EP1970538A1 - Rotorscheibe einer Strömungsmaschine - Google Patents
Rotorscheibe einer Strömungsmaschine Download PDFInfo
- Publication number
- EP1970538A1 EP1970538A1 EP08152232A EP08152232A EP1970538A1 EP 1970538 A1 EP1970538 A1 EP 1970538A1 EP 08152232 A EP08152232 A EP 08152232A EP 08152232 A EP08152232 A EP 08152232A EP 1970538 A1 EP1970538 A1 EP 1970538A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- disk
- ribs
- platforms
- feet
- disc
- 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
- 238000013519 translation Methods 0.000 claims abstract description 10
- 230000000717 retained effect Effects 0.000 claims abstract description 8
- 230000001681 protective effect Effects 0.000 claims description 29
- 238000011144 upstream manufacturing Methods 0.000 claims description 7
- 230000014759 maintenance of location Effects 0.000 claims description 6
- 238000012856 packing Methods 0.000 claims description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 230000003071 parasitic effect Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/322—Blade mountings
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
Definitions
- the present invention relates to a fan rotor disk of a turbomachine, such as an airplane turbojet engine.
- a rotor disk is formed at its periphery with an alternation of cells and ribs and carries a plurality of blades, each formed of a blade connected to a foot engaged axially and radially retained in a cell of the disk. Platforms are fixed between the blades by means of radial flanges connected to corresponding radial flanges formed on the ribs of the disc.
- the kinematics of mounting and dismounting of the platforms on the ribs of the disk requires the platform to translate on the rib so that the holes of the flanges of the platform are engaged with pins or rods provided on the ribs. flanges of the disc.
- the lateral edges of the platforms must be sufficiently close to the blades of the blade to avoid parasitic air circulation to the disk.
- the blades of a fan have a curved profile, which requires that the lateral edges of the platforms are also curved.
- clearance is required between the edges of the platforms and the blades and induces air leaks to the disk. This game is particularly important at the axial ends of the platform.
- the accumulation of blade / platform games on the entire disk causes a decrease in the efficiency of the turbomachine.
- the invention aims in particular to provide a simple, economical and effective solution to these various problems.
- turbomachine blower rotor disc having at its periphery blades whose feet are retained in disk cavities, and inter-blade platforms fixed on ribs delimited by the mounting cavities of the blades. blade roots, protective linings being mounted between the sides of the disc cavities and the blade roots, characterized in that the protective linings have a C-shaped section enabling them to be engaged in translation and to retain them radially on the flanges. ribs of the disk and constitute locking means of the platforms on the ribs of the disk.
- the linings are used to protect the blade roots against friction on the inner walls of the cell.
- the lining is usually made of a material having a greater wear resistance than the blade root and the disc.
- the linings exert an additional function by allowing the inter-blade platforms to be held radially in position on the ribs of the rotor disk by locking means.
- the invention therefore reduces the clearance between the blade and the platform since the platform no longer has to be inserted axially, the locking being provided by the linings.
- the lateral edges of the platform can thus perfectly correspond to the curvature of the blade of the blade.
- the platforms on the disc comprise feet applied to the ribs of the disk, these feet being engaged and retained in cutouts or windows of the linings.
- the packings can be moved in translation on the ribs between a release position and a position for retaining the feet of the platforms, and are immobilized in their retaining position by an annular piece mounted on the upstream face. of the disc for the axial retention of the blade roots in the cavities of the disc.
- This locking system by translation of the protective lining allows mounting of the platform with a minimum of play on a rib of the disc.
- the feet of the platforms comprise radial uprights and axial flanges extending upstream from the radial uprights.
- the axial flanges are inside the protective lining and thus allow the platform to be held on the rib of the disk.
- the cells and ribs of the disk, and the protective linings have a helical profile.
- the blades of the moving blades are mounted in cavities of the disk which form an angle with the axis of the disk.
- there is a disproportion of rib thicknesses ensuring the radial retention of the blades on each side of the blade root which is the source of premature wear of the feet of the blade. blades.
