EP1965037B1 - Axial and radial support of the unison ring for inlet guide vane assemblies of hot gas expanders - Google Patents

Axial and radial support of the unison ring for inlet guide vane assemblies of hot gas expanders Download PDF

Info

Publication number
EP1965037B1
EP1965037B1 EP07004362.5A EP07004362A EP1965037B1 EP 1965037 B1 EP1965037 B1 EP 1965037B1 EP 07004362 A EP07004362 A EP 07004362A EP 1965037 B1 EP1965037 B1 EP 1965037B1
Authority
EP
European Patent Office
Prior art keywords
sliding
unison ring
hot gas
adjusting ring
spiral insert
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.)
Not-in-force
Application number
EP07004362.5A
Other languages
German (de)
French (fr)
Other versions
EP1965037A1 (en
Inventor
Vinko Mikulec
Martin WÜLLER
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Priority to EP07004362.5A priority Critical patent/EP1965037B1/en
Publication of EP1965037A1 publication Critical patent/EP1965037A1/en
Application granted granted Critical
Publication of EP1965037B1 publication Critical patent/EP1965037B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/95—Preventing corrosion

Definitions

  • the invention relates to a turbomachine, in particular H exertgasexpander, with at least one inlet housing to which a modsleitapparat is mounted, wherein the specimensleitapparat has a collar, wherein the turbomachine first and second sliding elements, which are associated with the adjusting ring, where the collar during a movement slides.
  • Turbomachines e.g. Gear machines of the type mentioned are characterized by a multi-shaft arrangement with different rotational speeds to a central drive wheel. This provides a compact unit for multi-stage compaction / expansion for a variety of media, preferably gaseous media.
  • Such gear machines expand the medium, which may have an inlet temperature of up to 300 ° C or, in a preferred embodiment, an inlet temperature of over 300 ° C.
  • an inlet temperature of up to 300 ° C or, in a preferred embodiment, an inlet temperature of over 300 ° C.
  • At a media inlet temperature of more than 300 ° C one speaks of so-called hot gas expanders.
  • H facedgasexpander have at least one inlet housing, in which the spiral insert is arranged.
  • the spiral insert carries an adjustable milieusleitapparat having a collar, vanes and bolts, wherein the bolts serve as a rotation axis for adjusting the vanes.
  • the guide vanes are therefore rotatably struck on the bolt, wherein the guide vanes are simultaneously connected via a driver with the adjusting ring. Now, if the collar rotated in a desired angular amount, cause the mit a forced adjustment of the vanes around the bolt, so that by adjusting the vanes influencing the direction and / or speed of the Medium flow to the blade or the impeller is effected.
  • the spiral insert thus has two functions. On the one hand, the spiral insert carries the adjusting mechanism (adjusting ring, etc.), with the spiral insert on the other also carries the contour ring.
  • the spiral insert with the associated inlet guide and the contour ring is pre-assembled outside of the inlet housing and used as a unit in this.
  • the adjusting ring is inserted into a corresponding recess of the spiral insert. Due to the thermal expansion or different expansion of the adjusting ring, at least relative to the spiral insert the adjusting ring must therefore be made substantially smaller in size than the recess. However, this results in a relatively large gap between the outer sides of the adjusting ring to the inner sides of the recess in the spiral insert. These large gaps also cause relatively large gap losses and further reduce the efficiency.
  • the adjusting ring can move due to the relatively loose use in the recess of the spiral insert under operating conditions in the recess and can even strike on the insides.
  • the collar or the spiral insert is subject to the thermal stresses considerably mechanical stresses, which reduce the life of the respective components.
  • the EP 0 227 475 A2 is already a hot gas expander of the type mentioned above, but the adjusting ring tends to tilt due to unfavorable leadership.
  • the US 2004 / 0109757A1 shows a guide of a collar for a diffuser adjustment of a compressor by means of rollers. This design tends to jam and rattle in the area of the roller axles, depending on the thermal condition of the machine, the axial guidance always having great play.
  • the EP 1 531 237 A2 also shows a guide for a compressor collar with elastic elements.
  • the invention is therefore based on the object to improve a turbomachine of the type mentioned, in particular hot gas expander, with simple means to the effect that the gap losses are reduced, so that the efficiency can be significantly increased.
  • the sliding elements are formed in a preferred embodiment as sliding plates made of a suitable material, wherein the sliding plates are preferably made of a temperature and corrosion-resistant base material, and are coated or treated accordingly.
  • the sliding elements or sliding plates made of steel or inconel and at least on their sliding surfaces with a special layer (eg Tribaloy ® ) be coated, the invention should not be limited to the exemplified material.
  • the sliding elements can also be coated over the entire surface.
  • the coating is preferably selected such that a coefficient of sliding friction is reduced, and at the same time high wear resistance is present is.
  • the coating preferably prevents seizure and is corrosion resistant.
  • a treatment by Kolsterizing ® corrosion-resistant surface hardening
  • the sliding members may also be formed entirely from the exemplified Tribaloy ® or other suitable material. Due to the advantageous design of the sliding elements, the hot gas expander can be operated at least up to an inlet temperature of 510 ° C.
  • the first sliding elements bear radially on the adjusting ring, so that the adjusting ring mounted radially is.
  • the spiral insert has on its inside a circumferential groove.
  • the groove can also be interrupted in the circumferential direction.
  • the groove receives the first sliding elements.
  • the respective sliding element is assigned in each case a holding element which is held securely in position in the spiral insert.
  • the respective holding element is preferably designed as a pin, which is held with its attachment end in the spiral insert, wherein a free end of the holding element or the pin is encompassed by the respective sliding element, which has a receiving bore corresponding thereto.
