EP1706593B1 - Turbine blade and gas turbine with such a turbine blade - Google Patents
Turbine blade and gas turbine with such a turbine blade Download PDFInfo
- Publication number
- EP1706593B1 EP1706593B1 EP05706868A EP05706868A EP1706593B1 EP 1706593 B1 EP1706593 B1 EP 1706593B1 EP 05706868 A EP05706868 A EP 05706868A EP 05706868 A EP05706868 A EP 05706868A EP 1706593 B1 EP1706593 B1 EP 1706593B1
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- EP
- European Patent Office
- Prior art keywords
- blade
- turbine
- sheet metal
- metal part
- turbine blade
- 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.)
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- 239000002184 metal Substances 0.000 claims abstract description 86
- 238000007789 sealing Methods 0.000 claims description 31
- 239000002826 coolant Substances 0.000 claims description 8
- 230000002093 peripheral effect Effects 0.000 claims description 6
- 238000001816 cooling Methods 0.000 description 17
- 230000000694 effects Effects 0.000 description 9
- 238000011161 development Methods 0.000 description 7
- 230000018109 developmental process Effects 0.000 description 7
- 238000000926 separation method Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000000284 resting effect Effects 0.000 description 2
- 238000007792 addition Methods 0.000 description 1
- 230000001010 compromised effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000005476 soldering Methods 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
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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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
Definitions
- the invention relates to a turbine blade with an airfoil arranged along a blade axis and with a platform region having at the foot of the airfoil a platform which extends transversely to the blade axis.
- the invention further relates to a gas turbine having a flow channel with an annular cross-section for a working medium extending along an axis of the gas turbine, a second blade arranged behind a first blade stage arranged along the axis, wherein a blade stage arranged a number of annular, radially into the channel having extending turbine blades.
- a gas turbine of this type occur in the flow channel after exposure to hot gas temperatures that can range between 1000 ° C and 1400 ° C.
- the platform of the turbine bucket due to the annular arrangement of a number of such turbine buckets in a bucket stage, forms part of the flow passage for a gas turbine working fluid in the form of hot gas, thus driving the axial turbine rotor via the turbine buckets.
- Such a strong thermal stress on the boundary of the flow channel formed by the platforms is countered by cooling a platform from behind, that is to say from the base of a turbine blade arranged below the platform.
- the foot and the platform region usually have a suitable sewer system for the application of a cooling medium.
- the platform area is formed as a double platform of two opposing platform walls. This ensures that the flow channel and thus the hot gas directly exposed, the flow channel limiting platform wall can be made thin.
- the execution in two platform walls results in a separation of functions for the platform walls.
- the platform wall delimiting the flow channel is essentially responsible for the sewerage of the hot gas.
- the opposite, not acted upon by the hot gas platform wall takes over the recording of the blade resulting from the blade loads. This separation of functions makes it possible to make the flow channel limiting platform wall so thin that the hot gas channelization is ensured without having to intercept substantial loads.
- sealing measures are necessary in a parting line between platforms of adjacent turbine blades of the same blade stage or adjacent turbine blades of successively arranged blade stages to prevent unwanted and excessive leakage of cooling medium in the hot gas flow channel.
- the measures required for sealing can lead to structurally and cooling technically difficult situations on a thermally highly loaded platform wall and represent an increased failure potential for a turbine blade and thus for a gas turbine.
- the invention is based, whose task is to provide a turbine blade with a platform that is simultaneously simple and also satisfies the geometrical-structural and cooling requirements within a flow channel limitation of a gas turbine advantageous. Furthermore, the sealing of the part joints between adjacent turbine blades should be particularly simple and inexpensive.
- the object is achieved by the invention with the turbine blade mentioned above, wherein according to the invention the platform is at least partially formed by a first resilient sheet metal part fixed to the airfoil which sealingly engages a smaller stop located on an adjacent turbine blade.
- the invention is based on the consideration that the use of a non-load-bearing platform for the representation of the boundary of a hot gas flow channel of a gas turbine is fundamentally suitable for cooling the platform, and thus the boundary of the flow channel, as effectively as possible.
- the essential insight lies the invention in that it is possible to equip the platform itself with an increased sealing effect, namely by the platform is made so thin-walled that it is formed by a voltage applied to the blade leaf resilient sheet metal part.
- the platform as a part of the hot gas acted upon flow limiting part meets all requirements with regard to the cooling and also a sealing element.
- the platform as such is sufficiently flexible to permit simultaneous relative movements of adjacent blades and other parts and still maintains the sealing effect. This eliminates the need for a special sealing element. This simplifies the design and cooling of the flow channel boundary.
- the first resilient sheet metal part is provided as a non-load-bearing platform wall which at least partially defines the hot-gas-charged flow channel.
- the platform thus consists at least partially of the first spring-elastic sheet-metal part fixed to the blade.
- the platform is formed by the first fixed to a first stop on one side of the airfoil elastic sheet metal part and is formed by a second at a second stop on the other side of the airfoil fixed sheet metal part.
- two sheet metal parts are expediently provided, which form the platform, which thus extend on both sides on one side and the other side of the airfoil transversely to the blade axis.
- the second sheet metal part resting against the blade leaf assumes the function of a first platform wall which does not carry the blade leaf, and the platform furthermore has a second platform wall carrying the blade leaf.
- a corresponding cooling space for pressurization with a cooling medium is formed between the first non-supporting platform wall of the second sheet metal part and the second thicker supporting platform wall as a special load-bearing structure.
- each stop can be designed in the form of a groove or edge. This allows a particularly reliable and aerodynamically favorable attachment of the sheet metal part at the foot of the airfoil.
- the sheet metal parts in particular the first, is held on a further stop of an adjacent turbine blade.
- this further stop in the form of a support formed be.
- a support may be formed by a formed between the blade root and foot of the airfoil step.
- the first sheet metal part of a first turbine blade engages behind the bearing of the adjacent turbine blade sealing.
- the second sheet metal part can advantageously engage behind the support arranged on the same turbine blade or, in addition or as an alternative, be attached to the step.
- the first resilient sheet metal part in the rest state is loosely against the further stop of the adjacent turbine blade.
- the sheet metal part there results a still to be explained sufficient attachment of the sheet metal part from the movement or fluidic connection of the turbine blade in the operating state of a gas turbine.
- the sealing effect of the first resilient sheet metal part on the further stop can be further improved if the first resilient sheet metal part rests under a self-generated bias on the other stop.
- a blade stage comprises a number of annularly arranged radially in the flow channel extending turbine blades, wherein according to the invention a turbine blade is designed according to one of the above type.
- the turbine blade is a blade.
- a blade is at one attached axially rotating turbine rotor and rotates when operating the gas turbine with the turbine rotor.
- a centrifugal force acting through the rotation from the base of the blade in the direction of the blade is generated.
- the development provides that the first resilient sheet metal part reaches a sufficient sealing effect between two adjacent sheet metal parts of two adjacent blades. Due to the centrifugal force, the first resilient sheet metal part of a first blade is pressed against a further stop of the second blade and thereby applied centrifugally mounted.
- the first resilient sheet metal part when operating the blade of the gas turbine, the first resilient sheet metal part also has the function of a sealing element.
- the contact surface of the first resilient sheet metal part acts on the further stop of the adjacent blade in the form of a support as a sealing abutment for the first sheet metal part.
- the turbine blade is provided as a guide vane on a peripheral turbine housing.
- a pressure gradient from the foot of the airfoil is produced in the direction of the airfoil by means of a cooling medium.
- the alternative development provides that the first resilient sheet metal part of a first vane through the Pressure gradient is pressed against the further stop a second vane and thereby pressure-fastened. The pressure gradient is thus generated by the fact that the first resilient sheet metal part is acted upon from the back with cooling medium and is thereby pressed against the other stop.
