EP2527743B1 - Segment component comprising high temperature cast material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for producing an annular combustion chamber - Google Patents
Segment component comprising high temperature cast material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for producing an annular combustion chamber Download PDFInfo
- Publication number
- EP2527743B1 EP2527743B1 EP12169511.8A EP12169511A EP2527743B1 EP 2527743 B1 EP2527743 B1 EP 2527743B1 EP 12169511 A EP12169511 A EP 12169511A EP 2527743 B1 EP2527743 B1 EP 2527743B1
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- European Patent Office
- Prior art keywords
- combustion
- combustion chamber
- chamber
- chamber wall
- annular
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
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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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49229—Prime mover or fluid pump making
- Y10T29/4927—Cylinder, cylinder head or engine valve sleeve making
Definitions
- the invention relates to a segment component of high-temperature casting material for an annular combustion chamber, an annular combustion chamber for an aircraft engine, an aircraft engine and a method for producing an annular combustion chamber.
- annular combustion chambers which are arranged axially between the compressor and the turbine.
- An annular combustion chamber has coaxially with the engine longitudinal axis a combustion chamber walls bounded annular space, which is also referred to as a flame tube.
- the injectors for the fuel are arranged along the annular cross section of the annular space. In operation, the fuel flames extend from these injectors into the annulus.
- a combustion chamber wall which during operation shields a fuel flame extending along a burner axis from the environment, has a bulge, the bulge pointing in a direction pointing away from the burner axis.
- a part of a segmental component for an outer combustion chamber wall of an annular combustion chamber has e.g. a bulge that points radially outward.
- a portion of a segmental component for an internal combustion chamber wall includes e.g. a bulge that points outward.
- the segmental component has a combustion chamber head, an inner combustion chamber wall and an outer combustion chamber wall, between which a fuel flame is arranged along a burner axis during operation.
- the inner combustion chamber wall, the combustion chamber head and the outer combustion chamber wall are connected together as a one-piece, U-shaped molded casting.
- the inner and / or the outer combustion chamber wall have a bulge in the direction pointing away from the burner axis.
- the at least one bulge of the combustion chamber wall is adapted substantially to the contour of the fuel flame during operation.
- the length and / or width of the derecognition essentially correspond to the length and / or width of the fuel flame during operation.
- Advantageous high temperature cast materials are a superalloy containing nickel, chromium, cobalt and / or nickel-iron, especially Inconel 738 / Inconel 738 LC, Inconel 939 / Inconel 939 LC, Inconel 713 / Inconel 713 LC, C1023, Mar M 002 and / or CM 274LC , These materials have a sufficient temperature resistance.
- an advantageous embodiment is provided if at least one mounting flange is arranged on the combustion chamber head. Furthermore, it is advantageous if a device for arranging an injector for fuel is provided on the combustion chamber head. Also, advantageously, at least one integrally formed on a combustion chamber wall nozzle for cooling air can be provided.
- the combustion chamber wall has an average thickness of between 1 and 4 mm, in particular 1.4 to 3 mm.
- annular combustion chamber for an aircraft engine with the features of claim 8.
- at least two segment components according to at least one of claims 1 to 7 are used.
- annular combustion chamber have a variable annular space height along the circumference of the annular space.
- the annulus height By adapting the annulus height to, for example, burner flames and / or injectors, the thermal and / or mechanical loading of the walls can be achieved. This applies in particular when regions A of a larger annular space height H RA alternate with regions B of a smaller annular space height H RB along the circumference, so that the combustion chamber walls form a type of wave-like structure
- areas are formed with a larger annulus height and areas with a smaller annulus height, which are arranged in the assembly injectors for the fuel in the areas with the larger annulus height.
- the areas of larger annulus height give the fuel flame more space and shield it from annoyance in the annulus.
- the segment components are interconnected by welds, in particular by electron beam welding, laser welds with IN626 Filler, Polymet 972 or other ductile welding consumables.
- the object is also achieved by methods for producing an annular combustion chamber.
- At least two segment components made of high-temperature cast material having an inner combustion chamber wall, an outer combustion chamber wall and a combustion chamber head are cast.
- the inner combustion chamber wall, the outer combustion chamber wall, and the combustion chamber head are connected together as a one-piece, U-molded casting, wherein the inner and / or outer combustion chamber wall has a bulge in the direction away from a burner axis.
- the at least two segment components are connected by welding to the annular combustion chamber.
- FIG. 1 In a perspective view, an annular combustion chamber is shown with an annular space 30, as used for example in an aircraft engine.
- the annular space 30 is arranged in the main flow direction of the aircraft engine behind the compressor, not shown here, and the inlet region of a turbine 40.
- two injectors 25 are visible, from which fuel flames 20 (not shown here) emerge along burner axes 21 during operation.
- the burner axes 21 and thus also the fuel flames 20 are thus between the inner combustion chamber wall 11 and the outer combustion chamber wall 12.
- This annular space 30 is also referred to as a flame tube.
- the combustion chamber walls 11, 12 thus shield the fuel flames 20 inwardly and outwardly from the environment.
- the annulus height H R (also referred to as Flammraum hope) varies in the axial direction of the aircraft engine, but is constant along the circumference of the annular combustion chamber 10.
- the invention described below with reference to various embodiments relates, inter alia, annular combustion chambers in which the ring combustion chamber height H R is non-constant along the circumference.
- Such an annular combustion chamber is e.g. composed of at least two segment components 10 made of high temperature casting material.
- each of the segmental components 10 would be e.g. 180 ° of the annulus 30 provide.
- a segment component 10 is shown, which covers a much smaller angular range, namely 30 °, as in the view of Fig. 2A is particularly clear.
- An annular combustion chamber composed of such segmental components 10, therefore has 12 of these segmental components 10.
- a segmental component 10 is shown in which parts form the inner combustion chamber wall 11 and the outer combustion chamber wall 12 when the segmental components 10 are assembled (see FIG Fig. 5 ).
- an opening 24 is provided for the injector 25, not shown here.
- the fuel flame 20 (not shown here) produced by the injector 25 extends along the burner axis 21 into the annular space 30 in the direction of the inlet region of the turbine 40 (not shown here, see FIG Fig. 1 ).
- This embodiment of the segment component 10 is produced in one piece from a high-temperature casting material.
- a superalloy may be used which contains nickel, chromium, cobalt and / or nickel-iron.