- the use of helical profiles for the cavities and ribs of the disk allows to maintain constant thicknesses on each side of the blade roots over the entire length of the disk, the linings having a helical profile to be engaged on the ribs.
- the platforms are advantageously mounted on the disk by radial translation.
- the invention also relates to a turbomachine, such as an aircraft turbojet, characterized in that it comprises a disk of the type described above.
- the invention also relates to a protection pad for blade roots in a turbomachine, characterized in that it has a section C and comprises cutouts or windows formed in its wall connecting the wings of the C, these cuts allowing to engage and hold feet of an inter-blade platform.
- the protective lining may have a helical profile.
- FIG 1 represents a portion of a disk 10 of a turbine engine carrying a blade 12 according to the prior art.
- the disk 10 comprises at its periphery an alternation of cells 14 and ribs 16 extending longitudinally over the entire length of the disk 10.
- the blade 12 is formed by a blade 18 connected to a blade root 20 is engaged and held radially in a cavity 14 of the disk 10.
- a platform 22 is positioned on a rib 16 of the disk 10, the edges 24 of the platform 22 being placed sufficiently close to the blade 18 of the adjoining blade 12 for avoid the air flows to the disc 10.
- the platform 22 is fixed by radial flanges extending inwardly on radial flanges 26 extending outwardly of a rib 16 of the disc 10.
- Stems 28 inserted in the flanges 26 of the disc 10 and the flanges of the platform 22 provide the radial retention of the platform 22 on the rib 16.
- the kinematics of mounting and dismounting of the platform 22 requires that its flanges are engaged in the rods 28 by a displacement movement of the platform 22 along the median axis of the rib 16.
- the blade 18 being bent, it is necessary to have a clearance between the edges 24 of the platform 22 and the blade 18 to allow movement along the median axis of the rib 16 of the platform 22.
- This game is of the order of 3 mm and is most important at the axial ends of the platform 22. An air flow can thus take place between the platform 22 and the blade 12 reducing the performance of the turbomachine.
- the invention makes it possible to reduce the clearance between the edges 24 of the platform and the blade 18 of the blade 12 by modifying the kinematics for mounting the platforms on the ribs 16 of the disk 10 and by using protective gaskets. to lock the platforms on the disk.
- gaskets are used to protect the blade roots 20 engaged in the cells 14 against the friction thereof on the sides of the cavities 14 of the disc.
- FIG 2 is schematically shown a protective lining 30 according to the invention, engaged in translation on a rib 16 of a disk 32 according to the invention of which only a portion is visible.
- the protective lining 30 has a C-shaped transverse section enabling it to be axially engaged and retained radially on the rib 16.
- the central portion 34 of the protective lining 30 extends over a portion of the rib 16 of the disk and is connected by substantially radial uprights 36 to the lateral edges 38 of the gasket 30 and extend over the entire length of the disk 32.
- the lateral edges 38 disposed inside the cell 14, bear against a part of the rib and provide the radial retention of the protective lining 30.
- the central portion 34 is substantially parallel to the outer peripheral surface of the rib 16 of the disk 32 and its axial ends 40 are substantially parallel to a plane perpendicular to the axis of the disk 32.
- the protective lining 30 not only makes it possible to prevent the blade roots 20 from being damaged, but also to keep the platform on the rib 16 of the disk 32 by forming locking means for the platform. form.
- the central portion 34 of the liner 30 comprises a window 42 and cutouts 40 at its axial ends.
- FIG 3 there is shown a platform 44 according to the invention comprising radially inwardly extending legs 46 which are formed of radial uprights 48 and axial flanges 50.
- the locking of a platform 44 placed on a rib 16 of the disc 32 is made by translationally inserting the protective lining 30 on a rib 16 of the disc 32.
- the lining 30 is moved on the rib 16 of the disc 32 until at a position such that the feet 46 of the platform 44 can be inserted by radial translation along the arrow A in a cutout 40 and the window 42 of the protective lining 30.