- the pressure gradient is sufficiently large, so that this is sufficient not only for a pressure fastening of the first resilient sheet metal part to the other stop, but also has the first resilient sheet metal part has the function of a sealing element during operation of the guide vane in the gas turbine.
- the contact surfaces of the first resilient sheet metal part act on a stop described above as sufficient sealing surfaces and the stop as an abutment for the first resilient sheet metal part.
- a boundary of the flow channel is formed, which is continuous.
- a continuous axial boundary of the flow channel is advantageously formed.
- it is in the Vane stages around vanes and turbine blades around vanes.
- FIG. 1 shows a gas turbine 1 with a along an axis 3 extending flow channel 5 with an annular cross-section for a working medium M.
- a number of blade stages are arranged in the flow channel 5, a number of blade stages are arranged.
- a second vane stage 9 is arranged behind a first vane stage 7 along the axis 3.
- a second blade stage 13 is disposed behind a first blade stage 11.
- the guide blade stages 7, 9 have a number of guide vanes 21, which are arranged annularly on a peripheral turbine housing 15 and extend radially into the flow channel 5.
- a rotor blade stage 11, 13 has a number of rotor blades 23 which extend in an annular manner on an axial turbine rotor 19 and extend radially into the flow conduit 5.
- the flow of a working medium M is generated in the form of a hot gas from a burner 17.
- a number of such burners 17 in a in the cross-sectional drawing of FIG. 1 Not shown annulus disposed about the axis 3 around.
- a vane 21 and a blade 23 are in the FIG. 1 shown schematically.
- a guide blade 21 has a blade tip 27 arranged along a blade axis 25, an airfoil 29 and a platform region 31.
- the platform region 31 has a platform 33 extending transversely to the blade axis 25 and a blade root 35.
- a rotor blade 23 has a blade tip 37 arranged along a blade axis, an airfoil 39 and a platform region 41.
- the platform region 41 has a platform 43 extending transversely to the blade axis 45 and a blade root 47.
- the peripheral boundary 49 is part of the peripheral turbine housing 15.
- the rotor-side boundary 51 is part of the turbine rotor 19 rotating in the operating state of the gas turbine 1.
- FIG. 2 shows a platform area 61 representative of a platform area 31, 41.
- first turbine blade 63 and second turbine blade 65 is shown representative of a first vane 21 of a first vane stage 7 and an axially directly behind it arranged second vane 21 of a second vane stage 9.
- the first turbine blade 63 and the second turbine blade 65 are also representative of one in the FIG. 1 shown first rotor blade 23 of the first blade stage 11 and an axially directly behind arranged second blade 23 of the second blade stage 13 shown.
- the turbine blades 63, 65 are vanes.
- the first turbine blade 63 has an airfoil 69 drawn in demolition.
- the second turbine blade 65 in this case has an airfoil 67 drawn in the demolition.
- a platform 71 which extends transversely to the blade axis 73, 75, is formed in the platform region 61 at the foot of the blade leaf 67, 69.
- the platform 71 is characterized on the one hand by a first spring-elastic sheet-metal part 79 shown in the first blade 63 and to others are formed by a second sheet metal part 77 shown in the second blade 65.
- the first resilient sheet metal part 79 is attached to a first stop 83 on one side of the airfoil 69, which side is shown in the first turbine blade 63.
- the second resilient sheet metal part 77 is attached to a second stop 81 on the other side of the airfoil 67, which side is shown in the second turbine blade 65.
- the attachment can be done for example by welding or soldering and is tight.
- the first stop 83 and the second stop 81 are each formed in the form of a groove, in each of which the first resilient sheet metal part 79 and the second sheet metal part 77 each pierces with its end on the blade 69 and the blade 67 end edge.
- the second resilient sheet metal part 77 is also held on a further stop 85 of the second turbine blade 65.
- the second sheet metal part 77 is attached to the stopper 85.
- the second sheet metal part 77 could engage behind the further stop 85.
- the latter is the case for the first resilient sheet metal part 79 of the first turbine blade 63, which is held together with the second sheet metal part 77 on the further stop 85 of the second turbine blade 67.
- the first resilient sheet metal part 79 loosely engages the further stop 85.
- the further stop 85 is designed to hold the second sheet metal part 77 and the first resilient sheet metal part 79 in the form of a support and thus forms a sealing surface on its side facing the first resilient sheet metal part 79. which serves as an abutment for the first resilient sheet metal part 79.
- the platform 71 comes on its rear side 89 largely without a support structure or a supporting platform wall. Rather, a first cooling space 93 and a second cooling space 91 are formed on the rear side 89, which make it possible to optimally cool the platform 71 in the area between the second turbine blade 65 and the first turbine blade 63. In this way, an otherwise usually complicated to design platform edge construction in connection with the further stopper 85 can be made easier and without thermally compromised area.
- first turbine blade 63 and the second turbine blade 65 preferably in the form of a in the FIG. 1 shown guide vane 21 or optionally also in the form of a in the FIG. 1 shown rotor blade 23, which is provided in particular at the further stop 85
- a turbine blade 65 63 in the form of a blade 23 on a turbine rotor 19, namely, a rotation from the foot of the blade 67, 69 in the direction 99 of the blade 67, 69th acting centrifugal force generated.
- the first resilient sheet metal part 79 by means of a self-generated by the first resilient sheet metal part 79 self-biasing abuts the other stop 85 sealingly. As a result, the contact pressure generated by the pressure gradient can be increased.
- the sheet metal parts 77, 79 of the platform 71 are centrifugally mounted or pressure-mounted and simultaneously develop their sealing effect and separation effect between the H thoroughlygasbeetzmannten flow channel 5 and thedemediumbeaufschlagten back 89 of the platform 71st
- a turbine blade 63, 65 has a blade blade 67, 69 arranged along a blade axis 73, 75 and a platform region 61 at the foot of the blade 67, 69 arranged a platform 71, which extends transversely to the blade axis 73, 75, proposed that the platform 71 is formed by a fixed to the blade plate 67, 69 sheet metal part 77, 79.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Control Of Turbines (AREA)
Abstract
Description
Die Erfindung betrifft eine Turbinenschaufel mit einem entlang einer Schaufelachse angeordneten Schaufelblatt und mit einem Plattformbereich, der am Fuße des Schaufelblattes angeordnet eine Plattform aufweist, die sich quer zur Schaufelachse erstreckt. Die Erfindung führt des Weiteren auf eine Gasturbine mit einem entlang einer Achse der Gasturbine sich erstreckenden Strömungskanal mit ringförmigem Querschnitt für ein Arbeitsmedium, einer zweiten hinter einer ersten entlang der Achse angeordneten Schaufelstufe, wobei eine Schaufelstufe eine Anzahl von ringförmig angeordneten, sich radial in den Kanal erstreckende Turbinenschaufeln aufweist.The invention relates to a turbine blade with an airfoil arranged along a blade axis and with a platform region having at the foot of the airfoil a platform which extends transversely to the blade axis. The invention further relates to a gas turbine having a flow channel with an annular cross-section for a working medium extending along an axis of the gas turbine, a second blade arranged behind a first blade stage arranged along the axis, wherein a blade stage arranged a number of annular, radially into the channel having extending turbine blades.
