EP3333484A1 - Plate-shaped component of a gas turbine - Google Patents
Plate-shaped component of a gas turbine Download PDFInfo
- Publication number
- EP3333484A1 EP3333484A1 EP17205686.3A EP17205686A EP3333484A1 EP 3333484 A1 EP3333484 A1 EP 3333484A1 EP 17205686 A EP17205686 A EP 17205686A EP 3333484 A1 EP3333484 A1 EP 3333484A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- plate
- shaped component
- cooling air
- edge strip
- base body
- 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.)
- Granted
Links
- 238000001816 cooling Methods 0.000 claims description 66
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 description 9
- 239000000654 additive Substances 0.000 description 8
- 230000000996 additive effect Effects 0.000 description 8
- 238000002485 combustion reaction Methods 0.000 description 8
- 230000035882 stress Effects 0.000 description 8
- 230000007704 transition Effects 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 230000002349 favourable effect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000010276 construction Methods 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 230000008021 deposition Effects 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
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- 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
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- 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
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
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- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
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- 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
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- 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
- F23R2900/03041—Effusion cooled combustion chamber walls or domes
Definitions
- the invention relates to a plate-shaped component of a gas turbine according to the features of the preamble of claim 1.
- the invention also relates to a gas turbine with a plate-shaped component.
- the invention relates to a plate-shaped component, which is formed, for example, in the form of a combustion chamber shingle.
- the plate-shaped component has a base body on which at least one edge region is provided.
- This edge region is designed in the form of a peripheral strip, which extends substantially to the surface of the main body.
- the edge strip has a thickness which differs from the thickness of the base body.
- the edge strip is formed with a greater thickness than the main body itself.
- Such a plate-shaped component in the form of a combustion chamber shingle is from the WO 2015069466 A1 previously known. Furthermore, on the EP 2 873 921 A1 Referenced.
- Components of the type described are preferably produced by means of an additive manufacturing method, for example by means of a laser deposition welding method or by means of DLD direct laser deposition.
- the respective component is built up from a powder supply layer by layer by melting the powder. This leads to local solidification of the respective molten layer. Thus, complex 3D geometries can be generated.
- the invention has for its object to provide a plate-shaped component, in particular for a gas turbine, in particular in the form of a combustion chamber shingle, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and has favorable material properties.
- an integrally connected with the base body and the skirting support body is arranged between the edge strip and the base body, which has a substantially triangular cross-section and which is provided with a plurality of slot-like recesses.
- the support body according to the invention which is arranged between the base body and the skirt, results in a usually vertical orientation of the body in the additive manufacturing process, an increasing transition from the wall thickness of the body to the skirt or vice versa. Sudden geometric changes, which could lead to residual stresses and cracking, are thus avoided.
- the support body according to the invention has a plurality of slot-like recesses, so that a substantially rib-like shape of the support body results. Overall, this leads with suitable dimensioning to a low accumulation of material at the transition between the body to the skirt. As a result, not only occurring voltage spikes are avoided, but also the possibility of effective cooling is created. This is possible in particular in that at least one cooling air hole is formed in the respective slot-like recess.
- each slot-like recess in each case a body penetrating the cooling air hole is arranged.
- the component according to the invention is particularly suitable when using brittle materials which have high requirements in terms of stress distribution and material strength.
- the invention thus provides a transition between components of different thickness or different volume, which allows the production of the component by means of an additive manufacturing process.
- the individual slot-like recesses can be geometrically designed in a suitable manner. The same applies to the preferred implementation of the cooling air holes. It is understood that the width of the recesses and the respective remaining width of the region of the support body between the recesses can also be adapted to the component geometries, such as the dimensioning and geometry of the cooling air hole. It is also possible to provide a plurality of cooling air holes in a recess.
- the remaining between the recesses strip-shaped areas of the support body lead to a reduction of residual stresses along the longitudinal side of the billet in the additive construction of the shingle.
- the occurrence of residual stresses can thereby be avoided, especially in the case of brittle materials. The risk of cracking is thus significantly reduced.
- the plate-shaped component according to the invention can be optimized with regard to cooling.
- the additive manufacturing process makes it possible to design the cooling holes differently over their length, for example to change the cross section. All this means that a sufficient volume of cooling air can be directed to the rear edge of the base body of the plate-shaped component opposite the edge strip.
- the possibility of making the cooling holes variable in their longitudinal extent, arcuate or coiled or meandering forms of cooling air holes can be realized. This leads to a more effective cooling.
- the plate-shaped component comprises additional cooling air holes, which extend through the edge strip and emanate from the slot-shaped recess.
- the additional cooling air holes are therefore edge air holes, which lead cooling air through the edge strip from the recess to the outside.
- the additional cooling air holes may preferably have a widening cross section in the direction of flow, in particular have a conically widening cross section.
- the additional cooling air holes act as a diffuser.
- Particularly preferred is a smallest cross section of the additional cooling air hole at the entrance to the edge strip or adjacent to Entry into the edge strip, ie in a range of 10% of a total length of the additional cooling air hole through the edge strip, available.
