EP1809435A1

EP1809435A1 - Method for electrolytic machining a workpiece having a through hole.

Info

Publication number: EP1809435A1
Application number: EP05786982A
Authority: EP
Inventors: Rene Jabado; Uwe Kaden; Ursus KRÜGER; Michael Rindler; Jan Steinbach; Peter Tiemann
Original assignee: Kortvelyessy Daniel; Reiche Ralph; Siemens AG
Current assignee: Kortvelyessy Daniel; Reiche Ralph; Siemens AG
Priority date: 2004-11-09
Filing date: 2005-09-16
Publication date: 2007-07-25
Also published as: WO2006051019A1; US20090208344A1; EP1655092A1

Abstract

In prior art, electrolytic methods are used for processing large exterior surfaces. According to the inventive method, through holes (7, 7', 7'', 7''', 7'''', 7''''') of a wall (4) are treated on the inside, one respective pole electrode (19, 19', 19'', 19''') being assigned to each through hole (7, 7', 7'', 7''') that is to be processed.

Description

Process for the electrolytic machining of a component and a component with through-hole

The invention relates to a method for internal machining of a through hole of a component according to the preamble of claim 1 and a component with through hole according to the preamble of claim 14.

Through holes of components sometimes need to be reworked because they do not have the desired geometry. This may be the case with a newly manufactured component, if the diameter has been too large, then material must be applied in the through hole.

It may likewise be that the through hole is oxidized or corroded due to the operation of the component and the oxidation or corrosion products must be removed, whereby the geometry changes, ie the cross section or the diameter of the through hole is increased.

It is reworked for a renewed use of the component, whereby the desired geometry has to be set again (EP 1 160 352 A1).

DE 198 32 767 A1 describes a method for cleaning a component, wherein the cleaning liquid flows through the through holes.

DE 34 03 402 discloses the electrochemical machining of a workpiece on the outer surface, wherein the electrolyte attacks the surface.

US 5,865,977 describes a method for determining the flow of an electrolyte through a channel. CH 397 900, DE 44 28 207 A1, US Pat. No. 6,234,752 B1, US Pat. No. 6,303,193 B1 and US 2003/0173213 A1 disclose methods for the electrolytic machining of a workpiece.

It is therefore an object of the invention to provide a method that allows the internal processing of a through hole.

The object is achieved by a method according to claim 1.

A further object of the invention is to show a component which can be used despite deviating geometry of a through-hole from a desired geometry.

The object is achieved by a component according to claim 14.

In the subclaims further advantageous measures are listed.

These measures can arbitrarily with each other in an advantageous manner

Way combined.

Show it

FIGS. 1 to 5 devices for carrying out the method according to the invention,

FIG. 6, 7 process substeps of the method according to the invention, FIG. 8 shows a schematic course of the temporal

Changing a flow rate, FIG. 9 shows a turbine blade,

10, 11 a combustion chamber and 12 a gas turbine. FIG. 1 shows a component 1 that, for example, has a cavity 3, at least one outer wall 4, 4 ^f with at least two through holes 7, 1 'in at least one outer wall 4, 4' and an inner 24 and an outer 25 surface ,

The component 1 can be, for example, a hollow (for example turbine blade 120, 130, FIG. 9) or plate-shaped component 1 (for example heat shield element 155, FIGS.

The through-holes 7, 7 'have a cross-section which is, for example, round and which has to be machined because, for example, it is too large for the application and therefore has to be tapered. Other geometries can also be processed by the method according to the invention.

A rejuvenation of the through holes 7, 7 'takes place by an electrolytic coating of the through holes 7, 7' on the respective inner surfaces 8, 8 '.

In particular, an electrolyte 28 flows through the passage holes 7, 7 ', for example in the direction of the arrow 10 (for example, from the inside to the outside, ie out of the cavity 3), to material on the inner surfaces 8, 8' of the through holes 7, 7 ' apply electrolytically.

The temporal progress of the inner coating of one, several or all of the through-holes 7, 7 'can be monitored, for example, by determining the flow (volume or mass per time) of the electrolyte 28 through the through-hole 7.

