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
  • B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
  • B23P19/04—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
  • B23P19/042—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for assembling or disassembling parts specially adapted for combustion engines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/005—Combined with pressure or heat exchangers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
  • B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
  • B23H9/14—Making holes
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
  • F23R2900/00018—Manufacturing combustion chamber liners or subparts
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
  • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
  • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling

Definitions

• Combustion chamber for a gas turbine as well as tool and method for the production of cooling channels in a gas turbine component
• the invention relates to a combustion chamber for a gas turbine having at least one housing component with a housing wall which is arranged around a hot gas path and comprises a hot gas acted upon by the hot side and a cold side opposite.
• a housing wall of the Ge ⁇ housing component runs a number of cooling channels, each ⁇ Weil's an inside.
• the cooling channels each comprise an inflow region which opens to the cold side and an outflow region which opens into the interior of the combustion chamber.
• the housing component may be, for example, the cylinder jacket-shaped end region of a flame tube of a tube combustion chamber. From the prior art, it is known, this cylinder jacket-shaped end portion with a
• cooling channels since this area is at least partially exposed to high thermal stress.
• These cooling channels can run parallel to the cylinder axis in the housing wall of the end region, so that the entire circumference of the end region can be traversed by cooling channels.
• a generic housing component may be drawn at ⁇ play, to a cylinder jacket-shaped housing component having a cylinder axis and parallel to the cylinder axis ver ⁇ cooling channels running in the housing wall of the component loading.
• the cooling channels can be introduced into the housing wall by means of electrochemical removal processes or spark erosion.
• a cylindrical channel is eroded into the housing wall by means of a cylindrical rod and the ablation method mentioned above.
• the channels can also be introduced in a paral ⁇ lel process step in the housing component by one of the number of cooling channels corresponding Number of such tools is used simultaneously to erode the cooling channels in the housing wall.
• the invention has for its object to provide a combustion chamber for a gas turbine of the type mentioned, a tool and a method for producing the cooling channels of the type mentioned, with which a cooling of the housing component, a reduction of Schadschermissio ⁇ nen the Combustion chamber and low production costs of the housing component is made possible.
• the object is achieved in a combustion chamber of the type mentioned in that
• turbulence generators are angeord ⁇ net in at least one of the cooling channels, which are formed as web-shaped ribs and extend along the inside of the cooling channel and are integrally formed with the housing wall.
• the turbulence generators according to the invention are produced simultaneously with the formation of the cooling channels on the inside of the cooling channels from the solid material of the housing component.
• the ribs of the cooling channel by means of egg ⁇ nes method according to any one of claims 23 or 24 Herge ⁇ provides.
• This allows a design of the housing component with particularly low production costs.
• the production method according to the invention with the tool according to the invention makes it possible to equip the housing component with turbulence generators during manufacture without significant additional costs.
• the tool according to the invention enables the Her ⁇ position of the turbulence generator in the form of ribs extending extend along the inside of the cooling channels and
• the tool according to the invention enables an exact Platzie ⁇ tion and reproducibility of the turbulence generators.
• the web-shaped ribs can run perpendicular to the longitudinal axis of the cooling channel, so that the ribs have two transverse to the flow direction in the cooling channel facing, circular segment-shaped or ring-segment-shaped side surfaces.
• This orientation and shape of the ribs is particularly easy to manufacture.
• a secondary flow is initiated downstream of the turbulence generators whose thickness can be adjusted to increase the heat transfer in a simple manner over the height of the ribs.
• the web ⁇ shaped ribs extend at an angle to the longitudinal axis of the cooling channel along the inside of the cooling duct and having two facing at an angle to the flow direction, essentially circular segment-shaped or ring segment-shaped Be ⁇ ten vom.
• the angle of attack of the rib course may preferably be 10-60 degrees.
• An angle of 45 degrees can be considered advantageous as DERS particular ⁇ .