  • the receiving bore is preferably designed such that the respective sliding element rests substantially free of play on the respective holding element or its free end.
  • the respective sliding member protrudes with its sliding surface slightly out of the respective groove and abuts on an outer side of the adjusting ring.
  • the adjusting ring has on its inner side at least one circumferentially extending groove, in which engages at least one of the second sliding elements.
  • the groove has a radial depth extension, so that the adjusting ring is axially supported by means of the second sliding element.
  • more than one groove can be provided.
  • the respective second sliding element protrudes with its free end region out of the respective groove, wherein a through-hole for receiving a connecting element, preferably a screw, is provided in the free end region.
  • the connecting element can be screwed into a threaded bore introduced in the spiral insert, wherein an adjusting element is preferably arranged between the free end region of the sliding element and the spiral insert.
  • the adjusting element is designed in a preferred embodiment as a setting plate, which advantageously to gauge (Flatness tolerance) is made to compensate for manufacturing tolerances.
  • FIG. 1 shows a turbomachine or gear machine, which is designed in the illustrated embodiment as a hot gas expander 1 with an inlet temperature of a preferably gaseous medium of up to 510 ° C.
  • the hot gas expander 1 has at least one inlet housing 2, in which a spiral insert 3 is arranged.
  • the spiral insert 3 is assigned to an inlet guide 4 and a contour ring 6.
  • the inlet housing 2 is further associated with a diffuser 7.
  • the inlet guide apparatus 4 has an adjusting ring 8, spacers 9 and guide vanes 11.
  • the guide vanes 11 are connected via drivers 12 with the adjusting ring 8, so that a rotation of the adjusting ring 8 causes a corresponding adjustment of the guide vanes 11 which are rotatably mounted on the spacers 9.
  • the spacers 9 thus serve as the axis of rotation of the guide vanes 11.
  • the adjusting ring 8 is seen in cross-section L-shaped with a base web 13 and a web 14 arranged perpendicular thereto.
  • the web 14 is oriented by the base web 13 in the direction of the contour ring 6.
  • the base web 13 has an outer side 17 oriented toward an inner side 16 of the spiral insert 3 and an inner side 18 lying opposite thereto. Between the outer side 17 and the inner side 18 of the base web 13, an end face 19 is arranged.
  • a circumferential groove 22 is introduced.
  • holding elements 23 are arranged securely in the center.
  • the respective holding element 23 is preferably designed as a pin which is fastened with its attachment end in the spiral insert 3.
  • a through hole may be provided in the spiral insert 3.
  • the respective holding element 23 may also be held in a bore closed to the outside 24 of the spiral insert 3.
  • first sliding elements 26 are preferably used without play.
  • the respective sliding elements 26 are preferably designed as a sliding plate and have a respective holding element 23 corresponding receiving bore, which in turn may be introduced continuously or closed to a sliding surface 27 of the respective sliding member 26.
  • the respective sliding element 26 comprises the retaining element 23 substantially free of play, wherein the retaining element 23 is received with its end region opposite the fastening end in the respective sliding element 26 or in its receiving bore.
  • the adjusting ring is guided radially in the spiral insert 3.
  • a second sliding element 28 is provided, which in turn is preferably designed as a sliding plate.
  • the second sliding member 28 for axial guidance engages with its insertion region 29 in a groove 31, which in the inside 18 of the Adjusting ring 8 and its base web 13 is introduced.
  • the groove 31 has a radial depth extension.
  • the insertion region 29 can also be referred to as a sliding surface 29.
  • the adjusting ring 8 at least three grooves 31, of which in the FIGS. 1 and 2 only one is shown.
  • the second sliding element 28 has a through hole for the passage of a connecting element 33, preferably a screw.
  • the connecting element 33 or the screw can be connected to a corresponding threaded bore 34 in the spiral insert 3, so that the sliding element 28 is held sufficiently firmly.
  • the adjusting element 36 is preferably designed as a setting plate, and preferably made to compensate for manufacturing tolerances on gauge.
  • the sliding elements 26 and 28 are made of a suitable material and preferably coated at least on their sliding surfaces 27 and 29 with suitable special layers or treated accordingly.
  • the spiral insert 3 is also associated with a setting system 37 for radial adjustability, a clamping system 38 for minimizing axial gaps and a suitable sealing system 39 that seals the contour ring 6 to the diffuser 7.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Die Erfindung betrifft eine Strömungsmaschine, insbesondere Heißgasexpander, mit zumindest einem Einlaufgehäuse, an dem ein Eintrittsleitapparat angebracht ist, wobei der Eintrittsleitapparat einen Stellring aufweist, wobei die Strömungsmaschine erste und zweite Gleitelemente aufweist, die dem Stellring zugeordnet sind, an denen der Stellring bei einer Bewegung gleitet.The invention relates to a turbomachine, in particular Heißgasexpander, with at least one inlet housing to which a Eintrittsleitapparat is mounted, wherein the Eintrittsleitapparat has a collar, wherein the turbomachine first and second sliding elements, which are associated with the adjusting ring, where the collar during a movement slides.

Strömungsmaschinen, z.B. Getriebemaschinen der eingangs genannten Art zeichnen sich durch eine Mehrwellenanordnung mit unterschiedlichen Rotationsgeschwindigkeiten um ein zentrales Antriebsrad aus. Hierdurch wird eine kompakte Einheit für eine mehrstufige Verdichtung/Expansion für eine Vielzahl von Medien, vorzugsweise von gasförmigen Medien zur Verfügung gestellt.Turbomachines, e.g. Gear machines of the type mentioned are characterized by a multi-shaft arrangement with different rotational speeds to a central drive wheel. This provides a compact unit for multi-stage compaction / expansion for a variety of media, preferably gaseous media.

