EP2218918A1 - Axial turbo compressor for a gas turbine with low blade-tip leakage losses and diffuser losses - Google Patents
Axial turbo compressor for a gas turbine with low blade-tip leakage losses and diffuser losses Download PDFInfo
- Publication number
- EP2218918A1 EP2218918A1 EP09002056A EP09002056A EP2218918A1 EP 2218918 A1 EP2218918 A1 EP 2218918A1 EP 09002056 A EP09002056 A EP 09002056A EP 09002056 A EP09002056 A EP 09002056A EP 2218918 A1 EP2218918 A1 EP 2218918A1
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- European Patent Office
- Prior art keywords
- shaft cover
- blade
- axial
- tips
- turbo compressor
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- 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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- 230000007423 decrease Effects 0.000 description 4
- 238000011084 recovery Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 230000001473 noxious effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/545—Ducts
- F04D29/547—Ducts having a special shape in order to influence fluid flow
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
- F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
Definitions
- the invention relates to a Axialturbover Why a gas turbine, wherein the Axialturbover Why a gas turbine has low gap losses.
- a gas turbine has a turbocompressor, for example, in axial construction.
- the turbocompressor has a housing with a stator attached thereto and a rotor surrounded by the housing.
- the rotor has a shaft on which the rotor is driven in rotation.
- a shaft cover Surrounding the shaft, a shaft cover is provided, whose outer contour together with the inner contour of the housing forms part of the flow channel through the turbocompressor.
- the flow channel has a cross section which widens in the flow direction, so that the flow channel is designed as a diffuser.
- the rotor has a plurality of rotor stages, each formed by a row of rotor blades. Furthermore, the stator has a plurality of stator blade rows, which are arranged alternately to the rows of rotor blades when viewed in the axial direction. Conventionally, seen in the flow direction after the last row of rotor blades, a row of vanes and then a Nachleitschaufelsch arranged.
- the rows of vanes have a plurality of blades, which are fastened with their one end respectively to the housing and with its other end pointing in the direction of the shaft.
- a blade tip is formed, which faces the shaft cover and is disposed immediately adjacent.
- the distance between the blade tips and the shaft cover is formed as a radial gap, which is dimensioned such that on the one hand, the blade tips do not abut the shaft cover during operation of the gas turbine and, on the other hand, the leakage flow through the radial gap that occurs during operation of the gas turbine is as low as possible.
- This gap must therefore be designed as low as possible, so that a high efficiency can be achieved and the full blading potential of the compressor can be exploited.
- the casing of the turbo-compressor is massively designed to withstand the pressure and temperature stresses in the operation of the gas turbine.
- the housing is rigid, so that the load application to the housing during operation of the gas turbine has only a small deformation of the housing result.
- the shaft cover is exposed to lower mechanical stresses during operation of the gas turbine, whereby the shaft cover is made thinner and less massive than the housing.
- the shaft cover is formed with smaller wall thicknesses compared to the housing and typically has different material properties than the housing, the shaft cover heats up faster than the housing with the guide blade rows attached thereto. This has the consequence that for starting and stopping the gas turbine, the shaft cover and the housing have a different thermal expansion rate, so that when starting and stopping the gas turbine, the height of the radial gap changes, the radial gap when starting is temporarily smaller and larger when starting.
- the radial gap is provided with a minimum height dimensioned such that in every operating state of the gas turbine - stationary and unsteady - the blade tips almost never touch the shaft cover. This has the consequence that at the blade tips a corresponding dimensioned radial gap is maintained, which leads to a reduction in the efficiency of the gas turbine.
- the blockage caused by the radial gap leads to a reduction of the main flow component, whereby the pressure recovery in the diffuser is reduced and disadvantageous detachment phenomena may occur.
- the object of the invention is to provide a Axialturbover Actually Noticer for a gas turbine, which has a high efficiency and high reliability.
- the axial turbocompressor for a gas turbine engine comprises a vane grille formed by vanes with hub-side freestanding blade tips, and a stationary shaft cover located immediately adjacent the blade tips on the hub side and defining the flow passage of the axial compressor with a gap between the shaft cover and the blade tips is formed, which is minimally dimensioned so that just the assembling of the Axialturbover Whyrs betechnikstelligbar, and in the shaft cover a plurality of recesses is provided, each blade tip is associated with one of the recesses immediately adjacent to its associated blade tip and so is dimensioned such that during operation of the Axialturbover Whyrs each blade tip is plunged into its associated recess without one of the blade tips, the shaft cover significantly affected.
- the gap between the blade tip and the shaft cover is set to the minimum necessary mounting gap, so that the height of the gap is reduced to the assembly-related minimum.
- the height of the minimal necessary mounting gap is chosen such that the Einkugeln the guide vane grille, in particular the rear vane grille, can be accomplished.