Bei einer Gasturbine dieser Art treten im Strömungskanal nach Beaufschlagung mit Heißgas Temperaturen auf, die im Bereich zwischen 1000 °C und 1400 °C liegen können. Die Plattform der Turbinenschaufel bildet infolge der ringförmigen Anordnung einer Anzahl solcher Turbinenschaufeln in einer Schaufelstufe einen Teil des Strömungskanals für ein die Gasturbine durchströmendes Arbeitsfluid in Form von Heißgas, das auf diese Weise den axialen Turbinenrotor über die Turbinenschaufeln antreibt. Einer derart starken thermischen Beanspruchung der durch die Plattformen gebildeten Begrenzung des Strömungskanals wird dadurch begegnet, dass eine Plattform von hinten, also vom unterhalb der Plattform angeordneten Fuß einer Turbinenschaufel her, gekühlt wird. Dazu weist der Fuß und der Plattformbereich üblicherweise eine geeignete Kanalisation zur Beaufschlagung mit einem Kühlmedium auf.In a gas turbine of this type occur in the flow channel after exposure to hot gas temperatures that can range between 1000 ° C and 1400 ° C. The platform of the turbine bucket, due to the annular arrangement of a number of such turbine buckets in a bucket stage, forms part of the flow passage for a gas turbine working fluid in the form of hot gas, thus driving the axial turbine rotor via the turbine buckets. Such a strong thermal stress on the boundary of the flow channel formed by the platforms is countered by cooling a platform from behind, that is to say from the base of a turbine blade arranged below the platform. For this purpose, the foot and the platform region usually have a suitable sewer system for the application of a cooling medium.
Aus der
In der
Bei der Ausführung einer Turbinenschaufel eingangs genannter Art sind in einer Teilfuge zwischen Plattformen aneinander grenzender Turbinenschaufeln der gleichen Schaufelstufe oder benachbarter Turbinenschaufeln von hintereinander angeordneten Schaufelstufen Dichtmaßnahmen notwendig, um ein ungewolltes und exzessives Ausströmen von Kühlmedium in den mit Heißgas beaufschlagten Strömungskanal zu verhindern. Die zur Abdichtung erforderlichen Maßnahmen können zu strukturell und kühlungstechnisch schwierigen Situationen an einer thermisch hochbelasteten Plattformwand führen und stellen ein erhöhtes Versagenspotential für eine Turbinenschaufel und damit für eine Gasturbine dar.In the execution of a turbine blade of the type mentioned sealing measures are necessary in a parting line between platforms of adjacent turbine blades of the same blade stage or adjacent turbine blades of successively arranged blade stages to prevent unwanted and excessive leakage of cooling medium in the hot gas flow channel. The measures required for sealing can lead to structurally and cooling technically difficult situations on a thermally highly loaded platform wall and represent an increased failure potential for a turbine blade and thus for a gas turbine.
Üblicherweise wird die Abdichtung solcher Teilfugen durch den Einbau besonderer Dichtelemente erzielt. Diese müssen jedoch einerseits flexibel genug sein, um gleichzeitige Relativbewegungen benachbarter Teile, insbesondere benachbarter Turbinenschaufeln und ihrer Plattformen zuzulassen und andererseits müssen sie dennoch eine Dichtwirkung erhalten. Der Einbau solcher Dichtelemente führt zu geometrisch und strukturell komplizierten Bauteilen. Als Folge davon sind besondere Kühlmaßnahmen notwendig, um schwer zugängliche Randbereiche einer Plattform ausreichend zu kühlen. Eine andere Turbinenschaufel gemäß dem Stand der Tecknik ist aus der
An dieser Stelle setzt die Erfindung an, deren Aufgabe es ist, eine Turbinenschaufel mit einer Plattform anzugeben, die gleichzeitig einfach ausgestaltet ist und auch den geometrisch-strukturellen und kühlungstechnischen Anforderungen im Rahmen einer Strömungskanalbegrenzung einer Gasturbine vorteilhaft genügt. Ferner soll die Abdichtung der Teilfugen zwischen benachbarten Turbinenschaufeln besonders einfach und kostengünstig erfolgen.At this point, the invention is based, whose task is to provide a turbine blade with a platform that is simultaneously simple and also satisfies the geometrical-structural and cooling requirements within a flow channel limitation of a gas turbine advantageous. Furthermore, the sealing of the part joints between adjacent turbine blades should be particularly simple and inexpensive.
Betreffend die Turbinenschaufel wird die Aufgabe durch die Erfindung mit der eingangs genannten Turbinenschaufel gelöst, bei der erfindungsgemäß die Plattform durch ein erstes am Schaufelblatt festliegendes federelastisches Blechteil zumindest teilweise gebildet ist, welches an einem an einer benachbarten Turbinenschaufel angeordneten miteren Anschlag dichtend anlegbar ist.With regard to the turbine blade, the object is achieved by the invention with the turbine blade mentioned above, wherein according to the invention the platform is at least partially formed by a first resilient sheet metal part fixed to the airfoil which sealingly engages a smaller stop located on an adjacent turbine blade.
Die Erfindung geht von der Überlegung aus, dass die Verwendung einer nicht-tragenden Plattform zur Darstellung der Begrenzung eines mit Heißgas beaufschlagten Strömungskanals einer Gasturbine grundsätzlich geeignet ist, die Plattform, und damit die Begrenzung des Strömungskanals, möglichst effektiv zu kühlen. Darüber hinausgehend liegt die wesentliche Erkenntnis der Erfindung darin, dass es möglich ist, die Plattform selbst mit einer erhöhten Dichtwirkung auszustatten, und zwar indem die Plattform derart dünnwandig ausgeführt wird, dass sie durch ein am Schaufelblatt anliegendes federelastisches Blechteil gebildet ist.The invention is based on the consideration that the use of a non-load-bearing platform for the representation of the boundary of a hot gas flow channel of a gas turbine is fundamentally suitable for cooling the platform, and thus the boundary of the flow channel, as effectively as possible. Beyond that, the essential insight lies the invention in that it is possible to equip the platform itself with an increased sealing effect, namely by the platform is made so thin-walled that it is formed by a voltage applied to the blade leaf resilient sheet metal part.
Damit erfüllt nämlich die Plattform als ein den Heißgas beaufschlagten Strömungskanal begrenzendes Teil alle Anforderungen hinsichtlich der Kühlung und auch eines Dichtelements. Durch das am Schaufelblatt festliegende federelastische Blechteil ist die Plattform als solche nämlich ausreichend flexibel, um gleichzeitige Relativbewegungen benachbarter Schaufelblätter und anderer Teile zuzulassen und erhält dennoch die Dichtwirkung. Damit entfällt die Notwendigkeit für ein besonderes Dichtelement. Dies vereinfacht die Ausgestaltung und Kühlung der Strömungskanalbegrenzung.Thus, the platform as a part of the hot gas acted upon flow limiting part meets all requirements with regard to the cooling and also a sealing element. By virtue of the spring-elastic sheet-metal part fixed to the blade, the platform as such is sufficiently flexible to permit simultaneous relative movements of adjacent blades and other parts and still maintains the sealing effect. This eliminates the need for a special sealing element. This simplifies the design and cooling of the flow channel boundary.
Gemäß der Erfindung ist das erste federelastische Blechteil als eine nicht-tragende Plattformwand vorgesehen, die den heißgasbeaufschlagten Strömungskanal zumindest teilweise begrenzt. Eine wie in der
Das zwischen Plattformen benachbarter Turbinenschaufeln bisher nötige Dichtelement kann entfallen, da das erste federelastische Blechteil der einen Turbinenschaufel dicht an der anderen der benachbarten Turbinenschaufel anliegt.The previously required between platforms of adjacent turbine blades sealing element can be omitted, since the first resilient sheet metal part of a turbine blade rests close to the other of the adjacent turbine blade.
Die Vorteile hinsichtlich Kühlung und Dichtwirkung des ersten federelastischen Blechteils für die Plattform und damit der Strömungskanalbegrenzung bleiben bestehen.The advantages in terms of cooling and sealing effect of the first resilient sheet metal part for the platform and thus the flow channel limitation remain.
