US20080183325A1 - Process for producing holes - Google Patents

Process for producing holes Download PDF

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Publication number
US20080183325A1
US20080183325A1 US12/040,384 US4038408A US2008183325A1 US 20080183325 A1 US20080183325 A1 US 20080183325A1 US 4038408 A US4038408 A US 4038408A US 2008183325 A1 US2008183325 A1 US 2008183325A1
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US
United States
Prior art keywords
component
geometry
process according
model
developing
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.)
Abandoned
Application number
US12/040,384
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English (en)
Inventor
Josef Kriegmair
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
Original Assignee
Individual
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=37457627&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=US20080183325(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Individual filed Critical Individual
Publication of US20080183325A1 publication Critical patent/US20080183325A1/en
Assigned to MTU AERO ENGINES GMBH reassignment MTU AERO ENGINES GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KRIEGMAIR, JOSEF
Priority to US14/632,626 priority Critical patent/US10265804B2/en
Abandoned legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/36—Removing material
    • B23K26/38—Removing material by boring or cutting
    • B23K26/382—Removing material by boring or cutting by boring
    • B23K26/388—Trepanning, i.e. boring by moving the beam spot about an axis
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/36—Removing material
    • B23K26/38—Removing material by boring or cutting
    • B23K26/382—Removing material by boring or cutting by boring
    • B23K26/384—Removing material by boring or cutting by boring of specially shaped holes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/36—Removing material
    • B23K26/38—Removing material by boring or cutting
    • B23K26/382—Removing material by boring or cutting by boring
    • B23K26/389—Removing material by boring or cutting by boring of fluid openings, e.g. nozzles, jets
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/18—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
    • G05B19/402—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control arrangements for positioning, e.g. centring a tool relative to a hole in the workpiece, additional detection means to correct position
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/18—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
    • G05B19/4097—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by using design data to control NC machines, e.g. CAD/CAM
    • G05B19/4099—Surface or curve machining, making 3D objects, e.g. desktop manufacturing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
    • B23P2700/06—Cooling passages of turbine components, e.g. unblocking or preventing blocking of cooling passages of turbine components
    • 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
    • Y10T408/00—Cutting by use of rotating axially moving tool
    • Y10T408/03—Processes
    • 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
    • Y10T408/00—Cutting by use of rotating axially moving tool
    • Y10T408/08—Cutting by use of rotating axially moving tool with means to regulate operation by use of templet, tape, card, or other replaceable information supply