- Typical high temperature cast alloys are in particular Inconel 738 / Inconel 738 LC, Inconel 939 / Inconel 939 LC, Inconel 713 / Inconel 713 LC, C1023, Mar M 002 and / or CM 274LC.
- the casting processes e.g., investment casting) allow segmental components 10 to be made with very thin walls and in very complex shapes.
- the combustion chamber walls 11, 12 have an average thickness of between 1 and 4 mm.
- the wall of the combustion chamber head 23 can between 2 and 4 mm.
- the shaping it is possible, for example, to form nozzle 15 for air cooling during casting.
- mounting flanges 23 can be molded integrally on the combustion chamber head 22. Basically, the possibilities of shaping are not limited to the illustrated features.
- the combustion chamber walls 11, 12 of this embodiment are contoured in a particular way.
- the inner combustion chamber wall 11 has a bulge 13, which points downwards in the representation selected here.
- the bulge 13 thus points away from the burner axis 21.
- the outer combustion chamber wall 12 has a bulge 14, which has the same shape in a slightly upward direction.
- the bulge 14 thus also points away from the burner axis 21.
- the bulges 13, 14 are arranged so that they correspond approximately to the contour of the fuel flame 20 when the annular combustion chamber is in operation.
- the bulge 13 on the inner combustion chamber wall 11 and the bulge 14 on the outer combustion chamber wall 12 extend in the axial direction approximately as far as the fuel flame 20 extends into the annular space.
- the axial extension of the bulges, 13, 14 is about 50 to 90% of the total axial extent of the annular space. Further, it is advantageous if the width B B of the bookings 13, 14 is about 30 to 60% of the width B of a segment component 10, wherein the width B of the bulge is smaller on the inside than on the outside.
- Fig. 2C is the one to view the Fig. 2B also shown that the bulges 13, 14 are approximately adapted to the contour of the fuel flame.
- a region A is drawn in, in which the annulus height H RA is increased by the stakes 13, 14 and a region B, in which the annulus height H RB is reduced.
- An arc length U of the segment component 10 is thus composed of A + 2B. It is advantageous if the proportion of the range A is 50 to 80% of the arc length U and the portion of the range B is 20 to 50% of the arc length U.
- H RA 0.7 - 0.9 H conv . This means that the height of the combustion chamber in the area outside the bulges 13, 14 is 70 to 90% of the usual height.
- segment components 10 are connected to each other, an annular combustion chamber is formed whose annular space height H R is variable in the circumferential direction.
- Segment components 10 are connected to each other, for example by laser or electron beam welding, whereby the introduced path energy is minimized. It can be a suitable, ductile filler used in welding (IN625 or Polymet 972).
- Such a compound rivet combustion chamber is in Fig. 3 shown.
- segment components 10 are used here to form an annular space 30.
- Areas A of a larger annular space height H RA alternate with areas B of a smaller annular space height H RB along the circumference, so that the combustion chamber walls 11, 12 form a kind of wave-like structure.
- the fuel flames 20 (not shown here) are in each case in the extended areas A. Between the fuel flames 20 are narrowed areas B. This leads to the effect that each fuel flame 20 can effectively burn in its own combustion chamber. Disturbances in a region of the annular space 30 can spread more severely in the entire annular space 30 due to the constrictions in the regions B.
- air may be directed from the compressor to the turbine 40 with less severe deflection, thereby reducing the pressure loss on this flow path.
- the described embodiment also has advantageous effects outside of the annular space 30, since the turbine cooling air K, which is guided outside the annular space, is also influenced by the contouring of the combustion chamber walls 11, 12.
- the pressure loss during the transfer of the turbine cooling air K from the compressor outlet to the combustion chamber is determined to enter the cooling system by the flow guidance in this way. If the turbine cooling air K has to be deflected repeatedly (in particular radially) and accelerated (and then decelerated again), then the pressure loss increases. In the burner axis 21, only a small amount of turbine cooling air K flows past the burner and mixing air hole in the direction of the turbine, so the pressure loss is not so decisive there.
- the combustion chamber head 22 is designed so that the turbine cooling air K is not greatly deflected radially outwards and inwards. These are the areas B between the bulges 13, 14, but at the respective outer sides of the annular space 30. After the radial deflection then takes place a deflection in the axial direction. Thus, in area B, there is a small deflection into the much deeper annuli around the narrower combustion chamber at this point.
- the flow of turbine cooling air K is in Fig. 3 shown schematically.
- the bulges 13, 14 cause a more uniform temperature distribution in the circumferential direction to form in the combustion chamber walls 11, 12, which has a positive influence on the service life of the annular combustion chamber.
- the combustion chamber wall 11, 12, due to the bulges 13, 14 relatively far away from the fuel flame 20.
- the combustion chamber walls 11, 12 are closer together, since the annulus height H R is lower here.
- the wall regions of the combustion chamber walls 11, 12 which are closest to the fuel flame 20 would be hotter than other regions. For these reasons, not so much cooling air needs to be used in area A. The cooling air thus saved is available for measures to reduce exhaust emissions.
- the inner combustion chamber wall 11 and the outer combustion chamber wall 12 have a wavy structure when made of segmental components 10, for example according to FIG Fig. 2 are composed.
- This wavy structure allows for easier compensation of thermal and / or mechanical stresses in the combustion chamber walls 11, 12 than would be possible in annular spaces with circular cross-sections in the circumferential direction.
- the segmental components 10 may be provided with a thermal barrier coating.
- a further embodiment of a segment component 10 is shown. Basically, it has the same functions and properties as the segment component 10 described above, so that reference can be made to the corresponding description.
- the bulge 13 has a rather small width in the vicinity of the combustion chamber head 23, which widens steadily, in order then to become smaller again.
- a segment component 10 it is also possible for a segment component 10 to have only one outer or inner part of the annular combustion chamber.
- Fig. 5 an embodiment of a segment component 10 is shown, which has only one outer combustion chamber wall 12. Like the previously described embodiments, this segmental component 10 also has a bulge 14 that faces away from the burner axis 21. To illustrate the use of this segmental component 10, are in Fig. 5 dashed lines the fuel flame 20 and the burner axis 21 drawn.
- annular combustion chamber can be constructed, as shown in FIG Fig. 6A , B is shown.
