EP4097334A1 - Distributeur de stator de turbomachine comprenant un anneau d'étanchéité continu et libre - Google Patents
Distributeur de stator de turbomachine comprenant un anneau d'étanchéité continu et libreInfo
- Publication number
- EP4097334A1 EP4097334A1 EP21716515.8A EP21716515A EP4097334A1 EP 4097334 A1 EP4097334 A1 EP 4097334A1 EP 21716515 A EP21716515 A EP 21716515A EP 4097334 A1 EP4097334 A1 EP 4097334A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbomachine
- sectors
- sealing ring
- platforms
- distributor
- 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.)
- Granted
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 19
- 230000000717 retained effect Effects 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 239000007789 gas Substances 0.000 abstract description 6
- 238000000926 separation method Methods 0.000 abstract 1
- 238000009423 ventilation Methods 0.000 description 6
- 238000010276 construction Methods 0.000 description 5
- 230000002028 premature Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
- F05D2240/00—Components
- F05D2240/55—Seals
- F05D2240/58—Piston ring seals
Definitions
- the subject of the invention is a turbomachine stator distributor comprising a continuous and free sealing ring.
- the distributors in question here are rings of fixed blades, fixed to a casing of the stator and alternating with rings of movable blades in compressors and turbines of turbomachines.
- the vanes are mounted on the stator casing by connections comprising interlocking hooks, and their radially internal ends are provided with sealing gaskets, in so-called abradable materials, cooperating with adjacent wipers (circular ridges) belonging to the rotor, to form labyrinth joints.
- the object of the invention is to reduce these drawbacks, and more precisely to reduce the flow of residual leaks through the labyrinth seal, while alleviating or even eliminating the constraints of ventilation of the casing around the distributor concerned.
- the invention relates, in general form, to a turbomachine stator distributor comprising ring sectors disposed circumferentially end to end around an axis of the turbomachine, each of the sectors comprising at least one fixed vane which extends from a radially internal platform, a sealing ring carrying an abradable sealing element surrounded by the platforms of the sectors, the sealing ring being connected to the platforms by slide connections, characterized in that each sliding link comprises a first sleeve integral with a sealing ring and a second sleeve integral with one of the platforms, the first and second sleeves being fitted into one another by sliding and delimiting a housing, and each sliding link comprising a spring contained in the housing and forced in the radial direction by being mounted on the one hand against one of the platforms and on the other hand against the sealing ring.
- the construction of the invention is therefore based on the joint presence of a continuous sealing ring, carrying the abradable, and of the main part of the distributor made up of angular sectors.
- the radial slides that connect them allow relatively large radial movements of the ring vis-à-vis the platforms by differential thermal expansions, as well as reduced movements in other directions (axial, tangential, and tilting) thanks to the little play between the inner sleeves and the outer sleeves. Concentricity is maintained by the springs.
- the ring As the heat transmission between the ring and the platforms is reduced in the invention than in other constructions, thanks to the fineness of the connection provided only by the slides, the ring is maintained more easily at a temperature close to that of the rotor than in other constructions, and its diameter can be adjusted independently of the radial position of the blade sectors, by the temperature of the gases passing in front of it.
- the invention improves the tightness by the best adjustment of the clearances between the abradable and the wipers that one can hope for, and also by the simple presence of the continuous ring, which interrupts the division of the distributor into sectors, at its end. radially inner.
- the housings contain radially oriented rods
- the springs are helical and threaded around the rods
- the rods belong to the platforms and comprise a free radially inner end penetrating into a cavity of the ring and retained in said cavity;
- Figure 1 general arrangement of a dispenser, in a design where it lacks the features of the invention
- FIG. 1 in perspective, an embodiment of the invention
- Figure 5 a general view of the dispenser.
- FIG. 1 represents, in longitudinal section, a portion of a turbomachine according to the known art and comprising a nozzle ring 1 between two rings of movable blades 2 and 3.
- the nozzle 1 comprises sectors 4 ring each comprising a few fixed vanes 5 between an outer platform 6 and an outer platform 7 also extending over ring sectors.
- the outer platform 6 is fixed to a stator casing 8 by mounting via an upstream hook 9 and a downstream hook 10 (upstream and downstream are understood in relation to the general direction of the gases s 'flowing in the turbomachine, for this entire description).
