EP2012965A1 - Gas turbine component and method for machining gas turbine components during production or reconditioning of said gas turbine components - Google Patents
Gas turbine component and method for machining gas turbine components during production or reconditioning of said gas turbine componentsInfo
- Publication number
- EP2012965A1 EP2012965A1 EP07721962A EP07721962A EP2012965A1 EP 2012965 A1 EP2012965 A1 EP 2012965A1 EP 07721962 A EP07721962 A EP 07721962A EP 07721962 A EP07721962 A EP 07721962A EP 2012965 A1 EP2012965 A1 EP 2012965A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- cavity
- plastic material
- processing step
- laser
- 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- Withdrawn
Links
Classifications
-
- 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
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
-
- 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
- B23K26/18—Working by laser beam, e.g. welding, cutting or boring using absorbing layers on the workpiece, e.g. for marking or protecting purposes
-
- 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
-
- 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
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
-
- 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
- F01D5/005—Repairing methods or devices
-
- 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
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- 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
-
- 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
- F05D2230/10—Manufacture by removing material
- F05D2230/13—Manufacture by removing material using lasers
-
- 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
- F05D2300/40—Organic materials
- F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- 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
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49318—Repairing or disassembling
-
- 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
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
Definitions
- Gas turbine component and method for processing gas turbine components in the production or repair of these gas turbine components are known.
- the invention relates to a gas turbine component and to a method for processing gas turbine components in the context of the manufacture or repair of these gas turbine components.
- Gas turbine components which have an inner cavity-referred to below as the first inner cavity-are already known.
- An example of such a design is a blade, such as a blade or blade of a gas turbine or an aircraft engine, which is provided for cooling purposes with an addressed first inner cavity.
- a first inner cavity which may also be formed as a channel or arrangement of a plurality of cooperating channels or as a chamber or chamber system and / or one or more undercuts (or undercuts), may in this case with holes or slots in combination stand, so that the overall arrangement of the inner cavity and the holes or slots allows air to flow through the blade.
- Such blades are also referred to as internally cooled or internally air cooled blades.
- a plurality of processing steps are typically carried out in each case.
- one of the processing steps carried out during the production is a "pouring" in the blade, the first inner cavity being formed as part of this casting process.
- the first inner cavity can also be formed in other ways. Holes or cooling holes or slots or cooling slots are usually introduced after the formation of an addressed first cavity. This may be such that cooling holes are introduced by means of a mechanical machining method, such as drilling, which extend from the outer surface of the blade to the first cavity. Another possibility is to introduce such holes or slots by means of a laser. While a mechanical drilling of such cooling holes can be ensured in a relatively simple manner,
- the area of action on which this laser arc is acted upon or the area of action of the laser is thus not only in the area of the laser bore but also on the wall section of the boundary wall of the first cavity opposite the laser bore. It would be desirable, however, that impairments or changes in this opposite wall section could be avoided or reduced.
- This problem can also occur, for example, in the coating of gas turbine components - be it within the scope of the manufacturing process or as part of a repair. If, for example, an internally air-cooled blade is at least partially stripped and then coated again during repair work, there is a risk that the cooling air holes may become clogged or their cross-sectional areas at least reduced during this coating.
- an area of the component or of the blade is acted upon, in which a corresponding action is undesirable.
- the invention is based on the object, a method for processing, in particular internal or internal air cooled, gas turbine components, which processing takes place in the production or repair of these gas turbine components to create, with the risk of undesirable or damaging effects in the context of Processing steps on the gas turbine component is reduced or even avoided.
- a method for processing, in particular internal or internal air-cooled, gas turbine components in the production or repair of these gas turbine components is proposed in which initially provided with at least a first inner cavity component is provided and then at least a first processing step on this Component is performed.
- plastic material is introduced into the first cavity before the at least one first processing step is carried out. This plastic material is removed after the first processing steps or from the first cavity again.
- the gas turbine component to be machined does not need to be a finished gas turbine component or a partially finished or serviceable gas turbine component, preferably a gas turbine blade, and more preferably internally cooled or gas turbine scoop.
- the gas turbine blade may be configured, for example, as a vane or blade of a turbine or a compressor of an aircraft engine.
