EP1564376B1 - Construction de rotor pour turbomachine - Google Patents

Construction de rotor pour turbomachine Download PDF

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Publication number
EP1564376B1
EP1564376B1 EP05100785.4A EP05100785A EP1564376B1 EP 1564376 B1 EP1564376 B1 EP 1564376B1 EP 05100785 A EP05100785 A EP 05100785A EP 1564376 B1 EP1564376 B1 EP 1564376B1
Authority
EP
European Patent Office
Prior art keywords
rotor
rotor core
rings
cooling air
hot gas
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
EP05100785.4A
Other languages
German (de)
English (en)
Other versions
EP1564376A2 (fr
EP1564376A3 (fr
Inventor
Klaus DÖBBELING
Joachim Krautzig
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 Switzerland AG
Original Assignee
Ansaldo Energia Switzerland 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 Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Publication of EP1564376A2 publication Critical patent/EP1564376A2/fr
Publication of EP1564376A3 publication Critical patent/EP1564376A3/fr
Application granted granted Critical
Publication of EP1564376B1 publication Critical patent/EP1564376B1/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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5853—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps heat insulation or conduction

Definitions

  • the present invention relates to the field of turbomachinery. It relates to a rotor according to the preamble of claim 1.
  • Rotors for high-temperature use in gas or steam turbines are preferably made of ferritic steels because of the lower material costs, the better weldability and ultrasound testability and because of the better fracture mechanical properties. Above 450 ° C, however, the mechanical properties of ferritic steels decrease so much that the use of austenitic steels becomes necessary.
  • the rotor located in gas turbines below the hot gas channel is shielded by separate blades and heat shields made of high temperature materials.
  • this shield has a highly segmented structure and the individual elements are attached to the rotor only by hooks of various types. If a ferritic material is used for the rotor, relatively large amounts of cooling air of at most 450 ° C for flushing the spaces between the rotor and the shielding elements are required. Compressors, even if they have outlet temperatures greater than about 450 ° C, have so far been mostly designed without any shielding and cooling because the clean shield provides little help against excessive peak loads and cooling with recirculation of cooling air into the compressor duct Efficiency deteriorates.
  • the essence of the invention is a rotor core of a first favorable Material that is not sufficient for the higher temperatures in the hot gas channel or cooling air channel, and then concentrically surround the rotor core with shielding rings of a second material, which shield the rotor core against the higher temperature in the hot gas channel or cooling air duct, the second material opposite the first material has a higher heat resistance.
  • the shielding rings are connected to the rotor core cohesively.
  • the first material is a ferritic steel and the second material is an austenitic steel. It has proven particularly useful to connect the shielding rings with the rotor core by soldering or welding. The shielding effect can be further improved if additional cooling channels for the passage of cooling air are provided on the inside of the shielding rings.
  • the shielding rings can be designed exclusively for shielding the rotor core and each have a flat rectangular or wedge-shaped cross section, or, if they shield the rotor core against the temperatures in the hot gas duct, can be designed to accommodate moving blades.
  • the shielding rings each have a cross-sectional profile in the form of a double T in order to achieve greater radial flexibility and thermal insulation.
  • a rotor 11 of a compressor 10 is shown in longitudinal section.
  • the compressor 10 is part of a gas turbine.
  • the section includes the high-pressure and output stages of the multi-stage compressor 10.
  • the rotor 11 is rotatably mounted within the compressor 10 about a rotor axis 21.
  • the rotor 11 consists of a plurality of rotor rings 16a, 16b, 16c arranged in succession in the axial direction, which are connected to one another by welds 15, 17.
  • the rotor 11 is surrounded concentrically by a hot gas channel 12 through which the compressed gas (air) flows in the direction of the drawn arrows.
  • blades 13 and vanes 14 are arranged in alternating rows in the axial direction one behind the other.
  • the vanes 14 are mounted on the hot gas channel 12 enclosing housing.
  • the blades 13 are fixed to the rotor 11 and rotate with the rotor 11 about the rotor axis 21.
  • the central rotor ring 16b in the section of which the high-pressure and output stages of the compressor 10 are located, and which is correspondingly exposed to the highest temperatures in the hot gas duct 12 (or in the cooling air duct), is composed of two different materials: the main component is a solid, central rotor core 22 made of a ferritic steel.
  • Several shielding rings 18 made of austenitic steel with a double T-shaped cross-sectional profile are pushed onto this rotor core one behind the other in the axial direction and welded to the rotor core 22 on the ring inner surface (welded connection 19). In another embodiment, they are soldered. Between adjacent shielding rings 18 are on the outer periphery recesses provided, which serve for receiving and holding the blades 13.
  • the thermal capacity of the rotor 11 is improved, without the rotor must be made entirely of an austenitic material.
  • the austenitic material shielding rings 18 between the hot gas passage 13 of the compressor or the turbine cooling air passage and the ferritic material rotor core 22, the temperatures at the compressor outlet and the cooling air in the cooling air passage can be raised by about 100 ° C.
  • the present invention proposes to use a rotor with a rotor core made of ferritic material, which is surrounded by relatively thin shielding rings of austenitic material, which are firmly connected to the rotor core by soldering or welding.
  • the cross-section of the shielding rings may vary depending on the local requirements: Wide and flat rectangular cross-sections, which are not the subject of the present invention, with a cylindrical or conical outer surface are particularly suitable for purely shielding purposes.
  • Individual rings may be provided with hooks for holding rotor blades.
  • the inventive rings with double T-profile allow greater radial flexibility and thermal insulation.
  • channels for a cooling medium may be integrated on the inner circumference of the shielding rings.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (5)