- the platform 44 shown in FIG. figure 3 comprises two feet 46 offset axially and which rest after insertion through the protective lining 30 on the rib 16 of the disc 32.
- the protective lining 30 is then translated according to the arrow B on the rib 16 so that the axial flanges 50 are retained radially by the central portion 34 of the protective lining 30, which ensures a radial locking of the platform 44 on the disk 32.
- the platform 44 undergoes the effect of the centrifugal force and performs a movement of radial displacement stopped by the axial flanges 50 which abut against the central portion 34 of the protective lining.
- the radial insertion of the platform 44 allows the curvature of the edges of the platform 44 coincides perfectly with the curvature of the blade 18 and the clearance between the platform 44 and the blade 12 is reduced.
- the lateral upstream ends of the lining 30 form projections 52 with respect to the upstream face of the disk 32 when the lining 30 is in the locking position of the platform 44. These projections 52 are intended to cooperate with a annular piece not shown, mounted on the upstream face of the disk 32 for the axial retention of the blade roots 20 and the protective liners 30.
- the cells 14 and the ribs 16 and the protective liners 30 have a helical profile.
- This profile makes it possible, in the case where the cells 14 make an angle with the axis of the disk 32, to keep a thickness e1 constant over the entire length of the disk 32 and substantially equal to the thickness e2 since the cells 14 and ribs 16 follow the cylindrical profile of the disc 32. This type of profile thus reduces the wear of the blade roots 20.
- the protective lining 30 may also serve as a stop or be deformed to avoid contact between the platform 44 and the blade 12 disengaged which can lead to the ejection of the platform 44.
- the protective liner 30 may comprise a variable number of cutouts 42 and openings according to the number of feet 46 required for the platform 44.
- the protective seals are metallic and have a thickness of between 0.1 and a few millimeters.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0701906A FR2913735B1 (fr) | 2007-03-16 | 2007-03-16 | Disque de rotor d'une turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1970538A1 true EP1970538A1 (de) | 2008-09-17 |
EP1970538B1 EP1970538B1 (de) | 2010-05-19 |
Family
ID=38657112
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08152232A Active EP1970538B1 (de) | 2007-03-16 | 2008-03-04 | Rotorscheibe einer Strömungsmaschine |
Country Status (7)
Country | Link |
---|---|
US (1) | US8277188B2 (de) |
EP (1) | EP1970538B1 (de) |
JP (1) | JP5152755B2 (de) |
CA (1) | CA2625317C (de) |
DE (1) | DE602008001269D1 (de) |
FR (1) | FR2913735B1 (de) |
RU (1) | RU2487249C2 (de) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2955904A1 (fr) * | 2010-02-04 | 2011-08-05 | Snecma | Soufflante de turbomachine |
WO2014033408A1 (fr) * | 2012-09-03 | 2014-03-06 | Snecma | Rotor de turbine pour une turbomachine |
FR3052485A1 (fr) * | 2016-06-08 | 2017-12-15 | Snecma | Rotor a element de dissipation d'energie |
FR3089258A1 (fr) * | 2018-12-03 | 2020-06-05 | Safran Aircraft Engines | Soufflante comprenant une plateforme inter-aubes fixée radialement par une tôle de protection sacrificielle |