- the gap between the blade tips and the shaft cover is provided with a minimum height that is selected such that, as in all imaginable operating conditions of the gas turbine, the blade tips hardly or not touch the shaft cover. This results in the gap with such a height that flows through the gap a significant mass flow of leakage flow, which leads to an undesirable efficiency reduction of the gas turbine.
- the gap is set to the minimum possible gap, namely to the minimum necessary assembly gap, so that the leakage flow through the gap is minimal.
- the axial turbocompressor has a high pressure recovery in the diffuser section and thus a high efficiency.
- the blade tips may dip into the recesses so that, although the gap is reduced to the minimum necessary assembly gap, noxious contact of the blade tips with the shaft cover during operation of the axial turbocompressor is inhibited.
- the flow around the blade tip decreases, as a result of which the leakage flow at the blade tip also decreases.
- the efficiency of the guide vane grille increases and losses and separations in the diffuser located downstream of the axial turbo-compressor are reduced.
- the degree of expansion of the diffuser ie the diffuser angle of the diffuser, may be greater than would be the case with a conventional diffuser. This is accompanied by a reduction in the overall length of the gas turbine compared to a conventional gas turbine.
- a honeycomb-like and / or felt-like structure is applied to the bottom of the depression, which can yield when touched by the blade tip.
- the honeycomb-like structure is a honeycomb.
- the blade tip can dip into the honeycomb-like and / or felt-like structure, whereby the blade tip is not damaged.
- the flow around the blade tip decreases when the blade tip is immersed in its associated recess during a certain operating state and digs into the honeycomb-like and / or felt-like structure. This advantageously additionally reduces the leakage flow at the blade tip.
- the recesses have an outline shape on the surface of the shaft cover, which is modeled after the profile of the associated vanes on the blade tip, and have a predetermined depth.
- the material of the shaft cover is arranged around the blade tip immersed in the recess such that, on the one hand, the blade tip does not hit the shaft cover when immersed in the recess and, on the other hand, the flow around the blade tip decreases.
- the depth of the depressions is determined such that during operation of the axial turbocompressor, the radial relative movements between the blade tips and the shaft seal can be compensated.
- the contour of the recesses is determined such that during operation of the Axialturbover Whyrs the axial relative movements between the blade tips and the shaft seal can be compensated.
- FIGS. 1 and 2 As it is from the FIGS. 1 and 2 As can be seen, has a Axialturbover Noticer 1 a Leitschaufelgitter 2, which is formed by a plurality of vanes 3.
- the guide vanes 3 are arranged in a row in the circumferential direction of the axial turbo-compressor 1 and have a longitudinal extent in the radial direction of the axial turbo-compressor 1.
- the Axialturbover Noticer 1 a housing 5, on the inside of the vanes 3 are fixed. Facing away from the housing 5, the guide vanes 3 have a blade tip 4 which points inwardly into the housing 5.
- a shaft cover 6 is arranged directly on the blade tips 3, which is a circumferentially symmetrical Ring is formed.
- a plurality of recesses 7 is provided at the blade tips 4 facing outside of the shaft cover 6, a plurality of recesses 7 is provided. Each recess 7 is associated with a different blade tip 4, wherein the recess 7 is located immediately adjacent to its associated vane tip 4.
- Each recess 7 has at the blade tips 4 facing the outside of the shaft cover 6 has an outline 8, which is modeled on the profile shape of the guide vane 3 on the vane tip 4. Further, each recess 7 is provided with a depth 9 in the shaft cover 6. The shape of the outline 8 and the depth 9 are determined such that, during operation of the axial turbocompressor, each blade tip 4 can dip into its associated recess 7, whereby the blade tip 4 does not or hardly touches the wave cover 6 when immersed.
- a honeycomb structure 10 is applied as shown in FIG. 1 is shown by way of example for the middle recess 7. If the blade tips 4 touch the honeycomb structure 10 during operation of the axial turbocompressor, the honeycomb structure 10 yields, so that the blade tip 4 presses into the honeycomb structure 10.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Die Erfindung betrifft einen Axialturboverdichter für eine Gasturbine, wobei der Axialturboverdichter geringe Spaltverluste hat.The invention relates to a Axialturboverdichter for a gas turbine, wherein the Axialturboverdichter has low gap losses.
Eine Gasturbine weist einen Turboverdichter beispielsweise in Axialbauweise auf. Der Turboverdichter weist ein Gehäuse mit einem daran angebrachten Stator und einen Rotor auf, der von dem Gehäuse umgeben ist. Der Rotor weist eine Welle auf, an der der Rotor drehantreibbar ist. Die Welle umgebend ist eine Wellenabdeckung vorgesehen, deren Außenkontur zusammen mit der Innenkontur des Gehäuses einen Teil des Strömungskanals durch den Turboverdichter bildet. Der Strömungskanal hat einen in Strömungsrichtung sich aufweitenden Querschnitt, so dass der Strömungskanal als ein Diffusor ausgebildet ist.A gas turbine has a turbocompressor, for example, in axial construction. The turbocompressor has a housing with a stator attached thereto and a rotor surrounded by the housing. The rotor has a shaft on which the rotor is driven in rotation. Surrounding the shaft, a shaft cover is provided, whose outer contour together with the inner contour of the housing forms part of the flow channel through the turbocompressor. The flow channel has a cross section which widens in the flow direction, so that the flow channel is designed as a diffuser.