The progress of the inner coating can be monitored continuously (for example online) or discontinuously. The monitoring can also be done only for a through hole 7, 7 '. For different geometries of the Through holes 7, 1 'it is recommended to monitor several through holes I ₁ 1'.

As a result of the material being applied to the inside 8, 8 'of the through-hole 7, 1' in the internal coating, the cross section of the through-hole 7, 7 'tapers and the flow rate of the electrolyte 28 per time t decreases.

It is determined based on previous calibration measurements, when the desired desired geometry of the through hole 7, 7 'is reached.

For determining the progress of the inner coating, any method of determining the flow rate of a medium through a through hole 7, 7 'may be used.

For flow rate measurements, in particular the various principles of pressure difference (pitot tube according to Bernoulli, flow measurement according to the differential pressure method or Venturi tube with membrane), the variable area flowmeter, the inductive flow measurement or the ultrasonic flowmeter can be used.

When material is applied in the through holes 7, 7 ', the composition or concentration of the electrolyte 28 that has passed through it changes (eg, the concentration of the coating material that decreases or the concentration of an element being removed increases), for example, capacitive or is detected inductively or by other types of concentration measurement.

For the electrolysis, the component 1 is, for example, a Gegenpolelektrode and is connected via electrical leads 16 with a current / voltage source 22 with another pole electrode 19, 19 ', which have the same polarity. The

Component 1 is a cathode in the coating process and in Decoating an anode. Accordingly, the pole electrodes 19, 19 'are anode or cathode.

Component 1 and pole electrodes 19, 19 'are arranged, for example, together in an electrolyte 28 (FIG. 2), so that an electrical circuit closes.

By way of example, the flow through the through-hole 7, 7 'can be determined on the basis of the determination of the current drop by means of calibration curves.

The electrolyte 28 may then, for example, caused by a propeller drive (not shown) through the through holes 7, 7 'to flow. In this case, the through holes 7, 7 'are arranged in the electrolyte 28.

In the case of a hollow component 1, the electrolyte 28 is pumped, for example, into the cavity 3, in the case of a turbine blade 120, 130, for example, down through the blade root 183, so that it exits through the through-holes 7, 7 'again. In this case, the through holes 7, 7 'may be arranged in the (FIG. 2) or outside (FIG. 3) of the electrolyte 28.

The through-holes 7, 7 'do not necessarily have to be present in the same electrolyte bath 28 as the component 1 and pole electrode 19.

The electrolyte 28 'for the internal coating of the through-holes 7, 7' can in fact also be supplied separately (FIG. 3), for example through the cavity 3 or from the outside through the through-holes 7, 7 '.

In the separate supply, for example, a different electrolyte 28 'can be used, as the electrolyte 28, in which the pole electrode 19, 19' and the component 1 are arranged. For example, the electrolytes 28, 28 'may be different in their composition and / or concentration of the material for the coating.

The through holes I ₁ 1 'can be arranged outside the electrolyte 28 (FIG. 3) or arranged in the electrolyte 28 (not shown).

As the material for the inner coating, for example, one or more metallic elements (Al, Pt, Cr) or alloys (MCrAlX) or ceramic materials (Al ₂ O ₃ ) may be used.

FIG. 4 shows an enlarged view of FIG. 1.

The component 1 has, for example, at least two through-holes 7, 7 ', which can be processed simultaneously for coating or stripping.

Each through-hole 7, 7 'is separately associated with, for example, a specially shaped pole electrode 19, 19', which is arranged either in the vicinity of the through-holes 7, 7 'or even in the through-holes 7, 7' (shown in dashed lines). Thus, for example, it is achieved that only or mainly the through-hole 7, 7 'is internally coated or stripped.

Different pole electrodes 19, 19 'are required, for example, if the through-holes 7, 7' already have a different geometry during the new production or if originally identical through-holes 7, 7 'are degraded differently during operation during reprocessing.

Since each through-hole 7, 7 'is assigned or can be assigned a separate pole electrode 19, 19', the potentials between the pole electrodes 19, 19 'and the wall 4 of the component 1 also decrease or decrease differently when the Distance of the pole electrodes 19, 19 'to the through holes 7, 7' is different, since the cross section of the Durch¬ holes 7, 7 'is different.