- a ventilation device is arranged outside the stator housing 8; it comprises tubular ramps 11 traversed by fresh gas flows subtracted from the compressor of the turbomachine, which extend substantially to the right of the assembly via the hooks 9 and 10, to blow fresh air there through orifices 12, to refresh the stator housing 8 at the place of assembly via the hooks 9 and 10 and therefore adjust the local thermal expansions of the stator housing 6 and thus the radial position of the crown sectors 4 of the distributor 1.
- the radially inner platform 7 comprises an abradable liner 33 at its radially inner end, which is directed radially inward and forms a labyrinth seal with radially facing wipers 13, depending on a rotor 14 to which belong the rings of movable blades such as 2 and 3.
- the axial XX and radial RR directions are considered with reference to the axis around which the turbomachine extends, the axial direction also corresponding to the axis rotor rotation 14.
- the sectors of distributor crowns 15 differ from those of known embodiments in that they comprise a radially internal platform 16 devoid of the abradable lining necessary for establish the seal with the rotor 14, an abradable layer which replaces it, now 17, belonging to a ring 18 continuous on a circumference, therefore common to the distributor crown sectors 15.
- the ring 18 comprises internal sleeves 19 annulars rising up on its radially outer face in the radial direction, and the free end (radially outer) of which is open.
- the internal sleeves 19 slide in external sleeves 20 which stand on the radially internal face of platforms 16 in a radial direction and whose free end (radially internal) is also open.
- the radially external face of the ring 18 carries a flat external rib 21 which extends along internal ribs 22 which are also flat of the distributor sectors 15.
- the internal ribs 22 are here contiguous with the external sleeves 20, without it is necessary.
- the internal sleeves 19 could be placed on the platforms 16, and the external sleeves 20 on the ring 18. They are shown integrally on the ring 18 and the platforms 16, that is to say manufactured at the same time as him and them, by foundry for example, but one could manufacture them separately and then fix them by welding or otherwise.
- the internal sleeves 19 and the external sleeves 20 define cylindrical housings 23 in which extend radially oriented rods 24, carried by the internal platforms 16 and comprising a threaded free end 25 (radially internal) on which is screwed a nut 26.
- a helical spring 27 is threaded around the rod 24.
- the internal sleeves 19, external sleeves 20 and springs 27 form sliding connections 35 between the valve sectors 15 and the ring 18 which allow the latter to move in a radial direction, contracting or expanding.
- each rod 24 is disposed with a clearance in a cavity 28 delimited by several portions assembled together of the ring 18, for example a cylindrical tire 29 which constitutes its main structure, and two reinforcements 30 and 31 of portions of the abradable 17 which follow one another in the axial direction of the turbomachine.
- the cavity 28 is provided with a bore 32 to allow the threaded free end 25 and the rod 24 to extend out and slide with sufficient play.
- each rod 24 is compressed between the internal platform 16 and the cylindrical tire 29 of the ring 18.
- This assembly allows the ring 18 to acquire a radial position determined exclusively by the thermal expansions that it sudden, due mainly to the gas current which circulates around it and passes through it passing in front of the abradable 17.
- the axial position and the angular position of the ring 18 are ensured with sufficient precision by the sliding of the internal sleeves 19 in the external sleeves 20.
- the radial position of the ring 18 therefore becomes more or less independent of that of the crown sectors distributor 15 and is no longer governed by the ventilation devices, the importance of which becomes less important and which can even be considered to be eliminated.
- This radial position of the ring 18 can be evaluated with sufficient precision to avoid excessive play or in the labyrinth seal or on the contrary the premature wear of the abradable 17, thanks to the knowledge of the foreseeable temperature of the circulating gases. in the turbomachine.
- the outer rib 21 partially eliminates the leaks from the clearances at the inner platforms 16 of the valve crown sectors 15 by covering part of the interstices between them at the location of the internal ribs 22.
- the ring 18 to the platforms 16 by the relatively few and not very bulky slides 35 contributes to the lightness of the construction, as does the sealing of their gap only by the parallel ribs 21 and 22, which have no structural role and can be fine.
- Figure 5 illustrates the complete dispenser 34.
- the sliding link 35 is present here on each of the distributor crown sectors 15, without this being necessary to properly support the ring. Three slides 35 might suffice; a number of three to twenty would be preferable to promote the guidance of the free expansion in operation.
