EP2143884A1 - Disque de rotor pour turbomachine - Google Patents

Disque de rotor pour turbomachine Download PDF

Info

Publication number
EP2143884A1
EP2143884A1 EP08012624A EP08012624A EP2143884A1 EP 2143884 A1 EP2143884 A1 EP 2143884A1 EP 08012624 A EP08012624 A EP 08012624A EP 08012624 A EP08012624 A EP 08012624A EP 2143884 A1 EP2143884 A1 EP 2143884A1
Authority
EP
European Patent Office
Prior art keywords
wheel disc
front side
wheel
barrier coating
thermal barrier
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Withdrawn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
EP08012624A
Other languages
German (de)
English (en)
Inventor
Yevgen Dr. Kostenko
Traugott Paul
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP08012624A priority Critical patent/EP2143884A1/fr
Publication of EP2143884A1 publication Critical patent/EP2143884A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/007—Preventing corrosion
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2118—Zirconium oxides

Definitions

  • the invention relates to a wheel disc for a turbomachine, wherein the wheel disc is designed for shrinking on a shaft, wherein the wheel disc has a front side and a rear side.
  • a turbomachine is, for example, a steam turbine, in particular a low-pressure steam turbine.
  • a low-pressure steam turbine essentially has a rotor with rotor blades arranged on this rotor and an inner housing arranged around the rotor. The inner housing has vanes that protrude between the blades.
  • rotors for low-pressure steam turbines which are made of a first cylindrical rotor material, wherein wheel disks are shrunk onto this rotor material. These wheel discs have an inner diameter which is slightly smaller than the outer diameter of the first rotor material. In a method step, the wheel disc is heated, so that the inner diameter is slightly larger than the diameter of the first rotor material by the thermal expansion.
  • the wheel disc is pulled onto the first rotor material and then cooled uniformly, so that the wheel disc is shrunk onto the first rotor material.
  • On such a wheel disc several blades are arranged.
  • the surface of the wheel disc and the surface of the inner housing arranged opposite the wheel disc form a flow channel through which a low-pressure steam flows during operation.
  • Low-pressure steam turbines are known, which are designed in such a way that the incoming steam flows in the flow channel and is also located in the spaces between the individual wheel disks and in front of the first wheel disk. Such flow conditions of the steam can cause the steam to be wet before the first wheel disk opposite to the steam, which is located after the wheel disc, which is usually overheated.
  • a known problem with such wheel disks is therefore the significant temperature transition between the superheated and wet areas of the first wheel disk.
  • This comparatively high temperature gradient may, in connection with the shrinking of the wheel disc to a first rotor material to an undesirable stress corrosion cracking in the region of the contact surface between the wheel disc and the first rotor material. This can cause cracks in this area, which leads to a reduction in lifespan.
  • the invention begins, whose task is to further develop the wheel disc such that stress corrosion cracking is reduced.
  • a wheel disc for a turbomachine wherein the wheel disc is designed for shrinking onto a shaft, wherein the wheel disc has a front side and a rear side, wherein a thermal barrier coating is arranged on the front side.
  • the invention thus paves the way to reduce the heat transfer of the steam to the front of the wheel disc, thereby reducing the integral temperature in the wheel disc.
  • the thermal barrier coating which is now used in an unusual manner in a low-pressure steam turbine on a wheel disc, is effectively avoided that the temperature of the steam leads to an undesirable increase in the temperature in the wheel disc.
  • the shrinkage can be withdrawn at the same time, since here too the low temperature is the design criterion for shrinkage design. Due to the lower temperature gradient in the wheel disc thereby the risk of cracking due to stress corrosion cracking is effectively reduced.
  • the front side of the wheel disc has a concave curvature.
  • a concave curvature of the front surface leads to a material savings of the wheel disc at the same time high demands on the strength of the wheel disc, which means that the wheel disc still has sufficient strength to accommodate the turbine blades.
  • the rear side of the wheel disc is also concave.
  • the wheel disc as a whole has less material, which leads to a lower centrifugal force.
  • the thermal barrier coating is constructed of the zirconia material.
  • the thermal barrier coating can be applied to the wheel disc via an adhesive layer.
  • Examples of a thermal barrier coating or an adhesive layer and further layers are in the WO 2006/133980 A1 disclosed. The content of WO 2006/133980 A1 is thus fully included in the disclosure of this application.
  • FIG. 1 shows a sectional view through part of a low-pressure steam turbine 1.
  • a first rotor material 3 is rotatably mounted about a rotation axis 2. Radulationn 4a, 4b, 4c and 4d are applied to the first rotor material 3.
  • the wheel disk 4a is in this case the first wheel disk seen in a flow direction 5.
  • steam flows via a vapor inflow region, not illustrated in the flow direction 5, into a flow channel 6.
  • the flow channel 6 is arranged essentially between the wheel discs 4a, 4b, 4c, 4d and a guide blade carrier 7.
  • the guide blade carrier 7 comprises a plurality of stator blades 8.
  • rotor blades 9 arranged on the wheel disks 4a, 4b, 4c, 4d are arranged in the flow channel 6.
  • the steam flowing in such a low-pressure steam turbine 1 has a temperature of less than 120 ° C and is relatively wet.
  • a thermal barrier coating 13 is applied on the front 10 of the first wheel 4a.
  • the thermal barrier coating 13 may be applied to the front 10 by known methods.
  • zirconia can be used as the material for the thermal barrier coating 13.
  • a non-illustrated adhesive layer can be applied, which provides a good connection between the thermal barrier coating 13 and the front 10 causes.
  • Examples of a thermal barrier coating 13 or an adhesive layer and further layers are known from the WO 2006/133980 A1 disclosed. The content of WO 2006/133980 A1 is thus fully included in the disclosure of this application.
  • the now lower temperature gradient 12 as a result of applying the thermal barrier coating 13 leads to an improved connection between the wheel disc 4a and the first rotor material 3 at the fitting point 14. At the fitting point 14, the risk of stress corrosion cracking is now reduced since the temperature gradient 12 is lower.
  • the wheel disc 4a is, as seen in cross-section, formed such that the front side 10 shows a concave curvature.
  • the rear side 11 is also concave. This leads to a weight reduction of the wheel disc as a whole, which leads to a reduction of the centrifugal forces during operation.
  • the thermal barrier coating 13 is applied to the concave curvature.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08012624A 2008-07-11 2008-07-11 Disque de rotor pour turbomachine Withdrawn EP2143884A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08012624A EP2143884A1 (fr) 2008-07-11 2008-07-11 Disque de rotor pour turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08012624A EP2143884A1 (fr) 2008-07-11 2008-07-11 Disque de rotor pour turbomachine

