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EP1705339B1 - Arbre de rotor, particulièrement pour une turbine à gaz - Google Patents

Arbre de rotor, particulièrement pour une turbine à gaz Download PDF

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Publication number
EP1705339B1
EP1705339B1 EP06110741.3A EP06110741A EP1705339B1 EP 1705339 B1 EP1705339 B1 EP 1705339B1 EP 06110741 A EP06110741 A EP 06110741A EP 1705339 B1 EP1705339 B1 EP 1705339B1
Authority
EP
European Patent Office
Prior art keywords
rotor shaft
cooling air
rotor
air channels
cavities
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.)
Not-in-force
Application number
EP06110741.3A
Other languages
German (de)
English (en)
Other versions
EP1705339A2 (fr
EP1705339A3 (fr
Inventor
Markus Roland Wiebe
Thomas Kramer
Holger Kiewel
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
General Electric Technology GmbH
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 General Electric Technology GmbH filed Critical General Electric Technology GmbH
Publication of EP1705339A2 publication Critical patent/EP1705339A2/fr
Publication of EP1705339A3 publication Critical patent/EP1705339A3/fr
Application granted granted Critical
Publication of EP1705339B1 publication Critical patent/EP1705339B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical

Definitions

  • the present invention relates to the field of rotary machines. It relates to a rotor shaft, in particular for a gas turbine, according to the preamble of claim 1.
  • a rotor disk with an elliptical cooling air opening arranged in the rotor disk is known.
  • additional cooling measures are often provided in order to achieve a sufficient service life of the material used at the high hot gas temperatures.
  • Such cooling measures include cooling air ducts which extend approximately in the radial direction from the inside to the outside through the rotor shaft and cooling air from an internal cooling air supply to the surface lead the rotor shaft.
  • cooling air ducts represent mechanical weakenings of the rotor shaft, which can have a negative effect on the high temperatures and centrifugal forces and the changing loads.
  • An essential point of the present solution is that the cooling air ducts for reducing mechanical stresses have an elliptical cross-section.
  • the rotor shaft further has a compressor part and a turbine part and the cooling air passages are arranged in the turbine part.
  • the turbine part has a plurality of rotor disks arranged one behind the other in the axial direction for fastening rotor blades, wherein the cooling air ducts are arranged between adjacent rotor disks.
  • An embodiment of the invention is characterized in that the cooling air ducts are arranged distributed over the circumference of the rotor shaft, and that the elliptical cross section of the cooling air ducts is oriented in each case so that the large main axis in the circumferential direction and the small main axis are aligned in the axial direction.
  • cavities are formed concentrically to the rotor axis in the interior of the rotor shaft, and that the cooling air channels emanate from at least one of the cavities and via this cavity with the Cooling air supply communicate. It is then particularly favorable for the cavities to have at least sections an elliptical cross-sectional contour to reduce mechanical stresses on the outer circumference, wherein the cross-sectional contour is preferably composed on the outer circumference of two elliptical sections of two mutually tilted ellipses whose major axes are oriented approximately in the radial direction are.
  • a rotor shaft 10 (without blading) reproduced a gas turbine.
  • the to the rotor axis (17 in Fig. 2 The rotationally symmetrical rotor shaft 10 is subdivided into a compressor part 11 and a turbine part 12. Between the two parts 11 and 12, the combustion chamber is arranged inside the gas turbine into which the air compressed in the compressor part 11 is introduced and from which the hot gas through the turbine part 12 flows.
  • the turbine part 12 has a plurality of rotor disks 13 arranged one behind the other in the axial direction, in which Fig. 3, 4 Axially aligned receiving slots 21 are formed around the circumference for receiving corresponding blades.
  • cooling air channels 14 are provided, which approximately radially outwardly depart from a formed inside the rotor shaft 10 cavity 15 and open at the surface of the rotor shaft 10 in the outer space ( Fig. 2 ).
  • the cavity 15 is in communication with a central, axially extending cooling air supply 16.
  • the cooling air channels (14 ') had a circular cross section, the cooling air channels 14 in the new configuration of Fig. 4 for reasons of mechanical stability an elliptical cross-section.
  • the elliptical cross section of the cooling air ducts 14 can already be predetermined during the casting of the rotor shaft. However, it is also conceivable to introduce such a cross section into the rotor shaft 10 by special machining methods such as eroding.
  • the ellipses of the channel cross-section of the cooling air channels 14 are oriented so that the major major axes are oriented in the circumferential direction, while the small main axes are parallel to the rotor axis 17. As a result, a maximum reduction of the mechanical stresses is achieved. It goes without saying that the advantages of an elliptical cross section are not limited to cooling air channels in the rotor shaft itself, but also apply to cooling air channels, which are arranged on other parts of the rotor such as blades or the like.
  • the concentric to the rotor axis 17 formed cavity 15 is also optimized in its cross-sectional profile in view of the mechanical stresses occurring.
  • the optimization of the cross-sectional profile takes place in the in Fig. 5 for further cavities 19, 20 in the compressor part 11 illustrated manner such that the edge contour on the outer circumference of the cavity 15, 19, 20 is formed at least partially elliptical.
  • the cross-sectional contour is at the outer periphery - as for the cavity 20 in Fig. 5 is shown - from two elliptical sections of two mutually tilted ellipses E1, E2 (in Fig. 5 dashed lines drawn together) whose major axes are oriented approximately in the radial direction.
  • Such a shape for the cavities present in the interior of the rotor shaft 10 is advantageous not only in connection with the cooling air channels 14 in the turbine part, but can also be used for other cavities 19, 20 which are located, for example, in the compressor part 11 of the rotor shaft 10.