- the plastic material is injected in an advantageous design or applied in a liquid or viscous state.
- a particularly expedient design is provided that the plastic material is injected or the first cavity is sprayed with plastic material, particularly preferably completely.
- the first cavity may be, for example, an opening or opening extending into the interior of the gas turbine component or a channel or an arrangement of a plurality of interacting channels or a chamber or a chamber system, or may be formed by the same.
- the first cavity may also be a bore, in particular laser bore or cooling (air) bore, be.
- the first cavity forms a kind of channel from which laser holes or cooling holes extend to the outer surface of these gas turbine blades in the finished state of the gas turbine blade.
- Such a channel formed as the first cavity may, for example, extend oblong; For example, it may be curved or meandering or otherwise.
- the first cavity may, for example, have one or more undercuts or undercuts or undercuts.
- the first cavity has been produced in the context of a G facultyreaes.
- the first cavity or first channel has in an advantageous embodiment at its one end to an outwardly open opening or main opening and is substantially closed at its other end.
- the or a first processing step is carried out by means of a laser.
- This first processing step may be, for example, laser drilling. With such a laser drilling through holes or cooling holes can be introduced into the gas turbine component or the blade. Such cooling holes can be introduced so that connect the addressed first cavity or first channel with the outer surface of the blade.
- the addressed plastic material may therefore be previously introduced into the first cavity or channel so that it is at least (also) positioned in the first cavity so that it in imaginary extension of the laser holes or cooling holes to be produced is positioned so that it shields the opposite wall portion of the channel or first cavity.
- the plastic material is in a particularly preferred embodiment, a substantially residue-free removable plastic material.
- the plastic material is polystyrene.
- an induction coil or induction mat is placed around the blade and the blade or the cavity or the blade channels are hereby heated, and preferably simultaneously flooded with oxygen or atmospheric oxygen.
- the heating can be carried out, for example, at a temperature which is in the range between 400 ° C and 800 ° C, preferably in the range of 400 ° C to 600 0 C, and is more preferably at about 500 0 C.
- the above-mentioned temperature values are especially suitable when the plastic material is polystyrene.
- the polystyrene burns or evaporates essentially without residue. It can further be provided that the blade is then cooled or rapidly cooled.
- the rapid cooling can be carried out, for example, with additional air or additional water, in particular air or water, which is or to the copper jaws or to the holding device whose material preferably has a good thermal conductivity is performed.
- This may, for example, be such as to allow the blades to be relatively quickly cooled down so that they can be gripped by hand, thereby reducing throughput times in the gas turbine blade manufacturing process.
- holes or openings are introduced in such a way that they connect the outer surface of the blade with the cavity addressed.
- Such holes or openings may, for example, be arranged at the end of the cavity facing away from the mentioned main opening.
- first and second processing step have been chosen in particular for the identification or distinctness of the processing steps, wherein the second processing step takes place after the first processing step in an advantageous design, provided preferred developments have both of these processing steps. Before the first or between the first and the second processing step but also one or more further processing steps can be performed.
- the gas turbine component or the blade is preferably made of a metallic or metal-containing material and / or of a material which cobalt and / or nickel - in particular as a base material or as a matrix material - and is optionally coated or provided with a coating and / or is alitiert;
- Other materials, and in particular materials which are proposed in the prior art for gas turbine components, in particular gas turbine blades, can be used as material for the gas turbine component or the blade.
- a device for carrying out the method or for processing, in particular in the context of production or maintenance of the gas turbine component, in particular a blade, for example, a device may be used which is designed as follows and for which the applicant reserves the right to protection combined or integrated mold, comprising: a laser, a holding device for holding the gas turbine component, which is designed in particular in the manner mentioned above, a spray device for spraying plastic material, in particular for spraying polystyrene, a heater for removing the plastic material, in particular as an induction coil or induction mat or, if appropriate, one or more of the following devices: an electronic control device for controlling the method for processing the gas turbine component, a device for stripping the gas turbine component, ie e is optionally the laser, a measuring device for measuring or checking of the processing results generated by the method or for measuring one or more characteristics of the gas turbine component. It may be further provided that an oxygen or Heilbuchzu arrangementseiiiutter is provided, which is optionally combined in the manner mentioned above with the holding device.