A separate monitoring or separate control of the pole electrodes 19, 19 'is particularly important in the inner coating of the through holes 7, 7'.

The separate control of the pole electrodes 19, 19 'can be applied not only in the coating process, but also in the decoating process.

In a stripping process, the distance di, d ₂ between projections 20, 20 'of the pole electrodes 19, 19' and the wall 4 becomes larger. If this distance becomes too large, the process stops automatically because the potential becomes too small. Since the distances di, d2 of the through holes 7, 7 'are different, the process stops individually in each through hole 7, 7' at different times.

Optionally, the separate pole electrodes 19, 19 'are electrically isolated from each other by an electrical insulation 49, but mechanically connected, so that the handling is simplified as a single tool 18.

In particular, the pole electrodes 19, 19 'are made of metal or carbon.

FIG. 5 shows a plurality of through holes 7, 7 ', 7 ", 1"', 7 "" with their pole electrodes 19, 19 ', 19 ", 19'".

The wall 4 may have a plurality of through-holes 7, 7 ', 7'',7''', 1 '''', 7 '''', all of which (not shown) or, as here, for example, only partially processed ( 7, 7 ', 7 ", 7'"). For example, a part of the through-holes 7, 1 ', 7 ", 7''' have a certain geometry and are processed together in one process.

The remaining through holes 1 '''', 1 '' are not processed '''or in a subsequent, separate electrolytic process step treated in the example, each through hole 1'''', η ^rr' '', in turn, a separate pole electrode 19 "", 19 '"" (not shown) can be assigned.

FIG. 6 shows a further variant of the method according to the invention.

Here, in a first step, at least one

Through hole 7 (Fig. 6a through hole 7 in the intermediate step still present as a blind hole 43, through hole 7 Fig. 6b), 6c)), for example, by means of a laser 37 and its laser beams 40 produced (Figure 6a).

In a further or the method step of Figure 6a replacing step for producing the Durchgangs¬ hole 7, an EDM electrode 46 is used in a Erodierverfahren, wherein the EDM electrode 46, the contour, in particular a more complex shape (diffuser 47) of the through hole 7 (Fig. 6b)).

This EDM electrode 46 can in turn be used as a pole electrode 19 in the subsequent electrolytic coating process (FIG. 6 c)). FIG. 7 shows a through-channel 7 which has projections 52 which locally constrict the flow. This is not desirable.

By applying high voltage pulses, in particular the local projections 52 can be removed during the stripping process, since here the distance between the pole electrode 19 and the projection 52 is small. This results in a uniform profile of the cross section of the passage hole 7, which is then coated or stripped off.

Optionally, masks for the surfaces 24, 25 may be used, so that only the through hole 7 is beschich¬ tet.

Optionally, only the inner surfaces 8 and the inner surface 24 of the component 1 can be coated. In this case, for example, aluminum is used for Innenalitierung.

In addition, the outer surface 25 of the component 1 could be coated with, if, for example, the outer surface should be aluminized.

Furthermore, only the inner surfaces 8 of the through holes 7 and the outer surface 25 of the component 1 may be coated, e.g. an MCrAlX layer on the outer surface 25 is needed.

FIG. 8 shows by way of example a schematic course of the temporal change of the flow rate through a through-hole 7 during a coating process.

When material is applied to the inner surfaces 8 of the through-hole 7 in the inner coating of the through-hole 7, thus, the cross section of the through-hole 7 tapers and the flow rate V / t decreases with time, as illustrated by the solid-line curve 31. The curve 31 can be determined continuously or discontinuously by measuring individual values 34.

In both cases, the measurement can be monitored online, i. the values are transmitted to a computer, which terminates the process when the predetermined value for the flow rate corresponding to a desired geometry of the through-hole 7 is reached.

The curve 31 is only schematic and may be of a different nature (e.g., linear).

FIG. 9 shows a perspective view of a blade 120, 130 as an exemplary component 1 with a through hole 7, which is processed according to the invention.

