EP1980631A1 - Procédé de grenaillage d'une aube de turbine pour la zone chaude d'une turbine à gaz - Google Patents

Procédé de grenaillage d'une aube de turbine pour la zone chaude d'une turbine à gaz Download PDF

Info

Publication number
EP1980631A1
EP1980631A1 EP07007613A EP07007613A EP1980631A1 EP 1980631 A1 EP1980631 A1 EP 1980631A1 EP 07007613 A EP07007613 A EP 07007613A EP 07007613 A EP07007613 A EP 07007613A EP 1980631 A1 EP1980631 A1 EP 1980631A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine
airfoil
turbine blade
mpa
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Withdrawn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
EP07007613A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Michael Dr. Dankert
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 EP07007613A priority Critical patent/EP1980631A1/fr
Publication of EP1980631A1 publication Critical patent/EP1980631A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/10—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for compacting surfaces, e.g. shot-peening
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D7/00—Modifying the physical properties of iron or steel by deformation
    • C21D7/02—Modifying the physical properties of iron or steel by deformation by cold working
    • C21D7/04—Modifying the physical properties of iron or steel by deformation by cold working of the surface
    • C21D7/06—Modifying the physical properties of iron or steel by deformation by cold working of the surface by shot-peening or the like
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon

Definitions

  • the invention relates to a method for blasting a turbine blade with a blade root, a blade platform and an airfoil, which is designed for the hot region of a gas turbine.
  • Gas turbines have a cold and a warm area, which differ in particular by the temperatures prevailing during operation here.
  • the compressor is associated with its compressor blades due to the present in him comparatively low operating temperature of the cold region of the gas turbine.
  • the combustor which may experience temperatures in excess of 600 ° C during operation, belongs to the hot region of the gas turbine.
  • Such a method is for example in the EP 0 074 918 A2 described here, in particular, is provided to bombard the leading and trailing edges of the compressor blade with the blasting material to produce in this area Kompressionsvorschreiben.
  • the turbine blades arranged in the combustion chamber are also exposed to high loads, whereby cracks can occur, in particular due to the tensile forces occurring during the rotation.
  • the high operating temperatures in addition, the cracking of the combustion chamber, so that the service life of the turbine blades is significantly reduced overall.
  • This object is achieved in that at least a portion of the airfoil of the turbine blade is bombarded with a blasting material to produce in this a compression bias.
  • the basic idea of the invention is thus to produce a compression bias by bombardment with a blasting material in a turbine blade for the hot region of a gas turbine, at least in a region of the highly loaded airfoil.
  • a blasting material for the hot region of a gas turbine, at least in a region of the highly loaded airfoil.
  • the corresponding area of the surface of the blade is bombarded with blasting material at high speed.
  • the blasting material impinging on the airfoil then transfers some of its kinetic energy, producing the compression biases.
  • These biases counteract the tensile forces occurring during operation of the irradiated turbine blade, so that the load is reduced and the probability of cracking decreases. This is especially true at the high temperatures to which the turbine blade is exposed in the combustion chamber of the gas turbine during operation.
  • a portion of the trailing edge and / or the leading edge of the airfoil is bombarded with the blasting material. These portions of the airfoil are subjected to particular stresses during operation, so generating compressive biases here is very efficient in order to increase the overall life of the turbine bucket.
  • compressive biases here is very efficient in order to increase the overall life of the turbine bucket.
  • the presence of Compression biases in the trailing edge of the airfoil are essential to prevent cracking in the turbine blade during operation.
  • a compression bias of 10 to 500 MPa by bombardment with blasting material. If the compressive stress is below 10 MPa, it is too weak to significantly counteract the tensile stresses occurring during operation. Conversely, when generating compression biases in the range greater than 500 MPa, damage to the airfoil may occur during blasting.
  • a compression bias in the range of 10 to 200 MPa, in particular from 50 to 150 MPa is generated. The stresses in this area effectively counteract the tensile stresses that occur, without the risk of damaging the blade when they are produced by blasting.
  • FIG. 1 schematically a turbine blade 1, with a blade root 2, a blade platform 3 and an airfoil 4 is shown, which is provided for the hot region of a gas turbine, ie for the combustion chamber.
  • the trailing edge of the airfoil 4 is shown in the front and the front edge of the airfoil 4 at the rear in the drawing.
  • the turbine blade 1 is made of a superalloy. This may be particularly a nickel superalloy and in particular RENE80.
  • the region 7 of the trailing edge 5 of the blade 4 located immediately above the blade platform 3 is bombarded with a blasting material.
  • a blasting material for example in the EP 0074 918 A2 described blasting materials and process parameters are used.
  • a compression bias of 10 to 500 MPa is generated.
  • the entire trailing edge 5 and / or the entire front edge 6 can be bombarded with blasting material.
  • the turbine blade 1 irradiated according to the invention has a longer service life than an unirradiated turbine blade when operating in the combustion chamber of a gas turbine.
  • the cracking is reduced due to the tensile stresses acting during operation. This has been proven by the comparative tests carried out.
  • the subsequent measurement of the growth rate of the fatigue cracks has been carried out in accordance with ASTM E 647-2005.
  • the growth rate of the fatigue cracks dA / dA ( ⁇ K 1 ) would be determined by increasing ⁇ K 1 , which tests were performed on a high-frequency machine.
  • the ratio R was 0.1 and the frequency 10 Hz.
  • the determination of the crack length was determined by potential gradient measurements, whereby the potential gradient was correlated with the final crack length.
  • the CT sample sNS9ct2 was loaded to 25 kN and discharged at 900 ° C ( FIG. 5 ).
  • the results of the subsequent fatigue cracking test for this CT sample are in the FIGS. 6 and 7 shown.
  • the range of stress intensity ⁇ K 10 was increased from 15 to 20 MPa m 1/2 to obtain fatigue crack growth.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07007613A 2007-04-13 2007-04-13 Procédé de grenaillage d'une aube de turbine pour la zone chaude d'une turbine à gaz Withdrawn EP1980631A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07007613A EP1980631A1 (fr) 2007-04-13 2007-04-13 Procédé de grenaillage d'une aube de turbine pour la zone chaude d'une turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07007613A EP1980631A1 (fr) 2007-04-13 2007-04-13 Procédé de grenaillage d'une aube de turbine pour la zone chaude d'une turbine à gaz

