WO2010091956A1 - Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses - Google Patents

Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses Download PDF

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Publication number
WO2010091956A1
WO2010091956A1 PCT/EP2010/050933 EP2010050933W WO2010091956A1 WO 2010091956 A1 WO2010091956 A1 WO 2010091956A1 EP 2010050933 W EP2010050933 W EP 2010050933W WO 2010091956 A1 WO2010091956 A1 WO 2010091956A1
Authority
WO
WIPO (PCT)
Prior art keywords
shaft cover
axial
tips
vane
blade
Prior art date
Application number
PCT/EP2010/050933
Other languages
German (de)
French (fr)
Inventor
Francois Benkler
Karl Klein
Torsten Matthias
Achim Schirrmacher
Oliver Schneider
Vadim Shevchenko
Ulrich Waltke
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to US13/201,065 priority Critical patent/US20110311355A1/en
Priority to CN201080008181.2A priority patent/CN102317634B/en
Priority to JP2011549507A priority patent/JP5567036B2/en
Priority to EP10702467A priority patent/EP2396555A1/en
Publication of WO2010091956A1 publication Critical patent/WO2010091956A1/en

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Classifications

    • 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
    • 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
    • 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
    • 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
    • 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
    • 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 an axial turbocompressor for a gas turbine, wherein the axial turbocharger has low radial 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 radial gap must therefore be designed as low as possible so that a high degree of efficiency can be achieved and the full blading potential of the compressor can be exploited.
  • it is also known, for example, from EP 1 079 075 A2 the hub-side ends of the blades by means of a
  • 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 temporarily smaller and larger when driving off is.
  • the radial gap is provided with such a dimensioned minimum height, that in each operating state of the gas turbine - both stationary and unsteady - the blade tips almost never touch the shaft cover. This has the consequence that at the blade tips a correspondingly sized radial gap is maintained, which leads to a reduction of 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 comprises a stator vane 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 radial gap between the shaft cover and the blade tips is formed, which is minimally dimensioned so that just the assembling of the Axialturbover Whyrs is accomplished, and in the shaft cover a plurality of blind hole-like depressions is provided, each blade tip is associated with one of the wells immediately adjacent to its associated blade tip and is dimensioned such that during operation of the Axialturbover Noners each blade tip is plunged into its associated recess without one of the blade tips, the shaft cover prevail touched.
  • the radial gap between the blade tip and the shaft cover on the minimum necessary mounting gap adjusted so that the height of the radial 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 radial gap between the blade tips and the shaft cover is provided with such a minimum necessary height that virtually as in all conceivable operating conditions of the
  • the radial gap is set to the minimum possible radial gap, namely to the minimum necessary assembly gap, so that the leakage flow through the radial 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 radial 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.
  • This increases the efficiency of the vane grille and losses and separations in the downstream of the Axialturbover confusers lying diffuser 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.
  • an 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 recesses is determined such that in the operation of the axial turbo compressor the radial relative movements between the blade tips and the shaft seal can be compensated.
  • the outline profile of the depressions is determined in such a way that, during operation of the axial turbocompressor, the axial relative movements between the blade tips and the shaft seal can be compensated.
  • Figure 1 is a perspective view of a section of the Axialturbover Whyrs is asymmetrical to the Axialturbover Whyrs is asymmetrical to the Axialturbover Whyrs is asymmetrical to the Axialturbover Whyrs is asymmetrical to the Axialturbover Whyrs is asymmetrical to the Axialturbover Whyrs is asymmetrical to the Axialturbover Noners.
  • Figure 2 is a view along the blade longitudinal axis of
  • an axial turbo-compressor 1 has a vane grille 2 formed by a plurality of vanes 3.
  • the guide vanes 3 are arranged lined up in the circumferential direction of the axial turbo-compressor 1 and have a longitudinal extension in the radial direction of the axial turbo-compressor 1. Further, 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 and is designed as a circumferentially symmetrical ring.
  • 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.
  • the recess 7 is formed like a blind hole and thus ends blind. That is, it is provided with a tightly closed ground to prevent leakage losses.
  • 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, wherein when diving the blade tip 4, the wave cover 6 is not or virtually touched.
  • a honeycomb structure 10 is applied, as shown by way of example in FIG. 1 for the central 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

The invention relates to an axial turbo compressor for a gas turbine having a stator vane assembly (2) that is formed by stator vanes (3) having vane tips (4) exposed on the hub side and a stationary shaft cover (6) that is arranged immediately next to the vane tips (4) on the hub side and delimits the flow channel of the axial compressor (1), wherein a radial gap is designed between the shaft cover (6) and the vane tips (4) that is minimally sized such that the axial turbo compressor (1) can just still be assembled, and there is a plurality of recesses (7) in the shaft cover (6), wherein one of the recesses (7) is allocated to each vane tip (4) that is arranged directly neighboring the vane tip (4) allocated thereto and is sized such that during operation of the axial turbo compressor (1) every vane tip (4) can be plunged into the recess (7) allocated thereto without one of the vane tips (4) significantly contacting the shaft cover (6).