Derartige Getriebemaschinen expandieren das Medium, welches eine Eintrittstemperatur von bis zu 300°C oder in einer bevorzugten Ausführung eine Eintrittstemperatur über 300°C aufweisen kann. Bei einer Medieneintrittstemperatur von mehr als 300°C spricht man auch von so genannten Heißgasexpandern.Such gear machines expand the medium, which may have an inlet temperature of up to 300 ° C or, in a preferred embodiment, an inlet temperature of over 300 ° C. At a media inlet temperature of more than 300 ° C one speaks of so-called hot gas expanders.

Diese Heißgasexpander weisen mindestens ein Einlaufgehäuse auf, in dem der Spiraleinsatz angeordnet ist. Der Spiraleinsatz trägt einen verstellbaren Eintrittsleitapparat, der einen Stellring, Leitschaufeln und Bolzen aufweist, wobei die Bolzen als Drehachse zum Einstellen der Leitschaufeln dienen.These Heißgasexpander have at least one inlet housing, in which the spiral insert is arranged. The spiral insert carries an adjustable Eintrittsleitapparat having a collar, vanes and bolts, wherein the bolts serve as a rotation axis for adjusting the vanes.

Die Leitschaufeln sind also drehbar an dem Bolzen angeschlagen, wobei die Leitschaufeln gleichzeitig über einen Mitnehmer mit dem Stellring verbunden sind. Wird nun der Stellring in einem gewünschten Winkelbetrag verdreht, bewirken die Mit nehmer eine Zwangsverstellung der Leitschaufeln um den Bolzen, so dass durch die Verstellung der Leitschaufeln eine Beeinflussung der Richtung und/oder der Geschwindigkeit des Mediumstroms zu der Laufschaufel bzw. zum Laufrad bewirkt wird.The guide vanes are therefore rotatably struck on the bolt, wherein the guide vanes are simultaneously connected via a driver with the adjusting ring. Now, if the collar rotated in a desired angular amount, cause the mit a forced adjustment of the vanes around the bolt, so that by adjusting the vanes influencing the direction and / or speed of the Medium flow to the blade or the impeller is effected.

Der Spiraleinsatz hat somit zwei Funktionen. Zum einen trägt der Spiraleinsatz den Verstellmechanismus (Stellring usw.), wobei der Spiraleinsatz zum anderen auch den Konturring trägt.The spiral insert thus has two functions. On the one hand, the spiral insert carries the adjusting mechanism (adjusting ring, etc.), with the spiral insert on the other also carries the contour ring.

Der Spiraleinsatz mit dem zugeordneten Eintrittsleitapparat und dem Konturring wird außerhalb des Einlaufgehäuses vormontiert und als Einheit in dieses eingesetzt.The spiral insert with the associated inlet guide and the contour ring is pre-assembled outside of the inlet housing and used as a unit in this.

Aufgrund der hohen thermischen Belastung, insbesondere bei Heißgasexpandern, wird jedoch beobachtet, dass sich die unterschiedlichen Bauteilkomponenten aufgrund der thermischen Einwirkung ausdehnen bzw. unterschiedlich ausdehnen. Wirkungsgradverluste entstehen, wenn die Spalte (radiale und/oder axiale Spalte) zwischen den Leitschaufeln bzw. dem Bolzen (als Drehachse der jeweiligen Leitschaufel) und der zugeordneten Kanalinnenwand, welche zum Teil von dem Stellring gebildet wird zu groß sind.Due to the high thermal load, in particular with hot gas expanders, however, it is observed that the different component components expand or expand differently due to the thermal effect. Efficiency losses occur when the gaps (radial and / or axial gaps) between the vanes or the bolt (as the axis of rotation of the respective vane) and the associated channel inner wall, which is formed in part by the adjusting ring are too large.

Weiterhin wird der Stellring in eine entsprechende Ausnehmung des Spiraleinsatzes eingesetzt. Aufgrund der thermischen Ausdehnung bzw. unterschiedlichen Ausdehnung des Stellrings zumindest bezogen auf den Spiraleinsatz muss der Stellring daher in seinen Abmaßen wesentlich kleiner hergestellt werden als die Ausnehmung. Dadurch entsteht aber ein relativ großer Spalt zwischen den Außenseiten des Stellrings zu den Innenseiten der Ausnehmung in dem Spiraleinsatz. Diese großen Spalte bewirken ebenfalls relativ große Spaltverluste und reduzieren den Wirkungsgrad weiter. Zudem kann sich der Stellring aufgrund des relativ lockeren Einsatzes in die Ausnehmung des Spiraleinsatzes unter Betriebsbedingungen in der Ausnehmung bewegen und kann sogar an den Innenseiten anschlagen. Natürlich unterliegt der Stellring bzw. der Spiraleinsatz dadurch zu den thermischen Beanspruchungen erheblichen mechanischen Beanspruchungen, welche die Lebensdauer der jeweiligen Komponenten herabsetzen.Furthermore, the adjusting ring is inserted into a corresponding recess of the spiral insert. Due to the thermal expansion or different expansion of the adjusting ring, at least relative to the spiral insert the adjusting ring must therefore be made substantially smaller in size than the recess. However, this results in a relatively large gap between the outer sides of the adjusting ring to the inner sides of the recess in the spiral insert. These large gaps also cause relatively large gap losses and further reduce the efficiency. In addition, the adjusting ring can move due to the relatively loose use in the recess of the spiral insert under operating conditions in the recess and can even strike on the insides. Of course, the collar or the spiral insert is subject to the thermal stresses considerably mechanical stresses, which reduce the life of the respective components.