- cooling in the region of the edge strip of the plate-shaped component can be effected exclusively by the slot-shaped recesses or by cooling air holes which are formed in the base body of the plate-shaped component or by additional cooling air holes which are formed in the edge strip of the plate-shaped component or by a combination of the additional cooling air holes through the skirting and the cooling air holes through the body.
- variants can be used with no cooling air hole at the recess, a cooling air hole in the edge strip or the body or two cooling air holes in the skirt and the body.
- the recess is formed symmetrically to the center plane of the cooling air hole. This results in uniform stress distributions in the region of the recess and the adjacent regions of the support body. Furthermore, the supply of cooling air is optimized in the cooling air hole.
- the slot-like recesses of the support body may be formed in a favorable embodiment of the invention so that the walls of the recess adjacent to the surface of the body on both sides initially have a rectilinear course of the wall, which merges into a rounded wall to form an arcuate structure in the upper part of the slot-like recess , It is particularly advantageous if the rounded wall course has a radius which is between 0.1 to 2 times, in particular 1 to 2 times, the width of the recess. In a particularly favorable development, it is provided that the rounded wall profiles form an angle between 45 ° and 120 °. As a result, the spike arc-like contour of the recesses in the side view is realized particularly effective.
- the spacing of adjacent recesses may, in the longitudinal direction of the edge strip, correspond to greater than or equal to half the width of the recesses.
- substantially equidistant recesses and remaining chamfer-like areas of the support body are provided alternately along the edge strip.
- the support body itself which forms a chamfer-like transition between the base body and the edge strip, may have an angle with respect to its surface to the surface of the base body between 30 ° and 60 °. An amount of 45 ° is preferred.
- the central axis of the cooling air hole at right angles or at an obtuse angle to the surface of the body, ie in a range of 90 ° to 180 °, to arrange.
- preferred cooling effects can be achieved, in particular, on regions of the edge strip or of the base body subjected to high thermal stress.
- FIG. 1 shows a perspective view in a partial view of a first embodiment of a plate-shaped component according to the invention, which is designed in the form of a combustion chamber shingles of a gas turbine.
- the plate-shaped component has a main body 1, which is designed as a flat plate.
- the base body 1 has a surface 6, which faces away from a combustion chamber interior of a gas turbine engine.
- the surface 6 is the cold surface of the plate-shaped member (combustion chamber shingles).
- a plurality of effusion cooling holes are formed, as known from the prior art.
- the main body 1 has a thickness d1.
- a skirt 2 which has a thickness d2.
- the thickness d1 is measured from the surface 6 of the main body 1 to the back thereof. In the same direction, the thickness d2 of the skirt 2 is defined.
- the edge strip 2 which is integrally formed by means of an additive method with the base body 1, is supported by a support body 3. This points, as this is from the Fig. 2 results in a substantially triangular cross section. Over the length of the support body it is provided with a plurality of recesses 4. The between the recesses 4 remaining areas of the support body 3 are thus strip-shaped or strip-shaped.
- each recess 4 at least one cooling air hole 5 is provided which extends from the recess 4 to the back of the main body 1, analogous to the Effusionskühllöchern 10th
- the free surface of the support body 3 has to the surface 6 of the base body 1 at an angle ⁇ , which may be between 30 ° and 60 °. A value of 45 ° is preferred.
- the Fig. 3 shows a plan view of the arrangement according to the Fig. 1 and 2 , It can be seen that the recess 4 has a width l3.
- the side walls of the recess 4, which in Fig. 3 are designated as l1 and l2, each have a rectilinear course of the wall 7 and go into a rounded wall 8, the radius of each with r1 and r2 in Fig. 3 is clarified.
- the two rounded wall curves 8 meet at an angle ⁇ . This can be between 45 ° and 120 °.
- the length of the rectilinear wall courses 7 (11 or 12) is preferably the same and ⁇ 0 mm.
- the radii r1 and r2 are also equal and are 0.1 to 2 times the width l3 of the recess 4.
- Both the straight wall profiles 7 with the lengths l1 and l2 and the rounded wall profiles 8 with the radii r1 and r2 are not necessarily necessary for the invention, other wall profiles can be realized to form the recess 4. Both the lengths l1 and l2 and the radii r1 and r2 can deviate from one another at the specified intervals. Also, it is not mandatory that the recess 4 is arranged symmetrically to a median plane of the cooling air hole 5.
- the Fig. 3 shows the positioning of the cooling air hole 6 with its central axis 9.
- the recesses 4 thus form a support structure, which is defined by two rounded or arcuate wall portions, between which the individual cooling air holes 5 are arranged.
- the production of the component according to the invention by an additive method is usually carried out with a vertical orientation of the body 1. If this is provided on all sides with a skirt, a skirt with the thickness d2 is first constructed. The transition to the base body 1 with a thickness d1 is carried out continuously by the respective support body 3, which is provided with the recesses 4.
- the component according to the invention can be provided with a rim 2 at all its edges.
- the plate-shaped base body 1 is not limited to a flat plate, it may also be curved or double-curved.
- Fig. 4 schematically shows a simplified plan view of a slot-like recess according to a second embodiment of the invention.
- the second embodiment essentially corresponds to the first embodiment, wherein in addition in each case an additional cooling air hole 15 is provided.