Description

Beschreibungdescription
Axialturboverdichter für eine Gasturbine mit geringen Radialspaltverlusten und DiffusorverlustenAxial turbo compressor for a gas turbine with low Radialspaltverlusten and diffuser losses
Die Erfindung betrifft einen Axialturboverdichter für eine Gasturbine, wobei der Axialturboverdichter geringe Radialspaltverluste hat.The invention relates to an axial turbocompressor for a gas turbine, wherein the axial turbocharger has low radial 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 Schaufel- spitze 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 Radialspalt ist deshalb so gering wie möglich auszulegen, damit ein hoher Wirkungsgrad erzielt und das volle Beschaufelungspotential des Verdichters ausgeschöpft werden kann. Alternativ zu freistehenden Verdichterschaufeln ist es auch beispielsweise aus der EP 1 079 075 A2 bekannt, die nabenseitigen Enden der Schaufelblätter mit Hilfe einerThe 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 radial gap must therefore be designed as low as possible so that a high degree of efficiency can be achieved and the full blading potential of the compressor can be exploited. As an alternative to free-standing compressor blades, it is also known, for example, from EP 1 079 075 A2, the hub-side ends of the blades by means of a
Sperrriegels gegen ein Herausbewegen aus einem nabenseitigen feststehenden Innenring zu sichern und gegen Schwingungserscheinungen zu dämpfen..To secure locking bar against moving out of a hub-side fixed inner ring and to dampen against vibration ..
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 Gehäu- ses 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 grö- ßer 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 temporarily smaller and larger when driving off is.
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 against the shaft cover and damage these, the radial gap is provided with such a dimensioned minimum height, that in each operating state of the gas turbine - both stationary and unsteady - the blade tips almost never touch the shaft cover. This has the consequence that at the blade tips a correspondingly sized radial gap is maintained, which leads to a reduction of 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 Radialspalt ausgebildet ist, der derart minimal dimensioniert ist, dass gerade noch das Zusammenbauen des Axialturboverdichters bewerkstelligbar ist, und in der Wellenabdeckung eine Mehrzahl von sacklochartigen 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 according to the invention comprises a stator vane 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 radial gap between the shaft cover and the blade tips is formed, which is minimally dimensioned so that just the assembling of the Axialturboverdichters is accomplished, and in the shaft cover a plurality of blind hole-like depressions is provided, each blade tip is associated with one of the wells immediately adjacent to its associated blade tip and 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 prevail touched.
Dadurch ist der Radialspalt zwischen der Schaufelspitze und der Wellenabdeckung auf den minimal notwendigen Montagespalt eingestellt, so dass die Höhe des Radialspalts 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 radial gap between the blade tip and the shaft cover on the minimum necessary mounting gap adjusted so that the height of the radial 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 Radialspalt zwischen den Schaufelspitzen und der Wellenabdeckung mit einer derart gewählten, minimal notwendigen Höhe versehen, dass so gut wie in allen denkbaren Betriebszuständen derIn a conventional turbocompressor, the radial gap between the blade tips and the shaft cover is provided with such a minimum necessary height that virtually as in all conceivable operating conditions of the
Gasturbine die Schaufelspitzen die Wellenabdeckung kaum oder nicht berühren. Dadurch ergibt sich der Radialspalt mit der derartigen Höhe, dass durch den Radialspalt ein merklicher Massenstrom an Leckageströmung strömt, der zu einer unerwünschten Wirkungsgradabsenkung der Gasturbine führt.Gas Turbine blade tips barely touch the shaft cover or not. This results in the radial gap having such a height that flows through the radial gap a significant mass flow of leakage flow, which leads to an undesirable reduction in efficiency of the gas turbine.
Hingegen ist beim erfindungsgemäßen Axialturboverdichter der Radialspalt auf den minimal möglichen Radialspalt, nämlich auf den minimal notwendigen Montagespalt, eingestellt, so dass die Leckageströmung durch den Radialspalt 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 radial gap is set to the minimum possible radial gap, namely to the minimum necessary assembly gap, so that the leakage flow through the radial 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 Radialspalt 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 radial 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 Radialspaltverhalten 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.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. This increases the efficiency of the vane grille and losses and separations in the downstream of the Axialturboverdichters lying diffuser are reduced. Overall follows from the improved Radial gap behavior a good overall machine behavior and 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.
Damit geht einher eine Reduktion der Baulänge der Gasturbine verglichen mit einer herkömmlichen Gasturbine.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 honig- wabenartige 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 an 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 anderer- seits 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 recesses is determined such that in the operation of the axial turbo compressor 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 Vertie- fungen 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 outline profile of the depressions is determined in such a way that, during operation of the axial turbocompressor, the axial relative movements between the blade tips and the shaft seal can be compensated.
Somit ist es unterbunden, dass im Betrieb des Axialturbover- dichters 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 the blade tips in axial relative movements between the blade tips and the shaft seal the blade tips touch the shaft seal during operation of Axialturboverdichters, 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 :In the following the invention will be shown with reference to a preferred embodiment of an axial turbocompressor according to the invention with reference to the attached schematic drawings. Show it :
Figur 1 eine perspektivische Ansicht eines Ausschnitts des Axialturboverdichters undFigure 1 is a perspective view of a section of the Axialturboverdichters and
Figur 2 eine Ansicht entlang der Schaufellängsachse desFigure 2 is a view along the blade longitudinal axis of
Ausschnitts aus Figur 1.Detail of Figure 1.
Wie es aus den Figuren 1 und 2 ersichtlich ist, weist ein Axialturboverdichter 1 ein Leitschaufelgitter 2 auf, das von einer Mehrzahl von Leitschaufeln 3 gebildet ist. Die Leit- schaufeln 3 sind in Umfangsrichtung des Axialturboverdichters 1 aufgereiht angeordnet und haben eine Längserstreckung in Radialrichtung des Axialturboverdichters 1. 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.As is apparent from FIGS. 1 and 2, an axial turbo-compressor 1 has a vane grille 2 formed by a plurality of vanes 3. The guide vanes 3 are arranged lined up in the circumferential direction of the axial turbo-compressor 1 and have a longitudinal extension in the radial direction of the axial turbo-compressor 1. Further, the Axialturboverdichter 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.
Nabenseitig ist unmittelbar an den Schaufelspitzen 3 eine Wellenabdeckung 6 angeordnet, die als ein umfangssymmetri- scher 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. Die Vertiefung 7 ist sacklochartig ausgebildet und endet somit blind. Das heißt, sie ist mit einem dicht verschlossenen Grund versehen, um Leckageverluste zu vermeiden.On the hub side, a shaft cover 6 is arranged directly on the blade tips 3 and is designed as a circumferentially symmetrical ring. 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. The recess 7 is formed like a blind hole and thus ends blind. That is, it is provided with a tightly closed ground to prevent leakage losses.
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 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, wherein when diving the blade tip 4, the wave cover 6 is not or virtually touched.
Am Grund einer jeden Vertiefung 7 ist eine Honigwabenstruktur 10 aufgebracht, wie es in Figur 1 beispielhaft für die mittlere Vertiefung 7 gezeigt ist. Berührt beim Betrieb des Axialturboverdichters die Schaufelspitzen 4 die Honigwabenstruktur 10, so gibt die Honigwabenstruktur 10 nach, so dass sich die Schaufelspitze 4 in die Honigwabenstruktur 10 eindrückt. At the bottom of each recess 7, a honeycomb structure 10 is applied, as shown by way of example in FIG. 1 for the central 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.