Publications (1)

Publication Number Publication Date
EP1980631A1 true EP1980631A1 (fr) 2008-10-15

Family

ID=38457745

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07007613A Withdrawn EP1980631A1 (fr) 2007-04-13 2007-04-13 Procédé de grenaillage d'une aube de turbine pour la zone chaude d'une turbine à gaz

Country Status (1)

Country Link
EP (1) EP1980631A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101927458A (zh) * 2010-07-13 2010-12-29 国电联合动力技术有限公司 一种风机叶片表面处理方法
CN104364031A (zh) * 2012-06-01 2015-02-18 斯奈克玛 制造用于涡轮引擎的叶片的金属加强件的方法
CN110951954A (zh) * 2019-12-25 2020-04-03 哈尔滨电气动力装备有限公司 核电站主泵导叶叶片表面喷丸强化工艺方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0074918A2 (fr) * 1981-09-10 1983-03-23 United Technologies Corporation Procédé de grenaillage et polissage simultanés
EP0924306A2 (fr) * 1997-12-18 1999-06-23 General Electric Company Pièce métallique et un procédé pour le martelage par choc laser d'une pièce métallique
US20050039511A1 (en) * 2003-03-14 2005-02-24 Prevey Paul S. Method and apparatus for providing a layer of compressive residual stress in the surface of a part
EP1741796A2 (fr) * 2005-06-30 2007-01-10 The General Electric Company Suppression de la torsion d'aube induite par chocs laser employant écrouissage à la grenaille
EP1752234A1 (fr) * 2005-08-12 2007-02-14 Snecma Pièce métallique traitée par mise en compression de sous couches et procédé pour obtenir une telle pièce