- the additional cooling air hole 15 extends from the slot-like recess 4 through the edge strip 2 of the plate-like component and opens on the outside of the edge strip.
- a flow cross section of the additional cooling air hole in the edge strip 2 preferably changes Fig. 4 shown, the additional cooling air hole 15 is formed as the diffuser, wherein the narrowest cross section is located at the entrance to the skirt 2.
- the additional cooling air hole 15 is preferably rectilinear.
- the additional cooling air hole 15 may also have a curved course in the flow direction. Due to the additional cooling air hole 15, the edge strip 2 can thus additionally be cooled. The diffuser formation of the additional cooling air hole 15 reduces the speed of the cooling air, whereby a cooling effect can be increased.
- Fig. 5 shows a fifth embodiment of the invention, which, in contrast to the first embodiment, no cooling air holes 5, which are arranged on the slot-like recess 4.
- Fig. 6 shows a fourth embodiment of the invention.
- the fourth embodiment corresponds essentially to the second embodiment, wherein, in contrast to the second embodiment, no cooling air holes 5 are provided by the base body 1, which are arranged at the bottom of the recess 4.
- the slot-shaped recess 4 is cooled only by the additional cooling air holes 15, which extend through the edge strip 2.
- the additional cooling air hole 15 through the skirt 2 is formed as a diffuser as in the second embodiment. It should be noted, however, that other geometric shapes may be provided for the additional cooling air hole 15, for example a constant cross section over the flow length of the additional cooling air hole 15.
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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)
Abstract
Die Erfindung bezieht sich auf ein plattenförmiges Bauteil einer Gasturbine mit einem Grundkörper (1), welcher an zumindest einem Randbereich einstückig mit einer im Wesentlichen rechtwinklig zur Oberfläche des Grundkörpers (1) ausgebildeten Randleiste (2) versehen ist, wobei der Grundkörper (1) eine unterschiedliche Dicke (d1) aufweist, als die Randleiste (2), dadurch gekennzeichnet, dass zwischen der Randleiste (2) und dem Grundkörper (1) ein einstückig mit dem Grundkörper (1) und der Randleiste (2) verbundener, mit einem im Wesentlichen dreieckigen Querschnitt versehener Stützkörper (3) angeordnet ist, welcher mit mehreren schlitzartigen Ausnehmungen (4) versehen ist. The invention relates to a plate-shaped component of a gas turbine having a base body (1) which is integrally provided on at least one edge region with a substantially perpendicular to the surface of the base body (1) formed edge strip (2), wherein the base body (1) a different thickness (d1), as the edge strip (2), characterized in that between the edge strip (2) and the base body (1) integrally connected to the base body (1) and the edge strip (2), with a substantially arranged triangular cross section provided supporting body (3) which is provided with a plurality of slot-like recesses (4).
Description
Die Erfindung bezieht sich auf ein plattenförmiges Bauteil einer Gasturbine gemäß den Merkmalen des Oberbegriffs des Anspruchs 1.The invention relates to a plate-shaped component of a gas turbine according to the features of the preamble of
Die Erfindung bezieht sich auch auf eine Gasturbine mit einem plattenförmigen Bauteil.The invention also relates to a gas turbine with a plate-shaped component.
Im Einzelnen betrifft die Erfindung ein plattenförmiges Bauteil, welches bspw. in Form einer Brennkammerschindel ausgebildet ist. Das plattenförmige Bauteil weist einen Grundkörper auf, an welchem zumindest ein Randbereich vorgesehen ist. Dieser Randbereich ist in Form einer Randleiste ausgebildet, welche sich im Wesentlichen zur Oberfläche des Grundkörpers erstreckt. Weiterhin weist die Randleiste eine Dicke auf, welche sich von der Dicke des Grundkörpers unterscheidet. Üblicherweise ist die Randleiste mit einer größeren Dicke ausgebildet, als der Grundkörper selbst.In detail, the invention relates to a plate-shaped component, which is formed, for example, in the form of a combustion chamber shingle. The plate-shaped component has a base body on which at least one edge region is provided. This edge region is designed in the form of a peripheral strip, which extends substantially to the surface of the main body. Furthermore, the edge strip has a thickness which differs from the thickness of the base body. Usually, the edge strip is formed with a greater thickness than the main body itself.
Ein derartiges plattenförmiges Bauteil in Form einer Brennkammerschindel ist aus der
Bauteile der beschriebenen Art werden bevorzugterweise mittels eines additiven Herstellungsverfahrens hergestellt, bspw. mittels eines Laserauftragsschweißverfahrens oder mittels DLD-direct laser deposition. Dabei wird das jeweilige Bauteil aus einem Pulvervorrat Schicht für Schicht durch Aufschmelzen des Pulvers aufgebaut. Dies führt zur lokalen Verfestigung der jeweiligen aufgeschmolzenen Schicht. Somit können komplexe 3D-Geometrien erzeugt werden.Components of the type described are preferably produced by means of an additive manufacturing method, for example by means of a laser deposition welding method or by means of DLD direct laser deposition. The respective component is built up from a powder supply layer by layer by melting the powder. This leads to local solidification of the respective molten layer. Thus, complex 3D geometries can be generated.