  1. Rotor (11) d'un moteur turbo à sollicitation thermique, plus particulièrement d'un compresseur (10) ou d'une turbine à gaz, ce rotor (11) étant logé de manière rotative autour d'un axe de rotor (21) et étant entouré de manière concentrique par un canal de gaz chaud (12) ou un canal d'air de refroidissement, le rotor (11) comprenant un noyau de rotor (22) constitué d'un premier matériau, le noyau de rotor (22) étant entouré de manière concentrique par des bagues de protection (18) constituées d'un deuxième matériau, qui protègent le noyau de rotor (22) contre la température dans le canal de gaz chaud (12) ou le canal d'air de refroidissement, le deuxième matériau présentant une résistance thermique supérieure à celle du premier matériau, et les bagues de protection (18) sont reliées par liaison de matière avec le noyau de rotor (22) ; le rotor (11) est caractérisé en ce que les bagues de protection (18) présentent chacune un profil de section ayant la forme d'un double T.
  2. Rotor selon la revendication 1, caractérisé en ce que le premier matériau est un acier ferritique et en ce que le deuxième matériau est un acier austénitique.
  3. Rotor selon la revendication 1 ou 2, caractérisé en ce que les bagues de protection (18) sont reliées avec le noyau de rotor (22) par brasage ou soudage.
  4. Rotor selon l'une des revendications 1 à 3, caractérisé en ce que, sur le côté interne des bagues de protection (18), sont prévus des canaux de refroidissement (20) pour le passage d'air de refroidissement.
  5. Rotor selon l'une des revendications 1 à 4, caractérisé en ce que les bagues de protection (18) protègent le noyau de rotor (22) contre les températures dans le canal de gaz chaud (12) et en ce que les bagues de protection (18) sont conçues pour le logement de pales (13).
EP05100785.4A 2004-02-14 2005-02-04 Construction de rotor pour turbomachine Not-in-force EP1564376B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004007327A DE102004007327A1 (de) 2004-02-14 2004-02-14 Rotor
DE102004007327 2004-02-14

Publications (3)

Publication Number Publication Date
EP1564376A2 EP1564376A2 (fr) 2005-08-17
EP1564376A3 EP1564376A3 (fr) 2013-06-19
EP1564376B1 true EP1564376B1 (fr) 2018-10-03

Family

ID=34684060

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05100785.4A Not-in-force EP1564376B1 (fr) 2004-02-14 2005-02-04 Construction de rotor pour turbomachine

Country Status (3)

Country Link
US (1) US7476078B2 (fr)
EP (1) EP1564376B1 (fr)
DE (1) DE102004007327A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9771802B2 (en) 2014-02-25 2017-09-26 Siemens Energy, Inc. Thermal shields for gas turbine rotor
US10036278B2 (en) * 2014-04-11 2018-07-31 United Technologies Corporation High pressure compressor thermal shield apparatus and system

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB543985A (en) * 1939-09-25 1942-03-23 Sulzer Ag Improvements in or relating to rotors for turbines
GB574752A (en) * 1943-02-12 1946-01-18 Ag Fuer Technische Studien Improvements in or relating to rotors for rotary machines, particularly steam or gasturbines
GB616432A (en) * 1946-08-30 1949-01-21 Power Jets Res & Dev Ltd Improvements relating to turbine rotors and the like bladed structures
GB612097A (en) * 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors
US2527446A (en) * 1948-09-17 1950-10-24 Westinghouse Electric Corp Turbine apparatus
CH349274A (de) * 1955-03-01 1960-10-15 Gen Electric Höchstdruck-Heissdampfturbine
DE1030358B (de) * 1955-09-30 1958-05-22 Gen Electric Befestigung eines Duesenkastens im Innengehaeuse einer Doppelgehaeuse-Hochtemperaturturbine
NL252407A (fr) * 1960-05-09 1900-01-01
DE2140816A1 (de) * 1971-08-14 1973-03-01 Motoren Turbinen Union Rotor fuer stroemungsmaschinen
JPS63108964A (ja) * 1986-10-24 1988-05-13 Hitachi Ltd 複合鋼塊軸の製造方法
DE3736836A1 (de) * 1987-10-30 1989-05-11 Bbc Brown Boveri & Cie Axial durchstroemte gasturbine
DE4239710A1 (de) * 1992-11-26 1994-06-01 Abb Patent Gmbh Läufer einer Turbine
RU2175069C2 (ru) * 1996-02-29 2001-10-20 Сименс Акциенгезелльшафт Вал турбины и способ его получения
DE19613472A1 (de) * 1996-04-04 1997-10-09 Asea Brown Boveri Vorrichtung zur Wärmedämmung
DE19615549B8 (de) * 1996-04-19 2005-07-07 Alstom Vorrichtung zum thermischen Schutz eines Rotors eines Hochdruckverdichters
DE19914227B4 (de) * 1999-03-29 2007-05-10 Alstom Wärmeschutzvorrichtung in Gasturbinen

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
US7476078B2 (en) 2009-01-13
EP1564376A2 (fr) 2005-08-17
US20050180847A1 (en) 2005-08-18
DE102004007327A1 (de) 2005-09-15
US20060269403A9 (en) 2006-11-30
EP1564376A3 (fr) 2013-06-19

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