- segment components 10 are connected to an inner full ring structure 31, in particular welded.
- segment components 10 are connected to an outer full ring structure 32, in particular welded Fig. 6A are the two full ring structures 31, 32 shown, each having only six segment components 10 for reasons of simplicity.
- the inner full ring structure 31 and the outer full ring structure 32 are connected to a combustion head structure 43, as shown in FIG Fig. 6B is shown.
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Description
Die Erfindung betrifft ein Segmentbauteil aus Hochtemperaturgussmaterial für eine Ringbrennkammer, eine Ringbrennkammer für ein Flugzeugtriebwerk, ein Flugzeugtriebwerk und ein Verfahren zur Herstellung einer Ringbrennkammer.The invention relates to a segment component of high-temperature casting material for an annular combustion chamber, an annular combustion chamber for an aircraft engine, an aircraft engine and a method for producing an annular combustion chamber.
Moderne Flugzeugtriebwerke weisen üblicherweise Ringbrennkammern auf, die axial zwischen Verdichter und Turbine angeordnet sind. Eine Ringbrennkammer weist koaxial zur Triebwerkslängsachse einen von Brennkammerwänden begrenzten Ringraum auf, der auch als Flammrohr bezeichnet wird. Entlang des ringförmigen Querschnitts des Ringraums sind die Injektoren für den Brennstoff angeordnet. Im Betrieb erstrecken sich die Brennstoffflammen von diesen Injektoren in den Ringraum hinein.Modern aircraft engines usually have annular combustion chambers, which are arranged axially between the compressor and the turbine. An annular combustion chamber has coaxially with the engine longitudinal axis a combustion chamber walls bounded annular space, which is also referred to as a flame tube. Along the annular cross section of the annular space, the injectors for the fuel are arranged. In operation, the fuel flames extend from these injectors into the annulus.
Aufgrund der hohen thermischen Belastungen müssen die Brennkammerwände entsprechend thermisch stabil ausgebildet sein. So ist es bekannt, die Brennkammerwände mit thermisch besonders belastbaren Platten auszustatten. Aus der
In der
Es ist die Aufgabe der vorliegenden Erfindung, Segmentbauteile für Ringbrennkammern zur Verfügung zu stellen, die thermisch und strömungstechnisch verbessert sind.It is the object of the present invention to provide segment components for annular combustion chambers, which are improved thermally and fluidically.
Diese Aufgabe wird durch ein Segmentbauteil mit den Merkmalen des Anspruchs 1 gelöst.This object is achieved by a segment component with the features of claim 1.
Dabei weist eine Brennkammerwand, die im Betrieb eine sich entlang einer Brennerachse erstreckende Brennstoffflamme gegenüber der Umgebung abschirmt, eine Ausbuchtung auf, wobei die Ausbuchtung in eine Richtung zeigt, die von der Brennerachse wegzeigt. Ein Teil eines Segmentbauteils für eine äußere Brennkammerwand einer Ringbrennkammer weist z.B. eine Ausbuchtung auf, die radial nach außen zeigt. Ein Teil eines Segmentbauteils für eine innere Brennkammerwand weist z.B. eine Ausbuchtung auf, die nach außen zeigt. Durch die Ausbuchtungen wird im unmittelbaren Bereich um die Brennerflamme ein größerer Raum geschaffen, indem der Abstand der Brennkammerwände zumindest bereichsweise um die Brennerflamme vergrößert wird.In this case, a combustion chamber wall, which during operation shields a fuel flame extending along a burner axis from the environment, has a bulge, the bulge pointing in a direction pointing away from the burner axis. A part of a segmental component for an outer combustion chamber wall of an annular combustion chamber has e.g. a bulge that points radially outward. A portion of a segmental component for an internal combustion chamber wall includes e.g. a bulge that points outward. By the bulges a larger space is created in the immediate area around the burner flame by the distance of the combustion chamber walls is at least partially increased by the burner flame.
Das Segmentbauteil weist einen Brennkammerkopf, eine innere Brennkammerwand und eine äußere Brennkammerwand, zwischen denen im Betrieb eine Brennstoffflamme entlang einer Brennerachse angeordnet ist, auf. Die innere Brennkammerwand, der Brennkammerkopf und die äußere Brennkammerwand sind miteinander als ein einteiliges, U-förmig gegossenes Gussteil verbunden.The segmental component has a combustion chamber head, an inner combustion chamber wall and an outer combustion chamber wall, between which a fuel flame is arranged along a burner axis during operation. The inner combustion chamber wall, the combustion chamber head and the outer combustion chamber wall are connected together as a one-piece, U-shaped molded casting.
Vorteilhafterweise weisen die innere und / oder die äußere Brennkammerwand eine Ausbuchtung in die Richtung auf, die von der Brennerachse wegzeigt.Advantageously, the inner and / or the outer combustion chamber wall have a bulge in the direction pointing away from the burner axis.
Dabei ist es besonders vorteilhaft, wenn die mindestens eine Ausbuchtung der Brennkammerwand im Wesentlichen an die Kontur der Brennstoffflamme im Betrieb angepasst ist. Dabei kann vorteilhafterweise die Länge und / oder Breite der Ausbuchung im Wesentlichen der Länge und / oder Breite der Brennstoffflamme im Betrieb entsprechen.It is particularly advantageous if the at least one bulge of the combustion chamber wall is adapted substantially to the contour of the fuel flame during operation. In this case, advantageously, the length and / or width of the derecognition essentially correspond to the length and / or width of the fuel flame during operation.
Vorteilhafte Hochtemperaturgussmaterialien sind eine Superlegierung enthaltend Nickel, Chrom, Kobalt und / oder Nickel-Eisen, insbesondere Inconel 738/ Inconel 738 LC, Inconel 939 / Inconel 939 LC, Inconel 713 / Inconel 713 LC, C1023, Mar M 002 und / oder CM 274LC. Diese Materialien weisen eine hinreichende Temperaturbeständigkeit auf.Advantageous high temperature cast materials are a superalloy containing nickel, chromium, cobalt and / or nickel-iron, especially Inconel 738 / Inconel 738 LC, Inconel 939 / Inconel 939 LC, Inconel 713 / Inconel 713 LC, C1023, Mar M 002 and / or CM 274LC , These materials have a sufficient temperature resistance.
