EP2948640A1 - Fixed diffuser vanes assembly for guiding flow through a turbomachine, comprising an internal platform with inbuilt reinforcements, and associated turbomachine and production method - Google Patents
Fixed diffuser vanes assembly for guiding flow through a turbomachine, comprising an internal platform with inbuilt reinforcements, and associated turbomachine and production methodInfo
- Publication number
- EP2948640A1 EP2948640A1 EP14704842.5A EP14704842A EP2948640A1 EP 2948640 A1 EP2948640 A1 EP 2948640A1 EP 14704842 A EP14704842 A EP 14704842A EP 2948640 A1 EP2948640 A1 EP 2948640A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- radial
- tongue
- annular
- turbomachine
- crown
- 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
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 10
- 230000002787 reinforcement Effects 0.000 title description 2
- 238000005192 partition Methods 0.000 claims abstract description 28
- 239000000463 material Substances 0.000 claims abstract description 14
- 238000009826 distribution Methods 0.000 claims description 13
- 238000005219 brazing Methods 0.000 claims description 6
- 238000011144 upstream manufacturing Methods 0.000 claims description 5
- 230000004907 flux Effects 0.000 claims description 2
- 238000005476 soldering Methods 0.000 claims 1
- 210000002105 tongue Anatomy 0.000 description 15
- 238000000034 method Methods 0.000 description 4
- 239000007787 solid Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 210000003462 vein Anatomy 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/237—Brazing
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
Definitions
- the field of the invention is that of fixed vanes for distribution of the air flow in a turbomachine.
- a turbomachine generally comprises, from upstream to downstream in the direction of the gas flow, a blower, one or more stages of compressors, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or several stages of turbines, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle.
- These turbines comprise a distributor of the air flow in the turbomachine, composed of a plurality of fixed blade stages each comprising a plurality of blades extending generally radially with respect to an axis of the turbomachine, and disposed between an inner annular platform and an outer annular platform by which said vanes are attached to the turbomachine.
- the blades are conventionally produced by a technique known as the foundry lost wax. Nuclei are thus inserted into the mold before injection of the wax, these cores being held in position by bushes, the association between the cores and the sockets being carried out manually.
- the invention aims to remedy this problem by proposing a fixed blade of flow distribution in a turbomachine, comprising an inner annular platform and a plurality of fixed vanes mounted on it, the inner platform comprising a support plate forming the base of said blades, a radial annular partition extending from the support plate towards an axis of the blade, and an inner ring attached to the radial annular partition, and having an inner surface on which is disposed a material abradable, the blade being characterized in that the inner ring comprises at least one cutout defining a tongue, the tongue being folded to bear against the radial annular partition.
- the blading according to the invention may further comprise at least one of the following characteristics:
- the or each tab is supported by at least one end portion on the radial wall, which allows to achieve only one tab fold and thus simplify the manufacture of the blade.
- the blade has several tabs, they can be arranged in a regular angular distribution on the circumference of the ring, so as to distribute equitably the abutting contacts and thus to confer a better stability to the blading.
- each tongue is brazed to the radial wall.
- the inner ring is attached to the radial annular partition at the through openings resulting each folding a corresponding tab.
- the abradable material is attached to the radial septum through each opening.
- the abradable material is brazed to the inner surface of the crown, and to the radial septum through each opening of the crown.
- the inner ring further comprises an annular tab extending upstream and an annular tab extending downstream relative to a stream of air in the vane.
- the invention also proposes a turbomachine comprising at least one such blade.
- the invention finally proposes a method of manufacturing a fixed blade of flow distribution according to the invention, comprising the steps of:
- the method according to the invention may further comprise at least one of the following characteristics:
- the step of fixing the crown on the radial wall comprises brazing the portion of each tongue at right angles to the crown on the wall.
- the method further comprises a step of brazing a layer of abradable material on an inner surface of the ring, and on the radial wall through a plurality of openings of the ring resulting from the folding of each tab.
- the distribution vane according to the invention is lighter but as robust as before since the reinforcement function in support against the partition radial is made by the inner crown of the vane itself, without adding material.
- FIG. 1 represents a partial sectional view of a flow distribution vane according to one embodiment of the invention.
- FIGS. 2a and 2b respectively represent a partial sectional view and a plan view of an inner annular platform inner ring of a flow distribution vane of FIG. 1.
- FIG. 3 schematically represents the main steps of the method of manufacturing a flux distribution vane according to one embodiment of the invention.