Der Rotor weist eine Mehrzahl von Rotorstufen auf, die jeweils von einer Rotorschaufelreihe gebildet sind. Ferner weist der Stator eine Mehrzahl von Statorschaufelreihen auf, die in Axialrichtung gesehen abwechselnd zu den Rotorschaufelreihen angeordnet sind. Herkömmlich ist in Strömungsrichtung gesehen nach der letzten Rotorschaufelreihe eine Leitschaufelreihe und danach eine Nachleitschaufelreihe angeordnet.The rotor has a plurality of rotor stages, each formed by a row of rotor blades. Furthermore, the stator has a plurality of stator blade rows, which are arranged alternately to the rows of rotor blades when viewed in the axial direction. Conventionally, seen in the flow direction after the last row of rotor blades, a row of vanes and then a Nachleitschaufelreihe arranged.
Die Leitschaufelreihen weisen eine Mehrzahl an Schaufeln auf, die mit ihrem einen Ende jeweils an dem Gehäuse befestigt sind und mit ihrem andern Ende in Richtung zu der Welle zeigen. An dem anderen Ende der Leitschaufel ist eine Schaufelspitze ausgebildet, die der Wellenabdeckung zugewandt und unmittelbar benachbart angeordnet ist. Der Abstand zwischen den Schaufelspitzen und der Wellenabdeckung ist als ein Radialspalt ausgebildet, der derart dimensioniert ist, dass einerseits die Schaufelspitzen beim Betrieb der Gasturbine an die Wellenabdeckung nicht anstoßen und andererseits die beim Betrieb der Gasturbine sich einstellende Leckageströmung durch den Radialspalt möglichst gering ist. Dieser Spalt ist deshalb so gering wie möglich auszulegen, damit ein hoher Wirkungsgrad erzielt und das volle Beschaufelungspotential des Verdichters ausgeschöpft werden kann.The rows of vanes have a plurality of blades, which are fastened with their one end respectively to the housing and with its other end pointing in the direction of the shaft. At the other end of the vane, a blade tip is formed, which faces the shaft cover and is disposed immediately adjacent. The distance between the blade tips and the shaft cover is formed as a radial gap, which is dimensioned such that on the one hand, the blade tips do not abut the shaft cover during operation of the gas turbine and, on the other hand, the leakage flow through the radial gap that occurs during operation of the gas turbine is as low as possible. This gap must therefore be designed as low as possible, so that a high efficiency can be achieved and the full blading potential of the compressor can be exploited.
Das Gehäuse des Turboverdichters ist massiv konstruiert, um den Druck- und Temperaturbeanspruchungen beim Betrieb der Gasturbine standhalten zu können. Ferner ist das Gehäuse steif ausgeführt, damit der Lasteintrag auf das Gehäuse beim Betrieb der Gasturbine eine nur kleine Verformung des Gehäuses zur Folge hat. Im Gegensatz dazu ist die Wellenabdeckung beim Betrieb der Gasturbine geringeren mechanischen Beanspruchungen ausgesetzt, wodurch die Wellenabdeckung dünner und weniger massiv als das Gehäuse ausgeführt ist.The casing of the turbo-compressor is massively designed to withstand the pressure and temperature stresses in the operation of the gas turbine. Furthermore, the housing is rigid, so that the load application to the housing during operation of the gas turbine has only a small deformation of the housing result. In contrast, the shaft cover is exposed to lower mechanical stresses during operation of the gas turbine, whereby the shaft cover is made thinner and less massive than the housing.
Dadurch, dass die Wellenabdeckung mit kleineren Wandstärken im Vergleich zum Gehäuse ausgebildet ist und in der Regel andere Materialeigenschaften als das Gehäuse hat, erwärmt sich die Wellenabdeckung schneller als das Gehäuse mit den daran befestigten Leitschaufelreihen. Dies hat zur Folge, dass zum Anfahren und Abfahren der Gasturbine die Wellenabdeckung und das Gehäuse eine unterschiedliche Wärmeausdehnungsgeschwindigkeit haben, so dass sich beim Anfahren und Abfahren der Gasturbine die Höhe des Radialspalts ändert, wobei der Radialspalt beim Anfahren temporär kleiner und beim Abfahren größer ist.Characterized in that the shaft cover is formed with smaller wall thicknesses compared to the housing and typically has different material properties than the housing, the shaft cover heats up faster than the housing with the guide blade rows attached thereto. This has the consequence that for starting and stopping the gas turbine, the shaft cover and the housing have a different thermal expansion rate, so that when starting and stopping the gas turbine, the height of the radial gap changes, the radial gap when starting is temporarily smaller and larger when starting.
