Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
  • F23M5/00—Casings; Linings; Walls
  • F23M5/08—Cooling thereof; Tube walls
  • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
• • 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
  • F23R3/002—Wall structures
• • 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
  • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
  • F23R3/60—Support structures; Attaching or mounting means
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
  • F23M2900/00—Special features of, or arrangements for combustion chambers
  • F23M2900/05004—Special materials for walls or lining
• • 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

Definitions

• the invention relates to a heat shield element, in particular for lining a combustion chamber wall with integrated cooling air ducts according to the preamble of claim 1.
• Impact cooling of the wall to be cooled but this is not an optimum with regard to the cooling air consumption nor to the achievable effect. Impact cooling essentially acts locally and the cooling of the hot gas acted parts takes place only on the back.
• WO 2006/064038 proposes the AI before a heat shield element, which includes within its wall cooling air channels on ⁇ . This allows a nearly optimal cooling of the heat shield element with low cooling air consumption. The cooling takes place in the cooling channels and causes a Tempe ⁇ raturverring réelle in the wall of the heat shield element to be cooled itself.
• the edge region of the heat shield element can be insufficiently cooled by the inner cooling air ducts.
• the object of the invention is to provide a heat shield element of the type mentioned that allows the same to minimize the consumption of cooling air in an advantageous cooling and at the same time as simple and kos ⁇ -effectively to manufacture and to assemble. Furthermore, it is an object of the invention to provide a method for
• the generic heat shield element is intended for use in a combustion chamber, which is in particular the combustion chamber in a gas turbine.
• the heat shield element initially comprises a wall which has a hot side which can be acted upon by a hot medium and a cold side which is opposite to the hot side.
• Surrounding the wall is an edge, which differs from the
• Hot side over which extends beyond the plane of the cold side.
• a fastening device which extends from the wall away from the hot side and out past the cold side.
• the fastening device has a passage opening, so that a fastening means can be attached to the fastening device when passed through the passage opening.
• cooling air inlets are arranged in the cooling air ducts, where ⁇ be arranged at cooling air outlets from the cooling air ducts in the region of the edge.
• ERS te cooling air outlets on the outside of the rim angeord ⁇ net, so that there is an exit of the cooling air into the gap between adjacent heat shield elements.
• the coolant flows through all parts of the heat ⁇ shield element in the order fastener, wall, edge and thus cools in all areas before the cooling air is discharged at the edge in the gap between two heat shield elements in the combustion chamber and blocks advantageous against the gap Induction of hot gas from the combustion chamber.
• third cooling air outlets are arranged on the hot side of the wall in the region of the edge, so that an outlet of the cooling air takes place immediately adjacent to the gap into the combustion chamber. This allows for additional film cooling of the heat shield element.
• the hot side of the heat shield element can thus be kept homogeneously at a constant temperature, since a protective de boundary layer between the hot combustion chamber gases and the heat shield element is formed.
• cooling air inlets are provided on an outer side of the fastening device.
• the fastening device is arranged centrally on the wall of the heat shield element ⁇ and is therefore the ideal place for the supply of cooling air into the cooling air ducts.
• second cooling air outlets are provided on the inside of the fastening device.
• the cooling function can be extended to the fastening means of the heat shield element.
• internally cooled mounting screws are used for the attachment of heat shield elements.
• fourth cooling air outlets are provided on the hot side in the region of its mountings ⁇ constriction device. This allows additional film cooling of the heat shield element in the region of the fastening, so that a protective boundary layer is formed between the hot combustion chamber gases and the fastening means.
• the second cooling air outlets and / or the fourth cooling air outlets are supplied by the cooling air ducts leading to the edge or if further cooling air ducts lead from the fastening device to the second and / or fourth cooling air outlets. It is advantageous if the through-opening its mountings ⁇ constriction device has a bearing surface for a screw head, so that the screw is sunk ⁇ zeschildelement in the installed state in the hit, so that it is not subjected to exponier ⁇ th position with hot gas.
• the heat shield member is substantially metal ⁇ lisch, ie it consists essentially of a metal or a metal alloy, such as high temperature resistant alloy coins ⁇ stanchions on iron, chromium, nickel or cobalt base. Compared to ceramics metals have a lower brittleness ⁇ as a more favorable thermal and thermal conductivity.
• the heat shield element is used as protection and for cooling a hot gas leading combustion chamber, preferably an annular combustor of a gas turbine comprising a support structure attached to the heat shield elements are such ⁇ introduced.
• the heat shield element is preferably provided with a loading attachment means, such as a screw, arranged on the supporting structure ⁇ .
• a loading attachment means such as a screw
• a metallic material with a suitable local distribution in powder form is remelted in layers on a substrate by means of laser radiation, so that in solidification of the molten powder in each case forms a further solid layer.