Während des Herstellungsverfahrens können geometrische Veränderungen der Bauteildicke in Abhängigkeit von der Orientierungsrichtung des Bauteils bei der Herstellung schon während des Aufschmelzverfahrens zu Spannungen und Rissen führen. Es können sich in dem Bauteil hohe Eigenspannungen aufbauen, die zu einem Versagen des Bauteils führen können. Zur Vermeidung derartiger starker Übergänge der jeweiligen Bauteildicken oder Bauteilvolumina ist es bekannt, Unterstützungsstrukturen zu nutzen, die zu einem geringeren Gradienten bei der Bauteildickenänderung führen. Derartige Unterstützungsstrukturen führen entweder zu lokalen vergrößerten Volumen-Bereichen der Bauteile oder müssen nachfolgend wieder entfernt werden. Im ersteren Fall erweisen sich die vergrößerten Bauteil-Volumina im Hinblick auf die Kühlung des Bauteils, bspw. einer Brennkammerschindel, als problematisch. Eine nachträgliche Entfernung der Unterstützungsstrukturen ist zum einen fertigungstechnisch aufwendig und stellt zum anderen nicht sicher, dass sich während der Fertigung bereits hohe Eigenspannungen, die zu Rissen führen können, gebildet haben.During the manufacturing process, geometric changes in the component thickness, depending on the direction of orientation of the component in the production during the reflow process already lead to tensions and cracks. It can build high residual stresses in the component, which can lead to failure of the component. To avoid such strong transitions of the respective component thicknesses or component volumes, it is known to use support structures that lead to a lower Gradients in the component thickness change lead. Such support structures either lead to locally increased volume areas of the components or must subsequently be removed again. In the former case, the increased component volumes prove to be problematic with regard to the cooling of the component, for example a combustion chamber shingle. A subsequent removal of the support structures is on the one hand production-technically complicated and, on the other hand, does not ensure that high internal stresses, which can lead to cracks, have already formed during production.
Der Erfindung liegt die Aufgabe zugrunde, ein plattenförmiges Bauteil, insbesondere für eine Gasturbine, insbesondere in Form einer Brennkammerschindel zu schaffen, welches bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit die Nachteile des Standes der Technik vermeidet und über günstige Materialeigenschaften verfügt.The invention has for its object to provide a plate-shaped component, in particular for a gas turbine, in particular in the form of a combustion chamber shingle, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and has favorable material properties.
Erfindungsgemäß wird die Aufgabe durch die Merkmalskombinationen des Anspruchs 1 gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention the object is achieved by the combination of features of
Erfindungsgemäß ist somit vorgesehen, dass zwischen der Randleiste und dem Grundkörper ein einstückig mit dem Grundkörper und der Randleiste verbundener Stützkörper angeordnet ist, welcher einen im Wesentlichen dreieckigen Querschnitt aufweist und welcher mit mehreren schlitzartigen Ausnehmungen versehen ist.According to the invention it is thus provided that an integrally connected with the base body and the skirting support body is arranged between the edge strip and the base body, which has a substantially triangular cross-section and which is provided with a plurality of slot-like recesses.
Durch den erfindungsgemäßen Stützkörper, welcher zwischen dem Grundkörper und der Randleiste angeordnet ist, ergibt sich bei einer üblicherweise vertikalen Ausrichtung des Grundkörpers bei dem additiven Fertigungsverfahren ein zunehmender Übergang von der Wanddicke des Grundkörpers zu der Randleiste oder umgekehrt. Plötzliche geometrische Veränderungen, die zu Eigenspannungen und Rissbildungen führen könnten, werden somit vermieden.By the support body according to the invention, which is arranged between the base body and the skirt, results in a usually vertical orientation of the body in the additive manufacturing process, an increasing transition from the wall thickness of the body to the skirt or vice versa. Sudden geometric changes, which could lead to residual stresses and cracking, are thus avoided.
Weiterhin kommt hinzu, dass der erfindungsgemäße Stützkörper eine Vielzahl von schlitzartigen Ausnehmungen aufweist, sodass sich eine im Wesentlichen rippenartige Form des Stützkörpers ergibt. Insgesamt führt dies bei geeigneter Dimensionierung zu einer geringen Materialanhäufung am Übergang zwischen dem Grundkörper zu der Randleiste. Hierdurch werden nicht nur auftretende Spannungsspitzen vermieden, vielmehr wird auch die Möglichkeit einer effektiven Kühlung geschaffen. Diese ist insbesondere dadurch möglich, dass in der jeweiligen schlitzartigen Ausnehmung zumindest ein Kühlluftloch ausgebildet ist.In addition, the support body according to the invention has a plurality of slot-like recesses, so that a substantially rib-like shape of the support body results. Overall, this leads with suitable dimensioning to a low accumulation of material at the transition between the body to the skirt. As a result, not only occurring voltage spikes are avoided, but also the possibility of effective cooling is created. This is possible in particular in that at least one cooling air hole is formed in the respective slot-like recess.
Vorzugsweise ist in jeder schlitzartigen Ausnehmung jeweils ein den Grundkörper durchdringendes Kühlluftloch angeordnet.Preferably, in each slot-like recess in each case a body penetrating the cooling air hole is arranged.