Damit beim Betrieb des Turboverdichters die Schaufelspitzen der Leitschaufelreihe nicht an die Wellenabdeckung anstoßen und diese beschädigen ist der Radialspalt mit einer derart dimensionierten Minimalhöhe versehen, dass in jedem Betriebszustand der Gasturbine - stationär wie instationär - die Schaufelspitzen die Wellenabdeckung so gut wie nie berühren. Dies hat zur Folge, dass an den Schaufelspitzen ein entsprechend dimensionierter Radialspalt vorgehalten ist, der zu einer Reduktion des Wirkungsgrades der Gasturbine führt.So that during operation of the turbocompressor, the blade tips of the guide blade row do not abut the shaft cover and damage it, the radial gap is provided with a minimum height dimensioned such that in every operating state of the gas turbine - stationary and unsteady - the blade tips almost never touch the shaft cover. This has the consequence that at the blade tips a corresponding dimensioned radial gap is maintained, which leads to a reduction in the efficiency of the gas turbine.
Ferner führt die von dem Radialspalt verursachte Blockage zu einer Reduktion der Hauptströmungskomponente, wodurch der Druckrückgewinn im Diffusor reduziert wird und nachteilige Ablösephänomene auftreten können.Furthermore, the blockage caused by the radial gap leads to a reduction of the main flow component, whereby the pressure recovery in the diffuser is reduced and disadvantageous detachment phenomena may occur.
Aufgabe der Erfindung ist es, einen Axialturboverdichter für eine Gasturbine zu schaffen, der einen hohen Wirkungsgrad und eine hohe Betriebssicherheit hat.The object of the invention is to provide a Axialturboverdichter for a gas turbine, which has a high efficiency and high reliability.
Der erfindungsgemäße Axialturboverdichter für eine Gasturbine weist ein Leitschaufelgitter, das von Leitschaufeln mit nabenseitig freistehenden Schaufelspitzen gebildet ist, und eine stationäre Wellenabdeckung auf, die nabenseitig den Schaufelspitzen unmittelbar benachbart angeordnet ist und den Strömungskanal des Axialverdichters abgrenzt, wobei zwischen der Wellenabdeckung und den Schaufelspitzen ein Spalt ausgebildet ist, der derart minimal dimensioniert ist, dass gerade noch das Zusammenbauen des Axialturboverdichters bewerkstelligbar ist, und in der Wellenabdeckung eine Mehrzahl von Vertiefungen vorgesehen ist, wobei einer jeden Schaufelspitze eine der Vertiefungen zugeordnet ist, die der ihr zugeordneten Schaufelspitze unmittelbar benachbart angeordnet und derart dimensioniert ist, dass beim Betrieb des Axialturboverdichters jede Schaufelspitze in ihre zugeordnete Vertiefung eintauchbar ist, ohne dass eine der Schaufelspitzen die Wellenabdeckung maßgeblich berührt.The axial turbocompressor for a gas turbine engine according to the present invention comprises a vane grille formed by vanes with hub-side freestanding blade tips, and a stationary shaft cover located immediately adjacent the blade tips on the hub side and defining the flow passage of the axial compressor with a gap between the shaft cover and the blade tips is formed, which is minimally dimensioned so that just the assembling of the Axialturboverdichters bewerkstelligbar, and in the shaft cover a plurality of recesses is provided, each blade tip is associated with one of the recesses immediately adjacent to its associated blade tip and so is dimensioned such that during operation of the Axialturboverdichters each blade tip is plunged into its associated recess without one of the blade tips, the shaft cover significantly affected.
Dadurch ist der Spalt zwischen der Schaufelspitze und der Wellenabdeckung auf den minimal notwendigen Montagespalt eingestellt, so dass die Höhe des Spalts auf das montagebedingte Minimum reduziert ist. Die Höhe des minimal notwendigen Montagespalts ist derart gewählt, dass das Einkugeln der Leitschaufelgitter, insbesondere der hinteren Leitschaufelgitter, bewerkstelligbar ist.As a result, the gap between the blade tip and the shaft cover is set to the minimum necessary mounting gap, so that the height of the gap is reduced to the assembly-related minimum. The height of the minimal necessary mounting gap is chosen such that the Einkugeln the guide vane grille, in particular the rear vane grille, can be accomplished.
In einem herkömmlichen Turboverdichter ist der Spalt zwischen den Schaufelspitzen und der Wellenabdeckung mit einer derart gewählten, minimal notwendigen Höhe versehen, dass so gut wie in allen denkbaren Betriebszuständen der Gasturbine die Schaufelspitzen die Wellenabdeckung kaum oder nicht berühren. Dadurch ergibt sich der Spalt mit der derartigen Höhe, dass durch den Spalt ein merklicher Massenstrom an Leckageströmung strömt, der zu einer unerwünschten Wirkungsgradabsenkung der Gasturbine führt.In a conventional turbocompressor, the gap between the blade tips and the shaft cover is provided with a minimum height that is selected such that, as in all imaginable operating conditions of the gas turbine, the blade tips hardly or not touch the shaft cover. This results in the gap with such a height that flows through the gap a significant mass flow of leakage flow, which leads to an undesirable efficiency reduction of the gas turbine.
