WO2009074355A1 - Turbomachine axiale à pertes d'interstice réduites - Google Patents

Turbomachine axiale à pertes d'interstice réduites Download PDF

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Publication number
WO2009074355A1
WO2009074355A1 PCT/EP2008/054849 EP2008054849W WO2009074355A1 WO 2009074355 A1 WO2009074355 A1 WO 2009074355A1 EP 2008054849 W EP2008054849 W EP 2008054849W WO 2009074355 A1 WO2009074355 A1 WO 2009074355A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
ring
axial
vane
vane ring
Prior art date
Application number
PCT/EP2008/054849
Other languages
German (de)
English (en)
Inventor
Hans-Thomas Bolms
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
Publication of WO2009074355A1 publication Critical patent/WO2009074355A1/fr

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical

Definitions

  • the invention relates to an axial turbomachine with a
  • An axial turbomachine is, for example, an axial turbine for a gas turbine.
  • a conventional axial turbine 101 shown in FIG. 2 is flowed through from its inlet 102 to its outlet 103.
  • the axial turbine 101 is formed by an opening in the flow direction annular channel which is bounded on the outside by a housing 104 and the inside of a hub 116.
  • a plurality of rotor stages 107 and a plurality of stator stages 108 are arranged, wherein the rotor stages 107 and the stator stages 108 are arranged alternately seen in the flow direction of the axial turbine 101.
  • the rotor stages 107 are each formed by a plurality of rotor blades 109, which are arranged side by side on the outer circumference of a rotor disk 113.
  • the stator stages 108 are each formed by a plurality of vanes 114 which are juxtaposed and secured along the inner circumference of the housing 104.
  • the vanes 114 have on the housing side a shroud 115, with which the vanes 114 are joined together to form a vane ring. Facing the longitudinal axis of the axial turbine 101, the guide vanes 114, the hub 116, which has on its side facing the rotor disc 113 a hub inner side 119.
  • the hub inner side 119 is arranged adjacent to a rotor disk outer side 120.
  • the inner side of the hub 119 and the outer side of the rotor disk 120 are designed as two cylinder surfaces arranged concentrically with respect to one another, which are arranged at a radial distance 122 from one another. Due to the radial distance 122 between the hub inner side 119 and the rotor disc outer 120, a radial gap 121 is provided which has the radial gap height 122.
  • the rotor disc 113 rotates, whereas the guide vane 114 with its hub 116 remains stationary.
  • a relative movement wherein it is prevented by providing the radial gap 121, that the hub inner side 119 and the rotor disk outer side 120 touch and grind against each other.
  • both the housing 104 with the guide vanes 114 and the rotor blades 109 with the rotor disk 113 are in contact with hot gas.
  • the housing 104 with the blades 109 has a more massive construction than the rotor disks 113 with the races 109. Therefore, the housing 104 and the vanes 114 heat up more slowly than the rotor disks 113 and the blades 109, whereby the rotor disk 113 is seen relative to the housing 104 expands to the outside.
  • the housing 104 with the guide vanes 114 attached thereto retains the original position.
  • the Radialspat 121 is provided correspondingly dimensioned with the radial gap height 122.
  • the disadvantage is that flows through the radial gap 121, a leakage flow that affects the aerodynamic efficiency of the axial turbine 101.
  • the operation of the axial turbine 101 is affected due to the provision of the radial gap 121, so that the performance and efficiency of the axial turbine 101 is reduced.
  • the object of the invention is to provide an axial turbine whose gap losses are low.
  • the axial turbine according to the invention has a conical housing in the throughflow direction, a guide vane ring attached thereto and a rotor which is connected to the guide
  • the inner rim of the vane ring facing the longitudinal axis of the axial turbomachine and the surface portion of the rotor facing the inner side of the vane ring are arranged at a radial distance from one another to form a radial gap and are designed as conical frustoconical surfaces arranged concentrically to one another in the flow direction ,
  • the radial gap has a conical course and can be minimized during operation of the axial turbomachine to reduce lossy, flowing through the annular gap leakage flow.
  • a different expansion speed of the housing and the stator vanes on the one hand and the rotor on the other hand can be adjusted.
  • the radial gap is reduced in an axial displacement of the rotor opposite to the opening of the frustoconical surfaces.
  • the radial distance at each point of the radial gap has the same value.
  • the two frusto-conical surfaces are arranged exactly concentric with each other, whereby a maximum possible clearance for a relative movement between the rotor and the vane ring is provided with the radial gap.
  • the opening angle of the frustoconical surface of the vane ring, the opening angle of the frustoconical surface of the rotor and the opening angle of the portion of the housing, which is located outside of the frusto-conical surfaces in the radial direction have the same opening angle.
  • the opening angle of the radial gap between the frustoconical surface of the rotor and the frustoconical surface of the vane ring may alternatively also be dependent on the distance of the radial gap from the axial bearing of the rotor.
  • the opening angle should be chosen so that the imaginary
  • Extension of the frustoconical surfaces converges in an imaginary cone tip and the cone tip is at that axial position, the longitudinal axis of the rotor, on which also the axial position of the axial bearing of the rotor is provided.
