EP1079070A3 - Heatshield for a turbine rotor - Google Patents

Heatshield for a turbine rotor Download PDF

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Publication number
EP1079070A3
EP1079070A3 EP00810682A EP00810682A EP1079070A3 EP 1079070 A3 EP1079070 A3 EP 1079070A3 EP 00810682 A EP00810682 A EP 00810682A EP 00810682 A EP00810682 A EP 00810682A EP 1079070 A3 EP1079070 A3 EP 1079070A3
Authority
EP
European Patent Office
Prior art keywords
rotor disks
contour
heat accumulation
accumulation unit
toothed
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
EP00810682A
Other languages
German (de)
French (fr)
Other versions
EP1079070A2 (en
EP1079070B1 (en
Inventor
Herbert Brandl
Peter Marx
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 Schweiz 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 Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP1079070A2 publication Critical patent/EP1079070A2/en
Publication of EP1079070A3 publication Critical patent/EP1079070A3/en
Application granted granted Critical
Publication of EP1079070B1 publication Critical patent/EP1079070B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • 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
    • F05D2240/40—Use of a multiplicity of similar components

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Beschrieben wird eine Vorrichtung zur Abtrennung eines mit einem heißen Arbeitsmedium durchströmten Raumbereiches von einem Raumbereich innerhalb einer Rotoranordnung einer Strömungsmaschine, vorzugsweise einer Gasturbine, mit wenigstens zwei axial hintereinander angeordneten Rotorscheiben, die über wenigstens einen Verbindungsbereich fest miteinander verbindbar sind und wenigstens im Bereich ihrer radialen Umfangsränder voneinander beabstandet sind, und mit einer flächig ausgebildeten Wärmestaueinheit, die zwischen zwei benachbarten Rotorscheiben angeordnet ist und zwei Verbindungskanten aufweist, entlang derer die Wärmestaueinheit jeweils im Bereich der Umfangsränder der benachbarten Rotorscheiben in Wirkverbindung bringbar ist, und die einen rotorseitig sich zwischen beiden Rotorscheiben erstreckenden Zwischenraum abdeckt.A device is described for the separation of a hot working medium area flowed through by a room area within a Rotor arrangement of a turbomachine, preferably a gas turbine, with at least two rotor disks arranged axially one behind the other, which at least a connection area can be firmly connected to one another and at least are spaced apart from one another in the region of their radial peripheral edges, and with a flat heat accumulation unit between two adjacent rotor disks is arranged and has two connecting edges, along which the Heat accumulation unit in the area of the peripheral edges of the adjacent rotor disks can be brought into operative connection, and the one on the rotor side between the two Covering rotor disks extending space.

Die Erfindung zeichnet sich dadurch aus, daß die Verbindungskanten der Wärmestaueinheit jeweils eine gezahnte Kontur mit stegartig ausgebildeten Verbindungselementen mit dazwischenbefindlichen Zwischenräumen aufweisen, daß jeweils im Bereich des Umfangsrandes der Rotorscheiben eine, zu der gezahnten Kontur der Verbindungskanten der Wärmestaueinheit in etwa korrespondierende gezahnte Gegenkontur vorgesehen ist, und daß die Verbindungselemente mit der gezahnten Gegenkontur in eine formschlüssige, lösbar feste Verbindung bringbar sind.

Figure 00000001
The invention is characterized in that the connecting edges of the heat accumulation unit each have a toothed contour with web-shaped connecting elements with intermediate spaces between them, that in each case in the region of the peripheral edge of the rotor disks there is provided a toothed counter-contour which corresponds approximately to the toothed contour of the connecting edges of the heat accumulation unit , and that the connecting elements with the toothed counter-contour can be brought into a form-fitting, releasably fixed connection.
Figure 00000001
EP00810682A 1999-08-26 2000-07-31 Heatshield for a turbine rotor Expired - Lifetime EP1079070B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19940525 1999-08-26
DE19940525A DE19940525A1 (en) 1999-08-26 1999-08-26 Heat accumulation unit for a rotor arrangement

Publications (3)

Publication Number Publication Date
EP1079070A2 EP1079070A2 (en) 2001-02-28
EP1079070A3 true EP1079070A3 (en) 2004-01-14
EP1079070B1 EP1079070B1 (en) 2005-03-16

Family

ID=7919697

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00810682A Expired - Lifetime EP1079070B1 (en) 1999-08-26 2000-07-31 Heatshield for a turbine rotor

Country Status (2)

