EP1965036A1 - Turbomachine avec virole réglable - Google Patents

Turbomachine avec virole réglable Download PDF

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Publication number
EP1965036A1
EP1965036A1 EP07004387A EP07004387A EP1965036A1 EP 1965036 A1 EP1965036 A1 EP 1965036A1 EP 07004387 A EP07004387 A EP 07004387A EP 07004387 A EP07004387 A EP 07004387A EP 1965036 A1 EP1965036 A1 EP 1965036A1
Authority
EP
European Patent Office
Prior art keywords
eccentric
spiral insert
housing
contour
rotor
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.)
Withdrawn
Application number
EP07004387A
Other languages
German (de)
English (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 EP07004387A priority Critical patent/EP1965036A1/fr
Priority to CN 200810082131 priority patent/CN101255803A/zh
Publication of EP1965036A1 publication Critical patent/EP1965036A1/fr
Withdrawn legal-status Critical Current

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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
    • 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
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
    • 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
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/35—Arrangement of components rotated

Definitions

  • the invention relates to a turbomachine in particular H
  • a rotor blade comprising a rotor, a housing, and a non-rotating flow contour, which limits flow channels in the region of the blades on one side.
  • Such turbomachines or geared machines 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. If now the adjusting ring is rotated in a desired angular amount, the drivers cause a forced adjustment of the guide vanes, so that the adjustment of the guide vanes influencing the direction and / or the 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 unit to be used must therefore be performed during assembly with relatively large-ßem radial clearance to the inlet housing or the impeller to avoid jamming due to different thermal expansion and axial To ensure freedom of movement.
  • the contouring gap between the contour ring surface and the corresponding blade edge of the impeller is sized so large that the efficiency of the hot gas expander is significantly reduced by extremely high gap losses.
  • the invention is therefore based on the object to improve a turbomachine of the type mentioned, in particular a hot gas expander, by simple means to the effect that the gap losses are reduced, so that the efficiency can be significantly increased.
  • the object is achieved in that by means of at least one adjustment system, by means of which the relative position of the flow contour to the housing in the circumferential direction is adjustable, the position of the flow contour to the rotor is in each case adjustable and / or detectable.
  • the flow contour in particular a spiral insert movable to the housing or to the inlet housing mountable, wherein the spiral insert is preferably seen in the radial direction movable adjustable or alignable.
  • the adjustable is movable to the housing or to the inlet housing mountable, wherein the spiral insert is preferably seen in the radial direction movable adjustable or alignable.
  • the adjustment system has a sliding element which is arranged in a recess or a groove of the spiral insert.
  • the sliding element may for example be designed as a sliding plate, which is made of a suitably suitable material, but the sliding element may also be provided with a corresponding coating.
  • the eccentric is designed as an eccentric sleeve, that is to say as an eccentrically drilled sleeve which has a bore with a bore axis offset relative to the center axis of the adjustment system, so that the eccentric sleeve has a wall thickness which changes in the circumferential direction at its insertion section.
  • the adjustment system has a connecting element for frictional connection of the spiral housing with the inlet housing.
  • the connecting element may be, for example, a stud bolt, which with its threaded portion in a corresponding Tapped hole engages in the inlet housing, with its bolt head rests against a contact flange of the eccentric.
  • the spiral insert is preassembled with its associated components outside the inlet housing and used as a unit in the inlet housing. For a first sufficient attachment or connection of the spiral insert with the inlet housing, it is sufficient if first the bolt or the connecting element is loosely screwed into the inlet housing, wherein the inserted into the bore of the slide plate eccentric with its abutment on both the sliding plate and the Bolt head is applied or is sufficiently braced for the following orientation.
  • the desired and required installation position of the spiral insert can be adjusted in the radial direction, so that the contouring gap between the contour ring or its outer side and the blades or their edges is minimized.
  • the required installation position i. a minimal Konturringspalt is set, the position or the setting by means of the bolt screw fixed in position.