- the nuts 26 serve essentially to support the ring 18 during assembly of the device. Provision is made for the cavities 28 to be wide enough to avoid stopping the nuts 26 regardless of the foreseeable thermal expansions of the ring 18.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2002923A FR3108675B1 (fr) | 2020-03-25 | 2020-03-25 | Distributeur de stator de turbomachine comprenant un anneau d’étanchéité continu et libre |
PCT/FR2021/050473 WO2021191540A1 (fr) | 2020-03-25 | 2021-03-22 | Distributeur de stator de turbomachine comprenant un anneau d'étanchéité continu et libre |
Publications (2)
Publication Number | Publication Date |
---|---|
EP4097334A1 true EP4097334A1 (fr) | 2022-12-07 |
EP4097334B1 EP4097334B1 (fr) | 2024-01-10 |
Family
ID=70295557
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP21716515.8A Active EP4097334B1 (fr) | 2020-03-25 | 2021-03-22 | Distributeur de stator de turbomachine comprenant un anneau d'étanchéité continu et libre |
Country Status (5)
Country | Link |
---|---|
US (1) | US11879339B2 (fr) |
EP (1) | EP4097334B1 (fr) |
CN (1) | CN115335587B (fr) |
FR (1) | FR3108675B1 (fr) |
WO (1) | WO2021191540A1 (fr) |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5346362A (en) * | 1993-04-26 | 1994-09-13 | United Technologies Corporation | Mechanical damper |
US6042334A (en) * | 1998-08-17 | 2000-03-28 | General Electric Company | Compressor interstage seal |
US6514041B1 (en) * | 2001-09-12 | 2003-02-04 | Alstom (Switzerland) Ltd | Carrier for guide vane and heat shield segment |
US7291946B2 (en) * | 2003-01-27 | 2007-11-06 | United Technologies Corporation | Damper for stator assembly |
US20070132193A1 (en) * | 2005-12-13 | 2007-06-14 | Wolfe Christopher E | Compliant abradable sealing system and method for rotary machines |
EP2905476B1 (fr) * | 2008-12-25 | 2016-11-30 | Mitsubishi Hitachi Power Systems, Ltd. | Agencement d'aube de stator et turbine à gaz |
FR2948965B1 (fr) * | 2009-08-06 | 2012-11-30 | Snecma | Etage redresseur pour une turbomachine |
US9482107B2 (en) * | 2009-09-28 | 2016-11-01 | Siemens Aktiengesellschaft | Gas turbine nozzle arrangement and gas turbine |
US9181817B2 (en) | 2010-06-30 | 2015-11-10 | General Electric Company | Method and apparatus for labyrinth seal packing rings |
FR2971022B1 (fr) * | 2011-02-02 | 2013-01-04 | Snecma | Etage redresseur de compresseur pour une turbomachine |
US9063423B2 (en) * | 2013-02-28 | 2015-06-23 | Eastman Kodak Company | Lithographic printing plate precursors and use |
US9500094B1 (en) * | 2013-04-23 | 2016-11-22 | S & J Deisgn, Llc | Turbine with radial acting seal |
EP3177812A1 (fr) * | 2014-08-08 | 2017-06-14 | Siemens Energy, Inc. | Système d'optimisation de logement de joint d'étanchéité inter-étage dans un moteur à turbine à gaz |
EP3315728B1 (fr) * | 2016-10-26 | 2022-01-12 | MTU Aero Engines AG | Palier amorti d'aube directrice |
DE102017221660A1 (de) * | 2017-12-01 | 2019-06-06 | MTU Aero Engines AG | Modul für eine Strömungsmaschine |
-
2020
- 2020-03-25 FR FR2002923A patent/FR3108675B1/fr active Active
-
2021
- 2021-03-22 EP EP21716515.8A patent/EP4097334B1/fr active Active
- 2021-03-22 WO PCT/FR2021/050473 patent/WO2021191540A1/fr unknown
- 2021-03-22 CN CN202180024114.8A patent/CN115335587B/zh active Active
- 2021-03-22 US US17/906,553 patent/US11879339B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3108675A1 (fr) | 2021-10-01 |
FR3108675B1 (fr) | 2022-11-04 |
WO2021191540A1 (fr) | 2021-09-30 |
CN115335587B (zh) | 2024-05-28 |
EP4097334B1 (fr) | 2024-01-10 |
CN115335587A (zh) | 2022-11-11 |
US20230160314A1 (en) | 2023-05-25 |
US11879339B2 (en) | 2024-01-23 |
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