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
  • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
  • F01D11/005—Sealing means between non relatively rotating elements
  • F01D11/006—Sealing the gap between rotor blades or blades 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
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/02—Blade-carrying members, e.g. rotors
• • 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
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades

Definitions

• the present invention relates to a rotating turbomachine, in particular a gas turbine.
• Rotary turbomachines usually have a rotor having at least two blade rows with multiple blades and at least one rotor heat shield with a plurality of shield elements, wherein the respective rotor heat shield is arranged axially between two adjacent blade rows. Furthermore, such a turbomachine usually comprises a stator which has at least one row of guide vanes arranged axially between two adjacent blade rows and having a plurality of guide vanes.
• the invention aims to remedy this situation.
• the invention as characterized in the claims, deals with the problem, for a turbomachine of the type mentioned, to provide an improved embodiment, which is characterized in particular by an increased efficiency.
• the invention is based on the general idea of combining an axial seal, which is formed by the interaction of a stator seal structure with a rotor-seal structure, with a radial seal passing through from one blade via the shield element to the other blade. To this way, leaks in the axial direction and in the radial direction can be reduced, which increases the efficiency of the turbomachine or its efficiency.
• the continuous radial seal is realized in the turbomachine according to the invention in that the protective shield elements and the rotor blades are coordinated so that the protective shield radial formed in the region of the shield elements passes uninterrupted into the blade radial seals formed in the region of the blades.
• the radial seals can be realized by means of sealing elements, which are arranged in the shield shield elements in protective shield grooves and in the region of the blades in blade grooves.
• the shield elements between their axial ends each have a radially inwardly recessed recess in which the rotor seal structure is arranged.
• said recess is dimensioned so that the axial seal is formed within this recess and is arranged offset radially inwardly relative to the blade radial seals of the adjacent blades.
• This design ensures that the axial seal is located in a region which is virtually outside a gas flow flowing in the gas path of the turbomachine, which improves the effectiveness of the axial seal. Through the depression, virtually a dead water zone is formed within the gas path, in which the axial seal achieves an improved sealing effect.
• FIGURE shows a simplified longitudinal section through a portion of a turbomachine. Ways to carry out the invention
• a rotating turbomachine 1 which is shown only partially, comprises a rotor 2 and a stator 3.
• the turbomachine 1 which is preferably a gas turbine, but which is also a compressor or a steam turbine can act
• the rotor 2 rotates about a rotor axis 4, which simultaneously defines the axial direction of the turbomachine 1.
• the rotor 2 has at least two rows of blades 5, each having a plurality of circumferentially adjacent to each other blades 6.
• the rotor 2 has at least one rotor heat shield 7, which is arranged in each case axially between two adjacent rotor blade rows 5. In the illustrated section of the turbomachine 1, two rotor heat shields 7 can be seen.
• the stator 3 may have a plurality of stator blade rows 8, of which at least one is arranged axially between two adjacent blade rows 5.
• Each vane row 8 has a plurality of circumferentially adjacent vanes 9.
• the at least one vane row 8 arranged axially between two adjacent rows of rotor blades 5 is regularly meant.
• the guide vanes 9 of at least one of these guide blade rows 8 have radially inward a stator seal structure 10, which can be designed to be closed in the circumferential direction.
• a stator seal structure 10 which can be designed to be closed in the circumferential direction.
• each vane 9 radially inwardly at its blade tip a flat, circumferentially and axially extending platform 11, which may be configured in the manner of a shroud.
• the stator seal structure 10 is disposed on these vane platforms 11.
• the respective rotor heat shield 7 generally includes a plurality of circumferentially adjacent shield members 12 which form the respective rotor heat shield 7 in the manner of ring segments.
• the individual shield elements 12 have radially outside a rotor seal structure 13 which extends closed in the circumferential direction.
• the rotor-seal structure 13 and the stator-seal structure 10 are arranged radially adjacent thereto and cooperate to form an axial seal 14.
• the section plane selected in FIG. 1 lies in the circumferential direction between two adjacent rotor blades 6 and between two shield elements 12 adjacent in the circumferential direction.
• the sectional plane thus lies in a longitudinal gap, which forms in each case between two rotor blades 6 or protective shield elements 12 which are adjacent in the circumferential direction.
• a blade radial seal 15 is formed on each side between two adjacent moving blades 6 of the same blade row 5, while on the other hand, a respective protective shield radial seal 16 is formed between two adjacent shielding elements 12.
• Both the respective blade radial seal 15 and the respective protective shield radial seal 16 separate in the radial direction a gas path 17, the turbomachine 1 from the rotor 2 and from a cooling gas path 18 which is formed radially between the rotor 2 and the respective radial seal 15, 16.
• the respective working gas such as a hot gas