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 (5)

  1. Arbre de rotor (10), plus particulièrement pour une turbine à gaz, dans laquelle des canaux d'air de refroidissement (14) sont prévus, qui s'étendent globalement dans la direction radiale de l'intérieur vers l'extérieur et qui sont reliés avec une alimentation en air de refroidissement (16) existant à l'intérieur de l'arbre du rotor (10), les canaux d'air de refroidissement (14) présentant, pour la réduction des contraintes mécaniques, une section elliptique et l'arbre de rotor (10) comprenant une partie de compresseur (11) et une partie de turbine (12) et les canaux d'air de refroidissement (14) étant disposés dans la partie de turbine (12), caractérisé en ce que la partie de turbine (12) comprend plusieurs disques de rotor (13) disposés les uns derrière les autres dans la direction axiale pour la fixation de pales et en ce que les canaux d'air de refroidissement (14) sont disposés entre des disques de rotor (13) adjacents.
  2. Arbre de rotor selon la revendication 1, caractérisé en ce que les canaux d'air de refroidissement (14) sont répartis sur la circonférence de l'arbre de rotor (10) et en ce que la section elliptique des canaux d'air de refroidissement (14) est orientée de façon à ce que le grand axe principal soit orienté dans la direction circonférentielle et le petit axe principale soit orienté dans la direction axiale.
  3. Arbre de rotor selon l'une des revendications 1 et 2, caractérisé en ce que, à l'intérieur de l'arbre de rotor (10), se trouvent des espaces creux (15, 19, 20) concentriques par rapport à l'axe du rotor (17) et en ce que les canaux d'air de refroidissement (14) sortent d'au moins un des espaces creux (15, 19, 20) et sont reliés, par l'intermédiaire de cet espace creux (15), avec l'alimentation en air de refroidissement (16).
  4. Arbre de rotor selon la revendication 3, caractérisé en ce que les espaces creux (15, 19, 20) présentent, pour la réduction des contraintes mécaniques sur la circonférence externe, au moins partiellement un contour de section elliptique (E1, E2).
  5. Arbre de rotor selon la revendication 4, caractérisé en ce que le contour de section sur la circonférence externe est constitué de deux portions elliptiques de deux ellipses (E1, E2) basculées l'une contre l'autre, dont les grands axes principaux sont orientés approximativement dans la direction radiale.
EP06110741.3A 2005-03-23 2006-03-07 Arbre de rotor, particulièrement pour une turbine à gaz Not-in-force EP1705339B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH5042005 2005-03-23

Publications (3)

Publication Number Publication Date
EP1705339A2 EP1705339A2 (fr) 2006-09-27
EP1705339A3 EP1705339A3 (fr) 2013-11-06
EP1705339B1 true EP1705339B1 (fr) 2016-11-30

Family

ID=35335753

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06110741.3A Not-in-force EP1705339B1 (fr) 2005-03-23 2006-03-07 Arbre de rotor, particulièrement pour une turbine à gaz

Country Status (2)