Vorteilhafte Weiterbildungen der Erfindung sind den Unteransprüchen zu entnehmen und geben im Einzelnen vorteilhafte Möglichkeiten an, insbesondere die Plattform hinsichtlich obiger Aufgabe weiterzubilden.Advantageous developments of the invention can be found in the dependent claims and specify in detail advantageous possibilities, in particular to further develop the platform with respect to the above task.
Gemäß einer besonders bevorzugten Weiterbildung der Erfindung ist vorgesehen, dass die Plattform durch das erste an einem ersten Anschlag auf der einen Seite des Schaufelblattes festliegendes federelastisches Blechteil gebildet ist und durch ein zweites an einem zweiten Anschlag auf der anderen Seite des Schaufelblattes festliegendes Blechteil gebildet ist. Damit sind zweckmäßigerweise zwei Blechteile vorgesehen, welche die Plattform bilden, die sich damit beidseitig auf der einen und der anderen Seite des Schaufelblattes quer zur Schaufelachse erstrecken.According to a particularly preferred embodiment of the invention, it is provided that the platform is formed by the first fixed to a first stop on one side of the airfoil elastic sheet metal part and is formed by a second at a second stop on the other side of the airfoil fixed sheet metal part. Thus, two sheet metal parts are expediently provided, which form the platform, which thus extend on both sides on one side and the other side of the airfoil transversely to the blade axis.
Zweckmäßigerweise übernimmt das am Schaufelblatt anliegende zweite Blechteil die Funktion einer ersten, das Schaufelblatt nicht-tragenden Plattformwand und die Plattform weist darüber hinaus eine zweite das Schaufelblatt tragende Plattformwand auf. Bei dieser Ausgestaltung ist zwischen der ersten nicht-tragenden Plattformwand aus dem zweiten Blechteil und der zweiten dicker ausgebildeten tragenden Plattformwand als eine besondere lasttragende Struktur ein entsprechender Kühlraum zur Beaufschlagung mit einem Kühlmedium gebildet.Expediently, the second sheet metal part resting against the blade leaf assumes the function of a first platform wall which does not carry the blade leaf, and the platform furthermore has a second platform wall carrying the blade leaf. In this embodiment, between the first non-supporting platform wall of the second sheet metal part and the second thicker supporting platform wall as a special load-bearing structure, a corresponding cooling space for pressurization with a cooling medium is formed.
Gemäß einer Weiterbildung der Erfindung kann jeder Anschlag in Form einer Nut oder Kante ausgebildet sein. Dies ermöglicht eine besonders zuverlässige und strömungstechnisch günstige Befestigung des Blechteils am Fuße des Schaufelblattes.According to one embodiment of the invention, each stop can be designed in the form of a groove or edge. This allows a particularly reliable and aerodynamically favorable attachment of the sheet metal part at the foot of the airfoil.
Im Rahmen einer bevorzugenden Weiterbildung der Erfindung hat es sich als zweckmäßig erwiesen, dass die Blechteile, insbesondere das erste, an einem weiteren Anschlag einer benachbarten Turbinenschaufel gehalten ist. Zweckmäßigerweise kann dieser weitere Anschlag in Form eines Auflagers gebildet sein. Beispielsweise kann ein solches Auflager durch eine zwischen Schaufelfuß und Fuß des Schaufelblattes angeformte Stufe gebildet sein. Das erste Blechteil einer ersten Turbinenschaufel hintergreift das Auflager der zu dieser benachbarten Turbinenschaufel dichtend. Das zweite Blechteil kann das an der gleichen Turbinenschaufel angeordnete Auflager vorteilhaft hintergreifen oder, zusätzlich oder alternativ, an der Stufe angefügt sein.As part of a preferred development of the invention, it has proven to be expedient that the sheet metal parts, in particular the first, is held on a further stop of an adjacent turbine blade. Conveniently, this further stop in the form of a support formed be. For example, such a support may be formed by a formed between the blade root and foot of the airfoil step. The first sheet metal part of a first turbine blade engages behind the bearing of the adjacent turbine blade sealing. The second sheet metal part can advantageously engage behind the support arranged on the same turbine blade or, in addition or as an alternative, be attached to the step.
Zweckmäßigerweise liegt das erste federelastische Blechteil im Ruhezustand lose an dem weiteren Anschlag der benachbarten Turbinenschaufel an. In diesem Fall ergibt sich eine noch zu erläuternde ausreichende Befestigung des Blechteils aus der Bewegung bzw. strömungstechnischen Anbindung der Turbinenschaufel im Betriebszustand einer Gasturbine.Advantageously, the first resilient sheet metal part in the rest state is loosely against the further stop of the adjacent turbine blade. In this case, there results a still to be explained sufficient attachment of the sheet metal part from the movement or fluidic connection of the turbine blade in the operating state of a gas turbine.
Die Dichtwirkung des ersten federelastischen Blechteils am weiteren Anschlag kann weiter verbessert werden, wenn das erste federelastische Blechteil unter einer selbst erzeugten Vorspannung an dem weiteren Anschlag anliegt.The sealing effect of the first resilient sheet metal part on the further stop can be further improved if the first resilient sheet metal part rests under a self-generated bias on the other stop.
Die Erfindung führt zur Lösung der Aufgabe darüber hinaus auf eine eingangs genannte Gasturbine, wobei eine Schaufelstufe eine Anzahl von ringförmig angeordneten sich radial in den Strömungskanal erstreckende Turbinenschaufeln aufweist, wobei erfindungsgemäß eine Turbinenschaufel gemäß einer oben genannten Art ausgeführt ist.The invention also leads to the achievement of the object on an initially mentioned gas turbine, wherein a blade stage comprises a number of annularly arranged radially in the flow channel extending turbine blades, wherein according to the invention a turbine blade is designed according to one of the above type.
Vorteilhafte Weiterbildungen der Gasturbine sind den weiteren Unteransprüchen zu entnehmen und geben im Einzelnen vorteilhafte Möglichkeiten an, insbesondere die Strömungskanalbegrenzung und die Funktionsweise der Turbinenschaufel im Rahmen der Strömungskanalbegrenzung im Sinne obiger Aufgabe auszugestalten.Advantageous developments of the gas turbine can be taken from the further subclaims and specify in particular advantageous possibilities, in particular to design the flow channel boundary and the mode of operation of the turbine blade within the scope of the flow channel limitation in the sense of the above problem.