- FIG. 1 and FIG. 2 shows an exemplary gas turbine blade according to the invention in schematic representation, wherein FIG. 1 shows a flow profile in FIG. 1 Shovel shown coarsely schematically and with reference to this Fig. An exemplary erfmdungswashes method is explained.
- a blade 1 of a gas turbine or an aircraft engine is shown.
- This blade 1 is designed here as a blade, as a turbine blade.
- such a blade may also be designed as a guide vane of a gas turbine or an aircraft engine, or as a guide or moving blade of a compressor of a gas turbine or an aircraft engine.
- the blade 1 has an airfoil 10 and a blade root 12. Furthermore, the blade 1 has a first inner cavity 14 or a first inner chamber or a first inner channel 14, whose wall or boundary in FIGS. 1 and 2 is delimited by the (dashed) lines 14a. This first inner cavity 14 may be provided with undercuts or undercuts or undercuts. The first inner cavity 14 opens in the region of the blade root 12 to the outside.
- the corresponding (main) opening 20 provided there at the area of the blade root 12 is here positioned so that it is located radially inside or in the radially inward-arranged region of the blade 1 in the case of a blade 1 mounted in an aircraft engine with respect to the turbine rotational axis.
- the first inner channel 14 or the first cavity 14 is filled with a residue-free removable plastic material, which is polystyrene here. This may be such that the first cavity 14 is substantially completely filled with the addressed polystyrene.
- the blade 1 shown in FIGS. 1 and 2 further includes a plurality of first openings 16 and a plurality of second openings 18.
- the openings 16, 18 extend from the outer surface 21 of the blade 1 to the first inner cavity 14, in the region of the airfoil 10.
- the first openings 16 are here as holes, namely laser holes, designed, and may also be referred to as cooling holes become.
- the second openings 18 are designed here slit-shaped, but may alternatively be (laser) holes or the like.
- the first inner cavity 14 is further connected to the blade outer via a main opening 20 of the first inner cavity 14, which, as already mentioned, is arranged here in the region of the blade root 12.
- the first inner cavity 14 is therefore connected to the exterior of the blade 1 only via the main opening 20 and, with respect to its cross-section, relatively smaller openings 16, 18 arranged in the region of the airfoil.
- the thus formed channel arrangement or cavity arrangement is used in the operation of the cooling or air cooling.
- Relatively cold air can be introduced into the blade 1 via the main opening 20 in relation to the ambient temperature of the blade 1, which then exits via the openings 16, 18.
- the "relatively" cold air may, for example, be in the range of 700 ° C., which is relatively low compared to the temperatures caused by the combustion gases of an aircraft engine in the area adjoining the combustion chamber.
- An inventive method can proceed in an exemplary embodiment as follows.
- a blade 1 provided with a first inner cavity 14 is provided.
- This blade 1 can be, for example, as illustrated in FIGS. 1 and 2 or explained with reference to this figure, although initially the openings 16, 18 are not provided.
- second openings 18 are created, which connect the outside of the blade 1 with the first inner cavity 14, as can also be clearly seen in FIG. 2, where the flow profile or a section through the airfoil 10 is shown is.
- the openings 18 can be positioned in the region of the outlet edge 24 of the blade 1, namely in particular there on the pressure side 26.
- the openings 18 may also have a different shape than the shape prescribed here.
- polystyrene 22 is injected into the hollow chamber 14 or the hollow chamber 14 is sprayed with polystyrene 22, which can be done via the second openings 18 and / or via the main opening 20. Depending on whether it takes place via the main opening 20 or the second openings 18, it is ensured by the respective other openings 20, 18 that no compressed air cushion is built up, which could prevent complete infestation of the chamber 14 with polystyrene 22.
- the first holes or cooling holes 16 are now generated by means of a laser.
- the holes 16 can therefore also be referred to as laser holes.
- These cooling holes 16 are arranged in the design according to FIGS. 1 and 2 in the region of the leading edge 28 of the blade 1. Characterized in that the first inner cavity 14 is filled with polystyrene 22, is prevented when laser drilling the opposite in the extension of these resulting holes 16 wall portion, the component of the first cavity 14 bounding wall 14a, by the laser radiation in an undesirable manner is impaired.