Hingegen ist beim erfindungsgemäßen Axialturboverdichter der Spalt auf den minimal möglichen Spalt, nämlich auf den minimal notwendigen Montagespalt, eingestellt, so dass die Leckageströmung durch den Spalt minimal ist. Dadurch hat der Axialturboverdichter einen hohen Druckrückgewinn in dem Diffusorabschnitt und somit einen hohen Wirkungsgrad.By contrast, in the axial turbocharger according to the invention the gap is set to the minimum possible gap, namely to the minimum necessary assembly gap, so that the leakage flow through the gap is minimal. As a result, the axial turbocompressor has a high pressure recovery in the diffuser section and thus a high efficiency.
Ferner können die Schaufelspitzen beim Betrieb des Axialturboverdichters in die Vertiefungen eintauchen, so dass, obwohl der Spalt auf den minimal notwendigen Montagespalt reduziert ist, eine schädliche Berührung der Schaufelspitzen mit der Wellenabdeckung beim Betrieb des Axialturboverdichters unterbunden ist.Further, during operation of the axial turbocompressor, the blade tips may dip into the recesses so that, although the gap is reduced to the minimum necessary assembly gap, noxious contact of the blade tips with the shaft cover during operation of the axial turbocompressor is inhibited.
Taucht die Schaufelspitze während eines bestimmten Betriebszustandes in ihre zugeordnete Vertiefung ein, so nimmt die Umströmung der Schaufelspitze ab, wodurch ebenfalls die Leckageströmung an der Schaufelspitze abnimmt. Dadurch steigt der Wirkungsgrad des Leitschaufelgitters und Verluste sowie Ablösungen in dem stromab des Axialturboverdichters liegenden Diffusor sind reduziert. Insgesamt folgt aus dem verbesserten Spaltverhalten ein gutes Gesamtmaschinenverhalten und ein hoher Gesamtmaschinenwirkungsgrad der Gasturbine. Im Umkehrschluss hierzu kann der Aufweitungsgrad des Diffusors, d.h. der Diffusorwinkel des Diffusors, größer gewählt sein, als dies bei einem herkömmlichen Diffuser der Fall wäre. Damit geht einher eine Reduktion der Baulänge der Gasturbine verglichen mit einer herkömmlichen Gasturbine.If the blade tip dips into its assigned depression during a certain operating state, the flow around the blade tip decreases, as a result of which the leakage flow at the blade tip also decreases. As a result, the efficiency of the guide vane grille increases and losses and separations in the diffuser located downstream of the axial turbo-compressor are reduced. Overall, the improved splitting behavior results in good overall machine behavior and a high overall engine efficiency of the gas turbine. Conversely, the degree of expansion of the diffuser, ie the diffuser angle of the diffuser, may be greater than would be the case with a conventional diffuser. This is accompanied by a reduction in the overall length of the gas turbine compared to a conventional gas turbine.
Es ist bevorzugt, dass am Grund der Vertiefung eine honigwabenartige und/oder filzartige Struktur aufgebracht ist, die bei Berührung durch die Schaufelspitze nachgeben kann. Bevorzugt ist die honigwabenartige Struktur ein Honeycomb.It is preferred that a honeycomb-like and / or felt-like structure is applied to the bottom of the depression, which can yield when touched by the blade tip. Preferably, the honeycomb-like structure is a honeycomb.
Dadurch kann die Schaufelspitze in die honigwabenartige und/oder filzartige Struktur eintauchen, wobei die Schaufelspitze nicht beschädigt wird. Daraus ergibt sich der Vorteil, dass der Abstand zwischen der Schaufelspitze und der honigwabenartigen und/oder filzartigen Struktur klein ausgeführt ist. Somit nimmt die Umströmung der Schaufelspitze ab, wenn die Schaufelspitze während eines bestimmten Betriebszustandes in ihrer zugeordneten Vertiefung eintaucht und sich in die honigwabenartige und/oder filzartige Struktur eingräbt. Dadurch nimmt vorteilhaft zusätzlich die Leckageströmung an der Schaufelspitze ab.As a result, the blade tip can dip into the honeycomb-like and / or felt-like structure, whereby the blade tip is not damaged. This results in the advantage that the distance between the blade tip and the honeycomb-like and / or felt-like structure is made small. Thus, the flow around the blade tip decreases when the blade tip is immersed in its associated recess during a certain operating state and digs into the honeycomb-like and / or felt-like structure. This advantageously additionally reduces the leakage flow at the blade tip.