  • spiral insert three adjustment systems are assigned, which are seen in the circumferential direction respectively mounted at 3,6 and 9 o'clock.
  • the eccentric advantageously allow a very simple and accurate installation of the spiral insert or the associated components, in particular the contour ring, so that the contouring gap can be designed extremely minimal. Due to the advantageous arrangement of the adjustment to 3.6 and 9 o'clock a centric position of the spiral insert in the radial direction is guaranteed even when heated to 510 ° C (inlet temperature). In addition, the spiral insert can advantageously move axially over the sliding plates, which is why the sliding elements have a correspondingly low friction Material can be made or coated with this.
  • the contouring gap between the impeller and the fixed contour ring can be adjusted or aligned, which can be set to a minimum level. This reduces the gap losses, which at the same time increases the efficiency of the hot gas expander.
  • FIG. 1 shows a turbomachine, such as a gear machine, which is designed in the illustrated embodiment as a hot gas expander 1 with a Eintemperatur a preferably gaseous medium of up to 510 ° C.
  • the hot gas expander 1 has an 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 spiral insert 3 is connected via an adjustment system 8 with the inlet housing 2, wherein in FIG. 1 due to the selected section, only a single adjustment system 8 can be seen.
  • FIG. 1 are two other adjustment systems 8, wherein the preferred way three provided adjustment system 8 are seen in the circumferential direction respectively mounted at 3,6 and 9 o'clock.
  • This in FIG. 1 recognizable adjustment system 8 is mounted eg at 3 o'clock.
  • the adjustment system, which is mounted at 9 o'clock is not recognizable.
  • the adjustment system 8, which is mounted at 6 o'clock is also not visible in the selected section.
  • the exemplified number of three adjustment systems should not be limited to this number is of course possible to provide less or more than three adjustment 8.
  • the adjustment system 8 has a sliding element 9, an eccentric 11 and a connecting element 12 ( FIG. 2 ).
  • the eccentric 11 is designed as eccentrically drilled sleeve.
  • the sliding element 9 can also be referred to as a sliding plate, which is arranged in a recess 13 or groove of the spiral insert 3, so that the spiral insert 3 is guided radially via the three sliding plates or three adjustment systems 8.
  • the sliding elements 9 are designed in such a way that they bear on the one hand against the inlet housing 2 and protrude somewhat beyond the spiral insert 3. Of course, the sliding elements 9 with their outside also flush with the spiral insert 3 complete.
  • a bore 14 is arranged, the center line X1 is arranged congruent to a bore 15 and the center line X2 in the inlet housing 2 when the spiral insert 3 is inserted or inserted in the inlet housing 2.
  • the bore 15 has an internal thread, which is designed corresponding to an external thread of the connecting element 12.
  • the connecting element 12 may for example be a bolt screw.
  • the eccentric 11 In the bore 14 of the eccentric 11 is set with its insertion portion 16.
  • the eccentric 11 is shown in the Embodiment designed as an eccentric sleeve with a through hole 17 whose center line X3 is offset to the congruent center lines X1 and X2 of the two holes 14 and 15.
  • the eccentric 11 seen on its wall in the circumferential direction has a changing wall thickness, wherein in FIG. 2 in the left plane of the drawing a minimum wall thickness and opposite to the right drawing plane a maximum wall thickness is shown.
  • the exemplified hot gas expander 1 also has an impeller 21, the blades 22 are spaced with their edges to a corresponding or to the blade edges opposite surface 23 of the contour ring 6, so that a contouring gap 24 is formed ( FIG. 1 ).
  • the spiral insert 3 is inserted into the inlet housing 2 and connected via the adjustment system 8 with the inlet housing 2, causes a rotation of the eccentric 11 via its abutment flange 18 a radial adjustment or orientation of the spiral insert 3 with the associated components, in particular the contour ring 6 the blades 22 and their edges, so that the contouring gap 24 can be minimized.
  • the minimum adjustment of the contouring gap 24 in the radial direction is achieved by an actuation or adjustment of all three adjustment systems 8.
  • the hot gas expander 1 can be removed.
  • a clamping system 26 and a suitable sealing system 27 may be assigned.
  • the spiral insert 3 can be movably axially adjustable via the sliding elements 9, so that the spiral insert 3 can move axially over the sliding elements 9.
  • the contour ring 6 can be sealed by the suitable sealing system 27 to the diffuser 7.
EP07004387A 2007-03-02 2007-03-02 Turbomachine avec virole réglable Withdrawn EP1965036A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP07004387A EP1965036A1 (fr) 2007-03-02 2007-03-02 Turbomachine avec virole réglable
CN 200810082131 CN101255803A (zh) 2007-03-02 2008-03-03 热气膨胀机的螺旋件的径向定位

