit kuehlung der turbinenteile
DE2941866C2 (de) * 1978-10-26 1982-08-19 Rolls-Royce Ltd., London Turbine für ein Gasturbinentriebwerk mit lufgekühlten Turbinenschaufeln
US4541774A (en) 1980-05-01 1985-09-17 General Electric Company Turbine cooling air deswirler
GB2075123B (en) 1980-05-01 1983-11-16 Gen Electric Turbine cooling air deswirler
DE3428892A1 (de) * 1984-08-04 1986-02-13 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Schaufel- und dichtspaltoptimierungseinrichtung fuer verdichter von gasturbinentriebwerken, insbesondere gasturbinenstrahltriebwerken
DE3606597C1 (de) * 1986-02-28 1987-02-19 Mtu Muenchen Gmbh Schaufel- und Dichtspaltoptimierungseinrichtung fuer Verdichter von Gasturbinentriebwerken
US6250883B1 (en) * 1999-04-13 2001-06-26 Alliedsignal Inc. Integral ceramic blisk assembly
US20040030666A1 (en) * 1999-07-30 2004-02-12 Marra John J. Method of designing a multi-stage compressor rotor
AU2005229202B2 (en) * 2004-03-30 2010-08-05 General Electric Technology Gmbh Device for supplying cooling air to a moving blade
US7186079B2 (en) * 2004-11-10 2007-03-06 United Technologies Corporation Turbine engine disk spacers
JP4675638B2 (ja) 2005-02-08 2011-04-27 本田技研工業株式会社 ガスタービンエンジンの２次エア供給装置
EP2067999A1 (fr) 2007-12-06 2009-06-10 Napier Turbochargers Limited Rotor de turbocompresseur de suralimentation refroidi par liquide et procédé de refroidissement d'un rotor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0313826A1 (fr) * 1987-10-30 1989-05-03 BBC Brown Boveri AG Turbine à gaz avec flux axial
EP0690202A2 (fr) * 1994-06-30 1996-01-03 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Arrangement pour la séparation des particules de poussière de l'air de refroidissement des aubes de turbine
EP0799971B1 (fr) 1996-04-04 2002-11-13 Alstom Barrière thermique pour rotor de turbine
GB2350408A (en) 1999-03-29 2000-11-29 Abb Alstom Power Ch Ag Turbomachine rotor heat shield
US20050163612A1 (en) * 2002-07-01 2005-07-28 Martin Reigl Steam turbine

Also Published As

Publication number Publication date
DE102012014646A1 (de) 2013-01-31
US20130028750A1 (en) 2013-01-31
US9382802B2 (en) 2016-07-05

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