Publications (1)

Publication Number Publication Date
EP2143884A1 true EP2143884A1 (fr) 2010-01-13

Family

ID=40091949

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08012624A Withdrawn EP2143884A1 (fr) 2008-07-11 2008-07-11 Disque de rotor pour turbomachine

Country Status (1)

Country Link
EP (1) EP2143884A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010012583A1 (de) 2010-03-23 2011-09-29 Alstom Technology Ltd. Verfahren zum Betrieb einer Dampfturbine mit einem Impulsrotor sowie Dampfturbine zur Durchführung des Verfahrens
US20120195758A1 (en) * 2011-01-31 2012-08-02 Narendra Are Methods and Systems For Controlling Thermal Differential In Turbine Systems
CN106523035A (zh) * 2015-09-11 2017-03-22 熵零股份有限公司 液轴气体叶轮机构、液轴气体轮机及其装置
US10533421B2 (en) 2014-10-29 2020-01-14 General Electric Technology Gmbh Steam turbine rotor

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB535566A (en) * 1939-06-13 1941-04-11 Oerlikon Maschf Improvements in or relating to a thermal protective device for rotating heat engines
GB1556274A (en) * 1977-04-19 1979-11-21 Rolls Royce Blade carrying disc for a gas turbine engine
US4279575A (en) * 1977-11-19 1981-07-21 Rolls-Royce Limited Turbine rotor
US20050136249A1 (en) * 2003-12-18 2005-06-23 Hideyuki Arikawa Heat resistant article having thermal barrier coatinging
DE202005019320U1 (de) * 2005-12-08 2006-02-09 Abb Turbo Systems Ag Abgasturbine mit Wärmeschutz
EP1710398A1 (fr) * 2005-03-31 2006-10-11 General Electric Company Composant de turbine autre qu'une aube avec un revêtement céramique résistant à la corrosion et son procédé de fabrication
WO2006133980A1 (fr) 2005-06-13 2006-12-21 Siemens Aktiengesellschaft Systeme de couches conçu pour un composant comprenant une couche d'isolation thermique et une couche metallique anti-erosion, procede de production dudit composant, et procede pour faire fonctionner une turbine a vapeur
EP1808576A1 (fr) * 2006-01-11 2007-07-18 Siemens Aktiengesellschaft Arbre de turbine d'une turbomachine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB535566A (en) * 1939-06-13 1941-04-11 Oerlikon Maschf Improvements in or relating to a thermal protective device for rotating heat engines
GB1556274A (en) * 1977-04-19 1979-11-21 Rolls Royce Blade carrying disc for a gas turbine engine
US4279575A (en) * 1977-11-19 1981-07-21 Rolls-Royce Limited Turbine rotor
US20050136249A1 (en) * 2003-12-18 2005-06-23 Hideyuki Arikawa Heat resistant article having thermal barrier coatinging
EP1710398A1 (fr) * 2005-03-31 2006-10-11 General Electric Company Composant de turbine autre qu'une aube avec un revêtement céramique résistant à la corrosion et son procédé de fabrication
WO2006133980A1 (fr) 2005-06-13 2006-12-21 Siemens Aktiengesellschaft Systeme de couches conçu pour un composant comprenant une couche d'isolation thermique et une couche metallique anti-erosion, procede de production dudit composant, et procede pour faire fonctionner une turbine a vapeur
DE202005019320U1 (de) * 2005-12-08 2006-02-09 Abb Turbo Systems Ag Abgasturbine mit Wärmeschutz