Definitions

  • the present technology relates generally to a process for producing holes in a component, in particular in a turbo engine, where each hole extends from a first surface at the exterior of the component to a second surface at the interior of the component. Furthermore, a production arrangement for carrying out the process is specified.
  • EP 1 246 711 131 describes, for example, such a process for producing an aperture, formed as a hole for cool air, in a metallic component of a gas turbine, where in that component the aperture comprises, at least in certain portions, a funnel which is formed so as to be non-cylindrical, extends from a first surface to a second surface of the component, and is formed with a laser beam.
  • Cool air holes have a close spacing, in the case of new types of components go into the component at different angles, and, in part, closely follow the wall geometry. Tolerances of the outer geometry, e.g. in blade profiles, and of the inner geometry, e.g. in cavities or cores, as well as the inconsistency between them make process-stable production difficult. Furthermore, process-stable production is made difficult because the tolerances of the outer surface cause shifting, twisting, or tilting of the component, which has an effect on the position and shape of the cool air holes.
  • the holes are produced on the basis of the nominal geometry.
  • the tolerances which are entailed in the clamping process are eliminated in part by measuring the component, which is usually done with tactile sensing devices. In so doing, the tolerances of the outer and inner geometries, such as cavities and cores, have previously not been taken into consideration.
  • one aspect of the presently described technology is to improve the process stated in the background.
  • a process is provided in which one avoids inadequately formed funnel geometries at the outer surface, incompletely drilled holes, misalignment of the exit apertures of the holes, drilling through the walls of the inner geometry, and the merging of holes due to the component tolerances, which are very large in comparison to the dimensions of the cool air holes.
  • FIG. 1 is a perspective representation of a turbine blade of a gas turbine with apertures formed as cool air holes.
  • FIG. 2 is a first extract from a component of the present technology in a schematic cross-sectional view.
  • FIG. 3 is a second extract of a component of the present technology in a schematic cross-sectional view.
  • a process for producing holes in a component, in particular of turbo engines, where each hole extends from a first surface at the exterior of the component to a second surface at the interior of the component comprises the following steps:
  • a 3-D model can be a surface model or a volume model.
  • a 3-D model can be developed via computer tomography (CT) but other processes are also conceivable. If the precision of the CT for the outer geometry is inadequate, then it is generated via an optical measurement process. CT and data from the optical process are linked to the 3-D model. In so doing, it is also sufficient to transfer into the 3-D model only the extracts which are necessary for producing holes in the individual component and its orientation (for example, 6-point nest).
  • each hole is adapted to the actual geometry within defined limits, where these limits can be the tolerances, (position, diameter, length of the cylinder, depth of the funnel, width of the funnel, length of the funnel, angle of the funnel) by shifting the pattern of holes or the individual hole or group of holes, tilting the hole, displacing the hole, adapting the diameter, shifting the diffuser in the axis of the hole, tilting the diffuser with axis of the hole, or adapting the angle of the diffuser.
  • tolerances position, diameter, length of the cylinder, depth of the funnel, width of the funnel, length of the funnel, angle of the funnel
  • the production programs are generated with traversing motions, removal volumes, and process parameters (feed rate, power, etc.) for the drilling processes for each individual hole of the respective component. These parameters can be ensured by testing. This makes possible the options that storing the production programs for each individual component can be dispensed with or that only storing of the transformation matrices and the process parameters per component is necessary.
  • the deviation in position of each individual component in the clamping device is advantageously corrected numerically.
  • the variation in the clamping process in so far as necessary, can also be determined via a measurement and corrected numerically.
  • the component is defined in the machine producing the holes, except for the uncertainty of the measurement, which with the correct choice of the means of measurement and the process parameters is negligible.
  • a production arrangement for producing holes in a component, in particular of turbo engines, e.g. a hole-producing system, where each hole extends from a first surface at the exterior of the component to a second surface at the interior of the component, is characterized by the fact that the arrangement comprises a central computer unit which is connected to a device for developing a 3-D model of the actual geometry of the component. Furthermore, the production arrangement comprises devices for automatically adapting the hole on the basis of the actual geometry of the component and devices for automatically generating production programs for each individual hole. With this arrangement, the process of the present technology can be carried out.
  • the central computer unit is connected to a device for automatically correcting the deviation of the component's position in the clamping device.
  • an advantageous extension of the production arrangement according to the present technology is characterized by the fact that an automatic drilling tool is connected to the computer unit.
  • the drilling tool can be provided for cutting, for electrochemical removal, or for erosion.
  • FIGS. 1-3 The figures are schematic representations and serve to explain the present technology. The same and similar components are represented by the same reference numbers. The specifications of directions relate to the turbo engine, unless otherwise specified.
  • FIG. 1 shows, in perspective representation and as a component, a turbine blade 1 of a gas turbine, such as, for example, an aircraft engine, in which numerous apertures 2 formed as cool air holes have been formed according to the process according to the present technology.
  • the cool air holes 2 run in general through the component wall 3 at an acute angle, which usually lies in the range of 12° to 35° with respect to the outer surface 4 of the component 1 and, for example, is 30°. From a cavity in the turbine blade 1 air from the compressor is conducted through the cool air holes 2 in order to conduct a film of cool air over the outer surface 4 of the turbine blade 1 .
  • the turbine blade 1 consists of a metal, such as, for example, an Ni-based or Co-based alloy, but can also consist of a ceramic material and another heat-resistant material, and for the production of cool air holes 2 is clamped in a processing machine in which it can be traversed or turned along several axes.
  • the relative motion between a drilling tool with which the forming of the cool air holes 2 is done and the component 1 to be processed is in general produced by moving the component 1 . Likewise, this can be achieved, in general, by a more limited motion of the drilling tool or a superimposed motion.
  • FIG. 2 shows an extract from component 1 in a schematic cross-sectional view.
  • the actual geometry of the outer surface 7 is represented with a thin line width and the nominal geometry of the outer surface with a thick line width.
  • the actual basis for the production 8 and the nominal basis for the production 6 are defined.
  • an inner surface 9 is represented, which in the present embodiment example bounds a cooling duct reaching through to the rotor.
  • nominal basis or actual basis 8 either a hole 11 on the actual basis or a hole 10 on the nominal basis, with corresponding hole axes 13 , 12 , is generated.
  • By the choice of the actual basis drilling through the rear wall of the inner surface 9 is avoided.
  • FIG. 3 shows a second extract from component 1 in a schematic cross-sectional view, said component corresponding in essence to the component represented in FIG. 2 .
  • the component in FIG. 3 comprises a second hole 16 , 17 , which comprises either a hole axis 15 based on the actual basis or a hole axis 14 based on the nominal basis.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Mechanical Engineering (AREA)
  • Plasma & Fusion (AREA)
  • Manufacturing & Machinery (AREA)
  • Human Computer Interaction (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
  • General Engineering & Computer Science (AREA)
US12/040,384 2005-09-06 2008-02-29 Process for producing holes Abandoned US20080183325A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US14/632,626 US10265804B2 (en) 2005-09-06 2015-02-26 Process and system for producing holes in turbine and other components