Das erfindungsgemäße Bauteil eignet sich insbesondere bei der Verwendung von spröden Werkstoffen, welche hinsichtlich der Spannungsverteilung und der Material-Festigkeit hohe Anforderungen haben.The component according to the invention is particularly suitable when using brittle materials which have high requirements in terms of stress distribution and material strength.
Erfindungsgemäß wird somit ein Übergang zwischen Bauteilen mit unterschiedlicher Dicke oder unterschiedlichem Volumen geschaffen, welcher die Herstellung des Bauteils mittels eines additiven Herstellverfahrens ermöglicht. Die einzelnen schlitzartigen Ausnehmungen können in geeigneter Weise geometrisch gestaltet werden. Gleiches gilt für die bevorzugte Implementierung der Kühlluftlöcher. Es versteht sich, dass die Breite der Ausnehmungen sowie die jeweilige verbleibende Breite des Bereichs des Stützkörpers zwischen den Ausnehmungen ebenso den Bauteilgeometrien angepasst werden kann, wie die Dimensionierung und Geometrie des Kühlluftlochs. Es ist auch möglich, mehrere Kühlluftlöcher in einer Ausnehmung vorzusehen.The invention thus provides a transition between components of different thickness or different volume, which allows the production of the component by means of an additive manufacturing process. The individual slot-like recesses can be geometrically designed in a suitable manner. The same applies to the preferred implementation of the cooling air holes. It is understood that the width of the recesses and the respective remaining width of the region of the support body between the recesses can also be adapted to the component geometries, such as the dimensioning and geometry of the cooling air hole. It is also possible to provide a plurality of cooling air holes in a recess.
Die zwischen den Ausnehmungen verbleibenden streifenförmigen Bereiche des Stützkörpers führen zu einer Reduzierung der Eigenspannungen entlang der Schindellängsseite beim additiven Aufbau der Schindel. Wie erwähnt, kann dadurch insbesondere bei spröden Materialien das Auftreten von Eigenspannungen vermieden werden. Die Gefahr der Rissbildung wird somit erheblich reduziert.The remaining between the recesses strip-shaped areas of the support body lead to a reduction of residual stresses along the longitudinal side of the billet in the additive construction of the shingle. As mentioned, the occurrence of residual stresses can thereby be avoided, especially in the case of brittle materials. The risk of cracking is thus significantly reduced.
Da bevorzugt in jeder der schlitzartigen Ausnehmungen zumindest ein Kühlluftloch vorgesehen ist, kann das erfindungsgemäße plattenförmige Bauteil hinsichtlich der Kühlung optimiert werden. Zusätzlich besteht durch das additive Herstellverfahren die Möglichkeit, die Kühllöcher über ihre Länge unterschiedlich zu gestalten, bspw. den Querschnitt zu verändern. All dies führt dazu, dass ein ausreichendes Kühlluftvolumen an die der Randleiste gegenüberliegende Rückseite des Grundkörpers des plattenförmigen Bauteils geleitet werden kann. Durch die Möglichkeit, die Kühllöcher in ihrer Längserstreckung variabel zu gestalten, sind auch bogenförmige oder gewendelte oder geschlängelte Formen von Kühlluftlöchern realisierbar. Dies führt zu einer effektiveren Kühlung.Since at least one cooling air hole is preferably provided in each of the slot-like recesses, the plate-shaped component according to the invention can be optimized with regard to cooling. In addition, the additive manufacturing process makes it possible to design the cooling holes differently over their length, for example to change the cross section. All this means that a sufficient volume of cooling air can be directed to the rear edge of the base body of the plate-shaped component opposite the edge strip. The possibility of making the cooling holes variable in their longitudinal extent, arcuate or coiled or meandering forms of cooling air holes can be realized. This leads to a more effective cooling.
Weiter bevorzugt umfasst das plattenförmige Bauteil zusätzliche Kühlluftlöcher, welche durch die Randleiste verlaufen und von der schlitzförmigen Ausnehmung ausgehen. Die zusätzlichen Kühlluftlöcher sind demnach Randluftlöcher, welche Kühlluft durch die Randleiste aus der Ausnehmung nach außen führen. Die zusätzlichen Kühlluftlöcher können in Durchströmungsrichtung bevorzugt einen sich erweiternden Querschnitt aufweisen, insbesondere einen sich konisch erweiternden Querschnitt aufweisen. Dadurch wirken die zusätzlichen Kühlluftlöcher als Diffusor. Besonders bevorzugt ist dabei ein kleinster Querschnitt des zusätzlichen Kühlluftlochs am Eintritt in die Randleiste oder benachbart zum Eintritt in die Randleiste, d.h. in einem Bereich von 10% einer Gesamtlänge des zusätzlichen Kühlluftlochs durch die Randleiste, vorhanden.More preferably, the plate-shaped component comprises additional cooling air holes, which extend through the edge strip and emanate from the slot-shaped recess. The additional cooling air holes are therefore edge air holes, which lead cooling air through the edge strip from the recess to the outside. The additional cooling air holes may preferably have a widening cross section in the direction of flow, in particular have a conically widening cross section. As a result, the additional cooling air holes act as a diffuser. Particularly preferred is a smallest cross section of the additional cooling air hole at the entrance to the edge strip or adjacent to Entry into the edge strip, ie in a range of 10% of a total length of the additional cooling air hole through the edge strip, available.