  • the rotor has a first group of blades and a second group of blades, the first group of blades being upstream and the second group of blades being downstream of the vane ring.
  • the blades are radially arranged at a distance from the housing, whereby a radial gap is formed in the housing area between the housing and the rotor blades.
  • the opening angle of the portion of the housing which is located in the radial direction outside the frustoconical surfaces, has the same opening angle as the frustoconical surfaces, the radial gap on the blades is substantially parallel to the frusto-conical running surfaces running.
  • the radial gap on the blades as well as the radial gap between the frustoconical surfaces is hydraulically optimized.
  • the rotor preferably has two rotor disks arranged side by side in the axial direction, the outer peripheral surfaces of which form the frustoconical surface of the rotor.
  • the first group of rotor blades is provided for the first rotor disk and the second group of rotor blades is provided for the second rotor disk, so that the two rotor disks are disposed adjacent one another in the axial direction.
  • the transition between the two rotor bridged by the frustoconical surface of the vane ring.
  • the vane ring comprises a plurality of vanes, which are arranged side by side in the circumferential direction and each hub side have a Leitschaufelkopfplatte with which an inner ring of the vane ring is formed.
  • the vane ring has a U-ring, which is arranged in the radial direction inside of the Leitschaufelkopflatten this encompassing, so that from the U-ring, the Leitschaufelkopfplatten are held together to the inner ring.
  • the frustoconical surface of the vane ring is provided on the radially inner side of the U-ring.
  • a stable construction of the guide vane ring is provided by means of the U-ring and, on the other hand, the frustoconical surface of the vane ring is formed.
  • a gas seal device be provided in the radial gap at the frustoconical surface of the vane ring and / or the truncated cone surface of the rotor. As a result, the flow resistance of the radial gap is increased, whereby the leakage flow through the radial gap is reduced.
  • the sealing device is preferably a labyrinth and / or a honeycomb.
  • the labyrinth and / or honeycomb may be of conventional design.
  • the U-ring is exposed to sealing gas. Due to the fact that the mass flow of the leakage flow, which occurs during operation of the axial turbomachine through the radial gap, is reduced, the barrier gas fraction can be reduced. be graced. Thus, a further increase in the efficiency of the axial turbomachine is achieved.
  • Fig. 1 shows a longitudinal section of an axial turbine according to the invention
  • Fig. 2 is a longitudinal section of a conventional axial turbine.
  • an axial turbine 1 can be flowed through from its inlet 2 to its outlet 3.
  • the axial turbine 1 has a housing 4 which has a housing contour 5 on its inside. Seen to the longitudinal axis of the axial turbine 1, this has a hub contour 6, wherein between the housing contour 5 and the hub contour 6 is formed in the flow direction widening annular channel.
  • Each rotor stage 7 has a plurality of rotor blades 9, which are formed elongated in the radial direction and each have a blade root 10 on the hub side.
  • the runners 9 On the housing side, the runners 9 each have a blade tip 11, which is arranged at a distance from the housing 4, so that a rotor blade gap 12 is formed between the housing 4 and the blade tip 11.
  • the axial turbine 1 furthermore has a plurality of rotor disks 13 threaded in the axial direction, wherein a plurality of rotor blades 9 with their blade feet 10 are fastened on the outer circumference of each rotor disk 13.
  • Each vane ring 8 is formed by a plurality of vanes 14, which are arranged side by side in the circumferential direction.
  • the guide vanes 14 form a cover band 15 on the housing side, and each have a guide vane head plate 16 on the hub side. With the guide vane head plate 16, the hub contour between two rotor stages 7 is formed.
  • the vane ring 8 also has a U-ring 17, which surrounds the vane head plates 16 and thus the guide vanes 14, so that the vane ring 8 is formed on the hub side as a stable structure. Seen in the axial direction, an axial gap 18 is formed between the U-ring 17 and the blade tips 10 located immediately upstream and the blade feet 10 located immediately downstream.
  • the U-ring 17 has on its inside viewed in the radial direction a frustoconical surface 19 which is inclined at the longitudinal axis of the axial turbine 1 by an opening angle. Facing the truncated cone surface 19, the two adjacent rotor disks 13 form on their outer circumference a frustoconical surface 20 which is concentric within the
  • Truncated cone surface 19 is located and forms the opening angle 23 with the longitudinal axis of the axial turbine.
  • the frustoconical surface 19 of the U-ring 17 and the frustoconical surface 20 of the rotor disks 13 are arranged at a radial distance from one another, so that a radial gap 21 is formed between the frustoconical surface 19 of the U-ring and the frustoconical surface 20 of the rotor disks 13.
  • Radial gap 21 has a constant radial gap height 22 across the axial direction.
  • a labyrinth 24 is provided within the radial gap 21.
  • the U-ring 17 is internally provided with a sealing air passage 25 by providing overpressure blocking air.
  • a blocking air hole 26 is provided in the region of the radial gap 18, so that sealing air is introduced through the sealing air hole 26 and the axial gap 18 to reduce the leakage flow.
  • an axial displacement of the rotor stages 7 can take place from the outlet 3 to the inlet 2 through a rotor displacement, so that the radial gap height 22 is reduced. As a result, the mass flow of the leakage flow through the radial gap is reduced.