Aus der EP 0 227 475 A2 ist bereits ein Heißgasexpander der eingangs genannten Art bekannt, dessen Stellring jedoch wegen ungünstiger Führung zum Verkannten neigt. Die US 2004/0109757A1 zeigt eine Führung eines Stellrings für eine Diffusorverstellung eines Verdichters mittels Rollen. Diese Ausführung neigt im Bereich der Rollenachsen zum Klemmen und Klappern, je nach dem thermischen Zustand der Maschine, wobei die Axialführung stets großes Spiel aufweist. Die EP 1 531 237 A2 zeigt ebenfalls eine Führung für einen Verdichterstellring mit elastischen Elementen.From the EP 0 227 475 A2 is already a hot gas expander of the type mentioned above, but the adjusting ring tends to tilt due to unfavorable leadership. The US 2004 / 0109757A1 shows a guide of a collar for a diffuser adjustment of a compressor by means of rollers. This design tends to jam and rattle in the area of the roller axles, depending on the thermal condition of the machine, the axial guidance always having great play. The EP 1 531 237 A2 also shows a guide for a compressor collar with elastic elements.

Der Erfindung liegt daher die Aufgabe zugrunde, eine Strömungsmaschine der eingangs genannten Art, insbesondere Heißgasexpander, mit einfachen Mitteln dahingehend zu verbessern, dass die Spaltverluste reduziert sind, so dass der Wirkungsgrad erheblich erhöht werden kann.The invention is therefore based on the object to improve a turbomachine of the type mentioned, in particular hot gas expander, with simple means to the effect that the gap losses are reduced, so that the efficiency can be significantly increased.

Erfindungsgemäß wird die Aufgabe durch eine Strömungsmaschine der eingangs genannten Art mit den Merkmalen des kennzeichnenden Teiles des Anspruchs 1 gelöst. Die Unteransprüche beinhalten vorteilhafte Weiterbildungen.According to the invention the object is achieved by a turbomachine of the type mentioned with the features of the characterizing part of claim 1. The dependent claims contain advantageous developments.

Die Gleitelemente sind in bevorzugter Ausgestaltung als Gleitplatten aus einem geeigneten Material gebildet, wobei die Gleitplatten bevorzugt aus einem temperatur- und korrosionsfesten Grundmaterial gefertigt sind, und entsprechend beschichtet oder behandelt sind. Beispielsweise können die Gleitelemente bzw. Gleitplatten aus Stahl oder Inconel bestehen und zumindest an ihren Gleitflächen mit einer Spezialschicht (z.B. Tribaloy®) beschichtet sein, wobei die Erfindung nicht auf den beispielhaft genannten Werkstoff beschränkt sein soll. Natürlich können die Gleitelemente auch vollflächig beschichtet sein. Die Beschichtung wird bevorzugt derart gewählt, dass ein Gleitreibungsbeiwert reduziert wird, und gleichzeitig eine hohe Verschleißfestigkeit vorhanden ist. Die Beschichtung verhindert vorzugsweise ein Fressen und ist korrosionsfest. Alternativ ist auch eine Behandlung durch Kolsterisieren® (korrosionsfestes Oberflächenhärten) möglich. Selbstverständlich können die Gleitelemente auch vollständig aus dem beispielhaft genannten Tribaloy® bzw. einem anderem geeigneten Werkstoff gebildet sein. Aufgrund der vorteilhaften Ausführung der Gleitelemente können die Heißgasexpander zumindest bis zu einer Einlasstemperatur von 510°C betrieben werden.The sliding elements are formed in a preferred embodiment as sliding plates made of a suitable material, wherein the sliding plates are preferably made of a temperature and corrosion-resistant base material, and are coated or treated accordingly. For example, the sliding elements or sliding plates made of steel or inconel and at least on their sliding surfaces with a special layer (eg Tribaloy ® ) be coated, the invention should not be limited to the exemplified material. Of course, the sliding elements can also be coated over the entire surface. The coating is preferably selected such that a coefficient of sliding friction is reduced, and at the same time high wear resistance is present is. The coating preferably prevents seizure and is corrosion resistant. Alternatively, a treatment by Kolsterizing ® (corrosion-resistant surface hardening) is possible. Of course, the sliding members may also be formed entirely from the exemplified Tribaloy ® or other suitable material. Due to the advantageous design of the sliding elements, the hot gas expander can be operated at least up to an inlet temperature of 510 ° C.

Vorteilhaft ist, dass die ersten Gleitelemente radial an den Stellring anliegen, so dass der Stellring radial gelagert ist. Zur radialen Führung des Stellrings ist weiter vorteilhaft vorgesehen, dass der Spiraleinsatz an seiner Innenseite eine umlaufende Nut aufweist. Die Nut kann natürlich in Umfangsrichtung auch unterbrochen sein. Die Nut nimmt die ersten Gleitelemente auf. Dem jeweiligen Gleitelement ist jeweils ein Halteelement zugeordnet, das lagesicher in dem Spiraleinsatz gehalten ist. Das jeweilige Haltelement ist bevorzugt als Stift ausgeführt, der mit seinem Befestigungsende in dem Spiraleinsatz gehalten ist, wobei ein freies Ende des Halteelementes bzw. des Stiftes von dem jeweiligen Gleitelement umgriffen wird, welches eine dazu korrespondierende Aufnahmebohrung aufweist. Die Aufnahmebohrung ist bevorzugt derart ausgeführt, dass das jeweilige Gleitelement im wesentlichen spielfrei an dem jeweiligen Halteelement bzw. seinem freien Ende anliegt. Das jeweilige Gleitelement ragt mit seiner Gleitfläche etwas aus der jeweiligen Nut heraus und liegt an einer Außenseite des Stellrings an.It is advantageous that the first sliding elements bear radially on the adjusting ring, so that the adjusting ring mounted radially is. For radial guidance of the adjusting ring is further advantageously provided that the spiral insert has on its inside a circumferential groove. Of course, the groove can also be interrupted in the circumferential direction. The groove receives the first sliding elements. The respective sliding element is assigned in each case a holding element which is held securely in position in the spiral insert. The respective holding element is preferably designed as a pin, which is held with its attachment end in the spiral insert, wherein a free end of the holding element or the pin is encompassed by the respective sliding element, which has a receiving bore corresponding thereto. The receiving bore is preferably designed such that the respective sliding element rests substantially free of play on the respective holding element or its free end. The respective sliding member protrudes with its sliding surface slightly out of the respective groove and abuts on an outer side of the adjusting ring.