CN113914999A (zh) * | 2021-12-14 | 2022-01-11 | 成都中科翼能科技有限公司 | 一种燃气轮机压气机装配方法 |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2913735B1 (fr) * | 2007-03-16 | 2013-04-19 | Snecma | Disque de rotor d'une turbomachine |
FR2933887B1 (fr) * | 2008-07-18 | 2010-09-17 | Snecma | Procede de reparation ou de reprise d'un disque de turbomachine et disque de turbomachine repare ou repris |
US8573947B2 (en) * | 2010-03-10 | 2013-11-05 | United Technologies Corporation | Composite fan blade dovetail root |
US8708656B2 (en) * | 2010-05-25 | 2014-04-29 | Pratt & Whitney Canada Corp. | Blade fixing design for protecting against low speed rotation induced wear |
GB201104994D0 (en) * | 2011-03-25 | 2011-05-11 | Rolls Royce Plc | a rotor having an annulus filler |
WO2014149366A1 (en) * | 2013-03-15 | 2014-09-25 | United Technologies Corporation | Injection molded composite fan platform |
US10590798B2 (en) | 2013-03-25 | 2020-03-17 | United Technologies Corporation | Non-integral blade and platform segment for rotor |
WO2015076900A2 (en) | 2013-10-11 | 2015-05-28 | United Technologies Corporation | Fan rotor with integrated platform attachment |
FR3037367B1 (fr) * | 2015-06-15 | 2017-06-30 | Snecma | Ensemble rotatif de turbomachine a garnitures de protection bombees |
GB201612288D0 (en) * | 2016-07-15 | 2016-08-31 | Rolls-Royce Ltd | A rotor assembly for a turbomachine and a method of manufacturing the same |
FR3082232B1 (fr) * | 2018-06-12 | 2020-08-28 | Safran Aircraft Engines | Systeme de maintien pour le demontage d'une roue a aubes |
FR3085711B1 (fr) * | 2018-09-06 | 2021-07-23 | Safran Aircraft Engines | Roue a aubes de turbomachine pour aeronef |
JP7269029B2 (ja) * | 2019-02-27 | 2023-05-08 | 三菱重工業株式会社 | 動翼及び回転機械 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3640640A (en) * | 1970-12-04 | 1972-02-08 | Rolls Royce | Fluid flow machine |
GB2064667A (en) * | 1979-11-30 | 1981-06-17 | United Technologies Corp | Turbofan rotor blades |
FR2608674A1 (fr) * | 1986-12-17 | 1988-06-24 | Snecma | Roue de turbine a aubes ceramique |
EP1085172A2 (de) * | 1999-09-17 | 2001-03-21 | General Electric Company | Befestigung für eine faserverstärkte Turbomaschinenschaufel |
EP1306523A1 (de) * | 2001-10-24 | 2003-05-02 | Snecma Moteurs | Schaufelplattformen eines rotierenden Bausatzes |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
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US323642A (en) * | 1885-08-04 | Cotton-planter | ||
US323072A (en) * | 1885-07-28 | William k | ||
US322493A (en) * | 1885-07-21 | Philippe sorgue | ||
GB928349A (en) * | 1960-12-06 | 1963-06-12 | Rolls Royce | Improvements in or relating to bladed rotors of fluid flow machines |
GB1276106A (en) * | 1969-12-19 | 1972-06-01 | Rolls Royce | FLUID FLOW MACHINE, e.g. GAS TURBINE ENGINE COMPRESSOR |
US3801222A (en) * | 1972-02-28 | 1974-04-02 | United Aircraft Corp | Platform for compressor or fan blade |
US5240375A (en) * | 1992-01-10 | 1993-08-31 | General Electric Company | Wear protection system for turbine engine rotor and blade |
EP1124038A1 (de) * | 2000-02-09 | 2001-08-16 | Siemens Aktiengesellschaft | Turbinenschaufelanordnung |
US6431835B1 (en) * | 2000-10-17 | 2002-08-13 | Honeywell International, Inc. | Fan blade compliant shim |
US6520742B1 (en) * | 2000-11-27 | 2003-02-18 | General Electric Company | Circular arc multi-bore fan disk |