Dabei liegt eine vorteilhafte Ausführungsform vor, wenn am Brennkammerkopf mindestens ein Befestigungsflansch angeordnet ist. Ferner ist es vorteilhaft, wenn am Brennkammerkopf eine Vorrichtung zur Anordnung eines Injektors für Brennstoff vorgesehen ist. Auch kann vorteilhafterweise mindestens ein einstückig an eine Brennkammerwand angeformter Stutzen für Kühlluft vorgesehen sein.In this case, an advantageous embodiment is provided if at least one mounting flange is arranged on the combustion chamber head. Furthermore, it is advantageous if a device for arranging an injector for fuel is provided on the combustion chamber head. Also, advantageously, at least one integrally formed on a combustion chamber wall nozzle for cooling air can be provided.
Vorteilhafterweise weist die Brennkammerwand bei einer Ausführungsform eine mittlere Dicke zwischen 1 und 4 mm, insbesondere 1,4 bis 3 mm auf.Advantageously, in one embodiment, the combustion chamber wall has an average thickness of between 1 and 4 mm, in particular 1.4 to 3 mm.
Die Aufgabe wird auch durch eine Ringbrennkammer für ein Flugzeugtriebwerk mit den Merkmalen des Anspruchs 8 gelöst. Dabei werden mindestens zwei Segmentbauteile gemäß mindestens einem der Ansprüche 1 bis 7 verwendet.The object is also achieved by an annular combustion chamber for an aircraft engine with the features of claim 8. In this case, at least two segment components according to at least one of claims 1 to 7 are used.
Vorteilhafte Ausführungsformen der Ringbrennkammer weisen entlang des Umfangs des Ringraums eine variable Ringraumhöhe auf. Durch die Anpassung der Ringraumhöhe an z.B. Brennerflammen und / oder Injektoren kann die thermische und / oder mechanische Belastung der Wandungen erreicht werden. Dies gilt insbesondere dann, wenn sich Bereiche A einer größeren Ringraumhöhe HRA mit Bereichen B einer geringeren Ringraumhöhe HRB entlang des Umfanges abwechseln, so dass die Brennkammerwände eine Art wellenartige Struktur ausbildenAdvantageous embodiments of the annular combustion chamber have a variable annular space height along the circumference of the annular space. By adapting the annulus height to, for example, burner flames and / or injectors, the thermal and / or mechanical loading of the walls can be achieved. This applies in particular when regions A of a larger annular space height H RA alternate with regions B of a smaller annular space height H RB along the circumference, so that the combustion chamber walls form a type of wave-like structure
Dabei ist es besonders vorteilhaft, wenn Bereiche mit einer größeren Ringraumhöhe und Bereiche mit einer kleineren Ringraumhöhe gebildet werden, wobei im Zusammenbau Injektoren für den Brennstoff in den Bereichen mit der größeren Ringraumhöhe angeordnet sind. Die Bereiche der größeren Ringraumhöhe geben der Brennstoffflamme mehr Platz und schirmen sie gegen Störungen im Ringraum ab.It is particularly advantageous if areas are formed with a larger annulus height and areas with a smaller annulus height, which are arranged in the assembly injectors for the fuel in the areas with the larger annulus height. The areas of larger annulus height give the fuel flame more space and shield it from annoyance in the annulus.
Ferner sind in vorteilhaften Ausgestaltungen die Segmentbauteile untereinander durch Schweißnähte, insbesondere durch Elektronenstrahlschweißen, Laserschweißnähte mit IN626 Filler, Polymet 972 oder anderen duktilen Schweißzusätze verbunden.Furthermore, in advantageous embodiments, the segment components are interconnected by welds, in particular by electron beam welding, laser welds with IN626 Filler, Polymet 972 or other ductile welding consumables.
Die Aufgabe wird auch durch ein Flugzeugtriebwerk mit einer Ringbrennkammer nach den Ansprüchen 8 bis 11 gelöst. Die gesamte Strömung vom Verdichter, über die Brennkammer bis zur Turbine wird durch die um die Flammen herum angeordneten Ausbuchtungen verbessert.The object is also achieved by an aircraft engine with an annular combustion chamber according to claims 8 to 11. All flow from the compressor, through the combustor to the turbine, is enhanced by the bulges around the flames.
Die Aufgabe wird ferner auch durch Verfahren zur Herstellung einer Ringbrennkammer gelöst.The object is also achieved by methods for producing an annular combustion chamber.
Dabei werden mindestens zwei Segmentbauteile aus Hochtemperaturgussmaterial mit einer inneren Brennkammerwand, einer äußeren Brennkammerwand und einem Brennkammerkopf gegossen. Die innere Brennkammerwand, die äußere Brennkammerwand und der Brennkammerkopf sind miteinander als ein einteiliges, U-förmig gegossenes Gussteil verbunden, wobei die innere und/oder die äußere Brennkammerwand eine Ausbuchtung in die Richtung aufweist, die von einer Brennerachse wegzeigt. Anschließend werden die mindestens zwei Segmentbauteile durch Schweißen, zur Ringbrennkammer verbunden.In this case, at least two segment components made of high-temperature cast material having an inner combustion chamber wall, an outer combustion chamber wall and a combustion chamber head are cast. The inner combustion chamber wall, the outer combustion chamber wall, and the combustion chamber head are connected together as a one-piece, U-molded casting, wherein the inner and / or outer combustion chamber wall has a bulge in the direction away from a burner axis. Subsequently, the at least two segment components are connected by welding to the annular combustion chamber.
Die Erfindung wird nachfolgend unter Bezugnahme auf die Figuren der Zeichnung anhand mehrerer Ausführungsbeispiele näher erläutert. Es zeigen:
- Fig. 1
- eine schematische, perspektivische Darstellung einer an sich bekannten Ringbrennkammer;
- Fig. 2
- eine perspektivische Darstellung einer Ausführungsform eines Segmentbauteils mit zwei Brennkammerwänden für eine Ringbrennkammer,
- Fig. 2A
- eine Ansicht vom Brennkammerkopf auf die Ausführungsform gemäß
Fig. 2 ; - Fig. 2B
- eine Schnittansicht der Ausführungsform gemäß
Fig. 2 in Längsrichtung; - Fig. 2C
- eine Schnittansicht der Ausführungsform gemäß
Fig. 2 senkrecht zur Längsrichtung; - Fig. 3
- eine axiale Schnittansicht auf eine Ausführungsform für eine Ringbrennkammer gebildet aus Segmentbauteilen gemäß der Ausführungsform nach
Fig. 2 ; - Fig.4
- eine Draufsicht auf eine weitere Ausführungsform eines Segmentbauteils mit zwei Brennkammerwänden,
- Fig. 5
- eine weitere Ausführungsform eines Segmentbauteils mit einer Brennkammerwand;
- Fig. 6A
- eine perspektivische Ansicht einer ersten Stufe des Aufbaus einer Ringraumstruktur;
- Fig. 6B
- eine perspektivische Ansicht einer zweiten Stufe des Aufbaus einer Ringraumstruktur.
