EP1833641A2 - Procede pour exposer des cavites a des rayonnements, notamment des cavites situees au niveau de turbines a gaz - Google Patents

Procede pour exposer des cavites a des rayonnements, notamment des cavites situees au niveau de turbines a gaz

Info

Publication number
EP1833641A2
EP1833641A2 EP05817204A EP05817204A EP1833641A2 EP 1833641 A2 EP1833641 A2 EP 1833641A2 EP 05817204 A EP05817204 A EP 05817204A EP 05817204 A EP05817204 A EP 05817204A EP 1833641 A2 EP1833641 A2 EP 1833641A2
Authority
EP
European Patent Office
Prior art keywords
blasting
khz
balls
cavities
gas turbine
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.)
Ceased
Application number
EP05817204A
Other languages
German (de)
English (en)
Inventor
Hoffmann-Ivy
Patrick Cheppe
Jean-Michel Duchazeaubeneix
Erwin Bayer
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.)
MTU Aero Engines AG
SONATS
Original Assignee
MTU Aero Engines GmbH
SONATS
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 MTU Aero Engines GmbH, SONATS filed Critical MTU Aero Engines GmbH
Publication of EP1833641A2 publication Critical patent/EP1833641A2/fr
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C5/00—Devices or accessories for generating abrasive blasts
    • B24C5/005—Vibratory devices, e.g. for generating abrasive blasts by ultrasonic vibrations
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/47—Burnishing
    • Y10T29/479—Burnishing by shot peening or blasting