• Minim ⁇ least a number of ribs are arranged in the cooling duct on the side of the inside of the cooling channel which faces towards the hot side.
• a further advantageous embodiment of the invention can provide that the ribs are arranged on one side in the channel.
• the height of the ribs may be selected such that the ribs block each 5-30% of the cross-sectional area of the cooling channel, preferably 10-15%.
• the specified percentage of obstructed cross sectional area has been found to be particularly effective for increasing the heat transfer, particularly when arranged on one side Rip ⁇ pen.
• a further advantageous embodiment of the invention can provide that the ribs are disposed at both ends and in pairs opposite ⁇ lying in the cooling channel.
• the height of the ribs can be selected such that the opposite ribs obstruct 10-40%, preferably 10-20% of the cross-sectional area of the cooling channel.
• the two-sided arrangement of the ribs amplifies the initiated secondary flows downstream of the turbulence generators, so that an improvement of the heat transfer is effected.
• the percentage of obstructed cross sectional area ofdeka ⁇ Nals has proved to be particularly effective for increasing the heat ⁇ transition, especially at oppositely disposed ⁇ ribs.
• the ribs are arranged on both sides and offset from each other in the cooling channel ⁇ .
• the height of the ribs may be selected such that each 5-30%, preferably 10-15% of
• Cross-sectional area of the cooling channel is blocked by the rib.
• This embodiment of the invention enables a more uniform, initiated by the turbulizer Sekundärströ ⁇ tion along the cooling channel, wherein the percentage of obstructed cross-sectional area of the cooling channel has proven to be particularly effective for increasing the heat transfer, especially in both sides and staggered ribs.
• the distance between the ribs and the next ribs arranged in the longitudinal direction of the cooling channel corresponds to 5-10 times the height of the ribs.
• This embodiment of the invention allows a substantially uniform heat transfer along the cooling channel.
• an inflow region of the cooling channel which amounts to at least 5-10 hydraulic diameters, is formed free of ribs.
• This area of the cooling channel does not have to be like with Turbulenzerzeu ⁇ because the inlet flow still ensures a high heat transfer here in the channel.
• vonei ⁇ Nander spaced cooling channels are arranged over the entire circumference of the housing wall of the housing component, wherein the at least one turbulence generator comprehensive cooling duct extends in the egg ⁇ nem thermally heavily stressed area of the housing wall.
• the cooling channels can also be equipped only in the sections with ribs that extend through areas subject to higher thermal stress.
• Another object of the invention is to provide a rod-shaped tool of the type mentioned for the production of cooling channels in a gas turbine component, so that ei ⁇ ne cooling of the housing component, a reduction of the pollutant emissions of the combustion chamber and low manufacturing costs of the housing component allows ,
• the object is achieved with a tool of the type initially mentioned a ⁇ that the rod-shaped tool at least on the first longitudinal portion having a substantially cylindrical shape with the following recesses:
• At least one first recess having a first cross-section which extends over the entire first length portion
• the tool is used in a method according to one of claims 23 or 24.
• the tool If the tool is driven with an axial direction of movement by means of a removal process in a housing wall, can be removed by a subsequent rotation of the tool by an angle previously not removed in the region of at least one portion of the material areas, said Region of the grooves, no material is removed so that mate rial ⁇ remains in the form of ribs at a distance of the grooves.
• the angle at which the tool is rotated takes place so far that the area not removed by the recess is at least passed through. If the groove depth is greater than the height of the recess, ribs remain in the form of the recess. If the groove depth is less than the height of the recess, annular ribs remain whose height is the
• the rod-shaped tool comprises on the first longitudinal section exactly one recess, which in particular has a circular segment-shaped cross-section.
• the tool can be easily made from a cylindrical rod.
• the tool can be aligned, for example when entering the housing wall with the recess towards the hot side. This allows the arrangement of ribs on the hot side facing thedeka ⁇ nals.