- This is schematically indicated in FIG. 2 for one of the holes 16, where denoted by the reference numeral 30 is a laser head, denoted by the reference numeral 32 laser radiation, and by the reference numeral 34 an addressed opposite wall portion.
- the opposite wall section 34 is shielded by means of the polystyrene 22 and thus prevents the laser radiation 32 from undesirably acting on this opposite wall section 34 or changing the surface or material properties of this wall section 34, in particular remaining permanent.
- the polystyrene 22 is subsequently removed again. This is done so that the polystyrene 22 is heated or heated, thereby burning or evaporating.
- the corresponding heating of the polystyrene 22 may, for example - as shown schematically in Fig. 1 - carried out by means of an induction coil 36.
- copper jaws 38 are provided, in which the blade root 12 is clamped.
- Such copper jaws 38 may have, as roughly indicated schematically in FIG. 1, an oxygen or air pressure supply or supply device 40, which may be connected to the main opening 20.
- an induction mat or another suitable heating device may be provided.
- the coil 36 or mat is placed around the blade and optionally the blade root 12.
- the heating device or induction coil 36 the blade channels or their interior are heated to about 500 ° C and simultaneously flooded via the oxygen or air pressure supply means 40 with oxygen or atmospheric oxygen.
- the polystyrene burns or evaporates essentially without residue. Essentially, this produces only water (H 2 O) and carbon dioxide (CO 2 ).
- rapid cooling takes place via the copper jaws 38 additionally with air or water.
- polystyrene 22 after removing the polystyrene 22 again polystyrene 22 is injected, and this time so that not only the first cavity 14 is sprayed with polystyrene 22, but also or alternatively the openings 16, 18.
- This allows at a subsequent coating process, which can also be referred to as a second processing step, to coat the surface of the blade 1, without thereby coating material penetrates into the openings 16, 18 and changes their cross-sectional area or even leads to blockages in the region of these openings 16, 18.
- the polystyrene 22 After the corresponding coating process by which, for example, a hot-temperature-resistant layer or a corrosion-temperature-resistant layer or the like is formed. is brought, the polystyrene 22 can be removed in the aforementioned manner again.
- the aforementioned second injection with polystyrene 22 can take place via openings 16 and / or 18 and / or via the main opening 20. It should be noted, furthermore, that the removal of polystyrene 22 in the embodiment described above by heating or heating, and inductive takes place. Instead, however, other removal methods may be provided, for example chemical.
- this makes it possible in a simple manner to limit the area of action of tools or the area of action given in the course of processing steps by means of the polystyrene 22 or a corresponding plastic, it being noted that the injection molding of polystyrene fast, clean and inexpensive to carry out. The burning or evaporation of polystyrene is also residue-free, fast, inexpensive and environmentally friendly feasible.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Plasma & Fusion (AREA)
- General Engineering & Computer Science (AREA)
- Laser Beam Processing (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102006010927A DE102006010927A1 (en) | 2006-03-09 | 2006-03-09 | Gas turbine component and method for processing gas turbine components in the production or repair of these gas turbine components |
PCT/DE2007/000361 WO2007101423A1 (en) | 2006-03-09 | 2007-02-27 | Gas turbine component and method for machining gas turbine components during production or reconditioning of said gas turbine components |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2012965A1 true EP2012965A1 (en) | 2009-01-14 |
Family
ID=38190129
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07721962A Withdrawn EP2012965A1 (en) | 2006-03-09 | 2007-02-27 | Gas turbine component and method for machining gas turbine components during production or reconditioning of said gas turbine components |