Definitions

  • the invention relates to a method for surface blasting of cavities, in particular of cavities on gas turbines.
  • Gas turbines in particular aircraft engines, have, in particular in the region of a compressor and a turbine, at least one rotor equipped with rotating blades, wherein the rotor blades are increasingly formed as an integral part of the rotor.
  • Integrally bladed rotors are also referred to as "blisk” (bladed disk) or “bling” (bladed ring). In such rotors usually extending in the radial direction through holes for fluids, for example, for oil, integrated.
  • Such bores are also referred to as "bleed holes" and represent cavities with small cross-sectional areas.Other bores extend in the axial direction and are often used for screwing, these bores also highly loaded zones or areas of compressor and turbine represent more cavities with small cross-sectional areas For example, during operation of a gas turbine, the rotors of the gas turbine rotor are particularly stressed, and in order to reduce the wear rate, the rotors are solidified by means of special surface treatment methods, including the surfaces described above To consolidate cavities with small cross-sectional areas and the associated transition radii.
  • the prior art typically employs shot peening, wherein the balls are accelerated by means of an air flow or a centrifuge.
  • shot peening wherein the balls are accelerated by means of an air flow or a centrifuge.
  • the surfaces of through-holes are to be solidified by means of balls accelerated by an airflow or a centrifuge, there is a problem that, in particular, corners of the through-holes between a surface of the rotor and an inner surface of the through-holes are subject to severe plastic deformation , whereby the ductility of the material in the region of the through holes can be reduced and thus adversely affected.
  • the methods known from the prior art for surface radiation are therefore only very limited suitable for machining cavities, in particular narrow cross-sectional areas.
  • the present invention is based on the problem to provide a novel method for surface blasting of cavities, in particular cavities on gas turbines.
  • balls are accelerated by means of at least one vibrator, wherein the accelerated balls are directed to surfaces of a cavity to be irradiated and the corresponding transition radii.
  • the vibrator is preferably positioned with a small distance, preferably with a distance in the order of the diameter of the balls used for blasting, from the cavity to be irradiated.
  • the inventive acceleration of the balls used for blasting by means of a vibrator results from multiple reflections a random direction of movement of the balls, whereby material deformations in the cavities are minimized. Furthermore, results from the lower number of balls used a temporally lower pulse density, which also reduces the risk of material damage is reduced. In order to provide a sufficient surface roughening impulse despite the reduced momentum impulse density, balls with an adapted diameter, a higher density and thus ultimately a larger mass are used.
  • the or each ultrasonic vibrator with a frequency between 10 kHz and 50 kHz, in particular with a frequency between 20 kHz and 40 kHz, operated, preferably balls with high density and hardness of a ceramic material, in particular made of tungsten carbide, used for blasting.
  • the method is used when blasting through holes extending in the radial direction of a gas turbine rotor or from connecting holes extending in the axial direction with a relatively small cross-sectional area of, in particular, 5 mm 2 to 100 mm 2 , such a through hole first being in a transitional area between a component surface and an inner surface of the through hole and then in the region of the inner surface is blasted, wherein for blasting balls with a diameter between 0.2 mm and 5 mm, in particular between 0.4 mm and 1 mm, are used, and wherein for blasting a radially outer transition region between the component surface and the inner surface of the passage bore and for blasting the inner surface of the vibrator with a frequency between 10 kHz and 50 kHz, in particular at 20 kHz, whereas for radiating a radially inner transition region between the component surface and the inner surface, the ultrasonic vibrator is operated at a frequency between 10 kHz and 50 kHz, in particular at 40 kHz.
  • Figure 1 is a highly schematic representation of a component with two radiating through holes.
  • FIG. 2 shows the blasting of a corner region or transition region between a component surface and an inner surface of the passage bore of the component of FIG. 1;
  • FIG. 3 shows the blasting of the inner surface of the passage bore of the component of FIG. 1;
  • FIG. 4 is a highly schematic representation of an integrally bladed gas turbine rotor during the blasting of a radially extending through bore from radially inward;
  • FIG. 5 is a highly schematic representation of an integrally bladed gas turbine rotor when blasting a radially extending through hole from radially outside;
  • Fig. 6 is a highly schematic representation of a gas turbine rotor when blasting a cavity between two rotor disks from radially inside.
  • FIG. 1 shows a disk-shaped component 10 with two through-bores 11 and 12.
  • the through-bores 11 and 12 are bores with a relatively small cross-sectional area, in particular with a cross-sectional area of 5 mm 2 to 100 mm 2 .
  • the through holes 11, 12 have an oval cross-sectional area with a length of 3.8 mm and a width of 1.2 mm.
  • the dimensions of the through holes 11, 12 are very small.
  • the balls are accelerated by means of at least one ultrasonic vibrator, in particular by means of a so-called ultrasonic sonotrode, the balls thus accelerated being then directed onto the surfaces of the cavity to be irradiated.
  • the or each ultrasound vibrator is operated at a frequency between 10 kHz and 50 kHz, in particular at a frequency between 20 kHz and 40 kHz.
  • balls made of a ceramic material preferably tungsten carbide used. It is also possible to use balls made of a steel alloy, preferably of a 10OCr ⁇ material.
  • the balls used for blasting preferably have a polished surface and a diameter which is adapted to the dimensions of the cavity to be irradiated.
  • balls with a diameter between 0.2 mm and 5 mm, in particular between 0.4 mm and 1 mm, are preferably used.
  • the procedure is preferably two-stage.
  • corner regions or transition regions are blasted between a surface 13 of the component 10 and an inner surface 14 of the through-bores 11 and 12, respectively.
  • the corner regions or transition regions are identified in FIG. 1 by the reference numeral 15 and, in the exemplary embodiment shown, form a radial transition between the surface 13 of the component 10 and the inner surface 14 of the respective bore 11 and 12, respectively Transition regions 15 is then the blasting of the inner surfaces 14 of the through holes 11 and 12th
  • An ultrasonic vibrator namely an ultrasonic sonotrode 16 is arranged for this purpose in the region of a surface 13 of the component 10 at a small distance from the through-bore 11 or 12 to be radiated.
  • the through-hole 11 or 12 is closed with a sealing plug 17.
  • the closure plug 17 can protrude as shown in FIG. 2 with a projection 18 in the passage bore 11 and 12 respectively.
  • the areas of the surface 13 which are not to be irradiated Transitional area 15 of the through-hole 11 and 12 are covered by means of a cover 19, wherein the cover 19 can simultaneously form a spacer to maintain the distance between the sonotrode 16 and the component 10.
  • the distance between the sonotrode 16 and the surface 13 of the component 10 during the blasting of the transition regions 15 in the range of a few millimeters, preferably in the range of five to fifty times the diameter of the balls used for blasting 20.
  • There are for blasting such Through holes preferably 20 balls used with a diameter between 0.4 mm and 1 mm.
  • a sonotrode 16 is positioned at a small distance from the surface 13 of the component 10, wherein the entire surface 13 and thus also the transition areas 15 previously radiated in the direction of FIG. 2 are covered by a cover 21.
  • the cover 21 also forms again a spacer for maintaining a defined distance between the sonotrode 16 and the component 10.
  • This distance is in the radiation of the inner surfaces 14 in the order of the diameter of the balls used for blasting, in particular of the order of half the diameter of the same.
  • the passage bore 11 or 12 is also closed by a sealing plug 22 on the opposite side of the sonotrode 16 when the inner surfaces 14 are blasted, but the sealing plug 22 does not protrude into the through-bore 11 or 12.
  • FIGS. 4 and 5 show a rotor disk 23 of an integrally bladed rotor, the blades of the integrally bladed rotor 23 being identified by the reference numeral 24.
  • through-bores 25 extending in the radial direction are integrated in the rotor disk 23, the through-bores serving for the passage of fluids, in particular of oil.
  • the passage bores 25 can be compared in terms of their geometric dimensions with the through holes 11 and 12 in FIG. 1, so that the blasting of the extending in the radial direction füreriesbohungen-. ments of the rotor disk 23 in principle, as described in connection with FIGS. 1 to 3, can be proceeded.
  • Fig. 4 shows the rays of the radially extending through holes 25 of the rotor disk 23 from radially inward
  • Fig. 5 shows the jets thereof from the radially outer.
  • the procedure is such that for blasting the radially outer corner areas or transition areas between a radially outer surface of the rotor disk 23 and an inner surface of the through-bores 25 and for blasting the inner surfaces of the rotor Through holes 25 an ultrasonic vibrator, namely an ultrasonic sonotrode 26, with a frequency of 10 kHz to 50 kHz, in particular at 20 kHz is operated.
  • the ultrasonic sonotrode 26 is at a frequency of 10 kHz to 50 kHz, in particular at 40 kHz, operated.
  • the number of balls used for blasting and the duration of ultrasonic shot peening are determined.
  • FIG. 6 shows a detail of a gas turbine rotor 29, which has two adjacent rotor disks 30 and 31.
  • a cavity 32 between the two adjacent rotor disks 30 and 31 can be solidified by means of balls 33 which are accelerated via an ultrasonic vibrator, namely an ultrasonic sonotrode 34.
  • an ultrasonic vibrator namely an ultrasonic sonotrode 34.
  • spheres made of tungsten carbide or a CO.sub.2 O.sub.0 material which, in contrast to the surface blasting of through-bores, have a larger diameter.
  • spheres having a diameter of 0.5 mm to 6 mm, preferably 2 mm are preferably used.
  • an ultrasonic shot peening process for surface hardening of cavities wherein the balls are accelerated by means of an ultrasonic vibrator, namely by means of an ultrasonic sonotrode.
  • the diameter of the balls is adapted to the cavity to be machined, preferably using balls of tungsten carbide.
  • the balls have a polished surface.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Finish Polishing, Edge Sharpening, And Grinding By Specific Grinding Devices (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Grinding And Polishing Of Tertiary Curved Surfaces And Surfaces With Complex Shapes (AREA)