Country Link
US (1) US7329086B2 (fr)
EP (1) EP1705339B1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH699996A1 (de) 2008-11-19 2010-05-31 Alstom Technology Ltd Verfahren zum bearbeiten eines gasturbinenläufers.
CH702191A1 (de) 2009-11-04 2011-05-13 Alstom Technology Ltd Geschweisster Rotor.
EP2837769B1 (fr) 2013-08-13 2016-06-29 Alstom Technology Ltd Arbre de rotor pour turbomachine
JP2015178832A (ja) * 2014-03-19 2015-10-08 アルストム テクノロジー リミテッドＡＬＳＴＯＭ Ｔｅｃｈｎｏｌｏｇｙ Ｌｔｄ 冷却孔入口を備えるロータ軸
FR3028883B1 (fr) * 2014-11-25 2019-11-22 Safran Aircraft Engines Arbre de rotor de turbomachine comportant une surface d'echange thermique perfectionnee
EP3205817A1 (fr) 2016-02-09 2017-08-16 Ansaldo Energia Switzerland AG Rotor refroidi par fluide pour une turbine à gaz
US10177618B2 (en) 2016-03-15 2019-01-08 General Atomics Rotor assembly and method of manufacturing
US10458242B2 (en) * 2016-10-25 2019-10-29 Pratt & Whitney Canada Corp. Rotor disc with passages

Family Cites Families (18)

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Publication number Priority date Publication date Assignee Title
US2575568A (en) * 1946-11-12 1951-11-20 Gulf Research Development Co Centrifugal gas-liquid separator
FR2552817B1 (fr) * 1978-11-27 1988-02-12 Snecma Perfectionnements au refroidissement des rotors de turbines
US4344738A (en) * 1979-12-17 1982-08-17 United Technologies Corporation Rotor disk structure
FR2732405B1 (fr) * 1982-03-23 1997-05-30 Snecma Dispositif pour refroidir le rotor d'une turbine a gaz
GB2189845B (en) * 1986-04-30 1991-01-23 Gen Electric Turbine cooling air transferring apparatus
FR2614654B1 (fr) * 1987-04-29 1992-02-21 Snecma Disque de compresseur axial de turbomachine a prelevement d'air centripete
FR2616480B1 (fr) 1987-06-10 1989-09-29 Snecma Dispositif de verrouillage d'aubes a pied marteau sur un disque de turbomachine et procedes de montage et de demontage
GB2265671A (en) 1992-03-24 1993-10-06 Rolls Royce Plc Bladed rotor for a gas turbine engine
DE4324034A1 (de) * 1993-07-17 1995-01-19 Abb Management Ag Gasturbine mit gekühltem Rotor
DE4428207A1 (de) * 1994-08-09 1996-02-15 Bmw Rolls Royce Gmbh Turbinen-Laufradscheibe mit gekrümmtem Kühlluftkanal sowie Herstellverfahren hierfür
DE19620828C1 (de) * 1996-05-23 1997-09-04 Siemens Ag Turbinenwelle sowie Verfahren zur Kühlung einer Turbinenwelle
GB9615394D0 (en) * 1996-07-23 1996-09-04 Rolls Royce Plc Gas turbine engine rotor disc with cooling fluid passage
JP3621523B2 (ja) * 1996-09-25 2005-02-16 株式会社東芝 ガスタービンの動翼冷却装置
DE19705441A1 (de) * 1997-02-13 1998-08-20 Bmw Rolls Royce Gmbh Turbinen-Laufradscheibe
JP3316418B2 (ja) 1997-06-12 2002-08-19 三菱重工業株式会社 ガスタービン冷却動翼
AT3140U1 (de) 1998-11-06 1999-10-25 Avl List Gmbh Kurbelgehäuse für eine brennkraftmaschine
DE19941134C1 (de) 1999-08-30 2000-12-28 Mtu Muenchen Gmbh Schaufelkranz für eine Gasturbine
US6474946B2 (en) * 2001-02-26 2002-11-05 United Technologies Corporation Attachment air inlet configuration for highly loaded single crystal turbine blades

Non-Patent Citations (1)

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Title
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Also Published As

Publication number Publication date
US20070086884A1 (en) 2007-04-19
US7329086B2 (en) 2008-02-12
EP1705339A2 (fr) 2006-09-27
EP1705339A3 (fr) 2013-11-06

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