Country Status (5)
Country | Link |
---|---|
US (1) | US7841084B2 (en) |
EP (1) | EP2012965A1 (en) |
CA (1) | CA2644094A1 (en) |
DE (1) | DE102006010927A1 (en) |
WO (1) | WO2007101423A1 (en) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2002035072A2 (en) * | 2000-09-05 | 2002-05-02 | Sudarshan Paul Dev | Nested core gas turbine engine |
US20070267109A1 (en) * | 2006-05-17 | 2007-11-22 | General Electric Company | High pressure turbine airfoil recovery device and method of heat treatment |
DE102009015401A1 (en) * | 2009-03-27 | 2010-09-30 | Mtu Aero Engines Gmbh | Covering device for a workpiece to be machined by means of a laser |
US8091229B2 (en) * | 2011-03-08 | 2012-01-10 | General Electric Company | Method of repairing a subsurface void or damage for a wind turbine blade |
CH707657A1 (en) * | 2013-02-21 | 2014-08-29 | Waterjet Robotics Ag C O Matthias Straubhaar | A process for drilling at least one hole in a workpiece by means of a machining beam from liquid. |
DE102013211047B4 (en) * | 2013-06-13 | 2015-04-30 | MTU Aero Engines AG | Method for closing cooling air holes |
CN103464964A (en) * | 2013-09-26 | 2013-12-25 | 常熟市淼泉压缩机配件有限公司 | Repair process of screw rod compressor rotor |
US10668654B2 (en) | 2015-01-30 | 2020-06-02 | Raytheon Technologies Corporation | Method for disposing a blocking material |
US10919116B2 (en) | 2018-06-14 | 2021-02-16 | Raytheon Technologies Corporation | Installation of laser vent holes into vertical walls of cavity-back airfoils |
US10828718B2 (en) * | 2018-06-14 | 2020-11-10 | Raytheon Technologies Corporation | Installation of waterjet vent holes into vertical walls of cavity-back airfoils |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4873414A (en) * | 1988-06-13 | 1989-10-10 | Rolls Royce Inc. | Laser drilling of components |
US5140127A (en) * | 1989-09-20 | 1992-08-18 | Rolls-Royce Plc | Laser barrier material |
JPH07279611A (en) * | 1994-04-07 | 1995-10-27 | Ishikawajima Harima Heavy Ind Co Ltd | Processing method for cooling hole of turbine blade |
US5800695A (en) * | 1996-10-16 | 1998-09-01 | Chromalloy Gas Turbine Corporation | Plating turbine engine components |
US5902647A (en) * | 1996-12-03 | 1999-05-11 | General Electric Company | Method for protecting passage holes in a metal-based substrate from becoming obstructed, and related compositions |
EP0851098A3 (en) | 1996-12-23 | 2000-09-13 | General Electric Company | A method for improving the cooling effectiveness of film cooling holes |
US5914060A (en) * | 1998-09-29 | 1999-06-22 | United Technologies Corporation | Method of laser drilling an airfoil |
US6544460B2 (en) * | 1998-11-20 | 2003-04-08 | United Technologies Corporation | Method and fixture for disposing filler material in an article |
US6251315B1 (en) * | 1998-11-20 | 2001-06-26 | United Technologies Corporation | Method for disposing a laser blocking material on the interior of an airfoil |
GB0128442D0 (en) * | 2001-11-28 | 2002-01-16 | Alstom Switzerland Ltd | Improved method of manufacture for turbine rotor drums |
US6709230B2 (en) * | 2002-05-31 | 2004-03-23 | Siemens Westinghouse Power Corporation | Ceramic matrix composite gas turbine vane |
US20040167270A1 (en) * | 2003-02-25 | 2004-08-26 | Dane Chang | Fugitive pattern for casting |
-
2006
- 2006-03-09 DE DE102006010927A patent/DE102006010927A1/en not_active Withdrawn
-
2007
- 2007-02-27 EP EP07721962A patent/EP2012965A1/en not_active Withdrawn
- 2007-02-27 WO PCT/DE2007/000361 patent/WO2007101423A1/en active Application Filing
- 2007-02-27 CA CA002644094A patent/CA2644094A1/en not_active Abandoned
-
2008
- 2008-08-22 US US12/196,626 patent/US7841084B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2007101423A1 * |
Also Published As
Publication number | Publication date |
---|---|
DE102006010927A1 (en) | 2007-09-13 |
US20090274550A1 (en) | 2009-11-05 |
US7841084B2 (en) | 2010-11-30 |
CA2644094A1 (en) | 2007-09-13 |
WO2007101423A1 (en) | 2007-09-13 |
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