- Fig. 1
- a schematic, perspective view of a known annular combustion chamber;
- Fig. 2
- 3 is a perspective view of an embodiment of a segment component with two combustion chamber walls for an annular combustion chamber,
- Fig. 2A
- a view from the combustion chamber head to the embodiment according to
Fig. 2 ; - Fig. 2B
- a sectional view of the embodiment according to
Fig. 2 longitudinal; - Fig. 2C
- a sectional view of the embodiment according to
Fig. 2 perpendicular to the longitudinal direction; - Fig. 3
- an axial sectional view of an embodiment for an annular combustion chamber formed from segment components according to the embodiment of FIG
Fig. 2 ; - Figure 4
- a top view of a further embodiment of a segment component with two combustion chamber walls,
- Fig. 5
- a further embodiment of a segment component with a combustion chamber wall;
- Fig. 6A
- a perspective view of a first stage of the construction of an annulus structure;
- Fig. 6B
- a perspective view of a second stage of the structure of an annulus structure.
In
Der Ringraum 30 ist in Hauptströmungsrichtung des Flugzeugtriebwerks hinter dem hier nicht dargestellten Kompressor und dem Einlaufbereich einer Turbine 40 angeordnet. In der Darstellung der
Der Abstand zwischen den Brennkammerwänden 11, 12, die Ringraumhöhe HR (auch als Flammraumhöhe bezeichnet) variiert zwar in axialer Richtung des Flugzeugtriebwerks, ist aber entlang des Umfangs der Ringbrennkammer 10 konstant.Although the distance between the
Die im Folgenden anhand verschiedener Ausführungsformen beschriebene Erfindung betrifft u.a. Ringbrennkammern, bei denen entlang des Umfangs die Ringbrennkammerhöhe HR nicht-konstant ist.The invention described below with reference to various embodiments relates, inter alia, annular combustion chambers in which the ring combustion chamber height H R is non-constant along the circumference.
Eine solche Ringbrennkammer ist z.B. aus mindestens zwei Segmentbauteilen 10 aus Hochtemperaturgussmaterial zusammengesetzt. Im Fall von zwei Segmentbauteilen würde jedes der Segmentbauteile 10 z.B. 180°des Ringraums 30 bereitstellen.Such an annular combustion chamber is e.g. composed of at least two
In
Eine Ringbrennkammer, aus solchen Segmentbauteilen 10 zusammengesetzt, weist daher 12 dieser Segmentbauteile 10 auf. Grundsätzlich ist es möglich, die Segmentbauteile 10 geometrisch anders zu gestalten, so dass weniger oder mehr als 12 Segmentbauteile 10 verwendet werden. Auch ist es nicht zwingend, dass eine gerade Anzahl von Segmentbauteilen 10 verwendet wird, um einen Ringraum 30 zu bilden.An annular combustion chamber, composed of such
In
Diese Ausführungsform des Segmentbauteils 10 ist einteilig aus einem Hochtemperaturgussmaterial hergestellt. Dazu kann vorteilhafterweise eine Superlegierung verwendet werden, die Nickel, Chrom, Kobalt und / oder Nickel-Eisen enthält. Typische Hochtemperaturgusslegierungen sind insbesondere Inconel 738/ Inconel 738 LC, Inconel 939 / Inconel 939 LC, Inconel 713 / Inconel 713 LC, C1023, Mar M 002 und / oder CM 274LC. Die Gussverfahren (z.B. Feinguss) erlauben, Segmentbauteile 10 mit sehr dünnen Wandungen und in sehr komplexen Formen herzustellen.This embodiment of the
So ist es z.B. vorteilhaft, wenn die Brennkammerwände 11, 12 eine mittlere Dicke zwischen 1 und 4 mm aufweisen. Die Wandung des Brennkammerkopfes 23 kann zwischen 2 und 4 mm betragen. In der Formgebung ist es z.B. möglich, Stutzen 15 für Luftkühlung beim Gießen mit anzuformen. Auch können Befestigungsflansche 23 am Brennkammerkopf 22 einstückig mitgegossen werden. Grundsätzlich sind die Möglichkeiten der Formgebung nicht auf die dargestellten Merkmale beschränkt.For example, it is advantageous if the
Die Brennkammerwände 11, 12 dieser Ausführungsform sind in einer besonderen Weise konturiert. Die innere Brennkammerwand 11 weist eine Ausbuchtung 13 auf, die in der hier gewählten Darstellung nach unten zeigt. Die Ausbuchtung 13 weist somit von der Brennerachse 21 weg. Die äußere Brennkammerwand 12 weist eine in etwas gleich geformte Ausbuchtung 14 nach oben auf. Die Ausbuchtung 14 weist somit ebenfalls von der Brennerachse 21 weg.The
Die Ausbuchtungen 13, 14 sind dabei so angeordnet, dass sie in etwa der Kontur der Brennstoffflamme 20 entsprechen, wenn die Ringbrennkammer im Betrieb ist.The
Diese Zusammenhänge sind schematisch in den
Die Ausbuchtung 13 an der inneren Brennkammerwand 11 und die Ausbuchtung 14 an der äußeren Brennkammerwand 12 reichen in axialer Richtung in etwa soweit, wie die Brennstoffflame 20 sich in den Ringraum erstreckt.The
In vorteilhaften Ausführungsformen beträgt die axiale Erstreckung der Ausbuchtungen, 13, 14 ca. 50 bis 90% der gesamten axialen Erstreckung des Ringraums. Ferner ist es vorteilhaft, wenn die Breite BB der Ausbuchungen 13, 14 ca. 30 bis 60% der Breite B eines Segmentbauteils 10 beträgt, wobei die Breite B der Ausbuchtung an der Innenseite kleiner ist als an der Außenseite.In advantageous embodiments, the axial extension of the bulges, 13, 14 is about 50 to 90% of the total axial extent of the annular space. Further, it is advantageous if the width B B of the