• a corresponding gas flow is symbolized by arrows 19.
• the blades 6 and the vanes 9 each extend through the gas path 17.
• a cooling gas flow which is indicated by arrows 20.
• the shield elements 12 and the blades 6 of the rotor heat shield 7 adjacent blade rows 5 are so each other matched so that the shield radial seal 16 passes without interruption both in the upstream blade radial seal 15 and in the downstream blade radial seal 15.
• This uninterrupted transition between the shield radial seal 16 and the two blade radial seals 15 is realized so that it can form a radial seal 21, which in the longitudinal direction of the one blade 6 via the respective shield member 12 to the other blade 6 quasi seamless or continuous is designed. It is noteworthy that both in an upstream transition 22 and at a downstream transition 23 between the shield element 12 and the respective blade 6, a continuous radial seal 21 can be realized.
• the respective blade radial seal 15 comprises in the region of blade roots 24 of the circumferentially adjacent blades 6 each a circumferentially open blade groove 25.
• the two blade grooves 25 of the respective blade radial seal 15 are aligned with their open sides facing each other, so that in these blade grooves 25 a plate-shaped or band-shaped sealing element 26 can be inserted.
• the shield radial seal 16 is constructed in a corresponding manner and has in regions 27 which adjoin the rotor seal structure 13, in the circumferentially adjacent shield elements 12 in each case one in the circumferential direction open Schutzschildnut 28.
• the protective shield grooves 28 of the two shielding elements 12 adjacent to one another in the circumferential direction are aligned with one another in the circumferential direction, so that a plate-shaped or band-shaped sealing element 26 can likewise be inserted into the protective shield grooves 28.
• the shield grooves 28 and the blade grooves 25 are suitably matched to one another so that in the transition regions 22, 23 axial longitudinal ends 29 of the shield grooves 28 axially aligned axially adjacent axial longitudinal ends 30 of the blade grooves 25.
• sealing element 26 which extends in the respective grooves 25, 28 from the one blade row 5 on the rotor heat shield 7 to the other blade row 5.
• a plurality of sealing elements 26 may be provided, in particular adjacent sealing elements 26 axially abutting one another between the axial longitudinal ends 29 of the protective shield grooves 28 and / or between the axial longitudinal ends 30 of the respective blade grooves 25.
• comparatively small sealing elements 26, which are arranged only in the respective transitional region 22 or 23 for bridging the annular axial gap there, extending on the one hand into the protective shield grooves 28 and on the other hand into the blade grooves 25.
• the shield elements 12 may according to the embodiment shown here between their axial ends, ie between the transition regions 22, 23 have a radially inwardly recessed recess 31.
• the rotor seal structure 13 is arranged.
• the guide vanes 9 are here dimensioned so that the stator seal structure 10 is disposed within this recess 31.
• the recess 31 may be dimensioned so that the formed by the interaction of the rotor seal structure 13 with the stator seal structure 10 axial seal 14 is formed within the recess 31.
• the axial seal 14 is arranged offset radially inwardly relative to the blade radial seals 15 of the adjacent blades 6. As a result, the axial seal 14 is located radially outside the gas flow 19 in the gas path 17 and in particular in a dead water region of the gas flow 19.
• the stator seal structure 10 may be configured so as to be grindable.
• the stator-seal structure 10 may be designed as a honeycomb structure 33 with radially oriented honeycombs for this purpose.
• the rotor seal structure 13 is designed einschleifend.
• the rotor-seal structure 13 is formed by at least one blade-shaped annular web 32. In the example shown, two such annular webs 32 are provided, which are arranged spaced apart in the axial direction.
• the rotor-seal structure 13 can be looped into the stator-seal structure 10, that is to say the respective annular web 32 penetrates into the honeycomb structure 33.
• stator seal structure 10 and the rotor seal structure 13 cooperate to form the axial seal 14 in the manner of a labyrinth seal.
• stator seal structure 10 more, z. B. have two annular axial sections 34 which are offset from an adjacent thereto, here middle annular axial section 35 radially outward.
• the rotor-seal structure 13 then has several, here two radially outwardly projecting annular webs 32, which are each arranged in the region of one of the radially outwardly offset radial sections 34.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Low-Molecular Organic Synthesis Reactions Using Catalysts (AREA)
• Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Applications Claiming Priority (2)

Publications (2)

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Family Applications (1)

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• 2007
  • 2007-12-04 CA CA2673079A patent/CA2673079C/fr not_active Expired - Fee Related
  • 2007-12-04 EP EP07847789A patent/EP2092164B1/fr not_active Not-in-force
  • 2007-12-04 JP JP2009541958A patent/JP5027245B2/ja not_active Expired - Fee Related
  • 2007-12-04 MX MX2009006599A patent/MX2009006599A/es active IP Right Grant
  • 2007-12-04 KR KR1020097012744A patent/KR101426715B1/ko not_active IP Right Cessation
  • 2007-12-04 AT AT07847789T patent/ATE483891T1/de active
  • 2007-12-04 DE DE502007005296T patent/DE502007005296D1/de active Active
  • 2007-12-04 WO PCT/EP2007/063288 patent/WO2008074633A1/fr active Application Filing
• 2009
  • 2009-06-19 US US12/487,830 patent/US8052382B2/en not_active Expired - Fee Related

Non-Patent Citations (1)

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