Im Rahmen einer ersten Weiterbildung ist die Turbinenschaufel eine Laufschaufel. Eine solche Laufschaufel ist an einem sich axial erstreckenden Turbinenrotor befestigt und dreht sich bei Betrieb der Gasturbine mit dem Turbinenrotor. Bei rotatorischem Betrieb einer Turbinenschaufel in Form einer Laufschaufel an dem Turbinenrotor ist eine durch die Rotation vom Fuße des Schaufelblattes her in Richtung des Schaufelblattes wirkende Fliehkraft erzeugt. Dabei sieht die Weiterbildung vor, dass das erste federelastische Blechteil eine ausreichende Dichtwirkung zwischen zwei aneinander angrenzenden Blechteilen zweier benachbarten Laufschaufeln erreicht. Durch die Fliehkraft wird das erste federelastische Blechteil einer ersten Laufschaufel gegen einen weiteren Anschlag der zweiten Laufschaufel gedrückt und dadurch fliehkraftbefestigt angelegt. Also ist, selbst im Falle, dass das erste federelastische Blechteil im Ruhezustand der Laufschaufel lose an dem weiteren Anschlag anliegt, wird durch die Fliehkraft gewährleistet, dass das federelastische Blechteil im Betriebszustand an der Laufschaufel dichtend anliegt. Bei Betrieb der Laufschaufel der Gasturbine hat das erste federelastische Blechteil also auch die Funktion eines Dichtelements. Dabei wirkt vorteilhaft die Anlagefläche des ersten federelastischen Blechteils an dem weiteren Anschlag der benachbarten Laufschaufel in Form eines Auflagers als dichtendes Widerlager für das erste Blechteil. Das Eindringen von die Turbine durchströmenden Heißgas durch den zwischen bisher von zwei Plattformen benachbarter Laufschaufeln gebildeten Spalt kann aufgrund der wirksamen Dichtung ebenso vermieden werden wie eine ungewollt große Leckage an Kühlmittel durch den Spalt in den Heißgasraum hinein.In the context of a first development, the turbine blade is a blade. Such a blade is at one attached axially rotating turbine rotor and rotates when operating the gas turbine with the turbine rotor. During rotary operation of a turbine blade in the form of a blade on the turbine rotor, a centrifugal force acting through the rotation from the base of the blade in the direction of the blade is generated. In this case, the development provides that the first resilient sheet metal part reaches a sufficient sealing effect between two adjacent sheet metal parts of two adjacent blades. Due to the centrifugal force, the first resilient sheet metal part of a first blade is pressed against a further stop of the second blade and thereby applied centrifugally mounted. Thus, even in the case that the first resilient sheet metal part in the resting state of the blade loosely rests against the further stop, is ensured by the centrifugal force that the resilient sheet metal part in the operating state against the blade sealingly. When operating the blade of the gas turbine, the first resilient sheet metal part also has the function of a sealing element. Advantageously, the contact surface of the first resilient sheet metal part acts on the further stop of the adjacent blade in the form of a support as a sealing abutment for the first sheet metal part. The penetration of hot gas flowing through the turbine through the gap formed between previously two platforms of adjacent blades can be avoided due to the effective seal as well as an unintentionally large leakage of coolant through the gap into the hot gas space inside.
Gemäß einer alternativen Weiterbildung der Gasturbine ist die Turbinenschaufel als Leitschaufel an einem peripheren Turbinengehäuse vorgesehen. Bei Betrieb einer Turbinenschaufel in Form einer Leitschaufel an dem Turbinengehäuse ist durch ein Kühlmedium ein Druckgefälle vom Fuße des Schaufelblattes her in Richtung des Schaufelblattes erzeugt. Dabei sieht die alternative Weiterbildung vor, dass das erste federelastische Blechteil einer ersten Leitschaufel durch das Druckgefälle gegen den weiteren Anschlag einer zweiten Leitschaufel gedrückt und dadurch druckbefestigt wird. Das Druckgefälle wird also dadurch erzeugt, dass das erste federelastische Blechteil von hinten mit Kühlmedium beaufschlagt wird und dadurch gegen den weiteren Anschlag gedrückt wird. Für eine Leitschaufel ist das Druckgefälle ausreichend groß, so dass dies nicht nur für eine Druckbefestigung des ersten federelastischen Blechteils an dem weiteren Anschlag ausreicht, sondern darüber hinaus bei Betrieb der Leitschaufel in der Gasturbine das erste federelastische Blechteil die Funktion eines Dichtelements hat. Die Anlageflächen des ersten federelastischen Blechteils wirken an einem oben erläuterten Anschlag als ausreichende Dichtflächen und der Anschlag als Widerlager für das erste federelastische Blechteil.According to an alternative development of the gas turbine, the turbine blade is provided as a guide vane on a peripheral turbine housing. When operating a turbine blade in the form of a guide vane on the turbine housing, a pressure gradient from the foot of the airfoil is produced in the direction of the airfoil by means of a cooling medium. The alternative development provides that the first resilient sheet metal part of a first vane through the Pressure gradient is pressed against the further stop a second vane and thereby pressure-fastened. The pressure gradient is thus generated by the fact that the first resilient sheet metal part is acted upon from the back with cooling medium and is thereby pressed against the other stop. For a guide vane, the pressure gradient is sufficiently large, so that this is sufficient not only for a pressure fastening of the first resilient sheet metal part to the other stop, but also has the first resilient sheet metal part has the function of a sealing element during operation of the guide vane in the gas turbine. The contact surfaces of the first resilient sheet metal part act on a stop described above as sufficient sealing surfaces and the stop as an abutment for the first resilient sheet metal part.
Im Rahmen einer Ausgestaltung der Gasturbine erweist es sich als vorteilhaft, dass zwischen einer ersten Turbinenschaufel und einer benachbarten zweiten Turbinenschaufel der gleichen Schaufelstufe von einem ersten federelastischen Blechteil der ersten Turbinenschaufel und von einem zweiten Blechteil der zweiten Turbinenschaufel eine Begrenzung des Strömungskanals gebildet ist, die durchgehend ist. Innerhalb einer Schaufelstufe wird auf diese Weise vorteilhaft eine durchgehende radiale Begrenzung des Strömungskanals gebildet.In the context of an embodiment of the gas turbine, it proves to be advantageous that between a first turbine blade and an adjacent second turbine blade of the same blade stage of a first resilient sheet metal part of the first turbine blade and a second sheet metal part of the second turbine blade a boundary of the flow channel is formed, the continuous is. Within a blade stage, a continuous radial boundary of the flow channel is advantageously formed in this way.
Im Rahmen einer weiteren Ausgestaltung der Gasturbine erweist es sich darüber hinaus als vorteilhaft, dass zwischen einer ersten Turbinenschaufel der ersten Schaufelstufe und einer bezogen auf den Rotor axial zur ersten Turbinenschaufel benachbarten zweiten Turbinenschaufel der zweiten Schaufelstufe von einem ersten federelastischen Blechteil der ersten Turbinenschaufel und von einem zweiten Blechteil der zweiten Turbinenschaufel eine Begrenzung des Strömungskanals gebildet ist, die durchgehend ist. Auf diese Weise wird vorteilhaft eine durchgehende axiale Begrenzung des Strömungskanals gebildet. Vorteilhaft handelt es sich bei den Schaufelstufen um Leitschaufelstufen und bei den Turbinenschaufeln um Leitschaufeln.In the context of a further embodiment of the gas turbine, it also proves to be advantageous that between a first turbine blade of the first blade stage and a second turbine blade of the second blade stage adjacent to the rotor axially to the first turbine blade of a first resilient sheet metal part of the first turbine blade and of a second sheet metal part of the second turbine blade, a boundary of the flow channel is formed, which is continuous. In this way, a continuous axial boundary of the flow channel is advantageously formed. Advantageously, it is in the Vane stages around vanes and turbine blades around vanes.
Wegen der oben erwähnten Arten einer durchgehenden Begrenzung entfallen nämlich die bei üblichen Begrenzungen eines Strömungskanals einer Gasturbine sonst abzudichtenden Teilfugen und die dann zusätzlich benötigten Dichtelemente. Die im Zusammenhang mit Dichtelementen auftretenden Probleme werden aufgrund der durchgehenden Begrenzung des Strömungskanals mit dem ersten federelastischen und dem zweiten Blechteil völlig beseitigt.Because of the above-mentioned types of continuous boundary namely accounts for the usual limitations of a flow channel of a gas turbine otherwise sealed part joints and then additionally required sealing elements. The problems associated with sealing elements are completely eliminated due to the continuous boundary of the flow channel with the first resilient and the second sheet metal part.
Dabei erweist es sich als zweckmäßig, dass ein erstes an einer ersten Turbinenschaufel angeordnetes federelastisches Blechteil und ein zweites an einer zweiten Turbinenschaufel angeordnetes Blechteil gemeinsam an dem weiteren Anschlag der ersten Turbinenschaufel gehalten sind. Details sind im Zusammenhang mit der Zeichnung erläutert.It proves to be expedient that a first arranged on a first turbine blade spring-elastic sheet metal part and a second arranged on a second turbine blade sheet metal part are held together on the further stop of the first turbine blade. Details are explained in connection with the drawing.