Zur axialen Führung des Stellrings ist es zweckmäßig im Sinne der Erfindung, wenn der Stellring an seiner Innenseite zumindest eine in Umfangsrichtung sich erstreckende Nut aufweist, in welche mindestens eines der zweiten Gleitelemente eingreift. Die Nut weist eine radiale Tiefenerstreckung auf, so dass der Stellring mittels des zweiten Gleitelementes axial gelagert ist. Natürlich können auch mehr als eine Nut vorgesehen sein. Vorteilhaft ragt das jeweilige zweite Gleitelement mit seinem freien Endbereich aus der jeweiligen Nut heraus, wobei in dem freien Endbereich eine Durchgangsbohrung zur Aufnahme eines Verbindungselementes, bevorzugt einer Schraube vorgesehen ist. Das Verbindungselement ist in einer in dem Spiraleinsatz eingebrachten Gewindebohrung einschraubbar, wobei zwischen dem freien Endbereich des Gleitelementes und dem Spiraleinsatz vorzugsweise ein Einstellelement angeordnet ist.For axial guidance of the adjusting ring, it is expedient for the purposes of the invention, when the adjusting ring has on its inner side at least one circumferentially extending groove, in which engages at least one of the second sliding elements. The groove has a radial depth extension, so that the adjusting ring is axially supported by means of the second sliding element. Of course, more than one groove can be provided. Advantageously, the respective second sliding element protrudes with its free end region out of the respective groove, wherein a through-hole for receiving a connecting element, preferably a screw, is provided in the free end region. The connecting element can be screwed into a threaded bore introduced in the spiral insert, wherein an adjusting element is preferably arranged between the free end region of the sliding element and the spiral insert.

Das Einstellelement ist in bevorzugter Ausgestaltung als Einstellplatte ausgeführt, welche vorteilhaft auf Stichmaß (Ebenheitstoleranz) gefertigt ist, um Fertigungstoleranzen auszugleichen.The adjusting element is designed in a preferred embodiment as a setting plate, which advantageously to gauge (Flatness tolerance) is made to compensate for manufacturing tolerances.

Mittels der zum einen radialen und zum anderen axialen Führung bzw. des radialen bzw. axialen Gleitens des Stellrings in dem Spiraleinsatz über die jeweiligen Gleitelemente können so Spaltmaße zwischen dem Stellring und dem Spiraleinsatz im Vergleich zum bekannten Heißgasexpander erheblich reduziert werden, da der Stellring in seinen Abmessungen an die dazu korrespondierende Ausnehmung in dem Spiraleinsatz im Wesentlichen angepasst hergestellt werden kann. Natürlich kann noch ein geringes Spaltmaß vorhanden sein, das aber, wie bereits erwähnt, erheblich kleiner als im bekannten Heißgasexpander ist. Zudem ist der Stellring über die Gleitelemente ausreichend lagesicher in der Ausnehmung aufgenommen, so dass ein Anschlagen des Stellrings an dem Spiraleinsatz vermieden ist. Hierdurch unterliegen die Komponenten einer reduzierten mechanischen Belastung, wodurch die zu erwartende Lebensdauer erhöht ist.By means of the one radial and the other axial guidance or the radial or axial sliding of the adjusting ring in the spiral insert on the respective sliding elements so gap dimensions between the collar and the spiral insert compared to the known hot gas expander can be significantly reduced, since the collar in his Dimensions can be made adapted to the corresponding recess in the spiral insert substantially. Of course, there may still be a small gap, but, as already mentioned, is considerably smaller than in the known hot gas expander. In addition, the adjusting ring is received on the sliding elements sufficiently secure in position in the recess, so that a striking of the adjusting ring is avoided on the spiral insert. As a result, the components of a reduced mechanical load, whereby the expected life is increased.

Insgesamt wird somit vorteilhaft erreicht, dass Spaltverluste reduziert sind, wodurch der Wirkungsgrad der Strömungsmaschine bzw. des beispielhaften Heißgasexpanders erhöht ist. Die Spaltmaße insbesondere zwischen dem Stellring und den Leitschaufeln können von vornherein minimaler ausgeführt werden.Overall, it is thus advantageously achieved that gap losses are reduced, as a result of which the efficiency of the turbomachine or of the exemplary hot gas expander is increased. The gaps, in particular between the collar and the vanes can be minimized from the outset.

Weiter vorteilhafte Ausgestaltungen der Erfindung sind in den Unteransprüchen und der folgenden Figurenbeschreibung offenbart. Es zeigen:

Fig. 1
einen Querschnitt durch einen beispielhaft dargestellten Heißgasexpander, und
Fig. 2
einen Stellring und einen Ausschnitt des Spiraleinsatzes aus Figur 1 als Einzelheit.
Further advantageous embodiments of the invention are disclosed in the subclaims and the following description of the figures. Show it:
Fig. 1
a cross section through a exemplified hot gas expander, and
Fig. 2
a collar and a section of the spiral insert FIG. 1 as a detail.

In den unterschiedlichen Figuren sind gleiche Teile stets mit denselben Bezugszeichen versehen, weswegen diese in der Regel auch nur einmal beschrieben werden.In the different figures, the same parts are always provided with the same reference numerals, which is why these are usually described only once.