The blade 120 may be a blade 120 or stator 130 of a turbomachine that extends along a longitudinal axis 121. The turbomachine may be a gas turbine of an aircraft or of a power plant for generating electricity, a steam turbine or a compressor.

The blade 120, 130 has, along the longitudinal axis 121, a mounting area 400 adjacent to one another, a blade platform 403 adjacent thereto and an airfoil 406. As a guide blade 130, the blade can have an additional platform at its blade tip 415 (not shown).

In the mounting region 400, a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown). The blade root 183 is designed, for example, as a hammer head. Other designs as Christmas tree or Schwal¬ benschwanzfuß are possible.

The blade 120, 130 has a leading edge 409 and a discharge edge 412 for a medium that flows past the blade 406.

In conventional blades 120, 130, in all areas 400, 403, 406 of the blade 120, 130, for example, massive metallic materials are used.

The blade 120, 130 can hereby be produced by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.

Workpieces with a monocrystalline structure or structures wer¬ used as components for machines that are exposed ho¬ hen mechanical, thermal and / or chemical stress. The production of such monocrystalline workpieces er¬ follows, for example, by directed solidification from the melt. These are casting methods in which the liquid metallic alloy solidifies into a monocrystalline structure, ie a single-crystal workpiece, or directionally. In this case, dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, ie grains which extend over the entire length of the workpiece and here, for general Sprach¬ use, referred to as directionally solidified) or a monocrystalline structure, ie The entire workpiece is made of a single crystal. In these processes, one must avoid the transition to globulitic (polycrystalline) solidification, since undirected growth necessarily results in transverse and longitudinal grain boundaries which negate the good properties of the directionally solidified or monocrystalline component. If the term generally refers to directionally solidified structures, it means both single crystals that have no grain boundaries or at most small-angle grain boundaries, and stem crystal structures that have grain boundaries that are probably in the longitudinal direction but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified structures.

Such methods are known from US Pat. No. 6,024,792 and EP 0 892 090 A1.

Refurbishment means that components 120, 130 may need to be stripped of protective layers after use (e.g., by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. This is followed by a re-coating of the component 120, 130 and a renewed use of the component 120, 130.

The blade 120, 130 is hollow.

If the blade 120, 130 to be cooled, and still has film cooling holes 7 (through hole 7), which can be post-processed by the method according to the invention. As a protection against corrosion, the blade 120, 130 spielsweise corresponding mostly metallic coatings and as protection against heat usually still a ceramic coating.

FIG. 10 shows a combustion chamber 110 of a gas turbine 100. The combustion chamber 110 is designed, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 102 arranged around the turbine shaft 103 in the circumferential direction open into a common combustion chamber space. For this purpose, the combustion chamber 110 in its entirety as ringför- configured structure which is positioned around the turbine shaft 103 around.

To achieve a comparatively high efficiency, the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C. In order to allow a comparatively long service life for these operating parameters, which are unfavorable for the materials, the combustion chamber wall 153 is provided on its side facing the working medium M with an inner lining formed from heat shield elements 155. Each heat shield element 155 is equipped on the working medium side with a particularly heat-resistant protective layer or made of highly heat-resistant material. Due to the high temperatures inside the combustion chamber 110, a cooling system is additionally provided for the heat shield elements 155 or for their holding elements.

A heat shield element 155 as an example of a component 1 (through hole 7) has, for example, holes (not shown) through which a fuel or fuel / gas mixture flows and which can be processed by means of the method according to the invention.

The materials of the combustion chamber wall and its coatings may be similar to the turbine blades.

FIG. 11 shows a heat shield arrangement 160, in which heat shield elements 155 are arranged on a supporting structure 163, one beside the other.

Usually, for example, for lining a larger hot gas space, such as e.g. a combustion chamber 110, a plurality of rows of heat shield elements 155 disposed adjacent to each other on the support structure 163.

The heat shield assembly 160 may, for example, the

Combustion chamber 110 and / or a transition region between Combustion chamber 110 and turbine blade 112 of a gas turbine 100 to prevent damage to the support structure 163 during operation of the gas turbine 100.