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0074918A2 (fr) * 1981-09-10 1983-03-23 United Technologies Corporation Procédé de grenaillage et polissage simultanés
EP0924306A2 (fr) * 1997-12-18 1999-06-23 General Electric Company Pièce métallique et un procédé pour le martelage par choc laser d'une pièce métallique
US20050039511A1 (en) * 2003-03-14 2005-02-24 Prevey Paul S. Method and apparatus for providing a layer of compressive residual stress in the surface of a part
EP1741796A2 (fr) * 2005-06-30 2007-01-10 The General Electric Company Suppression de la torsion d'aube induite par chocs laser employant écrouissage à la grenaille
EP1752234A1 (fr) * 2005-08-12 2007-02-14 Snecma Pièce métallique traitée par mise en compression de sous couches et procédé pour obtenir une telle pièce

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101927458A (zh) * 2010-07-13 2010-12-29 国电联合动力技术有限公司 一种风机叶片表面处理方法
CN101927458B (zh) * 2010-07-13 2012-08-22 国电联合动力技术有限公司 一种风机叶片表面处理方法
CN104364031A (zh) * 2012-06-01 2015-02-18 斯奈克玛 制造用于涡轮引擎的叶片的金属加强件的方法
CN104364031B (zh) * 2012-06-01 2016-09-07 斯奈克玛 制造用于涡轮引擎的叶片的金属加强件的方法
CN110951954A (zh) * 2019-12-25 2020-04-03 哈尔滨电气动力装备有限公司 核电站主泵导叶叶片表面喷丸强化工艺方法

Similar Documents

Publication Publication Date Title
EP0697503B1 (fr) Procédure pour la construction d'une aube de turbine en alliage de base (alpha-bêta)-Titane
EP2137381B1 (fr) Procédé de fabrication d'aubes mobiles de turbine recouvertes
EP2435589B1 (fr) Procédé et dispositif de durcissement de surface d'un élément de construction qui est constitué dans la région de sa surface à durcir d'un composé intermétallique
WO2008071165A1 (fr) Dispositif et procédé de réparation ou de fabrication de pointes d'aubes d'une turbine à gaz, notamment d'un moteur d'avion
EP2072176A1 (fr) Procédé destiné à la fabrication d'une couche de protection à base d'acier contre l'érosion utilisant le laser; Composant comprenant une telle couche de protection à base d'acier contre l'érosion
EP3581668B1 (fr) Procédé de fabrication d'un composant à partir de gamma-tial et composant fabriqué correspondant
EP1904257A1 (fr) Procede de fabrication d'un blindage pour une aube de turbine
DE69626878T2 (de) Gasturbinenschaufeln mit Laserschock behandelte Kanten
EP1805344B1 (fr) Procede de fabrication d'une piece pourvue d'un revetement de protection contre l'usure
Persson et al. Evaluation of service-induced damage and restoration of cast turbine blades
EP1980631A1 (fr) Procédé de grenaillage d'une aube de turbine pour la zone chaude d'une turbine à gaz
WO2007101743A1 (fr) Procédé de fabrication d'une pièce de compresseur ou de turbine et pièce de compresseur ou de turbine ainsi obtenue
EP1654441B1 (fr) Revêtement de turbine à gaz et procédé de fabrication d'un tel revêtement
DE102006058678A1 (de) Verfahren und Vorrichtung zum Oberflächenstrahlen eines Teilelements eines Bauteils einer Gasturbine
WO2007144374A1 (fr) Procédé d'enduction d'un élément comportant des cavités à sa surface
DE102007034242A1 (de) Reparaturverfahren
CH715037B1 (de) Leitgitter für eine Strömungsmaschine und Verfahren zum Herstellen desselben.
EP3274561B1 (fr) Aube de rotor pour une turbine à gaz, procédé de fabrication et procédé de post-production
DE102018203777A1 (de) Nachbehandlungsverfahren für Schaufeln einer Strömungsmaschine
DE102019217434A1 (de) Verfahren zur schichtweisen additiven Herstellung eines Verbundwerkstoffs
EP3088122B1 (fr) Reparation de segments de conduit d'ecoulement monocristallins a l'aide de refonte monocristalline
Catteau et al. New Steel Grades for Deep Carburizing of Windmill Transmission Components
EP1914382A1 (fr) Procédé de réparation d'une aube de turbine
DE69120175T2 (de) Reparaturtechnik für Schaufelfüsse
DE102014204527A1 (de) Lötverfahren mit Couponfixierung zum Reparieren eines Turbinenbauteils

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 HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

AKX 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: 20090416

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566