Somit kann eine Kühlung im Bereich der Randleiste des plattenförmigen Bauteils ausschließlich durch die schlitzförmigen Ausnehmungen erfolgen oder durch Kühlluftlöcher, welche im Grundkörper des plattenförmigen Bauteils ausgebildet sind oder durch zusätzliche Kühlluftlöcher, welche in der Randleiste des plattenförmigen Bauteils ausgebildet sind oder durch eine Kombination der zusätzlichen Kühlluftlöcher durch die Randleiste und der Kühlluftlöcher durch den Grundkörper. Somit können Varianten mit keinem Kühlluftloch an der Ausnehmung, einem Kühlluftloch in der Randleiste oder dem Grundkörper oder zwei Kühlluftlöcher in der Randleiste und dem Grundkörper verwendet werden.Thus, cooling in the region of the edge strip of the plate-shaped component can be effected exclusively by the slot-shaped recesses or by cooling air holes which are formed in the base body of the plate-shaped component or by additional cooling air holes which are formed in the edge strip of the plate-shaped component or by a combination of the additional cooling air holes through the skirting and the cooling air holes through the body. Thus, variants can be used with no cooling air hole at the recess, a cooling air hole in the edge strip or the body or two cooling air holes in the skirt and the body.
In besonders günstiger Ausgestaltung der Erfindung ist vorgesehen, dass die Ausnehmung symmetrisch zur Mittelebene des Kühlluftlochs ausgebildet ist. Hierdurch ergeben sich gleichmäßige Spannungsverteilungen im Bereich der Ausnehmung und der angrenzenden Bereiche des Stützkörpers. Weiterhin wird die Zuleitung der Kühlluft in das Kühlluftloch optimiert.In a particularly favorable embodiment of the invention it is provided that the recess is formed symmetrically to the center plane of the cooling air hole. This results in uniform stress distributions in the region of the recess and the adjacent regions of the support body. Furthermore, the supply of cooling air is optimized in the cooling air hole.
Die schlitzartigen Ausnehmungen des Stützkörpers können in günstiger Ausgestaltung der Erfindung so ausgebildet sein, dass die Wandungen der Ausnehmung angrenzend an die Oberfläche des Grundkörpers beidseitig zunächst einen geradlinigen Wandverlauf aufweisen, welcher zur Ausbildung einer spitzbogenartigen Struktur im oberen Bereich der schlitzartigen Ausnehmung in einen abgerundeten Wandverlauf übergeht. Dabei ist es besonders günstig, wenn der abgerundete Wandverlauf einen Radius aufweist, welcher zwischen dem 0,1- bis 2-fachen, insbesondere 1- bis 2-fachen, der Breite der Ausnehmung beträgt. In besonders günstiger Weiterbildung ist vorgesehen, dass die abgerundeten Wandverläufe einen Winkel zwischen 45° und 120° bilden. Hierdurch wird die in der Seitenansicht spitzbogenartige Kontur der Ausnehmungen besonders wirkungsvoll realisiert.The slot-like recesses of the support body may be formed in a favorable embodiment of the invention so that the walls of the recess adjacent to the surface of the body on both sides initially have a rectilinear course of the wall, which merges into a rounded wall to form an arcuate structure in the upper part of the slot-like recess , It is particularly advantageous if the rounded wall course has a radius which is between 0.1 to 2 times, in particular 1 to 2 times, the width of the recess. In a particularly favorable development, it is provided that the rounded wall profiles form an angle between 45 ° and 120 °. As a result, the spike arc-like contour of the recesses in the side view is realized particularly effective.
Der Abstand benachbarter Ausnehmungen kann, in Längsrichtung der Randleiste, größer oder gleich der Hälfte der Breite der Ausnehmungen entsprechen. Somit sind alternierend längs der Randleiste im Wesentlichen gleichbreite Ausnehmungen und verbleibende fasenartige Bereiche des Stützkörpers vorgesehen.The spacing of adjacent recesses may, in the longitudinal direction of the edge strip, correspond to greater than or equal to half the width of the recesses. Thus, substantially equidistant recesses and remaining chamfer-like areas of the support body are provided alternately along the edge strip.
Der Stützkörper selbst, welcher einen fasenartigen Übergang zwischen dem Grundkörper und der Randleiste bildet, kann hinsichtlich seiner Oberfläche einen Winkel zur Oberfläche des Grundkörpers zwischen 30 ° und 60 ° aufweisen. Ein Betrag von 45 ° ist dabei bevorzugt.The support body itself, which forms a chamfer-like transition between the base body and the edge strip, may have an angle with respect to its surface to the surface of the base body between 30 ° and 60 °. An amount of 45 ° is preferred.