Ferner ist es bevorzugt, dass die Vertiefungen einen Umrissverlauf an der Oberfläche der Wellenabdeckung haben, der dem Profil der ihr zugeordneten Leitschaufeln an der Schaufelspitze nachempfunden ist, und eine vorbestimmte Tiefe haben.Further, it is preferable that the recesses have an outline shape on the surface of the shaft cover, which is modeled after the profile of the associated vanes on the blade tip, and have a predetermined depth.
Somit ist um die in die Vertiefung eingetauchte Schaufelspitze das Material der Wellenabdeckung derart angeordnet, dass einerseits die Schaufelspitze beim Eintauchen in die Vertiefung nicht an die Wellenabdeckung stößt und andererseits die Umströmung der Schaufelspitze abnimmt.Thus, the material of the shaft cover is arranged around the blade tip immersed in the recess such that, on the one hand, the blade tip does not hit the shaft cover when immersed in the recess and, on the other hand, the flow around the blade tip decreases.
Bevorzugt ist, dass die Tiefe der Vertiefungen derart bestimmt ist, dass im Betrieb des Axialturboverdichters die radialen Relativbewegungen zwischen den Schaufelspitzen und der Wellenabdichtung kompensierbar sind.It is preferred that the depth of the depressions is determined such that during operation of the axial turbocompressor, the radial relative movements between the blade tips and the shaft seal can be compensated.
Dadurch ist vorteilhaft erreicht, dass ein Zusammenstoßen der Schaufelspitze mit der Wellenabdeckung im Betrieb des Axialturboverdichters unterbunden ist, so dass die Betriebssicherheit des Axialturboverdichters hoch ist.As a result, it is advantageously achieved that collision of the blade tip with the shaft cover during operation of the axial turbocompressor is prevented, so that the operational reliability of the axial turbocompressor is high.
Außerdem ist es bevorzugt, dass der Umrissverlauf der Vertiefungen derart bestimmt ist, dass im Betrieb des Axialturboverdichters die axialen Relativbewegungen zwischen den Schaufelspitzen und der Wellenabdichtung kompensierbar sind.In addition, it is preferred that the contour of the recesses is determined such that during operation of the Axialturboverdichters the axial relative movements between the blade tips and the shaft seal can be compensated.
Somit ist es unterbunden, dass im Betrieb des Axialturboverdichters die Schaufelspitzen bei axialen Relativbewegungen zwischen den Schaufelspitzen und der Wellenabdichtung die Schaufelspitzen die Wellenabdichtung berühren, so dass die Betriebssicherheit des Axialturboverdichters hoch ist.Thus, it is prevented that in operation of the Axialturboverdichters the blade tips in axial relative movements between the blade tips and the shaft seal the blade tips touch the shaft seal, so that the reliability of the Axialturboverdichters is high.
Im Folgenden wird die Erfindung anhand einer bevorzugten Ausführungsform eines erfindungsgemäßen Axialturboverdichters anhand der beigefügten schematischen Zeichnungen gezeigt. Es zeigen:
- Figur 1
- eine perspektivische Ansicht eines Ausschnitts des Axialturboverdichters und
Figur 2- eine Ansicht entlang der Schaufellängsachse des Ausschnitts aus
Figur 1 .
- FIG. 1
- a perspective view of a section of the Axialturboverdichters and
- FIG. 2
- a view along the blade longitudinal axis of the cut out
FIG. 1 ,
Wie es aus den
Ferner weist der Axialturboverdichter 1 ein Gehäuse 5 auf, an dem innenseitig die Leitschaufeln 3 befestigt sind. Dem Gehäuse 5 abgewandt weisen die Leitschaufeln 3 eine Schaufelspitze 4 auf, die nach innen in das Gehäuse 5 zeigt.Further, the Axialturboverdichter 1 a
Nabenseitig ist unmittelbar an den Schaufelspitzen 3 eine Wellenabdeckung 6 angeordnet, die als ein umfangssymmetrischer Ring ausgebildet ist. An der den Schaufelspitzen 4 zugewandten Außenseite der Wellenabdeckung 6 ist eine Mehrzahl an Vertiefungen 7 vorgesehen. Jede Vertiefung 7 ist einer anderen Schaufelspitze 4 zugeordnet, wobei die Vertiefung 7 unmittelbar benachbart zu ihrer zugeordneten Leitschaufelspitze 4 angesiedelt ist.On the hub side, a