In order to reduce the thermal loads, it is provided, for example, to cool the heat shield elements 155 in each case on their surface facing away from the combustion chamber 110 by means of cooling air.

At least two adjacent heat shield elements 155a, 155b form a cooling air channel 166 between the support structure 163 and the surface of the heat shield elements 155a, 155b facing away from the hot gas 113. In this way, the two mentioned adjacent heat shield elements 155a, 155b communicate, e.g. via the cooling air flow L flowing directly from one of the neighbors to the other in the common cooling air passage 166 formed by the neighbors.

In the figure 11 four heat shield elements 155 are shown as an example, which form a common cooling air duct 166. However, there is also a significantly larger number of heat shield elements in question, which can also be arranged in several rows.

The cooling air L, which is fed through openings 169 (through holes 7) in the cooling air duct 166, cools the heat shield elements 155 back, for example by means of impingement cooling, the cooling air L practically perpendicular to the hot gas remote from the surface of the heat shield elements 155 and thereby absorb thermal energy can dissipate. The cooling of the heat shield elements 155 can continue to take place by convection cooling, wherein cooling air L thereby sweeps substantially parallel to the surface of the heat shield elements 155 at the rear along and thereby also absorb and dissipate thermal energy. In FIG. 11, the cooling air L as the cooling air flow largely moves from right to left in the cooling air passage 166 formed by the heat shield members 155 and can be supplied to a burner 107 provided in the combustion chamber 110, for example, to be used for combustion become.

In order to prevent leakage of the cooling air L from the cooling air duct 166 directly into the combustion chamber 110 and entry of hot gas from the combustion chamber 110 into the cooling air duct 166, sealing elements 172, for example, are provided between the heat shield elements 155.

For example, FIG. 11 also shows a screwing device 175, for example a countersink for receiving a screw. Advantageously, to anchor the heat shield elements 155 to the support structure 163, a fastening element, for example a screw, is inserted into the screwing device 175 and fastened on the side of the support structure 103, for example by means of a nut.

FIG. 12 shows by way of example a gas turbine 100 in a longitudinal partial section.

The gas turbine 100 has inside a rotatably mounted about a Rotations¬ axis 102 rotor 103, which is also referred to as Turbi¬ nenläufer. Along the rotor 103 successively follow an intake housing 104, a compressor 105, for example, a torus-like

Combustion chamber 110, in particular annular combustion chamber 106, with several coaxially arranged burners 107, a turbine 108 and the exhaust housing 109. The annular combustion chamber 106 communicates with an annular annular hot gas channel 111, for example. Four turbine stages 112 connected in series form the turbine 108. Each turbine stage 112 is formed for example from two Schaufel¬ rings. As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.

The guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example. Coupled to the rotor 103 is a generator or work machine (not shown).

During operation of the gas turbine 100, air 105 is sucked in by the compressor 105 through the intake housing 104 and compressed. The compressed air provided on the turbine-side end of the compressor 105 is fed to the burners 107 and mixed there with a fuel. The mixture is then burned in the combustion chamber 110 to form the working medium 113. From there, the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120. The working medium 113 unwinds on the rotor blades 120 in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and this drives the working machine coupled to it ,

The components exposed to the hot working medium 113 are subject to thermal loads during the operation of the gas turbine 100. The guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the highest thermal load in addition to the heat shield bricks which line the annular combustion chamber 106.

To withstand the prevailing temperatures, they can be cooled by means of a coolant. Likewise, substrates of the components can have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure). Iron, nickel or cobalt-based superalloys are used as material for the components, in particular for the turbine blades 120, 130 and components of the combustion chamber 110. Such superalloys are known, for example, from EP 1 204 776, EP 1 306 454, EP 1 319 729, WO 99/67435 or WO 00/44949; these writings are part of the revelation.

Likewise, blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one member of the group

Iron (Fe), cobalt (Co), nickel (Ni), X is an active element and represents yttrium (Y) and / or silicon and / or at least one element of rare earths) and heat through a thermal barrier coating. The thermal barrier coating is, for example, ZrÜ2, Y2Ü4-Zrθ2, i. it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.