• the grooves extend perpendicular to the longitudinal axis around the circumference of the first length section.
• the groove is interrupted by the recess.
• the groove runs from one edge of the recess running parallel to the longitudinal axis along the convex surface to the other edge of the recess.
• the tool can be arranged on one side in the cooling channel ribs erzeu ⁇ gene having perpendicularly oriented to the flow direction ringseg- ment-shaped side surfaces. If the ribs are to have side surfaces corresponding to the recess cross-section, the groove depth is to be selected correspondingly larger. Furthermore, it can be advantageously provided that the grooves extend at an angle to the longitudinal axis around the circumference of the first longitudinal section.
• ribs can be produced which have side faces pointing obliquely to the flow direction.
• the angle of attack of the ribs is determined by the angle of the grooves to the longitudinal axis of the tool.
• the angle may be 10-60 degrees, preferably 45 degrees.
• This angle of attack is suitable for increasing the heat transfer over a longer cooling channel section in comparison to the ribs or other areas aligned at right angles to the flow direction at angles of attack.
• the groove depth and the circle segment height are selected such that cooling channels produced with the tool have ribs arranged on one side, which obstruct the cross section of the cooling channels by 5-30%, preferably 10-15%.
• the specified percentage of obstructed cross sectional area has been found to be particularly effective for increasing the heat transfer, particularly when arranged on one side Rip ⁇ pen.
• the bar-shaped tool on the first length portion comprises exactly two opposite ⁇ opposite recesses, which in particular in each case have a circle segment-shaped cross section.
• the grooves may extend in both remaining, convexly curved surface areas of the first longitudinal section.
• the grooves may be arranged in pairs opposite or offset from each other.
• the spacing of the grooves in the longitudinal direction of the rod-shaped tool is 5 to 10 times the groove depth or the circle segment height, depending on which of the two sizes is smaller.
• the invention also relates to a tool arrangement for introducing cooling ducts into a gas turbine component, with an annular or ring-segment-shaped support device and a number of rod-shaped tools, which are arranged on the support device such that the tools project with the front end and with the Longitudinal axis are fixed perpendicular to the ring plane of the support device to this.
• the tool assembly according to the invention permits the one ⁇ brin supply of cooling passages in a gas turbine component such that a cooling of the housing component, a reduction in the emissions of the combustion chamber and low manufacturing costs of the housing component are enabled.
• At least one of the rod-shaped tools ent ⁇ speaking any one of claims 12 to 20 is formed and Untitled befes- rotatable about its longitudinal axis on the carrier device.
• the tooling arrangement enables the parallel production of a number of cooling channels.
• the rotatable on the carrier direction attached rod-shaped tools can be driven, for example, using a toothed ring.
• the at least one tool formed according to one of claims 12 to 20 is used in a method according to one of claims 23 or 24.
• the tool arrangement is designed such that the cooling channels can be introduced into the gas turbine component by means of electrochemical removal or spark erosion.
• the invention also relates to a method for introducing cooling channels into a gas turbine component, in particular into the housing wall of a gas turbine component of the combustion chamber according to one of claims 1 to 11.
• the method enables the introduction of cooling channels in a gas turbine component, so that a cooling of the Housing ⁇ se component, a reduction of the pollutant emissions of the combustion chamber and low production costs of the housing component are made possible.
• At least one rod-shaped tool according to one of claims 12 to 20 is moved in the axial direction of the tool in an axial movement by means of a removal process into the gas turbine component, and in a subsequent step the areas between the ribs removed, wherein the portions are removed currency ⁇ rend the tool is rotated around its longitudinal axis by an angle, wherein the tool is pulled out subsequently in an axial direction of movement of the gas turbine component.
• the grooves extend the tool at an angle to the longitudinal axis Anstell ⁇ of the tool, and the tool is rotated in a superimposed motion through an angle and moved simultaneously in the axial direction to remove the areas between the ridges corresponding to the angle of the grooves.