Figur 1 zeigt eine Strömungsmaschine bzw. Getriebemaschine, die in dem dargestellten Ausführungsbeispiel als Heißgasexpander 1 mit einer Eintrittstemperatur eines vorzugsweise gasförmigen Mediums von bis zu 510°C ausgeführt ist. Der Heißgasexpander 1 weist mindestens ein Einlaufgehäuse 2 auf, in dem ein Spiraleinsatz 3 angeordnet ist. Dem Spiraleinsatz 3 ist ein Eintrittsleitapparat 4 und ein Konturring 6 zugeordnet. Dem Einlaufgehäuse 2 ist weiterhin ein Diffusor 7 zugeordnet. FIG. 1 shows a turbomachine or gear machine, which is designed in the illustrated embodiment as a hot gas expander 1 with an inlet temperature of a preferably gaseous medium of up to 510 ° C. The hot gas expander 1 has at least one inlet housing 2, in which a spiral insert 3 is arranged. The spiral insert 3 is assigned to an inlet guide 4 and a contour ring 6. The inlet housing 2 is further associated with a diffuser 7.

Der Eintrittsleitapparat 4 weist einen Stellring 8, Abstandhalter 9 und Leitschaufeln 11 auf.The inlet guide apparatus 4 has an adjusting ring 8, spacers 9 and guide vanes 11.

Die Leitschaufeln 11 sind über Mitnehmer 12 mit dem Stellring 8 verbunden, so dass ein Verdrehen des Stellrings 8 eine entsprechende Verstellung der Leitschaufeln 11 bewirkt, die drehbar an den Abstandhaltern 9 befestigt sind. Die Abstandhalter 9 dienen somit als Drehachse der Leitschaufeln 11.The guide vanes 11 are connected via drivers 12 with the adjusting ring 8, so that a rotation of the adjusting ring 8 causes a corresponding adjustment of the guide vanes 11 which are rotatably mounted on the spacers 9. The spacers 9 thus serve as the axis of rotation of the guide vanes 11.

In dem dargestellten Ausführungsbeispiel ist der Stellring 8 im Querschnitt gesehen L-förmig mit einem Basissteg 13 und einem senkrecht dazu angeordneten Steg 14 ausgeführt. Der Steg 14 ist von dem Basissteg 13 in Richtung zum Konturring 6 orientiert. Der Basissteg 13 weist eine zu einer Innenseite 16 des Spiraleinsatzes 3 orientierte Außenseite 17 und eine dazu gegenüberliegende Innenseite 18 auf. Zwischen der Außenseite 17 und der Innenseite 18 des Basissteges 13 ist eine Stirnseite 19 angeordnet.In the illustrated embodiment, the adjusting ring 8 is seen in cross-section L-shaped with a base web 13 and a web 14 arranged perpendicular thereto. The web 14 is oriented by the base web 13 in the direction of the contour ring 6. The base web 13 has an outer side 17 oriented toward an inner side 16 of the spiral insert 3 and an inner side 18 lying opposite thereto. Between the outer side 17 and the inner side 18 of the base web 13, an end face 19 is arranged.

In dem Spiraleinsatz 3 ist eine an den Stellring 8 korrespondierende Ausnehmung 21 angeordnet, welche den Stellring 8 aufnimmt. Zwischen der Stirnseite 19 sowie der Außenseite 18 des Stellrings 8 bzw. seines Basissteges 13 und der jeweils korrespondierenden Innenseite 16 des Spiraleinsatzes bzw. seiner Ausnehmung 21 ist ein geringer Spalt vorhanden.In the spiral insert 3 a corresponding to the adjusting ring 8 recess 21 is arranged, which receives the adjusting ring 8. Between the end face 19 and the outer side 18 of the adjusting ring 8 or its base web 13 and the respective corresponding inner side 16 of the spiral insert or its recess 21, a small gap is present.

Zur radialen Führung ist in der Innenseite 16 des Spiraleinsatzes 3 ist eine umlaufende Nut 22 eingebracht. In der Nut 22 sind Halteelemente 23 lagesicher mittig angeordnet. Das jeweilige Halteelement 23 ist bevorzugt als Stift ausgeführt, der mit seinem Befestigungsende in dem Spiraleinsatz 3 befestigt ist. Zur Aufnahme des jeweiligen Halteelementes 23 kann eine Durchgangsbohrung in dem Spiraleinsatz 3 vorgesehen sein. Das jeweilige Halteelement 23 kann aber auch in einer zur Außenseite 24 des Spiraleinsatzes 3 geschlossenen Bohrung gehalten sein.For radial guidance is in the inner side 16 of the spiral insert 3, a circumferential groove 22 is introduced. In the groove 22 holding elements 23 are arranged securely in the center. The respective holding element 23 is preferably designed as a pin which is fastened with its attachment end in the spiral insert 3. For receiving the respective holding element 23, a through hole may be provided in the spiral insert 3. However, the respective holding element 23 may also be held in a bore closed to the outside 24 of the spiral insert 3.

In die umlaufende Nut 22 sind erste Gleitelemente 26 bevorzugt spielfrei eingesetzt. Die jeweiligen Gleitelemente 26 sind bevorzugt als Gleitplatte ausgeführt und weisen eine zum jeweiligen Haltelement 23 korrespondierende Aufnahmebohrung auf, die wiederum durchgehend eingebracht oder zu einer Gleitfläche 27 des jeweiligen Gleitelementes 26 geschlossen sein kann. Das jeweilige Gleitelement 26 umfasst das Halteelement 23 im Wesentlichen spielfrei, wobei das Halteelement 23 mit seinem zum Befestigungsende gegenüberliegenden Endbereich in dem jeweiligen Gleitelement 26 bzw. in dessen Aufnahmebohrung aufgenommen ist.In the circumferential groove 22 first sliding elements 26 are preferably used without play. The respective sliding elements 26 are preferably designed as a sliding plate and have a respective holding element 23 corresponding receiving bore, which in turn may be introduced continuously or closed to a sliding surface 27 of the respective sliding member 26. The respective sliding element 26 comprises the retaining element 23 substantially free of play, wherein the retaining element 23 is received with its end region opposite the fastening end in the respective sliding element 26 or in its receiving bore.