Jede Vertiefung 7 hat an der den Schaufelspitzen 4 zugewandten Außenseite der Wellenabdeckung 6 einen Umriss 8, der der Profilform der Leitschaufel 3 an der Leitschaufelspitze 4 nachempfunden ist. Ferner ist jede Vertiefung 7 mit einer Tiefe 9 in der Wellenabdeckung 6 vorgesehen. Die Form des Umrisses 8 und die Tiefe 9 sind derart bestimmt, dass im Betrieb des Axialturboverdichters jede Schaufelspitze 4 in ihre zugeordnete Vertiefung 7 eintauchen kann, wobei beim Eintauchen die Schaufelspitze 4 die Wellenabdeckung 6 nicht oder so gut wie kaum berührt.Each
Am Grund einer jeden Vertiefung 7 ist eine Honigwabenstruktur 10 aufgebracht, wie es in
Claims (5)
mit einem Leitschaufelgitter (2), das von Leitschaufeln (3) mit nabenseitig freistehenden Schaufelspitzen (4) gebildet ist, und einer stationären Wellenabdeckung (6), die nabenseitig den Schaufelspitzen (4) unmittelbar benachbart angeordnet ist und den Strömungskanal des Axialverdichters (1) abgrenzt,
wobei zwischen der Wellenabdeckung (6) und den Schaufelspitzen (4) ein Spalt ausgebildet ist, der derart minimal dimensioniert ist, dass gerade noch das Zusammenbauen des Axialturboverdichters (1) bewerkstelligbar ist, und in der Wellenabdeckung (6) eine Mehrzahl von Vertiefungen (7) vorgesehen ist,
wobei einer jeden Schaufelspitze (4) eine der Vertiefungen (7) zugeordnet ist, die der ihr zugeordneten Schaufelspitze (4) unmittelbar benachbart angeordnet und derart dimensioniert ist, dass beim Betrieb des Axialturboverdichters (1) jede Schaufelspitze (4) in ihre zugeordnete Vertiefung (7) eintauchbar ist, ohne dass eine der Schaufelspitzen (4) die Wellenabdeckung (6) maßgeblich berührt.Axial turbo compressor for a gas turbine,
with a vane grille (2) which is formed by vanes (3) with hub-side free-standing vane tips (4), and a stationary shaft cover (6) which is located immediately adjacent the vane tips (4) on the hub side and the flow duct of the axial compressor (1) delimits
wherein between the shaft cover (6) and the blade tips (4) a gap is formed which is minimally dimensioned so that the assembly of the Axialturboverdichters (1) can be accomplished, and in the shaft cover (6) has a plurality of recesses (7 ) is provided,
wherein each blade tip (4) is associated with one of the recesses (7), which is immediately adjacent to its associated blade tip (4) and dimensioned such that during operation of the Axialturboverdichters (1) each blade tip (4) in its associated recess ( 7) is submersible without one of the blade tips (4), the shaft cover (6) significantly touched.
wobei am Grund einer jeden Vertiefung (7) eine honigwabenartige und/oder filzartige Struktur (10) aufgebracht ist, die bei Berührung durch die Schaufelspitzen (4) nachgeben kann.Axial turbo compressor according to claim 1,
wherein at the bottom of each recess (7) an honeycomb-like and / or felt-like structure (10) is applied, which can give in contact with the blade tips (4).
wobei jede Vertiefung (7) einen Umrissverlauf (8) an der Oberfläche der Wellenabdeckung (6) hat, der dem Profil der Leitschaufeln (3) an der Schaufelspitze (4) nachempfunden ist, und eine vorbestimmte Tiefe (9) hat.Axial turbo compressor according to claim 1 or 2,
wherein each recess (7) has an outline (8) on the surface of the shaft cover (6) which is modeled on the profile of the guide vanes (3) on the blade tip (4) and has a predetermined depth (9).
wobei die Tiefe (9) der Vertiefungen (7) derart bestimmt ist, dass im Betrieb des Axialturboverdichters (1) die radialen Relativbewegungen zwischen den Schaufelspitzen (4) und der Wellenabdeckung (6) kompensierbar sind.Axial turbo compressor according to claim 3,
wherein the depth (9) of the recesses (7) is determined such that during operation of the Axialturboverdichters (1), the radial relative movements between the blade tips (4) and the shaft cover (6) are compensated.
wobei der Umrissverlauf (8) der Vertiefungen (7) derart bestimmt ist, dass im Betrieb des Axialturboverdichters (1) die axialen Relativbewegungen zwischen den Schaufelspitzen (4) und der Wellenabdeckung (6) kompensierbar sind.Axial turbo compressor according to claim 3 or 4,
wherein the contour (8) of the recesses (7) is determined such that during operation of the Axialturboverdichters (1), the axial relative movements between the blade tips (4) and the shaft cover (6) are compensated.