Ein besonders bevorzugtes Ausführungsbeispiel der Erfindung wird nachfolgend anhand der Zeichnung beschrieben. Diese soll das Ausführungsbeispiel nicht maßgeblich darstellen, vielmehr ist die Zeichnung, wo zur Erläuterung dienlich, in schematisierter und/oder leicht verzerrter Form ausgeführt. Im Hinblick auf Ergänzungen der aus der Zeichnung unmittelbar erkennbaren Lehren wird auf den einschlägigen Stand der Technik verwiesen. Im Einzelnen zeigt die Zeichnung in:
- FIG 1
- eine besonders bevorzugte Ausführungsform einer Gas- turbine mit einem Strömungskanal und einer bevorzug- ten Ausführung der Leit- und Laufbeschaufelung in schematisierter Form in einer Querschnittsansicht;
- FIG 2
- einen Plattformbereich einer besonders bevorzugten Ausführungsform einer ersten Turbinenschaufel einer ersten Schaufelstufe und einer axial zur ersten Turbinenschaufel benachbarten zweiten Tur- binenschaufel einer zweiten Schaufelstufe in perspek- tivischer Ansicht.
- FIG. 1
- a particularly preferred embodiment of a gas turbine with a flow channel and a preferred embodiment of the guide and blading in a schematic form in a cross-sectional view;
- FIG. 2
- a platform region of a particularly preferred embodiment of a first turbine blade of a first blade stage and of a second turbine blade adjacent to the first turbine blade Bell bucket of a second bucket stage in a perspective view.
Eine Leitschaufel 21 und eine Laufschaufel 23 sind in der
Eine Laufschaufel 23 weist eine entlang einer Schaufelachse angeordnete Schaufelspitze 37, ein Schaufelblatt 39 und einen Plattformbereich 41 auf. Der Plattformbereich 41 weist eine sich quer zur Schaufelachse 45 erstreckende Plattform 43 und einen Schaufelfuß 47 auf.A
Die Plattform 33 einer Leitschaufel 21 und die Plattform 43 einer Laufschaufel 23 bilden dabei jeweils einen Teil einer Begrenzung 49, 51 des Strömungskanals 5 für das Arbeitsmedium M, welches die Gasturbine 1 durchströmt. Die periphere Begrenzung 49 ist dabei Teil des peripheren Turbinengehäuses 15. Die rotorseitige Begrenzung 51 ist dabei Teil des im Betriebszustand der Gasturbine 1 sich drehenden Turbinenrotors 19.The
Wie in der
Die
Die erste Turbinenschaufel 63 weist ein im Abbruch gezeichnetes Schaufelblatt 69 auf. Die zweite Turbinenschaufel 65 weist dabei ein im Abbruch gezeichnetes Schaufelblatt 67 auf. Bei der ersten Turbinenschaufel 63 und der zweiten Turbinenschaufel 65 ist im Plattformbereich 61 am Fuße des Schaufelblattes 67, 69 eine Plattform 71 gebildet, die sich quer zur Schaufelachse 73, 75 erstreckt. Dabei ist die Plattform 71 zum einen durch ein bei der ersten Schaufel 63 gezeigtes erstes federelastisches Blechteil 79 und zum anderen durch ein bei der zweiten Schaufel 65 gezeigtes, zweites Blechteil 77 gebildet. Das erste federelastische Blechteil 79 ist an einem ersten Anschlag 83 auf der einen Seite des Schaufelblattes 69 befestigt, welche Seite bei der ersten Turbinenschaufel 63 gezeigt ist. Das zweite federelastische Blechteil 77 ist an einem zweiten Anschlag 81 auf der anderen Seite des Schaufelblattes 67 befestigt, welche Seite bei der zweiten Turbinenschaufel 65 gezeigt ist. Die Befestigung kann beispielsweise durch Schweißen oder Löten erfolgen und ist dabei dicht. Der erste Anschlag 83 und der zweite Anschlag 81 ist dabei jeweils in Form einer Nut ausgebildet, in welche jeweils das erste federelastische Blechteil 79 und das zweite Blechteil 77 jeweils mit seiner am Schaufelblatt 69 bzw. am Schaufelblatt 67 endenden Kante einstößt. Das zweite federelastische Blechteil 77 ist darüber hinaus an einem weiteren Anschlag 85 der zweiten Turbinenschaufel 65 gehalten. Bei der vorliegenden Ausführungsform ist das zweite Blechteil 77 am Anschlag 85 angefügt. Alternativ oder zusätzlich könnte das zweite Blechteil 77 auch den weiteren Anschlag 85 hintergreifen. Letzteres ist der Fall für das erste federelastische Blechteil 79 der ersten Turbinenschaufel 63, das gemeinsam mit dem zweiten Blechteil 77 an dem weiteren Anschlag 85 der zweiten Turbinenschaufel 67 gehalten ist. Dazu hintergreift das erste federelastische Blechteil 79 lose den weiteren Anschlag 85. Der weitere Anschlag 85 ist zum Halten des zweiten Blechteils 77 und des ersten federelastischen Blechteils 79 in Form eines Auflagers ausgebildet und bildet somit auf seiner dem ersten federelastischen Blechteil 79 zugewandten Seite eine Dichtfläche, die als Widerlager für das erste federelastische Blechteil 79 dient.The
Auf die oben geschilderte Weise ist zwischen der ersten Turbinenschaufel 63 und der zweiten Turbinenschaufel 65 vom ersten federelastischen Blechteil 79 der ersten Turbinenschaufel 63 und vom zweiten Blechteil 77 der zweiten Turbinenschaufel 65 eine Begrenzung 87 des Strömungskanals 5 gebildet, wobei die Begrenzung 87 durchgehend ist. Auf diese Weise erlaubt die Verwendung einer dünnwandigen, nicht-tragenden Plattform 71 zur Darstellung der Begrenzung 87 in Form eines zweiten Blechteils 77 und eines ersten federelastischen Blechteils 79 die gleichzeitige Wirkung der Blechteile 77, 79 als ein Dichtelement. Ein Dichtelement dieser Art ist gleichzeitig flexibel genug, um Relativbewegungen der benachbarten ersten Turbinenschaufel 63 und zweiten Turbinenschaufel 65 zu erlauben und hat dennoch eine ausreichende Dichtwirkung. Dadurch wird ein Dichtelement eingespart, wie es bei bisher üblichen aneinander gegenüberliegenden Plattformen zur Abdichtung von Teilfugen notwendig gewesen wäre. Potentiell gefährdete, strukturell und thermisch ungünstige Aufnahmekonstruktionen eines solchen Dichtelements werden damit vermieden.In the manner described above, between the
Bei der hier gezeigten Ausführungsform kommt die Plattform 71 auf ihrer Rückseite 89 weitgehend ohne eine Stützkonstruktion oder eine tragende Plattformbewandung aus. Vielmehr ist auf der Rückseite 89 ein erster Kühlraum 93 und ein zweiter Kühlraum 91 gebildet, die es erlauben, die Plattform 71 in dem Bereich zwischen der zweiten Turbinenschaufel 65 und der ersten Turbinenschaufel 63 optimal zu kühlen. Auf diese Weise kann eine sonst üblicherweise kompliziert auszugestaltende Plattformrandkonstruktion im Zusammenhang mit dem weiteren Anschlag 85 einfacher und ohne thermisch gefährdeten Bereich gestaltet werden. Zur Unterstützung der Kühlung in den Kühlräumen 91, 93 ist die vom Fuße des Schaufelblattes 67, 69 ausgehende Tragkonstruktion 95, 97 der Turbinenschaufeln 65, 63 gestaltoptimiert zum Schaufelfuß 35, 47 in der
Je nach Betriebsweise der ersten Turbinenschaufel 63 und der zweiten Turbinenschaufel 65, vorzugsweise in Form einer in der
Bei Betrieb einer Turbinenschaufel 65, 63 in Form einer in