Weiterhin ist es erfindungsgemäß möglich, die Mittelachse des Kühlluftlochs rechtwinklig oder in einem stumpfen Winkel zur Oberfläche des Grundkörpers, d.h. in einem Bereich von 90 ° bis 180 °, anzuordnen. Hierdurch sind bevorzugte Kühleffekte insbesondere an thermisch stark beanspruchten Bereichen der Randleiste oder des Grundkörpers erzielbar.Furthermore, it is possible according to the invention, the central axis of the cooling air hole at right angles or at an obtuse angle to the surface of the body, ie in a range of 90 ° to 180 °, to arrange. As a result, preferred cooling effects can be achieved, in particular, on regions of the edge strip or of the base body subjected to high thermal stress.
Im Folgenden wird die Erfindung anhand eines Ausführungsbeispiels in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:
- Fig. 1
- eine schematische perspektivische Teilansicht eines ersten Ausführungsbeispiels der Erfindung,
- Fig. 2
- eine perspektivische Seitenansicht gemäß
Fig. 1 , - Fig. 3
- eine vereinfachte Draufsicht gemäß
Fig. 1 ,oder 2 - Fig. 4
- eine schematische Draufsicht eines zweiten Ausführungsbeispiels der Erfindung,
- Fig. 5
- eine schematische, perspektivische Seitenansicht eines dritten Ausführungsbeispiels der Erfindung, und
- Fig. 6
- eine schematische, vereinfachte Draufsicht eines vierten Ausführungsbeispiels der Erfindung.
- Fig. 1
- a schematic perspective partial view of a first embodiment of the invention,
- Fig. 2
- a perspective side view according to
Fig. 1 . - Fig. 3
- a simplified plan view according to
Fig. 1 or 2 . - Fig. 4
- a schematic plan view of a second embodiment of the invention,
- Fig. 5
- a schematic, perspective side view of a third embodiment of the invention, and
- Fig. 6
- a schematic, simplified plan view of a fourth embodiment of the invention.
Die
In dem Grundkörper 1 sind eine Vielzahl von Effusionskühllöchern ausgebildet, so wie dies aus dem Stand der Technik bekannt ist.In the
Der Grundkörper 1 weist eine Dicke d1 auf.The
Am Randbereich des Grundkörpers 1 ist einstückig mit diesem eine Randleiste 2 ausgebildet, welche eine Dicke d2 hat. Die Dicke d1 wird von der Oberfläche 6 des Grundkörpers 1 zu dessen Rückseite gemessen. In gleicher Richtung wird die Dicke d2 der Randleiste 2 definiert.At the edge region of the
Die Randleiste 2, welche einstückig mittels eines additiven Verfahrens mit dem Grundkörper 1 ausgebildet wird, ist über einen Stützkörper 3 abgestützt. Dieser weist, so wie sich dies aus der
In jeder Ausnehmung 4 ist zumindest ein Kühlluftloch 5 vorgesehen, welches sich von der Ausnehmung 4 aus zur Rückseite des Grundkörpers 1 erstreckt, analog den Effusionskühllöchern 10.In each
Die freie Fläche des Stützkörpers 3 weist zur Oberfläche 6 des Grundkörpers 1 einen Winkel β auf, welcher zwischen 30° und 60° betragen kann. Ein Wert von 45 ° ist bevorzugt.The free surface of the
Die
Die Länge der geradlinigen Wandverläufe 7 (11 bzw. l2) ist bevorzugterweise gleich und ≥ 0 mm. Die Radien r1 und r2 sind ebenfalls gleich und betragen das 0,1- bis 2-fache der Breite l3 der Ausnehmung 4.The length of the rectilinear wall courses 7 (11 or 12) is preferably the same and ≥ 0 mm. The radii r1 and r2 are also equal and are 0.1 to 2 times the width l3 of the
Sowohl die geradlinigen Wandverläufe 7 mit den Längen l1 und l2 als auch die abgerundeten Wandverläufe 8 mit den Radien r1 und r2 sind nicht zwingend für die Erfindung notwendig, es können auch andere Wandverläufe realisiert werden, um die Ausnehmung 4 auszubilden. Sowohl die Längen l1 und l2 als auch die Radien r1 und r2 können voneinander in den angegebenen Intervallen abweichen. Auch ist es nicht zwingend erforderlich, dass die Ausnehmung 4 symmetrisch zu einer Mittelebene des Kühlluftlochs 5 angeordnet ist.Both the
Die
Die Fertigung des erfindungsgemäßen Bauteils durch ein additives Verfahren erfolgt üblicherweise mit vertikaler Ausrichtung des Grundkörpers 1. Sofern dieser an allen Seiten mit einer Randleiste versehen ist, wird zunächst eine Randleiste mit der Dicke d2 aufgebaut. Der Übergang zum Grundkörper 1 mit einer Dicke d1 erfolgt kontinuierlich durch den jeweiligen Stützkörper 3, welcher mit den Ausnehmungen 4 versehen wird.The production of the component according to the invention by an additive method is usually carried out with a vertical orientation of the
Es versteht sich, dass das erfindungsgemäße Bauteil an allen seinen Rändern mit einer Randleiste 2 versehen sein kann. Weiterhin ist erfindungsgemäß der plattenförmige Grundkörper 1 nicht auf eine ebene Platte beschränkt, er kann auch gekrümmt oder doppelt gekrümmt ausgebildet sein.It is understood that the component according to the invention can be provided with a
- 11
- Grundkörperbody
- 22
- Randleistesidebar
- 33
- Stützkörpersupport body