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102005042270.5 2005-09-06
DE102005042270.5A DE102005042270B4 (de) 2005-09-06 2005-09-06 Verfahren zum Fertigen von Bohrungen und Fertigungsanordnung hierfür
PCT/DE2006/001497 WO2007028355A1 (fr) 2005-09-06 2006-08-26 Procede de production d'alesages

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2006/001497 Continuation WO2007028355A1 (fr) 2005-09-06 2006-08-26 Procede de production d'alesages

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US14/632,626 Continuation US10265804B2 (en) 2005-09-06 2015-02-26 Process and system for producing holes in turbine and other components

Publications (1)

Publication Number Publication Date
US20080183325A1 true US20080183325A1 (en) 2008-07-31

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ID=37457627

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US12/040,384 Abandoned US20080183325A1 (en) 2005-09-06 2008-02-29 Process for producing holes
US14/632,626 Expired - Fee Related US10265804B2 (en) 2005-09-06 2015-02-26 Process and system for producing holes in turbine and other components

Family Applications After (1)

Application Number Title Priority Date Filing Date
US14/632,626 Expired - Fee Related US10265804B2 (en) 2005-09-06 2015-02-26 Process and system for producing holes in turbine and other components

Country Status (5)

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US (2) US20080183325A1 (fr)
EP (1) EP1924391B2 (fr)
DE (2) DE102005042270B4 (fr)
PL (1) PL1924391T5 (fr)
WO (1) WO2007028355A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102248306A (zh) * 2011-04-02 2011-11-23 周明 一种激光钻孔高温合金材料燃气轮机叶片的装备和工艺方法
US9611824B2 (en) * 2015-02-18 2017-04-04 Caterpillar Inc. Process for manufacturing an injector body
CN109158776A (zh) * 2018-11-14 2019-01-08 中国航发动力股份有限公司 一种高压涡轮导向叶片气膜孔激光加工方法
US10500678B2 (en) 2016-10-06 2019-12-10 Xiamen University Method for producing drilled cooling holes in a gas turbine engine component
FR3097786A1 (fr) * 2019-06-27 2021-01-01 Safran Procede de percage d'une aube de turbomachine en fonction de la geometrie interne de l'aube et aube associee
US20230193772A1 (en) * 2021-12-21 2023-06-22 Raytheon Technologies Corporation Fabrication of cooling holes using laser machining and ultrasonic machining
US20230212949A1 (en) * 2021-10-22 2023-07-06 Raytheon Technologies Corporation Gas turbine engine article with cooling holes for mitigating recession

