EP1564376A2 - Construction de rotor pour turbomachine - Google Patents

Construction de rotor pour turbomachine Download PDF

Info

Publication number: EP1564376A2
Authority: EP; European Patent Office
Prior art keywords: rotor; rotor core; abschirmringe; cooling air; hot gas
Prior art date: 2004-02-14
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

EP05100785A

Other languages

German (de)

English (en)

Other versions

EP1564376A3 (fr

EP1564376B1 (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

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.)

2004-02-14

Filing date

2005-02-04

Publication date

2005-08-17

2005-02-04 Application filed by Alstom Technology AG filed Critical Alstom Technology AG

2005-08-17 Publication of EP1564376A2 publication Critical patent/EP1564376A2/fr

2013-06-19 Publication of EP1564376A3 publication Critical patent/EP1564376A3/fr

2018-10-03 Application granted granted Critical

2018-10-03 Publication of EP1564376B1 publication Critical patent/EP1564376B1/fr

2025-02-04 Anticipated expiration legal-status Critical

Status Expired - Lifetime legal-status Critical Current

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Images

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. she relates to a rotor according to the preamble of claim 1.
Compressors are, even if they have outlet temperatures of more than about 450 ° C had previously been designed mostly without any shielding and cooling because the pure shielding little help against excessive peak loads brings and cooling with a return of cooling air in the Compressor channel deteriorates the efficiency.
the object is solved by the entirety of the features of claim 1.
the essence of the invention is a rotor core of a first favorable Material to be produced for the higher temperatures in the hot gas channel or Cooling air channel is insufficient, and then the rotor core concentric with Shielding rings of a second material to surround, which the rotor core shield against the higher temperature in the hot gas duct or cooling air duct, wherein the second material is higher than the first material Has heat resistance.
the shielding rings are doing with the rotor core cohesively connected.
the first material is a ferritic steel and second material austenitic steel.
the shielding effect can be further improved if on the inside of the Shielding rings additionally cooling channels for the flow of cooling air are provided.
the shielding rings can only be used be designed to shield the rotor core and each a flat have rectangular or wedge-shaped cross-section, or they can, if they Shield the rotor core against the temperatures in the hot gas duct Receiving rotor blades be formed. But you can also each one Cross sectional profile in the form of a double T have to have a larger radial To achieve flexibility and thermal insulation.
a rotor 11 of a compressor 10 in Longitudinal section reproduced.
the compressor 10 is part of a gas turbine. Of the Section includes the high-pressure and output stages of the multi-stage Compressor 10.
the rotor 11 is within the compressor 10 by a Rotor axle 21 rotatably mounted.
the rotor 11 consists of several in the axial Direction successively arranged rotor rings 16 a, 16 b, 16 c, the through Weld seams 15, 17 are interconnected.
the rotor 11 is concentric surrounded by a hot gas channel 12, through which in the direction of drawn arrows the compressed gas (air) flows.
blades 13 and vanes 14 are arranged in the hot gas channel 12 in alternating rows in the axial direction successively blades 13 and vanes 14 are arranged.
the Guide vanes 14 are on the hot gas channel 12 enclosing housing appropriate.
the blades 13 are attached to the rotor 11 and rotate with the rotor 11 around the rotor axis 21.
the central rotor ring 16b in whose section the high-pressure and Output stages of the compressor 10 are located, and according to the highest temperatures in the hot gas duct 12 (or in the cooling air duct) exposed is is composed of two different materials: main component is one solid, central rotor core 22 made of a ferritic steel. On this Rotor core are in the axial direction one behind the other several shielding 18 off austenitic steel with double T-shaped cross-sectional profile slid and at the ring inner surface with the rotor core 22 welded (welded connection 19). In another embodiment, they are soldered. Between adjacent shielding rings 18 are recesses on the outer circumference provided, which serve for receiving and holding the blades 13. Below the blades 13 are located between the shield 18 Cavities. Run through the T-shaped foot region of the shielding rings 18 just above the welds 19 in the axial direction additional Cooling channels 20, which the thermal decoupling between the rotor core 22 and Heissgaskanal 12 or cooling air duct further improve.
the thermal load capacity of the rotor 11th improved without the rotor made entirely of an austenitic material must be made. Due to the arrangement of the shield 18 from austenitic material between the hot gas duct 13 of the compressor or the cooling air duct of the turbine and the rotor core 22 of ferritic material The temperatures at the compressor outlet or the cooling air in the Cooling air duct can be raised by about 100 ° C. At the same time is only a small one Amount of cooling air at a lower temperature for cooling the inside of the Shielding rings 18 (by means of the cooling channels 20) necessary. This can be done achieve significant improvements in efficiency without the rotor in its entirety must be made of a different material.
the present invention proposes a rotor with a rotor core use of ferritic material, the relatively thin shielding from austenitic material is surrounded by the soldering or soldering to the rotor core Welding are firmly connected.
the cross section of the shielding rings may vary depending on Be different from local requirements: wide and flat rectangular Cross sections with a cylindrical or conical outer surface are special suitable for pure shielding purposes. Individual rings can be hooked for the Be provided bracket of blades. Rings with double T profile allow greater radial flexibility and heat insulation.

Landscapes

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

EP05100785.4A 2004-02-14 2005-02-04 Construction de rotor pour turbomachine Expired - Lifetime EP1564376B1 (fr)

Applications Claiming Priority (2)

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

Publications (3)

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

Family

ID=34684060

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP05100785.4A Expired - Lifetime 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

2004
- 2004-02-14 DE DE102004007327A patent/DE102004007327A1/de not_active Withdrawn
2005
- 2005-02-04 EP EP05100785.4A patent/EP1564376B1/fr not_active Expired - Lifetime
- 2005-02-14 US US11/056,367 patent/US7476078B2/en not_active Expired - Fee Related

Also Published As

Publication number	Publication date
US20050180847A1 (en)	2005-08-18
EP1564376A3 (fr)	2013-06-19
US20060269403A9 (en)	2006-11-30
DE102004007327A1 (de)	2005-09-15
EP1564376B1 (fr)	2018-10-03
US7476078B2 (en)	2009-01-13

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Publication	Publication Date	Title
DE69934846T2 (de)	2007-10-18	Dampfturbine mit Bürstendichtung
DE69516423T2 (de)	2000-10-12	Dichtsteifenanordnung für gasturbinenstahltriebwerke
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