EP3728796A1 - Roue de turbine - Google Patents
Roue de turbineInfo
- Publication number
- EP3728796A1 EP3728796A1 EP17832261.6A EP17832261A EP3728796A1 EP 3728796 A1 EP3728796 A1 EP 3728796A1 EP 17832261 A EP17832261 A EP 17832261A EP 3728796 A1 EP3728796 A1 EP 3728796A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- wiper
- type
- downstream
- upstream
- platform
- 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- Withdrawn
Links
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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
Definitions
- the invention relates to a turbomachine wheel, such as a turbine wheel, and a turbomachine comprising such a wheel.
- a turbomachine comprises a so-called primary annular air circuit and a secondary air annular circuit.
- the primary air circuit extends from upstream to downstream through low and high pressure compressors, a combustion chamber and high and low pressure turbines.
- the low pressure turbine 10 comprises a plurality of wheels 12 arranged axially alternately with annular rows of stator vanes 14.
- the wheels 12 comprise vanes 16 carried by discs 18 integral with one another by via a low pressure turbine shaft rotating the shaft of a blower wheel or power shaft and the rotor of the low pressure compressor.
- the stator vanes 14 are carried radially outwardly by a turbine casing 20.
- Each turbine wheel 12 comprises a radially inner annular platform 22 and a radially outer annular platform 24 between which a blade 25 extends, these platforms 22, 24 being able to be formed of a plurality of flat sections. forms circumferentially juxtaposed end to end to define the inner and outer limits of flow of the primary air flow.
- the external platform 24 comprises wipers 26a, 26b extending radially outwards towards an abradable panel 28 carried by the turbine casing 20 and formed of a wall 30 supporting a honeycomb structure 32 said nest bee.
- the honeycomb structure 32 may have, as can be seen in FIG. 1, two tracks 32a, 32b for rubbing the wipers 26a, 26b, a first 32a being arranged upstream and radially inside a second 32b arranged downstream of the first 32a.
- the wiper 26a upstream therefore extends a distance radially lower than the downstream wiper 26b.
- the invention makes it possible to provide a simple, economical and effective solution to the aforementioned problems.
- a turbomachine wheel comprising a plurality of blades extending radially and connected at one of their ends radially inner or outer to an annular platform carrying annular wipers extending from said platform. in a direction opposite to the blade between a first radial end connected to the platform and a second free opposite radial end, to cooperate in sealing with a ring opposite radial, characterized in that one of the the upstream wiper and the downstream wiper is of a first type or a second type, the first type corresponding to a wiper with the upstream face which is curved concave and the downstream face which is curved convex and the second type corresponding to a wiper with the upstream and downstream faces which are substantially flat and parallel to each other, the first end of said wiper being arranged downstream of its second end Emite.
- said wiper is arranged at the downstream end of said platform. This positioning is more effective in terms of reducing the parasitic air flow than the positioning at the upstream end.
- the upstream and downstream faces of the wiper of the first type have a radius of substantially constant curvature between its first end and second end.
- the invention also relates to a turbomachine turbine, such as a high-pressure turbine, comprising at least one mobile wheel of the type described above.
- turbomachine such as a turboprop or a turbojet, comprising such a turbine.
- FIGS. 2 and 3 are schematic sectional views of the radially outer end of a turbine wheel according to the invention and according to two embodiments.
- FIG. 2 showing the radially outer end of a turbine wheel 34 according to the invention comprising a downstream annular wiper 36 and an upstream annular wiper 38.
- the downstream wiper 36 is of a first type different from the second type of the upstream wiper 38.
- the wiper 36 downstream comprises a concave curved upstream face 36a and a second convex curved downstream face 36b.
- the wiper 38 upstream comprises an upstream face 38a and a downstream face 38b which are flat and substantially parallel to each other.
- Each of the upstream and downstream wipers 36 comprises a first radial end 36c, 38c which is connected to the platform 24 and a second radial end 36d, 38d opposite the first end 36c, 38c and forming a free end intended to rub sealing with the honeycomb structure 32 of the abradable material 28 as already mentioned above in connection with Figure 1.
- the first end 36c, 38c of each of the downstream wiper 36 and the upstream wiper 38 is arranged downstream of its second end 36d, 38d, this axial offset being represented in FIG. 2 by the straight line 36e, 38e in dotted lines passing through said first end 36c, 38c and second end 36d, 38d of the upstream wipers 38 and downstream 36.