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07004387A EP1965036A1 (fr) 2007-03-02 2007-03-02 Turbomachine avec virole réglable

Publications (1)

Publication Number Publication Date
EP1965036A1 true EP1965036A1 (fr) 2008-09-03

Family

ID=38323945

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07004387A Withdrawn EP1965036A1 (fr) 2007-03-02 2007-03-02 Turbomachine avec virole réglable

Country Status (2)

Country Link
EP (1) EP1965036A1 (fr)
CN (1) CN101255803A (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012110329A1 (de) * 2012-10-29 2014-04-30 Firma IHI Charging Systems International GmbH Verstellbarer Leitapparat für eine Turbine und Verfahren zur Herstellung eines verstellbaren Leitapparates
EP2487333A3 (fr) * 2011-02-09 2017-11-22 Siemens Aktiengesellschaft Turbine dotée d'un rotor et d'un boîtier de turbine réglables l'un par rapport à l'autre
EP4015830A1 (fr) 2020-12-18 2022-06-22 Siemens Energy Global GmbH & Co. KG Turbomachine radiale

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1120216B (de) * 1958-11-24 1961-12-21 Ford Werke Ag Gasturbine
DE1178253B (de) * 1962-03-03 1964-09-17 Maschf Augsburg Nuernberg Ag Axial-durchstroemte Kreiselradmaschine mit einstellbarem Deckband
US4127357A (en) * 1977-06-24 1978-11-28 General Electric Company Variable shroud for a turbomachine
GB2042646A (en) * 1979-02-20 1980-09-24 Rolls Royce Rotor blade tip clearance control for gas turbine engine
US4776168A (en) * 1987-05-21 1988-10-11 Woollenweber William E Variable geometry turbocharger turbine
DE10060740A1 (de) * 2000-12-07 2002-06-13 Alstom Switzerland Ltd Vorrichtung zur Spaltmasseinstellung für eine Strömungsmaschine
US20040109757A1 (en) * 2002-12-06 2004-06-10 York International Corporation Variable geometry diffuser mechanism

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1120216B (de) * 1958-11-24 1961-12-21 Ford Werke Ag Gasturbine
DE1178253B (de) * 1962-03-03 1964-09-17 Maschf Augsburg Nuernberg Ag Axial-durchstroemte Kreiselradmaschine mit einstellbarem Deckband
US4127357A (en) * 1977-06-24 1978-11-28 General Electric Company Variable shroud for a turbomachine
GB2042646A (en) * 1979-02-20 1980-09-24 Rolls Royce Rotor blade tip clearance control for gas turbine engine
US4776168A (en) * 1987-05-21 1988-10-11 Woollenweber William E Variable geometry turbocharger turbine
DE10060740A1 (de) * 2000-12-07 2002-06-13 Alstom Switzerland Ltd Vorrichtung zur Spaltmasseinstellung für eine Strömungsmaschine
US20040109757A1 (en) * 2002-12-06 2004-06-10 York International Corporation Variable geometry diffuser mechanism

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2487333A3 (fr) * 2011-02-09 2017-11-22 Siemens Aktiengesellschaft Turbine dotée d'un rotor et d'un boîtier de turbine réglables l'un par rapport à l'autre
DE102012110329A1 (de) * 2012-10-29 2014-04-30 Firma IHI Charging Systems International GmbH Verstellbarer Leitapparat für eine Turbine und Verfahren zur Herstellung eines verstellbaren Leitapparates
EP4015830A1 (fr) 2020-12-18 2022-06-22 Siemens Energy Global GmbH & Co. KG Turbomachine radiale

Also Published As

Publication number Publication date
CN101255803A (zh) 2008-09-03

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