Abstract

Cette turbomachine axiale présente : un boîtier (4) conique dans la direction d'écoulement ; une couronne d'aubes directrices (8) fixée sur ce boîtier ; et un rotor qui est disposé sur la couronne d'aubes directrices en étant directement voisin de celle-ci vers l'intérieur. Le côté intérieur de la couronne d'aubes directrices qui est tourné vers l'axe longitudinal de la turbomachine axiale (1) et la partie de surface du rotor qui est tournée vers le côté intérieur de la couronne d'aubes directrices (8) sont disposés à une distance radiale (22) l'un par rapport à l'autre en formant un interstice radial (21), et sont réalisés sous la forme de surfaces tronconiques (19, 20) coniques dans la direction d'écoulement, disposées concentriquement l'une par rapport à l'autre.
PCT/EP2008/054849 2007-12-10 2008-04-22 Turbomachine axiale à pertes d'interstice réduites WO2009074355A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007059341.6 2007-12-10
DE102007059341 2007-12-10

Publications (1)

Publication Number Publication Date
WO2009074355A1 true WO2009074355A1 (fr) 2009-06-18

Family

ID=39673233

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/054849 WO2009074355A1 (fr) 2007-12-10 2008-04-22 Turbomachine axiale à pertes d'interstice réduites

Country Status (1)

Country Link
WO (1) WO2009074355A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2538030A1 (fr) * 2011-06-22 2012-12-26 Siemens Aktiengesellschaft Système d'étanchéité à labyrinthe pour une turbine à gaz
EP3511526A1 (fr) * 2018-01-12 2019-07-17 United Technologies Corporation Dispositif d'étanchéité et moteurs à turbine à gaz

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2307520A (en) * 1995-11-14 1997-05-28 Rolls Royce Plc Gas turbine engine sealing arrangement
EP0894945A2 (fr) * 1997-07-29 1999-02-03 Siemens Aktiengesellschaft Turbine et aubage de turbine
EP1249577A1 (fr) * 2001-04-12 2002-10-16 Siemens Aktiengesellschaft Turbine à gaz avec des éléments de virole axialement mobile
EP1369562A2 (fr) * 2002-06-05 2003-12-10 Nuovo Pignone Holding S.P.A. Dispositif de support pour une tuyère de guidage d'une turbine à gaz
EP1600607A2 (fr) * 2004-05-27 2005-11-30 ROLLS-ROYCE plc Dispositif pour régler le jeu radial du rotor d'une turbine à gaz
EP1614862A1 (fr) * 2004-07-07 2006-01-11 Hitachi, Ltd. Turbine à gas et méthode de refroidissement et d' étanchement d'une turbine à gas

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2307520A (en) * 1995-11-14 1997-05-28 Rolls Royce Plc Gas turbine engine sealing arrangement
EP0894945A2 (fr) * 1997-07-29 1999-02-03 Siemens Aktiengesellschaft Turbine et aubage de turbine
EP1249577A1 (fr) * 2001-04-12 2002-10-16 Siemens Aktiengesellschaft Turbine à gaz avec des éléments de virole axialement mobile
EP1369562A2 (fr) * 2002-06-05 2003-12-10 Nuovo Pignone Holding S.P.A. Dispositif de support pour une tuyère de guidage d'une turbine à gaz
EP1600607A2 (fr) * 2004-05-27 2005-11-30 ROLLS-ROYCE plc Dispositif pour régler le jeu radial du rotor d'une turbine à gaz
EP1614862A1 (fr) * 2004-07-07 2006-01-11 Hitachi, Ltd. Turbine à gas et méthode de refroidissement et d' étanchement d'une turbine à gas

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2538030A1 (fr) * 2011-06-22 2012-12-26 Siemens Aktiengesellschaft Système d'étanchéité à labyrinthe pour une turbine à gaz
EP3511526A1 (fr) * 2018-01-12 2019-07-17 United Technologies Corporation Dispositif d'étanchéité et moteurs à turbine à gaz
US10760442B2 (en) 2018-01-12 2020-09-01 Raytheon Technologies Corporation Non-contact seal with angled land
EP4279770A3 (fr) * 2018-01-12 2024-02-21 RTX Corporation Dispositif d'étanchéité pour moteurs à turbine à gaz

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