Mit seiner Gleitfläche 27 liegt das jeweilige Gleitelement 26 auf der Außenseite 17 des Stellrings 8 bzw. seines Basissteges 13 an.With its sliding surface 27, the respective sliding member 26 abuts on the outer side 17 of the adjusting ring 8 or its base web 13.

Mittels der ersten Gleitelemente 26 ist der Stellring radial in dem Spiraleinsatz 3 geführt.By means of the first sliding elements 26, the adjusting ring is guided radially in the spiral insert 3.

Zur axialen Führung des Stellrings 8 in dem Spiraleinsatz 3 ist ein zweites Gleitelement 28 vorgesehen, welches wiederum bevorzugt als Gleitplatte ausgeführt ist. Das zweite Gleitelement 28 zur axialen Führung greift mit seinem Einsteckbereich 29 in eine Nut 31 ein, die in die Innenseite 18 des Stellrings 8 bzw. seines Basissteges 13 eingebracht ist. Die Nut 31 weist eine radiale Tiefenerstreckung auf. Der Einsteckbereich 29 kann auch als Gleitfläche 29 bezeichnet werden. Zweckmäßiger Weise weist der Stellring 8 zumindest drei Nuten 31 auf, von denen in den Figuren 1 und 2 lediglich eine dargestellt ist.For axial guidance of the adjusting ring 8 in the spiral insert 3, a second sliding element 28 is provided, which in turn is preferably designed as a sliding plate. The second sliding member 28 for axial guidance engages with its insertion region 29 in a groove 31, which in the inside 18 of the Adjusting ring 8 and its base web 13 is introduced. The groove 31 has a radial depth extension. The insertion region 29 can also be referred to as a sliding surface 29. Appropriately, the adjusting ring 8 at least three grooves 31, of which in the FIGS. 1 and 2 only one is shown.

An seinem zu der Gleitfläche 29 gegenüberliegenden freien Endbereich 32 weist das zweite Gleitelement 28 eine Durchgangsbohrung zur Durchführung eines Verbindungselementes 33, vorzugsweise einer Schraube auf. Das Verbindungselement 33 bzw. die Schraube ist mit einer dazu korrespondierenden Gewindebohrung 34 in dem Spiraleinsatz 3 verbindbar, so dass das Gleitelement 28 hinreichend fest gehalten ist.At its opposite to the sliding surface 29 free end portion 32, the second sliding element 28 has a through hole for the passage of a connecting element 33, preferably a screw. The connecting element 33 or the screw can be connected to a corresponding threaded bore 34 in the spiral insert 3, so that the sliding element 28 is held sufficiently firmly.

Zwischen dem zweiten Gleitelement 28 und der zugeordneten Fläche des Spiraleinsatzes 3 ist ein Einstellelement 36 angeordnet. Das Einstellelement 36 ist bevorzugt als Einstellplatte ausgeführt, und zum Ausgleich von Fertigungstoleranzen vorzugsweise auf Stichmaß gefertigt.Between the second sliding element 28 and the associated surface of the spiral insert 3, an adjusting element 36 is arranged. The adjusting element 36 is preferably designed as a setting plate, and preferably made to compensate for manufacturing tolerances on gauge.

Die Gleitelemente 26 und 28 sind aus einem geeigneten Material gefertigt und bevorzugt zumindest an ihren Gleitflächen 27 bzw. 29 mit geeigneten Spezialschichten beschichtet bzw. entsprechend behandelt.The sliding elements 26 and 28 are made of a suitable material and preferably coated at least on their sliding surfaces 27 and 29 with suitable special layers or treated accordingly.

In dem in Figur 1 dargestellten Ausführungsbeispiel ist dem Spiraleinsatz 3 zudem ein Einstellsystem 37 zur radialen Einstellbarkeit, ein Spannsystem 38 zur Minimierung axialer Spalte und ein geeignetes Dichtsystem 39 zugeordnet, dass den Konturring 6 zum Diffusor 7 abdichtet.In the in FIG. 1 illustrated embodiment, the spiral insert 3 is also associated with a setting system 37 for radial adjustability, a clamping system 38 for minimizing axial gaps and a suitable sealing system 39 that seals the contour ring 6 to the diffuser 7.

Claims (5)

  1. Turbomachine,
    in particular a hot gas expander,
    having at least one inlet casing (2) to which there is attached an inlet guide apparatus (4),
    wherein the inlet guide apparatus has a unison ring (8), wherein
    the turbomachine has first and second sliding elements (26; 28) which are assigned to the unison ring (8) and on which the unison ring (8) slides when moving,
    characterized in that
    the unison ring (8) has, on its inner side (18), at least one groove (31) which extends in the circumferential direction and in which at least one second sliding element (28) engages,
    wherein the groove (31) has a radial depth such that the unison ring (8) is mounted axially by means of the second sliding element (28).
  2. Turbomachine according to Claim 1,
    characterized in that
    the sliding elements (26; 28) are embodied as sliding plates, are made of a temperature- and corrosion-resistant base material and are coated or treated at least on their sliding faces (27; 29).
  3. Turbomachine according to Claim 1 or 2,
    characterized in that
    the first sliding elements (26) bear radially against the unison ring (8) such that the unison ring (8) is mounted radially.
  4. Turbomachine according to one of the preceding claims,
    characterized in that
    the respective first sliding element (26) is assigned a retaining element (23) that has a securing end which is held in a volute insert (3) arranged in the inlet casing (2),
    wherein an end region - opposite the securing end - of the retaining element (23) is surrounded by the respective sliding element (26).
  5. Turbomachine according to one of the preceding claims,
    characterized in that
    the sliding element (28) has, in its free end region (32) opposite the sliding face (29), a through-bore for the insertion of a connecting element (33) which can be screwed into a corresponding threaded bore (34) in the volute insert (3),
    wherein an adjustment element (36) is arranged between the free end region (32) and the volute insert (3).
EP07004362.5A 2007-03-02 2007-03-02 Axial and radial support of the unison ring for inlet guide vane assemblies of hot gas expanders Not-in-force EP1965037B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07004362.5A EP1965037B1 (en) 2007-03-02 2007-03-02 Axial and radial support of the unison ring for inlet guide vane assemblies of hot gas expanders