FR2819289B1 (fr) * | 2001-01-11 | 2003-07-11 | Snecma Moteurs | Systeme de retention des aubes de type combine ou cascade |
US6860722B2 (en) * | 2003-01-31 | 2005-03-01 | General Electric Company | Snap on blade shim |
US7284958B2 (en) * | 2003-03-22 | 2007-10-23 | Allison Advanced Development Company | Separable blade platform |
FR2913735B1 (fr) * | 2007-03-16 | 2013-04-19 | Snecma | Disque de rotor d'une turbomachine |
-
2007
- 2007-03-16 FR FR0701906A patent/FR2913735B1/fr active Active
-
2008
- 2008-03-04 EP EP08152232A patent/EP1970538B1/de active Active
- 2008-03-04 DE DE602008001269T patent/DE602008001269D1/de active Active
- 2008-03-12 CA CA2625317A patent/CA2625317C/fr active Active
- 2008-03-13 RU RU2008109760/06A patent/RU2487249C2/ru active
- 2008-03-14 US US12/048,726 patent/US8277188B2/en active Active
- 2008-03-14 JP JP2008065685A patent/JP5152755B2/ja active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3640640A (en) * | 1970-12-04 | 1972-02-08 | Rolls Royce | Fluid flow machine |
GB2064667A (en) * | 1979-11-30 | 1981-06-17 | United Technologies Corp | Turbofan rotor blades |
FR2608674A1 (fr) * | 1986-12-17 | 1988-06-24 | Snecma | Roue de turbine a aubes ceramique |
EP1085172A2 (de) * | 1999-09-17 | 2001-03-21 | General Electric Company | Befestigung für eine faserverstärkte Turbomaschinenschaufel |
EP1306523A1 (de) * | 2001-10-24 | 2003-05-02 | Snecma Moteurs | Schaufelplattformen eines rotierenden Bausatzes |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2955904A1 (fr) * | 2010-02-04 | 2011-08-05 | Snecma | Soufflante de turbomachine |
WO2011095722A1 (fr) * | 2010-02-04 | 2011-08-11 | Snecma | Soufflante de turbomachine |
CN102753788A (zh) * | 2010-02-04 | 2012-10-24 | 斯奈克玛 | 涡轮引擎风扇 |
US9376925B2 (en) | 2010-02-04 | 2016-06-28 | Snecma | Turbine engine fan |
RU2555099C2 (ru) * | 2010-02-04 | 2015-07-10 | Снекма | Вентилятор газотурбинного двигателя |
CN102753788B (zh) * | 2010-02-04 | 2015-02-11 | 斯奈克玛 | 涡轮引擎风扇 |
CN104603397A (zh) * | 2012-09-03 | 2015-05-06 | 斯奈克玛 | 涡轮机的涡轮转子 |
FR2995003A1 (fr) * | 2012-09-03 | 2014-03-07 | Snecma | Rotor de turbine pour une turbomachine |
WO2014033408A1 (fr) * | 2012-09-03 | 2014-03-06 | Snecma | Rotor de turbine pour une turbomachine |
CN104603397B (zh) * | 2012-09-03 | 2016-06-29 | 斯奈克玛 | 涡轮机的涡轮转子和涡轮机 |
US10329912B2 (en) | 2012-09-03 | 2019-06-25 | Safran Aircraft Engines | Turbine rotor for a turbomachine |
FR3052485A1 (fr) * | 2016-06-08 | 2017-12-15 | Snecma | Rotor a element de dissipation d'energie |
FR3089258A1 (fr) * | 2018-12-03 | 2020-06-05 | Safran Aircraft Engines | Soufflante comprenant une plateforme inter-aubes fixée radialement par une tôle de protection sacrificielle |
CN113914999A (zh) * | 2021-12-14 | 2022-01-11 | 成都中科翼能科技有限公司 | 一种燃气轮机压气机装配方法 |
Also Published As
Publication number | Publication date |
---|---|
US20080226457A1 (en) | 2008-09-18 |
FR2913735B1 (fr) | 2013-04-19 |
RU2487249C2 (ru) | 2013-07-10 |
US8277188B2 (en) | 2012-10-02 |
JP2008232146A (ja) | 2008-10-02 |
CA2625317C (fr) | 2015-04-28 |
CA2625317A1 (fr) | 2008-09-16 |
FR2913735A1 (fr) | 2008-09-19 |
RU2008109760A (ru) | 2009-09-20 |
DE602008001269D1 (de) | 2010-07-01 |
JP5152755B2 (ja) | 2013-02-27 |
EP1970538B1 (de) | 2010-05-19 |
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