In
In
Eine Bogenlänge U des Segmentbauteils 10 setzt sich somit aus A + 2B zusammen. Es ist vorteilhaft, wenn der Anteil des Bereiches A 50 bis 80% der Bogenlänge U und der Anteil des Bereichs B 20 bis 50% der Bogenlänge U ausmacht.An arc length U of the
Ferner sind in
Vorteilhafte Ausgestaltungen weisen Ausbuchtungen 13, 14 auf, für die gilt: HRA = 1,1 - 1,5 Hkonv. Dies bedeutet, dass die Höhe des Brennraumes im Bereich der Ausbuchtungen 13, 14 zwischen 10 und 50% gegenüber der konventionellen Bauart erweitert wird.Advantageous embodiments have
Es ist auch vorteilhaft, wenn im Bereich B, d. h. Bereichen ohne Ausbuchrungen 13, 14 gilt: HRA = 0,7 - 0,9 Hkonv. Dies bedeutet, dass die Höhe des Brennraumes im Bereich außerhalb der Ausbuchtungen 13, 14 70 bis 90% der üblichen Höhe beträgt.It is also advantageous if, in region B, ie regions without
Werden nun mehrere dieser Segmentbauteile 10 miteinander verbunden, so wird eine Ringbrennkammer gebildet, deren Ringraumhöhe HR in Umfangsrichtung variabel ist. Segmentbauteile 10 werden z.B. durch Laser oder Elektronenstrahlschweißen miteinander verbunden, wobei die eingebrachte Streckenenergie minimiert wird. Es kann ein geeigneter, duktiler Filler beim Schweißen verwendet (IN625 oder Polymet 972) werden.If now several of these
Eine dermaßen zusammengesetzte Rinnbrennkammer ist in
Die Brennstoffflammen 20 (hier nicht dargestellt) liegen dabei jeweils in den erweiterten Bereichen A. Zwischen den Brennstoffflammen 20 liegen verengte Bereiche B. Dies führt dazu, dass jede Brennstoffflamme 20 gewissermaßen in einem eigenen Brennraum brennen kann. Störungen in einem Bereich des Ringraums 30 können sich auf Grund der Verengungen in den Bereichen B schwerer im ganzen Ringraum 30 ausbreiten.The fuel flames 20 (not shown here) are in each case in the extended areas A. Between the
Auch kann in den Bereichen B zwischen den Injektoren 25 Luft mit weniger starker Umlenkung vom Verdichter zur Turbine 40 geführt werden, wodurch der Druckverlust auf diesem Strömungspfad sinkt.Also, in areas B between the
Die beschriebene Ausführungsform hat aber auch außerhalb des Ringraums 30 vorteilhafte Wirkungen, da auch die Turbinenkühlluft K, die außerhalb des Ringraums geführt wird, durch die Konturierung der Brennkammerwände 11, 12 beeinflusst wird.However, the described embodiment also has advantageous effects outside of the
Dabei wird der Druckverlust bei der Überführung der Turbinenkühlluft K vom Verdichteraustritt an der Brennkammer vorbei zum Eintritt in das Kühlsystem durch die Strömungsführung auf diesem Weg bestimmt. Muss die Turbinenkühlluft K wiederholt (insbesondere radial) umgelenkt und beschleunigt (und dann wieder verzögert) werden, dann erhöht sich der Druckverlust. In der Brennerachse 21 strömt nur wenig Turbinenkühlluft K an dem Brenner und Mischluftloch vorbei in Richtung Turbine, daher ist der Druckverlust dort nicht so ausschlaggebend.In this case, the pressure loss during the transfer of the turbine cooling air K from the compressor outlet to the combustion chamber is determined to enter the cooling system by the flow guidance in this way. If the turbine cooling air K has to be deflected repeatedly (in particular radially) and accelerated (and then decelerated again), then the pressure loss increases. In the
Zwischen den Brennern ist bei der vorliegenden Ausführungsform der Brennkammerkopf 22 so gestaltet, dass die Turbinenkühlluft K nicht erst stark radial nach außen und innen umgelenkt wird. Dies sind die Bereiche B zwischen den Ausbuchtungen 13, 14, aber an den jeweiligen Außenseiten des Ringraums 30. Nach der radialen Ablenkung erfolgt dann eine Umlenkung in axialer Richtung. Somit erfolgt im Bereich B eine kleine Umlenkung in die viel tieferen Annuli um die an dieser Stelle schmalere Brennkammer. Der Strom der Turbinenkühlluft K ist in
Bei entsprechender Strömungsführung entstehen so weniger Druckverluste. Der Druckverlust wird durch die Einbuchtung zwischen den Brennern vermindert. Durch die tieferen Annuli hat die Turbinenkühlluft K auch im Vergleich zur üblichen Spaltströmung weniger Kontakt zur heißen Brennkammerwand und wird somit kälter bei der Turbine angeliefert, was der Kühlwirkung in der Turbine zugute kommt.With appropriate flow control so less pressure losses. The pressure loss is reduced by the indentation between the burners. As a result of the lower annuli, the turbine cooling air K also has less contact with the hot combustion chamber wall compared to the usual gap flow and is thus delivered colder to the turbine, which benefits the cooling effect in the turbine.