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07004362.5A EP1965037B1 (en) 2007-03-02 2007-03-02 Axial and radial support of the unison ring for inlet guide vane assemblies of hot gas expanders

Publications (2)

Publication Number Publication Date
EP1965037A1 EP1965037A1 (en) 2008-09-03
EP1965037B1 true EP1965037B1 (en) 2016-12-14

Family

ID=38311553

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07004362.5A Not-in-force EP1965037B1 (en) 2007-03-02 2007-03-02 Axial and radial support of the unison ring for inlet guide vane assemblies of hot gas expanders

Country Status (1)

Country Link
EP (1) EP1965037B1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012003213A1 (en) * 2012-02-17 2013-08-22 Ihi Charging Systems International Gmbh Adjustable distributor for a turbine of an exhaust gas turbocharger and turbine for an exhaust gas turbocharger
DE102016006357A1 (en) * 2016-05-21 2017-11-23 Dürr Systems Ag Turbine housing and turbine with such a turbine housing
DE102017223791A1 (en) 2017-12-27 2019-06-27 Siemens Aktiengesellschaft Shaft seal arrangement of a turbomachine, turbomachine
US10947861B2 (en) 2018-02-26 2021-03-16 Garrett Transportation I Inc Variable vane mechanism for turbocharger with unison ring and bearing members having independent material characteristics

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4741666A (en) 1985-12-23 1988-05-03 Ishikawajima-Harima Jukogyo Kabushiki Kaisha Variable displacement turbocharger
DE10238412A1 (en) * 2002-08-22 2004-03-04 Volkswagen Ag Turbocharger with variable turbine geometry for IC engines has guide blade adjusting ring born in three inner radial bearings
US6872050B2 (en) 2002-12-06 2005-03-29 York International Corporation Variable geometry diffuser mechanism
GB0326544D0 (en) 2003-11-14 2003-12-17 Rolls Royce Plc Variable stator vane arrangement for a compressor
DE102004037082A1 (en) * 2004-07-30 2006-03-23 Volkswagen Ag Exhaust gas turbocharger for internal combustion engine of especially motor vehicle has first slide surface formed on bearing housing and axially guides adjustment ring on side facing away from guide vane carrier

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP1965037A1 (en) 2008-09-03

Similar Documents

Publication Publication Date Title
DE102008014678B4 (en) Turbocharger with a variable turbine geometry VTG
EP2209969B1 (en) Supercharger device
EP1977084B1 (en) Adjustable guiding device
EP1672178B1 (en) Boîtier de turbine d'un turbocompresseur d'échappement à géométrie variable de turbine
WO2009092678A1 (en) Turbine; in particular for an exhaust gas turbocharger; and exhaust gas turbocharger
EP2452076B1 (en) Turbomachine impeller
EP3000984A1 (en) Turbine vane adjustment device for a gas turbine
DE102012106789B4 (en) Adjustable diffuser for a turbine, turbine for an exhaust gas turbocharger and exhaust gas turbocharger
EP2131042A2 (en) Adjustable coolant pump for the coolant circuit of a combustion engine
DE69818589T2 (en) Positioning drive device with play adjustment for variable tubular diffuser
EP1965037B1 (en) Axial and radial support of the unison ring for inlet guide vane assemblies of hot gas expanders
DE102011003522A1 (en) Coupled outlet diffuser angle adjustment
EP2194230A1 (en) Guide blade assembly for an axial turbo engine
EP1420152A2 (en) Turbocharger
EP3091188B1 (en) Flow engine with a sealing arrangement
EP3078808A1 (en) Rotor blade row for a flow engine
EP2617947A2 (en) Aviation gas turbine with adjustable fan
DE102008034751A1 (en) Exhaust gas turbocharger for internal combustion engine, has floatingly mounted spacer ring provided between guide vanes and turbine housing, linked with inflowing exhaust gas via pressure channel and rearwardly subjected with exhaust gas
EP2310634B1 (en) Rotating blade system for a row of rotating blades of a turbomachine
DE102006053731A1 (en) Device with a temperature change responsive compensation element
EP2984295A1 (en) Sealing ring segment for a stator of a turbine
DE2740192C2 (en) Gap seal for an axially flow-around guide vane of a turbomachine that is adjustable about its longitudinal axis
DE102012206302A1 (en) Variable turbine and/or compressor geometry for charging device e.g. exhaust gas turbocharger, has channel formed in blade bearing ring in adjacent state to blade trunnions, to equalize pressure between control chamber and flow space
DE1286333B (en) Ring-shaped guide device for gas turbine engines with axial flow
EP1965038B1 (en) Actuation device for the unison ring of a variable geometry turbine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

17P Request for examination filed

Effective date: 20090302

AKX Designation fees paid

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

17Q First examination report despatched

Effective date: 20090511

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160708

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 853783

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170115

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502007015317

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20161214

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170315

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170414

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170314

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170414

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502007015317

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PCOW

Free format text: NEW ADDRESS: WERNER-VON-SIEMENS-STRASSE 1, 80333 MUENCHEN (DE)

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20170915

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20170314

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20171130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170331

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170302

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170302

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170314

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170331

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 853783

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170302

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170331

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20180518

Year of fee payment: 12

Ref country code: CH

Payment date: 20180614

Year of fee payment: 12

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170302

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20180327

Year of fee payment: 12

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20070302

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502007015317

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20161214

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191001

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190331

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190302

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161214