Country Link
EP (1) EP1079070B1 (en)
DE (2) DE19940525A1 (en)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2825748B1 (en) * 2001-06-07 2003-11-07 Snecma Moteurs TURBOMACHINE ROTOR ARRANGEMENT WITH TWO BLADE DISCS SEPARATED BY A SPACER
CA2619730A1 (en) 2005-08-23 2007-03-01 Alstom Technology Ltd Locking and fixing device for a heat shield element for a rotor unit of a turbomachine
EP1898054B1 (en) * 2006-08-25 2018-05-30 Ansaldo Energia IP UK Limited Gas turbine
US8221062B2 (en) * 2009-01-14 2012-07-17 General Electric Company Device and system for reducing secondary air flow in a gas turbine
US8235656B2 (en) * 2009-02-13 2012-08-07 General Electric Company Catenary turbine seal systems
US8177495B2 (en) * 2009-03-24 2012-05-15 General Electric Company Method and apparatus for turbine interstage seal ring
US8348603B2 (en) * 2009-04-02 2013-01-08 General Electric Company Gas turbine inner flowpath coverpiece
FR2966867B1 (en) 2010-10-28 2015-05-29 Snecma ROTOR DISC ASSEMBLY FOR A TURBOMACHINE
EP2832952A1 (en) 2013-07-31 2015-02-04 ALSTOM Technology Ltd Turbine blade and turbine with improved sealing
US10036278B2 (en) * 2014-04-11 2018-07-31 United Technologies Corporation High pressure compressor thermal shield apparatus and system
US10502080B2 (en) 2015-04-10 2019-12-10 United Technologies Corporation Rotating labyrinth M-seal
EP3168205B1 (en) 2015-11-12 2018-10-10 Ansaldo Energia IP UK Limited Gas turbine part and method for manufacturing such gas turbine part
EP3168204B1 (en) 2015-11-12 2019-02-27 Ansaldo Energia IP UK Limited Method for manufacturing a gas turbine part
FR3057016B1 (en) * 2016-09-30 2020-10-23 Safran Aircraft Engines DESIGN PROCESS OF AN IMPROVED ROTOR AND ROTOR ORGAN
EP3318724A1 (en) * 2016-11-04 2018-05-09 Siemens Aktiengesellschaft Sealing segment of a rotor and rotor
DE102017220336A1 (en) * 2017-11-15 2019-05-16 Siemens Aktiengesellschaft Sealing segment of a rotor and rotor
EP3788236B1 (en) * 2018-08-02 2023-06-21 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor disks
FR3120894B1 (en) * 2021-03-19 2023-02-24 Safran Aircraft Engines TURBOMACHINE ROTOR, INCLUDING A LABYRINTH SEAL RING MOUNTED ON DISC FERRULES
CN117722235B (en) * 2024-02-18 2024-05-17 中国航发四川燃气涡轮研究院 Double-radial-plate turbine disc

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB790029A (en) * 1955-04-10 1958-01-29 Maschf Augsburg Nuernberg Ag Built-up rotor for axial flow rotary machines, more particularly for gas turbines
GB848465A (en) * 1957-06-14 1960-09-14 Napier & Son Ltd Rotors of multi-stage axial flow compressors or turbines
US4432697A (en) * 1981-04-10 1984-02-21 Hitachi, Ltd. Rotor of axial-flow machine
US5865600A (en) * 1995-11-10 1999-02-02 Mitsubishi Heavy Industries, Ltd. Gas turbine rotor
EP0921273A1 (en) * 1997-06-11 1999-06-09 Mitsubishi Heavy Industries, Ltd. Rotor for gas turbines

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5236302A (en) * 1991-10-30 1993-08-17 General Electric Company Turbine disk interstage seal system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB790029A (en) * 1955-04-10 1958-01-29 Maschf Augsburg Nuernberg Ag Built-up rotor for axial flow rotary machines, more particularly for gas turbines
GB848465A (en) * 1957-06-14 1960-09-14 Napier & Son Ltd Rotors of multi-stage axial flow compressors or turbines
US4432697A (en) * 1981-04-10 1984-02-21 Hitachi, Ltd. Rotor of axial-flow machine
US5865600A (en) * 1995-11-10 1999-02-02 Mitsubishi Heavy Industries, Ltd. Gas turbine rotor
EP0921273A1 (en) * 1997-06-11 1999-06-09 Mitsubishi Heavy Industries, Ltd. Rotor for gas turbines

Also Published As

Publication number Publication date
DE19940525A1 (en) 2001-03-01
EP1079070A2 (en) 2001-02-28
EP1079070B1 (en) 2005-03-16
DE50009768D1 (en) 2005-04-21

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