Zusammenfassend wird, um eine Begrenzung 87 eines Strömungskanals 5 einer Gasturbine 1 möglichst einfach auszugestalten, bei einer Turbinenschaufel 63, 65 mit einem entlang einer Schaufelachse 73, 75 angeordnete Schaufelblatt 67, 69 und mit einem Plattformbereich 61, der am Fuße des Schaufelblattes 67, 69 angeordnet eine Plattform 71 aufweist, die sich quer zur Schaufelachse 73, 75 erstreckt, vorgeschlagen, dass die Plattform 71 durch ein am Schaufelblatt 67, 69 festliegendes Blechteil 77, 79 gebildet ist. Dies führt auch auf eine Gasturbine 1 mit einem sich entlang einer Achse 3 der Gasturbine 1 erstreckenden Strömungskanal 5 mit ringförmigem Querschnitt für ein Arbeitsmedium M, einer zweiten 9, 13 hinter einer ersten 7, 11 entlang der Achse 3 angeordneten Schaufelstufe wobei eine Schaufelstufe 7, 9, 11, 13 eine Anzahl von ringförmig angeordneten, sich radial in den Kanal 5 erstreckende Turbinenschaufeln 63, 65 gemäß dem obigen Konzept aufweist.To summarize, in order to design a
- 11
- Gasturbinegas turbine
- 33
- Achseaxis
- 55
- Strömungskanalflow channel
- 7, 97, 9
- Leitschaufelstufevane stage
- 11, 1311, 13
- LaufschaufelstufeBlade stage
- 1515
- Turbinengehäuseturbine housing
- 1717
- Brennerburner
- 1919
- Turbinenrotorturbine rotor
- 2121
- Leitschaufelvane
- 2323
- Laufschaufelblade
- 25, 4525, 45
- Schaufelachseblade axis
- 27, 3727, 37
- Schaufelspitzeblade tip
- 29, 3929, 39
- Schaufelblattairfoil
- 31, 4131, 41
- Plattformbereichdeck area
- 33, 4333, 43
- Plattformplatform
- 35, 4735, 47
- Schaufelfußblade
- 49, 5149, 51
- Begrenzunglimit
- 6161
- Plattformbereichdeck area
- 63, 6563, 65
- Turbinenschaufelturbine blade
- 67, 6967, 69
- Schaufelblattairfoil
- 7171
- Plattformplatform
- 73, 7573, 75
- Schaufelachseblade axis
- 77, 7977, 79
- Blechteilsheet metal part
- 81, 8381, 83
- Anschlagattack
- 8585
- Anschlagattack
- 8787
- Begrenzunglimit
- 8989
- Rückseiteback
- 91, 9391, 93
- Kühlraumrefrigerator
- 95, 9795, 97
- Tragkonstruktionsupporting structure
- 9999
- Richtungdirection
- MM
- Arbeitsmediumworking medium
Claims (14)
- Turbine blade (63, 65) with a blade leaf (67, 69) arranged along a blade axis (73, 75) and with a platform region (61), which, arranged at the foot of the blade leaf (67, 69), has a platform (71) extending transversely with respect to the blade axis (73, 75), the platform (71) being formed at least partially by first resilient elastic sheet metal part (79) fixed to a first abutment (83) arranged on the blade leaf (67, 69), characterized in that the sheet metal part (79) can be laid sealingly against the further abutment (85) arranged on an adjacent turbine blade (63, 65).
- Turbine blade (63, 65) according to Claim 1, characterized in that the platform (71) comprises a second sheet metal part (77) fixed to a second abutment (81) on the other side of the blade leaf (67).
- Turbine blade (63, 65) according to Claim 2, characterized in that each abutment (81, 83) is designed in the form of a groove or edge.
- Turbine blade (63, 65) according to one of Claims 1 to 3, characterized in that the further abutment (85) is produced in the form of a bearing support.
- Turbine blade (63, 65) according to one of Claims 1 to 4, characterized in that, in the state of rest of the turbine blade (63, 65), the first resilient elastic sheet metal part (79) lies loosely against the further abutment (85).
- Turbine blade (63, 65) according to one of Claims 1 to 5, characterized in that the first resilient elastic sheet metal part (79) lies against the further abutment (85) under a self-generated prestress.
- Turbine blade (63, 65) according to one of Claims 1 to 6, characterized in that the platform region (61) has a blade foot (35, 47) as a load-bearing structure.
- Gas turbine (1), with a flow duct (5) extending along an axis (3) having an annular cross section for a working medium (M), and a second (9, 13) blade stage arranged downstream of a first (7, 11) along the axis (3), a blade stage (7, 9, 11, 13) having a number of annularly arranged turbine blades (63, 65) according to one of the preceding claims which extend radially into the flow duct (5).
- Gas turbine (1) according to Claim 8, characterized in that, during the rotary operation of a turbine blade (63, 65) in the form of a moving blade (23) on an axial turbine rotor (19), a centrifugal force acting from the foot of the blade leaf in the direction (99) of the blade leaf is generated as the result of rotation, the first resilient elastic sheet metal part (79) being pressed against a further abutment (85) by means of the centrifugal force and thereby lying against the latter, fastened by centrifugal force.
- Gas turbine (1) according to Claim 8, characterized in that, during the operation of a turbine blade (63, 65) in the form of a guide blade (21) on a peripheral turbine casing (15), a pressure drop from the foot of the blade leaf in the direction (99) of the blade leaf is generated by a cooling medium, the first resilient elastic sheet metal part (79) being pressed against a further abutment (85) by means of the pressure drop and thereby lying against the latter, fastened by pressure.
- Gas turbine (1) according to Claim 8 to 10, characterized in that, during the operation of the turbine blade (63, 65) in the gas turbine (1), the first resilient elastic sheet metal part (79) has the function of a sealing element.
- Gas turbine (1) according to one of Claims 8 to 11, characterized in that a boundary of the flow duct (5), which boundary is continuous, is formed, between a first turbine blade (63) and an adjacent second turbine blade (65) of the same blade stage (7, 9, 11, 13), by a first resilient elastic sheet metal part (79) of the first turbine blade (63) and by a second sheet metal part (77) of the second turbine blade (65).
- Gas turbine (1) according to one of Claims 8 to 11, characterized in that a boundary (87) of the flow duct (5), which boundary is continuous, is formed, between a first turbine blade (63) of the first blade stage (7, 11) and a second turbine blade (65), axially adjacent to the first turbine blade (63), of the second blade stage (9, 13), by a first resilient elastic sheet metal part (79) of the first turbine blade (63) and by a second sheet metal part (77) of the second turbine blade (63).
- Gas turbine (1) according to one of Claims 8 to 12, characterized in that a first resilient elastic sheet metal part (77) arranged on a first turbine blade (63) and a second sheet metal part (79) arranged on a second turbine blade (65) are held jointly at a further abutment (85) of one of the two turbine blades (63, 65).