- These lines 36e, 38e are inclined obliquely upstream with respect to a plane perpendicular to the axis 40 of the wheel 34.
- the upstream wiper thus defines a first type of wiper and the downstream wiper defines a second type of wiper.
- the downstream wiper 44 is of the second type, that is to say with an upstream face 44a and a downstream face 44b that are plane and parallel. one to the other while the upstream wiper 46 is of the first type that is to say with a concave curved upstream face 46a and a convex curved downstream face 46b.
- Both of the upstream and downstream wipers 44 comprise a first radial end 44c, 46c and a second radial end 44d, 46d, the first ends 44c, 46c being also axially offset downstream with respect to the second end 44d. , 46d radially outer.
- the upstream and downstream wipers 44 are inclined obliquely upstream with respect to a plane perpendicular to the axis 40 of the wheel 42.
- the embodiment of the wheel of Figure 2 provides a better reduction of the parasitic air flow compared to the embodiment of the wheel of Figure 3. Indeed, it was observed that the flow rate of total air flowing between the radially outer end of the wheel and the abradable is more strongly reduced when the downstream wiper is of the first type or of the second type, which indicates that the achievement of a good seal on the last wiper is particularly important, and that this reduction is even more important when the wiper downstream 36 is of the first type.
- the radius of curvature of the upstream faces 36a, 46a and downstream 36b, 46b of wipers 36, 46 of the first type may be substantially constant between the first end and the second end of a wiper.
- the inclination of the wipers 36, 38, 44, 46 is such that the generatrix of the cone of revolution passing through the first end 36c, 38c, 44c, 46c and the second end 36d, 38d, 44d, 46d is inclined. oblique with respect to a plane perpendicular to the axis 40 of the wheel 34, 42 of a value strictly greater than 0 ° and less than or equal to 60 °, preferably between 15 ° and 45 ° and still more preferably from order of 30 °.
- turbine wheel 34, 42 could comprise an annular number of wipers greater than two as shown in the figures, these embodiments being an integral part of the object of the invention. . Also, if in the embodiments shown in Figures 2 and 3, each wheel 34, 42 comprises wipers of a first type and a second type, each wheel 34, 42 may also comprise a wiper of the first type at its end. upstream or downstream or a wiper of the second type at its upstream or downstream end, without leaving the object of the subject of the invention.
- the wipers 36, 38, 44, 46 have been presented as being annular.
- this term should be understood as indicating wipers which extend annularly 360 ° and can be formed of a plurality of sectors of wipers circumferentially juxtaposed one after the other.
- Figures 4, 5, 6 and 7 show alternative embodiments of the invention.
- the upstream annular wiper 48 extends substantially radially outwardly from the platform 24 and the downstream annular wiper 50 is of the first type.
- the upstream annular wiper 52 is of the first type and the downstream annular wiper 54 extends substantially radially outwardly from the platform 24.
- the upstream annular wiper 56 extends substantially radially outwardly from the platform 24 and the downstream annular wiper 58 is of the second type.