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09002056A EP2218918A1 (en) | 2009-02-13 | 2009-02-13 | Axial turbo compressor for a gas turbine with low blade-tip leakage losses and diffuser losses |
EP10702467A EP2396555A1 (en) | 2009-02-13 | 2010-01-27 | Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses |
US13/201,065 US20110311355A1 (en) | 2009-02-13 | 2010-01-27 | Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses |
CN201080008181.2A CN102317634B (en) | 2009-02-13 | 2010-01-27 | Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses |
PCT/EP2010/050933 WO2010091956A1 (en) | 2009-02-13 | 2010-01-27 | Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses |
JP2011549507A JP5567036B2 (en) | 2009-02-13 | 2010-01-27 | Axial turbo compressor for gas turbine with low gap loss and low diffuser loss |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09002056A EP2218918A1 (en) | 2009-02-13 | 2009-02-13 | Axial turbo compressor for a gas turbine with low blade-tip leakage losses and diffuser losses |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2218918A1 true EP2218918A1 (en) | 2010-08-18 |
Family
ID=40469901
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09002056A Withdrawn EP2218918A1 (en) | 2009-02-13 | 2009-02-13 | Axial turbo compressor for a gas turbine with low blade-tip leakage losses and diffuser losses |
EP10702467A Withdrawn EP2396555A1 (en) | 2009-02-13 | 2010-01-27 | Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10702467A Withdrawn EP2396555A1 (en) | 2009-02-13 | 2010-01-27 | Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses |
Country Status (5)
Country | Link |
---|---|
US (1) | US20110311355A1 (en) |
EP (2) | EP2218918A1 (en) |
JP (1) | JP5567036B2 (en) |
CN (1) | CN102317634B (en) |
WO (1) | WO2010091956A1 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2538031A1 (en) * | 2011-06-22 | 2012-12-26 | Siemens Aktiengesellschaft | Rotor with sealing element for a stationary gas turbine |
US20130156559A1 (en) * | 2010-06-17 | 2013-06-20 | Snecma | Compressor and a turbine engine with optimized efficiency |
CN104074799A (en) * | 2013-11-17 | 2014-10-01 | 中国科学院工程热物理研究所 | Axial-flow compressor with expanding meridional channel and design method of axial-flow compressor |
WO2023180668A1 (en) * | 2022-03-24 | 2023-09-28 | Safran Helicopter Engines | Module for an aircraft turbine engine |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
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DE102014203605A1 (en) | 2014-02-27 | 2015-08-27 | Rolls-Royce Deutschland Ltd & Co Kg | Blade row group |
EP2977559B1 (en) * | 2014-07-25 | 2017-06-07 | Safran Aero Boosters SA | Axial turbomachine stator and corresponding turbomachine |
US9988918B2 (en) * | 2015-05-01 | 2018-06-05 | General Electric Company | Compressor system and airfoil assembly |
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- 2009-02-13 EP EP09002056A patent/EP2218918A1/en not_active Withdrawn
-
2010
- 2010-01-27 WO PCT/EP2010/050933 patent/WO2010091956A1/en active Application Filing
- 2010-01-27 US US13/201,065 patent/US20110311355A1/en not_active Abandoned
- 2010-01-27 CN CN201080008181.2A patent/CN102317634B/en not_active Expired - Fee Related
- 2010-01-27 JP JP2011549507A patent/JP5567036B2/en not_active Expired - Fee Related
- 2010-01-27 EP EP10702467A patent/EP2396555A1/en not_active Withdrawn
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WO1995017584A1 (en) * | 1993-12-22 | 1995-06-29 | Alliedsignal Inc. | Insertable stator vane assembly |
EP1079075A2 (en) * | 1999-08-09 | 2001-02-28 | United Technologies Corporation | Stator assembly for a rotary machine and clip member for a stator assembly |
EP1219785A1 (en) * | 2000-12-19 | 2002-07-03 | United Technologies Corporation | Gas turbine vane installation |
EP1707744A2 (en) * | 2005-03-07 | 2006-10-04 | The General Electric Company | Stator vane with inner and outer shroud |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130156559A1 (en) * | 2010-06-17 | 2013-06-20 | Snecma | Compressor and a turbine engine with optimized efficiency |
US9488179B2 (en) * | 2010-06-17 | 2016-11-08 | Snecma | Compressor and a turbine engine with optimized efficiency |
EP2538031A1 (en) * | 2011-06-22 | 2012-12-26 | Siemens Aktiengesellschaft | Rotor with sealing element for a stationary gas turbine |
WO2012175274A1 (en) * | 2011-06-22 | 2012-12-27 | Siemens Aktiengesellschaft | Rotor with sealing element for a stationary gas turbine |
CN104074799A (en) * | 2013-11-17 | 2014-10-01 | 中国科学院工程热物理研究所 | Axial-flow compressor with expanding meridional channel and design method of axial-flow compressor |
WO2023180668A1 (en) * | 2022-03-24 | 2023-09-28 | Safran Helicopter Engines | Module for an aircraft turbine engine |
FR3133886A1 (en) * | 2022-03-24 | 2023-09-29 | Safran Helicopter Engines | MODULE FOR AIRCRAFT TURBOMACHINE |
Also Published As
Publication number | Publication date |
---|---|
CN102317634A (en) | 2012-01-11 |
CN102317634B (en) | 2014-06-25 |
US20110311355A1 (en) | 2011-12-22 |
JP5567036B2 (en) | 2014-08-06 |
JP2012518109A (en) | 2012-08-09 |
EP2396555A1 (en) | 2011-12-21 |
WO2010091956A1 (en) | 2010-08-19 |
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