- FIG. 1 there is shown a partial view of a fixed blade 10 of distribution of the air flow flowing in a turbomachine, the direction of flow of the air flow being represented by an arrow F , the vane forming a stage of a distributor of a turbomachine turbine, for example a low-pressure turbine.
- Blading 10 comprises a plurality of fixed blades 1 1 arranged radially with respect to an axis of the turbomachine (not shown), which is also the axis of the blade, said blades being mounted on an inner annular platform 12.
- the platform 12 comprises an annular partition 120 extending radially with respect to the axis of the turbomachine, as well as an annular plate 121 for supporting the blades 1 1, extending on either side of the partition. annular at a radially outer end thereof.
- the platform 12 also comprises an inner ring 122 extending on either side of the radial annular partition 120, at its radially inner end, and on which a layer of abradable material 123 is attached.
- the inner ring 122 has a median annular section 1220 extending substantially axially with respect to the axis of the blade, and two end annular tabs 1221, 1222 extending respectively to the upstream and downstream of the blading relative to the airflow, being radially offset relative to the center section 1220, said sections being inclined relative to the axis of the blading.
- These sections are shaped to cooperate with rotor blade spoilers placed upstream and downstream with respect to the blade 10, in order to form labyrinth type seals, to avoid recirculation of air in one direction.
- the inner ring 122 comprises, on its median section 1220, at least one, and preferably a plurality of U-shaped cutouts 1223, each cutout thus comprising two preferably but non-limitatively parallel portions 1224 (forming the branches of the "U” ") Joined at one end by a transverse portion 1225 (forming the base of the" U ").
- the portions 1224 are oriented substantially parallel to the axis of the blade and the transverse portion 1225 and disposed on the downstream side of the blank with respect to the air flow.
- Each cutout 1223 thus delimits a tongue 1226 detached from the rest of the median section by the three portions of the cutout. Because of the shape of the cutouts, each tab extends over a ring sector.
- At least one end portion 1227 of each cutout is bent at right angles to the middle section of the ring 122 so as to extend substantially radially.
- each tongue can also be bent at right angles to the crown.
- Each tongue thus folded releases an opening 1228 in ring sector in the ring 122.
- the cutouts 1 123, and therefore the tongues 1226 and the openings 1228 are distributed regularly, that is to say at constant angular intervals relative to the axis of the blade, along the circumference of the blade. crowned.
- the ring 122 has, on an annular zone of its median section of the width of the openings, an alternation of solid areas and openings 1228.
- the ring 122 is attached to the radial partition 120 at the annular zone comprising the alternation of openings and solid areas, the end 1227 of the tabs at right angles to the ring bearing against the wall radial.
- the tongues cut in the crown constitute the surface to be soldered on the radial partition, thus making it possible to assemble the crown to the radial partition without adding additional elements (for example sheets, tabs on a radial partition ).
- the blading is thus lightened.
- the layer of abradable material 123 attached to the ring can also be reported on the radial wall through each opening 1228 of said ring.
- the layer of abradable material 123 is brazed firstly on the radial wall through each opening, and secondly on the radially inner surface of the middle section 1220 of the inner ring.
- the ring 122 may comprise only a cutout 1223 U, it thus occupies a smaller space. Other types of attachment can nevertheless be integrated in the crown in addition to this single cut.
- a plurality of U-shaped cutouts 1223 are produced on the circumference of an annular ring 122, in accordance with the cuts described above, the cuts being preferably evenly distributed over said circumference.
- each cutout 1223 is folded at right angles outwardly of the ring, so that the end 1227 of each tongue is oriented substantially radially with respect to the axis of the crown.
- the crown 122 is reported on the radial partition 120 of an internal platform with a fixed blade, the blades 11 and the outer platform of the blade may also be already mounted. on the internal platform.
- the crown is attached so that the folded ends of each tongue bear against the radial partition, and the radial annular partition is disposed at the openings 1228 made in the ring.
- the ends of the tongues 1226 bearing against the radial partition, as well as the zones of the ring between two consecutive openings are brazed to the radial wall.
- a layer of abradable material 123 on the assembly obtained in the previous step preferably by brazing the layer on the radially inner surface of the median portion 1220 of the ring, and at the openings 1228, brazing the layer 123 to the radial wall (also on its radially inner surface).