- the upstream annular wiper 60 is of the second type and the downstream annular wiper extends substantially radially outwardly from the platform 24.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/FR2017/053710 WO2019122541A1 (fr) | 2017-12-19 | 2017-12-19 | Roue de turbine |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3728796A1 true EP3728796A1 (fr) | 2020-10-28 |
Family
ID=61005842
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17832261.6A Withdrawn EP3728796A1 (fr) | 2017-12-19 | 2017-12-19 | Roue de turbine |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP3728796A1 (fr) |
CN (1) | CN111448367A (fr) |
WO (1) | WO2019122541A1 (fr) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3099786B1 (fr) * | 2019-08-07 | 2021-07-30 | Safran Helicopter Engines | Aube mobile pour une roue d’une turbomachine |
FR3107301B1 (fr) * | 2020-02-19 | 2022-03-11 | Safran Aircraft Engines | aube pour roue aubagée mobile de turbomachine d’aéronef comprenant un becquet d’étanchéité à section évolutive optimisée |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6926495B2 (en) * | 2003-09-12 | 2005-08-09 | Siemens Westinghouse Power Corporation | Turbine blade tip clearance control device |
US7281894B2 (en) * | 2005-09-09 | 2007-10-16 | General Electric Company | Turbine airfoil curved squealer tip with tip shelf |
FR2957115B1 (fr) * | 2010-03-05 | 2012-03-30 | Snecma | Etage de turbine dans une turbomachine |
US20110280715A1 (en) * | 2010-05-11 | 2011-11-17 | General Electric Company | Curved labyrinth seals |
GB2492546A (en) * | 2011-07-04 | 2013-01-09 | Alstom Technology Ltd | A labyrinth seal for an axial fluid flow turbomachine |
EP2647795B1 (fr) * | 2012-04-04 | 2018-11-07 | MTU Aero Engines AG | Système d'étanchéité pour turbomachine |
ES2579065T3 (es) * | 2012-12-21 | 2016-08-04 | Mtu Aero Engines Gmbh | Álabe de turbina con anillo de refuerzo y diente de corte |
FR3001759B1 (fr) * | 2013-02-07 | 2015-01-16 | Snecma | Rouge aubagee de turbomachine |
FR3007065B1 (fr) * | 2013-06-14 | 2017-11-10 | Snecma | Anneau abradable pour turbomachine |
-
2017
- 2017-12-19 WO PCT/FR2017/053710 patent/WO2019122541A1/fr unknown
- 2017-12-19 EP EP17832261.6A patent/EP3728796A1/fr not_active Withdrawn
- 2017-12-19 CN CN201780097306.5A patent/CN111448367A/zh active Pending
Also Published As
Publication number | Publication date |
---|---|
WO2019122541A1 (fr) | 2019-06-27 |
CN111448367A (zh) | 2020-07-24 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
FR3072720A1 (fr) | Carter pour turbomachine comprenant une portion centrale en saillie relativement a deux portions laterales dans une region de jonction | |
CA2885650C (fr) | Carter et roue a aubes de turbomachine | |
FR2980235A1 (fr) | Anneau pour une turbine de turbomachine | |
FR2977909A1 (fr) | Aube de rotor pour une turbomachine | |
FR3001759A1 (fr) | Rouge aubagee de turbomachine | |
CA2647057A1 (fr) | Distributeur sectorise pour une turbomachine | |
WO2019122541A1 (fr) | Roue de turbine | |
EP3201438B1 (fr) | Aube mobile de turbomachine, comprenant un ergot engageant une entaille de blocage d'un disque de rotor | |
FR2965009A1 (fr) | Ensemble de rotor destine a des moteurs a turbine | |
EP4136326A1 (fr) | Turbine pour une turbomachine | |
FR3091720A1 (fr) | Ensemble pour une turbomachine | |
FR3071273A1 (fr) | Ensemble d'etancheite de turbine pour turbomachine | |
FR2939852A1 (fr) | Etage d'aubes statoriques dans un compresseur | |
FR3066533B1 (fr) | Ensemble d'etancheite pour une turbomachine | |
FR3053386A1 (fr) | Roue de turbine | |
EP4088008B1 (fr) | Aube pour une roue aubagée mobile de turbomachine d'aéronef, roue aubagée mobile, turbine et turbomachine associées | |
EP4165286A1 (fr) | Ensemble annulaire pour turbine de turbomachine | |
WO2019122540A1 (fr) | Roue de turbomachine avec léchettes convexe ou concave | |
FR3108938A1 (fr) | Anneau d’étanchéité pour un rotor de turbine de turbomachine | |
FR3100836A1 (fr) | Aubes mobiles pour turbine | |
FR3053385A1 (fr) | Roue de turbomachine | |
FR2944554A1 (fr) | Turbine haute-pression de turbomachine | |
BE1028234B1 (fr) | Aube pour compresseur de turbomachine | |
FR3055145A1 (fr) | Secteur angulaire d'aube de stator de turbomachine | |
WO2023156726A1 (fr) | Assemblage pour une turbomachine d'aéronef et turbomachine d'aéronef |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: UNKNOWN |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE |
|
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 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20200618 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
DAV | Request for validation of the european patent (deleted) | ||
DAX | Request for extension of the european patent (deleted) | ||
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
INTG | Intention to grant announced |
Effective date: 20211021 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20220301 |