Ingesamt kann der Gesamtdruckverlust verringert werden, was den Brennstoffbedarf senkt. Außerdem fließt weniger Luft zwischen den Injektoren 25 in den Bereich des Brennkammerkopfes 22 als an der Position der Injektoren 25, so dass an diesen Umfangspositionen hinreichend Luft zur Überleitung in die Turbine 40 zur Verfügung steht.Overall, the total pressure loss can be reduced, which lowers the fuel requirement. In addition, less air flows between the
Des Weiteren führen die Ausbuchtungen 13, 14 dazu, dass sich in den Brennkammerwänden 11, 12 eine gleichmäßigere Temperaturverteilung in Umfangsrichtung ausbildet, was einen positiven Einfluss auf die Lebensdauer der Ringbrennkammer hat. In den Bereichen A, in denen die Brennstoffflame 20 liegt, ist die Brennkammerwand 11, 12, auf Grund der Ausbuchtungen 13, 14 relativ weit von der Brennstoffflamme 20 entfernt. In den Bereichen B, zwischen den Brennstoffflammen 20, liegen die Brennkammerwände 11, 12 dichter beieinander, da die Ringraumhöhe HR hier geringer ist. Ohne die Ausbuchtungen 13, 14 wären die Wandungsbereiche der Brennkammerwände 11, 12, die der Brennstoffflamme 20 am nächsten sind, heißer als andere Bereiche. Aus diesen Gründen muss im Bereich A nicht so viel Kühlluft verwendet werden. Die so eingesparte Kühlluft steht für Maßnahmen zur Verminderung der Abgasemissionen zur Verfügung.Furthermore, the
Wie in
Wenn es notwendig erscheint (z.B. bei größeren Flugzeugtriebwerken), können die Segmentbauteile 10 mit einer Wärmedämmschicht versehen werden.If deemed necessary (e.g., in larger aircraft engines), the
Wenn ein duktiler Schweißzusatz verwendet wird, muss im Fall nachträglichen Laserbohrens an der Ringbrennkammer nicht auf die Positionen der Längsschweißnähte zwischen den Segmentbauteilen 10 Rücksicht genommen werden.When using a ductile weld filler, in the case of subsequent laser drilling at the annular combustion chamber, the positions of the longitudinal welds between the
In
Im Gegensatz zu den im Wesentlichen rechteckigen Ausbuchtungen 13, 14 bei der Ausführungsform gemäß
Grundsätzlich sind mit dem Gussverfahren auch andere Formen für Ausbuchtungen möglich, die einem bestimmten Einsatzzweck angepasst werden können. Gerade durch die Verwendung der oben genannten Materialien und dem Gussverfahren ist es möglich, die Ausbuchtungen 13, 14 gezielt zu formen.In principle, other shapes for bulges are possible with the casting process, which can be adapted to a particular application. Just by using the above-mentioned materials and the casting process, it is possible to form the
In den
Grundsätzlich ist es aber auch möglich, dass ein Segmentbauteil 10 nur einen äußeren oder inneren Teil der Ringbrennkammer aufweist. In
Auch mit dieser Ausführungsform und einem entsprechenden Segmentbauteil 10 für die innere Brennkammerwand 11 lässt sich eine Ringbrennkammer aufbauen, wie dies in
Dazu werden mindestens zwei Segmentbauteile 10' zu einer inneren Vollringstruktur 31 verbunden, insbesondere verschweißt. Ferner werden zwei Segmentbauteile 10" zu einer äußeren Vollringstruktur 32 verbunden, insbesondere verschweißt. In
- 1010
- Segmentbauteilsegment component
- 1111
- innere Brennkammerwandinner combustion chamber wall
- 1212
- äußere Brennkammerwandouter combustion chamber wall
- 1313
- Ausbuchtung innerer BrennkammerwandBulge of inner combustion chamber wall
- 1414
- Ausbuchtung äußerer BrennkammerwandBulge outer combustion chamber wall
- 1515
- Stutzen für KühlluftNozzle for cooling air
- 2020
- Brennstoffflammefuel flame
- 2121
- BrennerachseBrenner
- 2222
- Brennkammerkopfbulkhead
- 2323
- Befestigungsflanschmounting flange
- 2424
- Vorrichtung zur Anordnung eines BrennersDevice for arranging a burner
- 2525
- Injektor für BrennstoffInjector for fuel
- 3030
- Ringraumannulus
- 3131
- innere Vollringstrukturinner full ring structure
- 3232
- äußere Vollringstrukturouter full ring structure
- 4040
- Einlaufbereich TurbineInlet area turbine
- KK
- TurbinenkühlluftTurbine cooling air
- HRA H RA
- Bereich größerer RingraumhöheRange of larger annulus height
- HRB H RB
- Bereich kleinerer RingraumhöheArea of smaller annulus height
- HR H R
- RingraumhöheAnnulus height
- Hkonv H conv
- übliche Ringraumhöheusual annulus height
- Ri R i
- Radius der inneren BrennkammerwandRadius of the inner combustion chamber wall
- Ra R a
- Radius der äußeren BrennkammerwandRadius of the outer combustion chamber wall
- BB
- Breite SegmentbauteilWide segmental component
- BB B B
- Breite AusbuchtungWide bulge
- LB L B
- Länge BrennstoffflammeLength of fuel flame
- LL
- Länge BrennstoffkammerLength of fuel chamber
- UU
- Bogenlänge eines SegmentbauteilsArc length of a segment component
Claims (13)
- Segment component made from a high-temperature casting material for an annular combustion chamber of an aircraft engine, featuring a combustion-chamber wall (11, 12) which in operation shields a fuel flame (20) extending along a burner axis (21) from the environment,- with the combustion-chamber wall (11, 12) having a bulge (13, 14) which points in a direction facing away from the burner axis (21),- with the segment component having a combustion-chamber head (22), an inner combustion-chamber wall (11) and an outer combustion-chamber wall (12), between which a fuel flame (20) is provided in operation, andcharacterized in that the inner combustion-chamber wall (11), the combustion-chamber head (22) and the outer combustion-chamber wall (12) are connected to one another in the form of a one-piece, U-shaped casting.
- Segment component in accordance with Claim 1, characterized in that the inner and/ or the outer combustion-chamber wall (11, 12) have/ has a bulge (13, 14) in the direction facing away from the burner axis (21).
- Segment component in accordance with Claim 1 or 2, characterized in that at least one bulge (13, 14) of the combustion-chamber wall (11, 12) is adapted substantially to the contour of the fuel flame (20) in operation, in particular that the combustion-chamber wall (11, 12) has a bulge (13, 14), the length (LB) and/ or width (BB) of which substantially corresponds to the length and/ or width of the fuel flame (20) in operation.
- Segment component in accordance with at least one of the preceding Claims, characterized in that the high-temperature casting material is a super-alloy containing nickel, chromium, cobalt and/ or nickel-iron, in particular Inconel 738/ Inconel 738 LC, Inconel 939/ Inconel 939 LC, Inconel 713/ Inconel 713 LC, C1023, Mar M 002 and/ or CM 274LC.
- Segment component in accordance with at least one of the preceding Claims, characterized in that at least one mounting flange (23) is arranged on the combustion-chamber head (22) and/ or a device (24) for arranging an injector (25) is provided on the combustion-chamber head (22).