Abstract

L'invention concerne un procédé permettant d'exposer des cavités à des rayonnements, notamment des cavités situées au niveau de turbines à gaz. Selon l'invention, des billes sont accélérées au moyen d'un vibreur, les billes accélérées dans la plage des ultrasons étant dirigées sur des surfaces d'une cavité à exposer à l'action de rayonnements. A cet effet, le vibreur est positionné de préférence à distance réduite de la cavité à exposer à l'action de rayonnements, de préférence à une distance de l'ordre de grandeur du diamètre des billes utilisées pour appliquer les rayonnements.
EP05817204A 2004-12-10 2005-12-07 Procede pour exposer des cavites a des rayonnements, notamment des cavites situees au niveau de turbines a gaz Ceased EP1833641A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004059592.5A DE102004059592B4 (de) 2004-12-10 2004-12-10 Verfahren zum Oberflächenstrahlen von Hohlräumen, insbesondere von Hohlräumen an Gasturbinen
PCT/DE2005/002205 WO2006061004A2 (fr) 2004-12-10 2005-12-07 Procede pour exposer des cavites a des rayonnements, notamment des cavites situees au niveau de turbines a gaz

Publications (1)

Publication Number Publication Date
EP1833641A2 true EP1833641A2 (fr) 2007-09-19

Family

ID=35840504

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05817204A Ceased EP1833641A2 (fr) 2004-12-10 2005-12-07 Procede pour exposer des cavites a des rayonnements, notamment des cavites situees au niveau de turbines a gaz

Country Status (5)

Country Link
US (1) US7644599B2 (fr)
EP (1) EP1833641A2 (fr)
CA (1) CA2589964C (fr)
DE (1) DE102004059592B4 (fr)
WO (1) WO2006061004A2 (fr)

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FR3061055B1 (fr) * 2016-12-26 2019-07-26 Safran Aircraft Engines Dispositif pour le traitement d'une piece metallique, procede et ensemble de projectiles associes
CN107488779A (zh) * 2017-08-07 2017-12-19 沈阳航空航天大学 一种内孔表面的反射式超声喷丸强化装置
CN107338350A (zh) * 2017-08-07 2017-11-10 沈阳航空航天大学 一种内孔表面的超声喷丸强化装置
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CN111705196B (zh) * 2020-05-29 2021-07-20 江苏大学 一种一次喷丸可实现双面加工装置
CN112589118B (zh) * 2020-10-30 2023-07-14 北京航天控制仪器研究所 一种基于弹丸撞击的激光选区熔化成形钛合金阀体零件内腔清理方法
CN114941066B (zh) * 2022-05-27 2023-06-02 南京航空航天大学 一种液氮冷却的超声喷丸加工装置及方法
CN115011771A (zh) * 2022-06-10 2022-09-06 中国航发北京航空材料研究院 一种涡轮轴螺栓孔弹丸式超声冲击强化装置及其强化方法

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Also Published As

Publication number Publication date
US20090095042A1 (en) 2009-04-16
DE102004059592A1 (de) 2006-05-04
DE102004059592B4 (de) 2014-09-04
US7644599B2 (en) 2010-01-12
WO2006061004A2 (fr) 2006-06-15
WO2006061004A3 (fr) 2006-08-03
CA2589964C (fr) 2013-08-06
CA2589964A1 (fr) 2006-06-15

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