• FIG. 1 shows schematically a gas turbine in longitudinal section according to the prior art
• FIG. 2 shows schematically a tube combustion chamber of a gas turbine in longitudinal section according to the prior art
• FIG. 5 is a cross-sectional view of that shown in FIG. 4.
• FIG. 6 is a further cross-sectional view of the ge ⁇ showed in Fig. 4 the cooling channel
• FIG. 7 shows a plan view of the front end of the tool shown in FIG. 9
• FIG. 8 is a cross-sectional view of that shown in FIG. 9
• FIG 9 schematically illustrates a tool according to the invention for the manufacture ⁇ position of the cooling passage illustrated in Figure 4,
• FIG. 10 shows schematically a cooling channel according to a second
• FIG. 11 is a cross-sectional view of that shown in FIG.
• FIG. 12 shows a further cross-sectional view of the cooling channel shown in FIG. 10, FIG.
• FIG. 13 is a plan view of the front end of the tool
• Figure 14 shown in Fig. 15 is a cross sectional view of the dargestell ⁇ ten in Figure 15 the tool
• FIG 15 schematically illustrates a tool according to the invention for the manufacture ⁇ position of the cooling passage illustrated in Figure 10,
• FIG. 16 shows schematically a cooling channel according to a third
• FIG. 17 shows a cross-sectional view of the cooling channel illustrated in FIG. 16, FIG.
• FIG. 18 shows a further cross-sectional view of the cooling channel shown in FIG. 16;
• FIG. 19 shows a plan view of the front end of the tool shown in FIG. 20 is a cross-sectional view of the dargestell ⁇ ten in Figure 21 the tool,
• FIG. 21 shows schematically a tool according to the invention for producing the cooling channel shown in FIG. 16, FIG.
• FIG. 22 shows schematically a cooling channel according to a fourth
• FIG. 23 is a plan view of the front end of the tool shown in FIG. 25.
• FIG. 23 is a plan view of the front end of the tool shown in FIG. 25.
• FIG. 24 shows a cross-sectional view of the tool illustrated in FIG. 25 and, schematically, a tool according to the invention for the position of the cooling channel shown in FIG. 1 shows a schematic sectional view of a gas turbine 1 ⁇ according to the prior art.
• the gas turbine 1 has inside a rotatably mounted about a rotation axis 2 rotor 3 with a shaft 4, which is also referred to as a turbine runner.
• a turbine runner which is also referred to as a turbine runner.
• the combustion chambers 10 each comprise a burner assembly 11 and a housing 12, which is designed to protect against hot gases is lined with a heat shield 20.
• the combustion system 9 communicates with a beispielswei ⁇ ring hot gas channel.
• a beispielswei ⁇ ring hot gas channel There are several hinterei ⁇ Nander turbine stages form the turbine 14.
• Each Turbi ⁇ nencut is formed of blade rings.
• a row formed of rotor blades 18 follows in the hot runner of a row formed by vanes 17.
• the guide vanes 17 are fastened to an inner housing of a stator 19, whereas the guide vanes Blades 18 are mounted in a row, for example by means of a Turbi ⁇ nenrace on the rotor 3.
• ⁇ is coupled to the rotor 3, a generator, for example (not shown).
• FIG. 2 shows a tube combustion chamber 22 of a gas turbine.
• a burner assembly 26 is arranged ⁇ .
• the main burners each comprise a centrally angeord- in the cylindrical housing of the premixing of the main burner designated burner lance, to which is attached ⁇ arranged in the premixing swirler vanes support (not shown).
• the burner assembly opens into a cylindrically shaped flame tube 28, which includes a first combustion zone 30 ⁇ and a cylindrical flame tube end portion 32, which may be referred to with housing component includes.
• the transfer duct is connected to an outer housing (not shown) at its upstream end with ⁇ means of a retaining bracket 37 attached to the gas turbine.