EP1808576A1 (fr) * 2006-01-11 2007-07-18 Siemens Aktiengesellschaft Arbre de turbine d'une turbomachine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010012583A1 (de) 2010-03-23 2011-09-29 Alstom Technology Ltd. Verfahren zum Betrieb einer Dampfturbine mit einem Impulsrotor sowie Dampfturbine zur Durchführung des Verfahrens
US20120195758A1 (en) * 2011-01-31 2012-08-02 Narendra Are Methods and Systems For Controlling Thermal Differential In Turbine Systems
US8784061B2 (en) * 2011-01-31 2014-07-22 General Electric Company Methods and systems for controlling thermal differential in turbine systems
US10533421B2 (en) 2014-10-29 2020-01-14 General Electric Technology Gmbh Steam turbine rotor
US11053799B2 (en) 2014-10-29 2021-07-06 General Electric Technology Gmbh Steam turbine rotor
CN106523035A (zh) * 2015-09-11 2017-03-22 熵零股份有限公司 液轴气体叶轮机构、液轴气体轮机及其装置

Similar Documents

Publication Publication Date Title
EP1843044B1 (fr) Compresseur axial pour une turbine à gaz
DE2756684C2 (de) Verfahren zum Fertigen einer Turbomaschinenschaufel und Strömungsturbomaschine mit derartigen Schaufeln
EP1914383B1 (fr) Aube de soufflante en matériau composite
EP1757773B1 (fr) Aube creuse de turbine
DE102012011952B4 (de) Turbinenschaufelblatt aus Verbundwerkstoff
EP2452076B1 (fr) Rotor de turbomachine
EP2478186B1 (fr) Rotor de turbomachine
DE2753773A1 (de) Laufschaufel
EP1869292B1 (fr) Partie structurale d'un ensemble turbine a vapeur, ensemble turbine a vapeur et utilisation et procede de fabrication de ladite partie
EP1766193B1 (fr) Garniture de rodage
DE2411992C2 (de) Turbinenlaufrad mit nachgiebiger Abstützung der Schaufelfüße
EP2143884A1 (fr) Disque de rotor pour turbomachine
EP1616081B1 (fr) Aube mobile, notamment pour une turbine a gaz
EP2647796A1 (fr) Système d'étanchéité pour turbomachine
EP3043085A1 (fr) Agencement d'aubes pour une turbo-machine thermique à flux axial et procédé de montage d'un élément amortisseur entre deux aubes d'une couronne d'aube d'une turbo-machine thermique
EP2220342B1 (fr) Plaque de protection contre l'érosion pour aubes mobiles
DE112015003695T5 (de) Dampfturbinenrotorblatt, Verfahren zum Herstellen eines Dampfturbinenrotorblatts, und Dampfturbine
EP2805023A1 (fr) Aube de turbine ainsi que procédé de fabrication d'aube de turbine correspondant
CH647301A5 (de) Laeuferrad einer turbine mit daran befestigten laufschaufeln.
EP2031183B1 (fr) Arbre de turbine à vapeur doté d'une couche d'isolation thermique
EP2112334A1 (fr) Boîtier extérieur pour une turbomachine
EP1857635A1 (fr) Aube de turbine pour une turbine à gaz
EP2644828A1 (fr) Aube de turbine modulaire avec plateforme
EP1857636A1 (fr) Aube de turbine et méthode d'adaptation de la rigidité de la plate-forme avec celle de l'aube
DE102009047799B4 (de) Turbinenschaufel, Turbinenwelle, Turbinenanlage und Verfahren zur Montage der Turbinenschaufel

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

AKY No designation fees paid
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20100714

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566