Claims

Patentansprüche claims
1. Axialturboverdichter für eine Gasturbine, 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 Radialspalt 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 dimensio- niert 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.An axial turbocompressor for a gas turbine, comprising a guide vane grille (2) formed by vanes (3) with hub-side freestanding vane tips (4) and a stationary shaft cover (6) located immediately adjacent the vane tips (4) on the hub side and the flow channel of the axial compressor (1) defines, between the shaft cover (6) and the blade tips (4) is formed a radial gap which is dimensioned so minimal that just the assembling of the Axialturboverdichters (1) can be accomplished, and in the shaft cover (6) 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 the Axialturboverdichters (1) each blade tip (4) is plunged into its associated recess (7) without one of Schaufelsp (4) the shaft cover (6) significantly touched.
2. Axialturboverdichter gemäß Anspruch 1, 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 .2. Axialturboverdichter according to claim 1, wherein at the bottom of each recess (7) has a honeycomb-like and / or felt-like structure (10) is applied, which can give in contact with the blade tips (4).
3. Axialturboverdichter gemäß Anspruch 1 oder 2, 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. An axial turbocompressor according to claim 1 or 2, wherein each recess (7) has an outline (8) on the surface of the shaft cover (6) modeled on the profile of the vanes (3) on the blade tip (4) and a predetermined one Depth (9) has.
4. Axialturboverdichter gemäß Anspruch 3, 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.4. Axialturboverdichter 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.
5. Axialturboverdichter gemäß Anspruch 3 oder 4, 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. 5. Axialturboverdichter according to claim 3 or 4, wherein the outline curve (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.
PCT/EP2010/050933 2009-02-13 2010-01-27 Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses WO2010091956A1 (en)

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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
JP2011549507A JP5567036B2 (en) 2009-02-13 2010-01-27 Axial turbo compressor for gas turbine with low gap loss and low diffuser loss
EP10702467A EP2396555A1 (en) 2009-02-13 2010-01-27 Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses

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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
EP09002056.1 2009-02-13

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