• the fire tube end portion 32 is a housing component having a
• Housing wall 23 which is arranged around a hot gas path around and a hot gas can be acted upon with hot side 25 and ei ⁇ ne opposite cold side 27 includes.
• the housing wall 23 of the flame tube end portion 32 has a number ofdekanä ⁇ sources.
• FIG 3 shows a greatly simplified schematic Dar ⁇ position of a development of a flame tube 28 (which may be also referred to as Basket) according to the prior art.
• a main flow direction in the combustion chamber is illustrated by the arrow 38 in order to apply the terms upstream and downstream of FIG.
• the area 40 marks the burner outlets of two burners (the burners may also be referred to as main swirlers) of the burner assembly. Downstream of the burner outputs are thereby formed (here schematically represented dirt shaped) widening portions 42 of the flame tube which are thermally more bean ⁇ sprucht (significantly higher wall temperature).
• the cone eng ⁇ increasing the basket wall temperature by the flame th, which affects the flow direction an increasing size of the basket.
• the illustration is a schematic diagram that approximately reproduces the situation in the combustion system.
• the regions 42 extend into the flame ⁇ pipe end portion 32nd Between these areas 42 are areas 50 that are thermally less stressed.
• the flame tube end region 32 can also be provided with housing component 33, which has a housing wall in which cooling channels 44 extend, which extend parallel to the main flow direction 38 and are equally spaced from each other.
• FIG. 4 shows a section of a cooling channel 54 according to a first exemplary embodiment of the invention.
• the cooling channel 54 extends rotationally symmetrically about a longitudinal axis 56 with a cylinder jacket-shaped inner side 58.
• turbulence generators are arranged, which are designed as web-shaped ribs 60.
• the web-shaped ribs 60 extend along the inside 58 of the cooling channel 54 and are integral with the
• Housing wall 23 is formed.
• the ribs 60 are arranged on one side in the cooling channel 54 and have in the longitudinal direction of the cooling channel in each case a distance 62 to the directly neigh ⁇ th ribs. These distances may or may not always be the same amount.
• the distance is 5-10 times the height 64 of the ribs.
• FIGS. 5 and 6 additionally show two cross-sectional views of the cooling channel 54 along the respective cut surfaces.
• the circular cross-section of the cooling channel 54 can be seen with a cross-sectional area 66.
• FIG. 6 shows a cross section through the cooling channel 54 in the region of a fin 60.
• the fin-shaped rib 60 is perpendicular to the longitudinal axis 56 of the cooling channel 54, so that the rib 60 has two transversely oriented to the flow direction in the cooling channel, circular segment-shaped side surfaces 68 on ⁇ has.
• FIG. 9 shows highly schematically the rod-shaped tool 70 according to the invention for the manufacture of the cooling channel 54 shown in Figure 4 in a housing component 33 of a Gasturbi ⁇ ne.
• the tool 70 extends along a longitudinal axis 72 from a front end 74 via a first longitudinal section 76 adjoining the front end up to one the opposite end 71.
• the first length portion 76 extends over the entire length of the tool 70 is shifted to the image of the tool 70 is separate of the cross section 78 of the first longitudinal section in Figure 7 Darge ⁇ represents.
• the circular cross-section 78 is reduced by one Kreisseg ⁇ ment.
• the rod-shaped tool 70 has a substantially cylindrical shape on the first longitudinal section 76 with exactly one first recess 80 extending over the entire first longitudinal section.
• the recess 80 has a circular segment-shaped cross-section 82.
• the rod-shaped tool 70 also comprises a number Nu ⁇ th 84, which extend perpendicular to the longitudinal axis 72.
• the cutout is shown in Figure 8 shows a cross-sectional view of the tool 70 in the region of a groove 84.
• the groove 84 extends in a remaining surface region 86 of the first length portion 76 with a groove depth 88.
• the grooves 84 extend from the one edge of the recess 80 to the another edge of the recess 80.