By suitable coating methods, e.g. Electron beam evaporation (EB-PVD) produces stalk-shaped grains in the thermal barrier coating.

The guide blade 130 has a guide blade root facing the inner housing 138 of the turbine 108 (not shown here) and a guide blade foot opposite

Guide vane head on. The vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.

Claims

claims

1. A method for the electrolytic machining of a component

at least two through holes (7, 7 ', 7 ", 7''',η"_"r ηrrrrr) _au f _WE is,

characterized,

in that the through holes (7, 7 ', 7 ", 1''', η,,,, _fl,,,, ) are provided _on their inner surface (8, 8 ^f , 8", 8 '",

8 "", 8 '"") are processed, in particular coated, that for the through holes (7, 7',

7 ", 7 '", 7 "", 7' "") each have a separate

Pol electrode (19, 19 ', 19 ", 19'") having the same polarity is used, that one pole electrode (19, 19 ', 19 ", 19'") another

Form (20, 20 ') as at least one other

Pol electrode (19 ', 19 ", 19'") and that an electrical voltage on the component (1) as Gegenpolelektrode and the at least two

Pole electrodes (19, 19 ', 19 ", 19'") is applied, is pulsed.

2. The method according to claim 1, characterized in that

an electrolyte (28, 28 ^Λ ) flows through the at least two through-holes (7, 7 ', 7 ", 7'", 7 "", 7 '""), in particular from the inside outwards out of a cavity (3), thus the through holes (7, 7 ^f , 7 ", 7 '", 7 "", 7'"") on their inner surface (8, 8 ^f , 8 ", 8 '", 8 "", 8 "''') to be edited.

3. The method according to claim 1 or 2, characterized in that

the component (1) with the through holes (7, 7 ^f , 1 '', 7 '", 7"",7'"") represents a Gegenpolelektrode in the electrolytic process.

4. The method according to one or more of the preceding claims, characterized

in that at least one, in particular two or more through-holes (7, 7 ^f , 7 ", 7 '", 7 "", 7'"") are produced by means of an EDM electrode (46), and in that this EDM electrode (46 ) is used as pole electrode (19, 19 ', 19'',19''') for the electrolytic process.

5. The method according to claim 1, 2 or 3, characterized in that

the at least two pole electrodes (19, 19 ', 19 ", 19'") are arranged outside a hollow component (1).

6. The method according to claim 1, characterized in that

the time-dependent flow of the electrolyte (28,

28 ') through at least one through hole (7, 7', 7 ",

7 '", 7" ", 7'" "), by means of which the progress of the inner coating of the at least one through-hole (7, 7 ', 1' ', 1'", 7 "",

7 '"") is determined.

7. The method according to claim 1, characterized

that the component (1) is arranged in an electrolyte (28), and that another electrolyte (28 '), in particular with a different chemical composition or different concentration of a coating material, through which at least two through-holes (7, 7', 7 ", 7 '", 7" ", 7'" ") flows.

8. The method according to claim 1, characterized in that

only the inner surface (8, 8 ', 8 ", 8'", 8 "", 8 '"") is coated.

9. The method according to claim 1, characterized in that

only the inner surface (8, 8 ', 8 ", 8'", 8 "", 8 '"") and an inner surface (24) of the component (1) is coated.

10. The method according to claim 1, characterized in that

only the inner surface (8, 8 ', 8 ", 8'", 8 "", 8 '"") and an outer surface (25) of the component (1) is coated.

11. The method according to claim 1, characterized in that

the inner surface (8, 8 ', 8 ", 8'", 8 "", 8 '""), an outer (25) and an inner (24) surface of the component (1) is coated.

12. component (1) having at least two through holes (7, 7 ^f , 7 ", 7 '", 7 "", 7'"") produced by the method according to claims 1 to 13.

13. Component according to claim 12, characterized

that the newly produced or reworkable component (1) is a turbine component, in particular a turbine blade (120, 130) or heat shield element (155), in particular a gas turbine (100), and in particular that at least one through hole (7, 7 ', 7 " , 7 '", 7" ", 7'" ") is a film cooling hole.