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DE102008016026A1 (de) 2008-03-28 2009-10-01 Mtu Aero Engines Gmbh Verfahren und Vorrichtung zum Vermessen wenigstens einer Bohrung in zumindest einer ersten Oberfläche eines Bauteils
CN106500637A (zh) * 2016-10-11 2017-03-15 中国航空工业集团公司北京航空精密机械研究所 一种对发动机叶片测量装置进行校准的装置
CN106500640A (zh) * 2016-10-11 2017-03-15 中国航空工业集团公司北京航空精密机械研究所 一种对发动机叶片测量装置进行校准的方法
DE102017208106A1 (de) * 2017-05-15 2018-11-15 Siemens Aktiengesellschaft Verfahren und Vorrichtung zur zumindest abschnittsweisen, bevorzugt vollständigen Bestimmung der äußeren und inneren Geometrie eines Bauteils mit wenigstens einem Hohlraum
US11407067B2 (en) * 2018-06-29 2022-08-09 Pratt & Whitney Canada Corp. Method for repairing a part
EP3664242B1 (fr) 2018-12-03 2022-10-26 Siemens Aktiengesellschaft Planification de fonctionnement prédictive dans un micro-réseau à échange de performance entre le micro-réseau et un réseau électrique principal
CN113634873B (zh) * 2021-08-31 2023-07-07 西安交通大学 基于干涉测量的激光加工后壁组合防护方法及系统

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US6744010B1 (en) * 1991-08-22 2004-06-01 United Technologies Corporation Laser drilled holes for film cooling
US5848115A (en) * 1997-05-02 1998-12-08 General Electric Company Computed tomography metrology
US6661930B1 (en) * 2000-04-25 2003-12-09 General Electric Company Method for nesting a computer model of a part with a computer model of a fixture
US6380512B1 (en) * 2001-10-09 2002-04-30 Chromalloy Gas Turbine Corporation Method for removing coating material from a cooling hole of a gas turbine engine component
US6723951B1 (en) * 2003-06-04 2004-04-20 Siemens Westinghouse Power Corporation Method for reestablishing holes in a component
US20060229759A1 (en) * 2003-08-04 2006-10-12 Alstom Technology Ltd Parametric production of drilled cooling holes
US7329832B2 (en) * 2003-08-27 2008-02-12 Alstom Technology Ltd. Automated adaptive machining of obstructed passages
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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102248306A (zh) * 2011-04-02 2011-11-23 周明 一种激光钻孔高温合金材料燃气轮机叶片的装备和工艺方法
US9611824B2 (en) * 2015-02-18 2017-04-04 Caterpillar Inc. Process for manufacturing an injector body
US10500678B2 (en) 2016-10-06 2019-12-10 Xiamen University Method for producing drilled cooling holes in a gas turbine engine component
CN109158776A (zh) * 2018-11-14 2019-01-08 中国航发动力股份有限公司 一种高压涡轮导向叶片气膜孔激光加工方法
FR3097786A1 (fr) * 2019-06-27 2021-01-01 Safran Procede de percage d'une aube de turbomachine en fonction de la geometrie interne de l'aube et aube associee
US20230212949A1 (en) * 2021-10-22 2023-07-06 Raytheon Technologies Corporation Gas turbine engine article with cooling holes for mitigating recession
US11959396B2 (en) * 2021-10-22 2024-04-16 Rtx Corporation Gas turbine engine article with cooling holes for mitigating recession
US20230193772A1 (en) * 2021-12-21 2023-06-22 Raytheon Technologies Corporation Fabrication of cooling holes using laser machining and ultrasonic machining

Also Published As

Publication number Publication date
EP1924391B1 (fr) 2009-12-30
EP1924391A1 (fr) 2008-05-28
US20160074969A1 (en) 2016-03-17
PL1924391T5 (pl) 2018-02-28
DE502006005802D1 (de) 2010-02-11
EP1924391B2 (fr) 2017-05-31
DE102005042270A1 (de) 2007-03-08
US10265804B2 (en) 2019-04-23
DE102005042270B4 (de) 2015-11-19
PL1924391T3 (pl) 2010-06-30
WO2007028355A1 (fr) 2007-03-15

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