• a three-dimensional CAD model is created in a first step, which is decomposed into a two- ⁇ th step in layers.
• the actual manufacturing of the heat shield element is in the following Schrit ⁇ th, whereby a layer of powder is applied to a Un ⁇ terlage in the third step, the fourth step, the applied powder is irradiated by a laser or remelted and in the fifth step, the base to the layer thickness is lowered from the second step.
• Schrit ⁇ th whereby a layer of powder is applied to a Un ⁇ terlage in the third step, the fourth step, the applied powder is irradiated by a laser or remelted and in the fifth step, the base to the layer thickness is lowered from the second step.
• Steps are repeated until the heat shield element is completely made.
• heat shield elements with comparatively small numbers of pieces are to be produced sensibly using this method. Also quickly to the needs reacts ⁇ the so system downtimes are reduced servicing.
• FIG. 1 shows a half section through a gas turbine with combustion chambers
• FIG. 2 shows a heat shield element according to the prior art
• Figure 3 shows an embodiment of an inventive
• Figure 4 shows an embodiment with an extension of
• FIG. 3 shows an embodiment of an inventive
• Figure 7 shows a section of the combustion chamber with film-cooled
• FIG. 1 shows a gas turbine 21, which is shown partly in longitudinal section.
• the gas turbine 21 has a compressor, an annular combustion chamber (20) with a plurality of burners for a liquid or gaseous fuel, a turbine for driving the compressor and a generator not shown in FIG.
• the combustion chamber wall is lined with heat shield elements 1, or the heat shield elements 1 are attached to a support structure 22 on the combustion chamber wall.
• air is sucked in from the environment.
• the compressor the air compressed and thereby partially heated.
• a small portion of the air is removed from the compressor and supplied as a coolant to the heat shield elements 1, the greater part of the air is supplied to the burners for combustion.
• the combustion chamber 20 the greater part of the air from the compressor is combined with the liquid or gaseous fuel and burnt. This creates a hot gas that drives the gas turbine 21.
• a relaxation and Ab ⁇ cooling of the hot gas In the turbine, a relaxation and Ab ⁇ cooling of the hot gas.
• FIG. 2 schematically shows a heat shield element 30 according to the prior art.
• the heat shield element 30 has a wall 2, which 2 has a hot side 3 (in FIG. 2 on the opposite side) which can be acted upon by a hot medium and a cold side 4 opposite the hot side 3, as well as an encircling wall bordering the wall 2, extending over the wall Furthermore, an attachment device 8, which extends substantially perpendicularly away from the wall 2, is arranged substantially in the middle of the cold side 4 of the wall 2, at the level of the cold side 4.
• the heat shield element 30 is fixed by the fixing device 8 through a screw or bolt to the support structure 22nd
• FIG. 3 a first exemplary embodiment of a heat shield element 1 according to the first embodiment of the invention is schematically shown, are arranged in the wall 2 to the edge 5 cooling channels 9 in which, starting from its mountings ⁇ constriction device. 8
• cooling air entries 10 on one
• FIG. 5 shows dung an exemplary embodiment of a heat shield element 1 according to the second embodiment of the inventions, which third cooling air outlets 15 are provided on the hot side 3 in the region of the edge. 5
• the hot side of the Hitzeschildele ⁇ ment 1 is kept homogeneous at a constant temperature.
• a protective boundary layer forms between the hot combustion chamber gases and the heat shield element 1.
• the arrangement of the third cooling air openings 15 in the region of the edge 5 also protects the gap between adjacent heat shield elements 1 before a hot gas intake.
• FIG. 6 shows a further exemplary embodiment of a heat shield element 1 according to the invention. This is initially designed analogously to the example from FIG. 3 and has a cooling air channel 9 extending from the fastening device 8 via the wall 2 to the edge 5. For this purpose, within the heat shield element in alternation with the
• Cooling air ducts 9 further cooling air ducts 29 are arranged, wel ⁇ che also extending starting from the outside of the fastening ⁇ generating device 8 to the wall 2 extend. There, the further cooling air channels 29 open into fourth cooling air outlets 25, which are arranged near the fastening device 8 on the hot side 3 of the wall 2.
• Figures 2 to 6 show the attachment device 8, 8 extends from the wall 2 of the heat shielding member 1 via the cold side 4 addition, and has a substantially perpendicular ⁇ rights oriented to the wall 2 through opening 16, which is adapted 16 to 16 a fastener 17 can accommodate. Furthermore, in FIGS. 3 to 6, it can be seen that bar, that the passage opening 16 has a contact surface 18 for a screw head 19.
• FIG. 7 shows a section of a combustion chamber with heat shield elements 1 according to the invention.
• the hot side 3 with the third cooling air outlets 15 for film cooling and the fastening of the heat shield elements 1 by fastening means 17, for example, can be seen

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

Priority Applications (2)

Applications Claiming Priority (2)

Publications (1)

Family

ID=54293259

Family Applications (1)

Country Status (4)

Cited By (3)

Families Citing this family (10)

Citations (6)

Family Cites Families (9)

• 2014
  • 2014-10-20 DE DE102014221225.1A patent/DE102014221225A1/de not_active Ceased
• 2015
  • 2015-10-13 WO PCT/EP2015/073661 patent/WO2016062581A1/de active Application Filing
  • 2015-10-13 EP EP15778966.0A patent/EP3183497B1/de active Active
  • 2015-10-13 CN CN201580056784.2A patent/CN107076414B/zh active Active

Patent Citations (6)

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