- Segment component in accordance with at least one of the preceding Claims, characterized by at least one nozzle (15) for cooling air integrally formed onto a combustion-chamber wall (11, 12).
- Segment component in accordance with at least one of the preceding Claims, characterized in that the combustion-chamber wall (11, 12) has a mean thickness between 1 and 4 mm, in particular 1.4 to 3 mm.
- Annular combustion chamber for an aircraft engine having at least two segment components (10) in accordance with at least one of the Claims 1 to 7.
- Annular combustion chamber in accordance with Claim 8, characterized by a variable annular space height (HR) along the circumference of the annular space (30), where in particular areas (A) with a greater annular space height (HRA) alternate with areas (B) with a lower annular space height (HRB) along the circumference.
- Annular combustion chamber in accordance with Claim 8 or 9, characterized by areas with a greater annular space height (HRA) and areas with a lower annular space height (HRB), where during assembly injectors (25) for the fuel are provided in the areas with the greater annular space height (HRA).
- Annular combustion chamber in accordance with at least one of the Claims 8 to 10, characterized in that the segment components (10) are connected to one another by welds, in particular electron beam welds, laser welds with IN626 Filler, Polymet 972 or other ductile filler materials.
- Aircraft engine having an annular combustion chamber in accordance with the Claims 8 to 11.
- Method for the manufacture of an annular combustion chamber in accordance with at least one of the Claims 8 to 11, with the following process steps:a) casting of at least two segment components (10) from a high-temperature casting material, with an inner combustion-chamber wall (11), an outer combustion-chamber wall (12) and a combustion-chamber head (22), which are connected to one another in the form of a one-piece, U-shaped casting, where the inner and/ or the outer combustion-chamber wall (11, 12) have/has a bulge (13, 14) in the direction facing away from a burner axis (21), and thenb) welding of the at least two segment components (10) to form an annular combustion chamber (10).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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DE102011076473A DE102011076473A1 (en) | 2011-05-25 | 2011-05-25 | High temperature casting material segment component for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine, and method of manufacturing an annular combustion chamber |
Publications (3)
Publication Number | Publication Date |
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EP2527743A2 EP2527743A2 (en) | 2012-11-28 |
EP2527743A3 EP2527743A3 (en) | 2015-01-21 |
EP2527743B1 true EP2527743B1 (en) | 2016-09-28 |
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EP12169511.8A Not-in-force EP2527743B1 (en) | 2011-05-25 | 2012-05-25 | Segment component comprising high temperature cast material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for producing an annular combustion chamber |
Country Status (3)
Country | Link |
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US (1) | US8646279B2 (en) |
EP (1) | EP2527743B1 (en) |
DE (1) | DE102011076473A1 (en) |
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DE102013222863A1 (en) | 2013-11-11 | 2015-05-13 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustor and method for its production |
DE102014204468A1 (en) * | 2014-03-11 | 2015-10-01 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustor and method for its production |
DE102016201452A1 (en) * | 2016-02-01 | 2017-08-03 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustor with wall contouring |
CN111059575B (en) * | 2018-10-16 | 2022-05-10 | 中发天信(北京)航空发动机科技股份有限公司 | Turbojet engine flame tube shell |
US20200318549A1 (en) * | 2019-04-04 | 2020-10-08 | United Technologies Corporation | Non-axisymmetric combustor for improved durability |
GB202019219D0 (en) * | 2020-12-07 | 2021-01-20 | Rolls Royce Plc | Lean burn combustor |
GB202019222D0 (en) | 2020-12-07 | 2021-01-20 | Rolls Royce Plc | Lean burn combustor |
US11940151B2 (en) | 2022-01-12 | 2024-03-26 | General Electric Company | Combustor with baffle |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
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GB741836A (en) * | 1953-03-05 | 1955-12-14 | Lucas Industries Ltd | Combustion chambers for jet-propulsion engines, gas turbines or other prime movers |
CA2056592A1 (en) * | 1990-12-21 | 1992-06-22 | Phillip D. Napoli | Multi-hole film cooled combustor liner with slotted film starter |
US5964091A (en) * | 1995-07-11 | 1999-10-12 | Hitachi, Ltd. | Gas turbine combustor and gas turbine |
DE19959292A1 (en) | 1999-12-09 | 2001-06-13 | Rolls Royce Deutschland | Method of manufacturing a combustion chamber of a gas turbine engine |
EP1312865A1 (en) * | 2001-11-15 | 2003-05-21 | Siemens Aktiengesellschaft | Gas turbine annular combustion chamber |
ES2307702T3 (en) * | 2002-11-22 | 2008-12-01 | Siemens Aktiengesellschaft | COMBUSTION CHAMBER FOR THE COMBUSTION OF A FUEL FLUID MIX. |
EP1482246A1 (en) * | 2003-05-30 | 2004-12-01 | Siemens Aktiengesellschaft | Combustion chamber |
US20050227106A1 (en) * | 2004-04-08 | 2005-10-13 | Schlichting Kevin W | Single crystal combustor panels having controlled crystallographic orientation |
GB2420614B (en) * | 2004-11-30 | 2009-06-03 | Alstom Technology Ltd | Tile and exo-skeleton tile structure |
US7325587B2 (en) * | 2005-08-30 | 2008-02-05 | United Technologies Corporation | Method for casting cooling holes |
US7540156B2 (en) * | 2005-11-21 | 2009-06-02 | General Electric Company | Combustion liner for gas turbine formed of cast nickel-based superalloy |
EP2100687A1 (en) * | 2008-02-29 | 2009-09-16 | Siemens Aktiengesellschaft | Potential-free wire heating during welding and device for this purpose |
-
2011
- 2011-05-25 DE DE102011076473A patent/DE102011076473A1/en not_active Withdrawn
-
2012
- 2012-05-25 EP EP12169511.8A patent/EP2527743B1/en not_active Not-in-force
- 2012-05-25 US US13/480,696 patent/US8646279B2/en active Active
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US20120304658A1 (en) | 2012-12-06 |
US8646279B2 (en) | 2014-02-11 |
EP2527743A2 (en) | 2012-11-28 |
EP2527743A3 (en) | 2015-01-21 |
DE102011076473A1 (en) | 2012-11-29 |
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