- 44
- Ausnehmungrecess
- 55
- KühlluftlochCooling air hole
- 66
- Oberflächesurface
- 77
- geradliniger Verlaufstraight course
- 88th
- abgerundeter Verlaufrounded course
- 99
- Mittelachsecentral axis
- 1010
- EffusionskühllochEffusionskühlloch
- 1515
- zusätzliches Kühlluftloch in der Randleisteadditional cooling air hole in the sidebar
- aa
- Abstand zwischen benachbarten AusnehmungenDistance between adjacent recesses
- d1d1
- Dicke des GrundkörpersThickness of the main body
- d2d2
- Dicke der RandleisteThickness of the sidebar
- l1, l2l1, l2
- Längen von geradlinigen Wandverläufen der AusnehmungLengths of rectilinear wall progressions of the recess
- l3l3
- Breite der Ausnehmung am Fuß des StützkörpersWidth of the recess at the foot of the support body
- r1, r2r1, r2
- Radius von abgerundeten Wandverläufen der AusnehmungRadius of rounded wall profiles of the recess
Claims (12)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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DE102016224632.1A DE102016224632A1 (en) | 2016-12-09 | 2016-12-09 | Plate-shaped component of a gas turbine and method for its production |
Publications (2)
Publication Number | Publication Date |
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EP3333484A1 true EP3333484A1 (en) | 2018-06-13 |
EP3333484B1 EP3333484B1 (en) | 2020-07-22 |
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ID=60654704
Family Applications (1)
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EP17205686.3A Active EP3333484B1 (en) | 2016-12-09 | 2017-12-06 | Tile of a gas turbine |
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US (1) | US10753612B2 (en) |
EP (1) | EP3333484B1 (en) |
DE (1) | DE102016224632A1 (en) |
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CN113924444A (en) * | 2019-06-07 | 2022-01-11 | 赛峰直升机引擎公司 | Method for manufacturing a flame tube for a turbomachine |
FR3097029B1 (en) * | 2019-06-07 | 2021-05-21 | Safran Helicopter Engines | Method of manufacturing a flame tube for a turbomachine |
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EP1022437A1 (en) * | 1999-01-19 | 2000-07-26 | Siemens Aktiengesellschaft | Construction element for use in a thermal machine |
EP2927592A1 (en) * | 2014-03-31 | 2015-10-07 | Siemens Aktiengesellschaft | Heat shield element, heat shield and turbine engine |
EP3056813A1 (en) * | 2015-02-12 | 2016-08-17 | Rolls-Royce Deutschland Ltd & Co KG | Seal of an edge gap between effusion shingle of a gas turbine combustor |
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EP1672281A1 (en) * | 2004-12-16 | 2006-06-21 | Siemens Aktiengesellschaft | Thermal shield element |
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DE102007018061A1 (en) * | 2007-04-17 | 2008-10-23 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustion chamber wall |
US7665306B2 (en) * | 2007-06-22 | 2010-02-23 | Honeywell International Inc. | Heat shields for use in combustors |
EP2182285A1 (en) * | 2008-10-29 | 2010-05-05 | Siemens Aktiengesellschaft | Burner insert for a gas turbine combustion chamber and gas turbine |
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DE102012022259A1 (en) * | 2012-11-13 | 2014-05-28 | Rolls-Royce Deutschland Ltd & Co Kg | Combustor shingle of a gas turbine and process for its production |
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DE102013223258A1 (en) * | 2013-11-14 | 2015-06-03 | Rolls-Royce Deutschland Ltd & Co Kg | Combustion heat shield element of a gas turbine |
DE102014204472A1 (en) * | 2014-03-11 | 2015-09-17 | Rolls-Royce Deutschland Ltd & Co Kg | Combustor shingle of a gas turbine |
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DE102014221225A1 (en) * | 2014-10-20 | 2016-04-21 | Siemens Aktiengesellschaft | Heat shield element and method for its production |
-
2016
- 2016-12-09 DE DE102016224632.1A patent/DE102016224632A1/en not_active Withdrawn
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2017
- 2017-12-06 US US15/833,471 patent/US10753612B2/en active Active
- 2017-12-06 EP EP17205686.3A patent/EP3333484B1/en active Active
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EP1022437A1 (en) * | 1999-01-19 | 2000-07-26 | Siemens Aktiengesellschaft | Construction element for use in a thermal machine |
EP2927592A1 (en) * | 2014-03-31 | 2015-10-07 | Siemens Aktiengesellschaft | Heat shield element, heat shield and turbine engine |
EP3056813A1 (en) * | 2015-02-12 | 2016-08-17 | Rolls-Royce Deutschland Ltd & Co KG | Seal of an edge gap between effusion shingle of a gas turbine combustor |
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US10753612B2 (en) | 2020-08-25 |
US20180163964A1 (en) | 2018-06-14 |
DE102016224632A1 (en) | 2018-06-14 |
EP3333484B1 (en) | 2020-07-22 |
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