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
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EP05706868A EP1706593B1 (en) | 2004-01-20 | 2005-01-12 | Turbine blade and gas turbine with such a turbine blade |
PL05706868T PL1706593T3 (en) | 2004-01-20 | 2005-01-12 | Turbine blade and gas turbine with such a turbine blade |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
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EP04001107A EP1557534A1 (en) | 2004-01-20 | 2004-01-20 | Turbine blade and gas turbine with such a turbine blade |
EP05706868A EP1706593B1 (en) | 2004-01-20 | 2005-01-12 | Turbine blade and gas turbine with such a turbine blade |
PCT/EP2005/000223 WO2005068785A1 (en) | 2004-01-20 | 2005-01-12 | Turbine blade and gas turbine equipped with a turbine blade of this type |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1706593A1 EP1706593A1 (en) | 2006-10-04 |
EP1706593B1 true EP1706593B1 (en) | 2011-08-17 |
Family
ID=34626466
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04001107A Withdrawn EP1557534A1 (en) | 2004-01-20 | 2004-01-20 | Turbine blade and gas turbine with such a turbine blade |
EP05706868A Not-in-force EP1706593B1 (en) | 2004-01-20 | 2005-01-12 | Turbine blade and gas turbine with such a turbine blade |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04001107A Withdrawn EP1557534A1 (en) | 2004-01-20 | 2004-01-20 | Turbine blade and gas turbine with such a turbine blade |
Country Status (9)
Country | Link |
---|---|
US (2) | US7607889B2 (en) |
EP (2) | EP1557534A1 (en) |
JP (1) | JP4499747B2 (en) |
CN (1) | CN100400795C (en) |
AT (1) | ATE520862T1 (en) |
ES (1) | ES2370644T3 (en) |
PL (1) | PL1706593T3 (en) |
RU (1) | RU2332575C2 (en) |
WO (1) | WO2005068785A1 (en) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7766609B1 (en) * | 2007-05-24 | 2010-08-03 | Florida Turbine Technologies, Inc. | Turbine vane endwall with float wall heat shield |
US20100003139A1 (en) * | 2008-07-03 | 2010-01-07 | Rotating Composite Technologies, Llc | Propulsor devices having variable pitch fan blades with spherical support and damping surfaces |
CN102196961B (en) * | 2008-09-29 | 2014-09-17 | 安德鲁·L·本德 | High efficiency turbine |
EP2282014A1 (en) * | 2009-06-23 | 2011-02-09 | Siemens Aktiengesellschaft | Ring-shaped flow channel section for a turbo engine |
US8356975B2 (en) * | 2010-03-23 | 2013-01-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured vane platform |
US9976433B2 (en) | 2010-04-02 | 2018-05-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured rotor blade platform |
US8550785B2 (en) | 2010-06-11 | 2013-10-08 | Siemens Energy, Inc. | Wire seal for metering of turbine blade cooling fluids |
RU2457336C1 (en) * | 2011-01-11 | 2012-07-27 | Светлана Владимировна Иванникова | Higher-efficiency turbine blading (versions) |
US20170049331A1 (en) * | 2011-05-02 | 2017-02-23 | Canon Kabushiki Kaisha | Object information acquiring apparatus and method of controlling the same |
US8961134B2 (en) * | 2011-06-29 | 2015-02-24 | Siemens Energy, Inc. | Turbine blade or vane with separate endwall |
US11035238B2 (en) * | 2012-06-19 | 2021-06-15 | Raytheon Technologies Corporation | Airfoil including adhesively bonded shroud |
US10344606B2 (en) * | 2013-04-01 | 2019-07-09 | United Technologies Corporation | Stator vane arrangement for a turbine engine |
JP6547274B2 (en) | 2014-10-20 | 2019-07-24 | 株式会社デンソー | Particulate matter detection sensor |
US10371162B2 (en) | 2016-10-05 | 2019-08-06 | Pratt & Whitney Canada Corp. | Integrally bladed fan rotor |
US11852018B1 (en) * | 2022-08-10 | 2023-12-26 | General Electric Company | Turbine nozzle with planar surface adjacent side slash face |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE579989C (en) * | 1933-07-04 | Karl Roeder Dr Ing | No-head blading for axially loaded steam or gas turbines | |
CH291898A (en) | 1951-06-09 | 1953-07-15 | Escher Wyss Ag | Blading on rotors of centrifugal machines with axial flow, especially steam, gas turbines and compressors. |
GB1119392A (en) * | 1966-06-03 | 1968-07-10 | Rover Co Ltd | Axial flow rotor for a turbine or the like |
US3446481A (en) | 1967-03-24 | 1969-05-27 | Gen Electric | Liquid cooled turbine rotor |
DE1801475B2 (en) * | 1968-10-05 | 1971-08-12 | Daimler Benz Ag, 7000 Stuttgart | AIR-COOLED TURBINE BLADE |
IT1079131B (en) | 1975-06-30 | 1985-05-08 | Gen Electric | IMPROVED COOLING APPLICABLE IN PARTICULAR TO ELEMENTS OF GAS TURBO ENGINES |
FR2503247B1 (en) * | 1981-04-07 | 1985-06-14 | Snecma | IMPROVEMENTS ON THE FLOORS OF A GAS TURBINE OF TURBOREACTORS PROVIDED WITH AIR COOLING MEANS OF THE TURBINE WHEEL DISC |
CH667493A5 (en) | 1985-05-31 | 1988-10-14 | Bbc Brown Boveri & Cie | DAMPING ELEMENT FOR DETACHED TURBO MACHINE BLADES. |
GB2251897B (en) * | 1991-01-15 | 1994-11-30 | Rolls Royce Plc | A rotor |
US6533544B1 (en) | 1998-04-21 | 2003-03-18 | Siemens Aktiengesellschaft | Turbine blade |
US6431835B1 (en) * | 2000-10-17 | 2002-08-13 | Honeywell International, Inc. | Fan blade compliant shim |
FR2831207B1 (en) * | 2001-10-24 | 2004-06-04 | Snecma Moteurs | PLATFORMS FOR BLADES OF A ROTARY ASSEMBLY |
US6860722B2 (en) * | 2003-01-31 | 2005-03-01 | General Electric Company | Snap on blade shim |
DE10340773A1 (en) | 2003-09-02 | 2005-03-24 | Man Turbomaschinen Ag | Rotor of a steam or gas turbine |
-
2004
- 2004-01-20 EP EP04001107A patent/EP1557534A1/en not_active Withdrawn
-
2005
- 2005-01-12 EP EP05706868A patent/EP1706593B1/en not_active Not-in-force
- 2005-01-12 WO PCT/EP2005/000223 patent/WO2005068785A1/en active Application Filing
- 2005-01-12 CN CNB2005800019558A patent/CN100400795C/en not_active Expired - Fee Related
- 2005-01-12 RU RU2006129944/06A patent/RU2332575C2/en not_active IP Right Cessation
- 2005-01-12 ES ES05706868T patent/ES2370644T3/en active Active
- 2005-01-12 PL PL05706868T patent/PL1706593T3/en unknown
- 2005-01-12 US US10/586,462 patent/US7607889B2/en not_active Expired - Fee Related
- 2005-01-12 JP JP2006548254A patent/JP4499747B2/en not_active Expired - Fee Related
- 2005-01-12 AT AT05706868T patent/ATE520862T1/en active
-
2009
- 2009-09-21 US US12/563,369 patent/US7963746B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
US20100008773A1 (en) | 2010-01-14 |
US20080232956A1 (en) | 2008-09-25 |
RU2006129944A (en) | 2008-02-27 |
JP2007518917A (en) | 2007-07-12 |
EP1706593A1 (en) | 2006-10-04 |
CN100400795C (en) | 2008-07-09 |
US7963746B2 (en) | 2011-06-21 |
JP4499747B2 (en) | 2010-07-07 |
ES2370644T3 (en) | 2011-12-21 |
RU2332575C2 (en) | 2008-08-27 |
CN1906380A (en) | 2007-01-31 |
WO2005068785A1 (en) | 2005-07-28 |
EP1557534A1 (en) | 2005-07-27 |
ATE520862T1 (en) | 2011-09-15 |
PL1706593T3 (en) | 2012-01-31 |
US7607889B2 (en) | 2009-10-27 |
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