• FIG. 10 shows a cooling channel 90 in a housing wall 23 according to a second exemplary embodiment of the invention.
• the cooling channel 90 differs from the cooling channel illustrated in FIG. 4 in that the web-shaped ribs 92 are arranged on both sides and in pairs opposite one another in the cooling channel 90.
• the ribs 92 extend transverse to the flow direction ⁇ 94 along the inner side 58 of the cooling channel 90 so that the circular segment-shaped side surfaces 96 are transverse to the direction of flow currents.
• the ribs 92 have a height 64.
• the two ribs 92 block in common, as shown in more detail in Figure 12, the cross-sectional surface 66 to a GeWiS ⁇ sen percentage.
• This percentage may be, for example, 10-40%, preferably 10-20%, of the cross-sectional area of the cooling channel 90 in the pairs oppositely disposed ribs. This percentage has proved to be advantageous for increasing the heat transfer in the cooling channel.
• 15 shows highly schematically the inventive rod-shaped tool 98 for producing the GE in Figure 10 ⁇ showed the cooling channel 90.
• the tool 98 differs from that shown in Figure 9 tool characterized that corresponds long of the first length portion 76 exactly two diligentlie ⁇ extending recesses 100 extend (see also the cross-sectional view in Figure 13).
• the grooves 102 run - as shown in the cross sectional view in Figure 14 in more detail verdeut ⁇ light) in the remaining two convexly curved upper surface portions of the first longitudinal portion 76, with the Nu ⁇ th pairs 102 extend opposite each other.
• FIG. 16 shows a cooling channel 106 in a housing wall 23 according to a third exemplary embodiment of the invention.
• the cooling channel 106 differs from the Darge ⁇ presented in Figure 10 thereby cooling channel, but that the web-like ribs are added on both sides are arranged in the cooling passage 106th On one side are the ribs 108. On the opposite side, the ribs 110. See also the cross-sectional views in Figure 17 and 18 along the cut surfaces XVII and XVIII.
• FIG. 21 shows a highly schematic representation of the rod-shaped tool 112 according to the invention for producing the cooling channel 106 shown in FIG. 16.
• the tool 112 differs from the tool shown in FIG. 15 in that the grooves 114 in the two remaining, convexly curved surface regions 116 the first longitudinal section 76 offset from each other - that is not opposite - are arranged.
• the cross section in the area of the sectional surface XX is shown in FIG. Figure 19 shows a cross section of the work ⁇ zeugs with the two opposite recesses.
• FIG. 22 shows a cooling channel 118 according to a fourth exemplary embodiment of the invention. This differs from the cooling channel shown in FIG. 4 in that an inflow region 120 and an outflow region 122 are formed free of ribs.
• the cooling channel 118 can be connected by means of a gur shown 25, inventive tool 124 are generated.
• the grooves 126 are distributed in a central region of the first length portion 76, so that a cooling channel made with the tool is formed rib-free in the upstream and downstream areas.
• the length of the tools of all illustrated embodiments ent ⁇ speaks here always essentially the length of the cooling channels to be produced with the tool.
• FIGS. 23 and 24 show cross sections of the tool shown in FIG.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Physics & Mathematics (AREA)
• Thermal Sciences (AREA)

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• 2014
  • 2014-09-08 JP JP2016539568A patent/JP2016530448A/ja active Pending
  • 2014-09-08 EP EP14766936.0A patent/EP3044515A1/de not_active Withdrawn
  • 2014-09-08 KR KR1020167005851A patent/KR20160040682A/ko not_active Application Discontinuation
  • 2014-09-08 CN CN201480049684.2A patent/CN105531544A/zh active Pending
  • 2014-09-08 US US14/914,880 patent/US20160199954A1/en not_active Abandoned
  • 2014-09-08 WO PCT/EP2014/069046 patent/WO2015032936A1/de active Application Filing

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