- brazing operations 300 and 400 can be performed simultaneously, which makes the process faster to implement.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1350582A FR3001252B1 (en) | 2013-01-23 | 2013-01-23 | FIXED FLOW DISTRIBUTION AUBING COMPRISING AN INTEGRATED REINFORCED INTERNAL PLATFORM |
PCT/FR2014/050113 WO2014114873A1 (en) | 2013-01-23 | 2014-01-22 | Fixed diffuser vanes assembly for guiding flow through a turbomachine, comprising an internal platform with inbuilt reinforcements, and associated turbomachine and production method |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2948640A1 true EP2948640A1 (en) | 2015-12-02 |
EP2948640B1 EP2948640B1 (en) | 2017-04-19 |
Family
ID=48521143
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14704842.5A Active EP2948640B1 (en) | 2013-01-23 | 2014-01-22 | Fixed diffuser vanes assembly for guiding flow through a turbomachine, comprising an internal platform with inbuilt reinforcements, and associated turbomachine and production method |
Country Status (8)
Country | Link |
---|---|
US (1) | US10024179B2 (en) |
EP (1) | EP2948640B1 (en) |
CN (1) | CN104937216B (en) |
BR (1) | BR112015017351B1 (en) |
CA (1) | CA2898864C (en) |
FR (1) | FR3001252B1 (en) |
RU (1) | RU2651919C2 (en) |
WO (1) | WO2014114873A1 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3082233B1 (en) * | 2018-06-12 | 2020-07-17 | Safran Aircraft Engines | TURBINE SET |
FR3100838B1 (en) * | 2019-09-13 | 2021-10-01 | Safran Aircraft Engines | TURBOMACHINE SEALING RING |
FR3103012B1 (en) * | 2019-11-12 | 2021-11-19 | Safran Aircraft Engines | Sectoral annular row of fixed vanes |
DE102020200073A1 (en) * | 2020-01-07 | 2021-07-08 | Siemens Aktiengesellschaft | Guide vane ring |
FR3113298B1 (en) * | 2020-08-10 | 2023-09-01 | Safran Aircraft Engines | Abradable holder for a low pressure distributor comprising a single sheet |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB807231A (en) * | 1955-05-20 | 1959-01-14 | Gen Electric | Securing means for blading of compressors or turbines |
US3018085A (en) * | 1957-03-25 | 1962-01-23 | Gen Motors Corp | Floating labyrinth seal |
DE3003469C2 (en) * | 1980-01-31 | 1987-03-19 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Device for connecting rotationally symmetrically arranged components for turbomachines, in particular gas turbine engines, which are exposed to different thermal influences |
US4767267A (en) * | 1986-12-03 | 1988-08-30 | General Electric Company | Seal assembly |
RU2171380C2 (en) * | 1999-04-27 | 2001-07-27 | Открытое акционерное общество "Авиадвигатель" | Nozzle block of turbine |
FR2928961B1 (en) * | 2008-03-19 | 2015-11-13 | Snecma | SECTORIZED DISPENSER FOR A TURBOMACHINE. |
FR2930592B1 (en) * | 2008-04-24 | 2010-04-30 | Snecma | TURBINE DISPENSER FOR A TURBOMACHINE |
-
2013
- 2013-01-23 FR FR1350582A patent/FR3001252B1/en active Active
-
2014
- 2014-01-22 RU RU2015135580A patent/RU2651919C2/en active
- 2014-01-22 BR BR112015017351-9A patent/BR112015017351B1/en active IP Right Grant
- 2014-01-22 US US14/762,782 patent/US10024179B2/en active Active
- 2014-01-22 CN CN201480005714.XA patent/CN104937216B/en active Active
- 2014-01-22 WO PCT/FR2014/050113 patent/WO2014114873A1/en active Application Filing
- 2014-01-22 CA CA2898864A patent/CA2898864C/en active Active
- 2014-01-22 EP EP14704842.5A patent/EP2948640B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
CN104937216A (en) | 2015-09-23 |
EP2948640B1 (en) | 2017-04-19 |
BR112015017351A2 (en) | 2017-07-11 |
FR3001252B1 (en) | 2015-02-13 |
CA2898864A1 (en) | 2014-07-31 |
US10024179B2 (en) | 2018-07-17 |
WO2014114873A1 (en) | 2014-07-31 |
RU2651919C2 (en) | 2018-04-24 |
RU2015135580A (en) | 2017-03-02 |
CN104937216B (en) | 2016-08-10 |
FR3001252A1 (en) | 2014-07-25 |
CA2898864C (en) | 2020-08-25 |
US20150377044A1 (en) | 2015-12-31 |
BR112015017351B1 (en) | 2021-12-14 |
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