EP2427658A1 - Rotor de soufflante d'un turboreacteur d'avion - Google Patents
Rotor de soufflante d'un turboreacteur d'avionInfo
- Publication number
- EP2427658A1 EP2427658A1 EP10723700A EP10723700A EP2427658A1 EP 2427658 A1 EP2427658 A1 EP 2427658A1 EP 10723700 A EP10723700 A EP 10723700A EP 10723700 A EP10723700 A EP 10723700A EP 2427658 A1 EP2427658 A1 EP 2427658A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- lock
- groove
- engaged
- fan rotor
- additional
- 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
- 238000011144 upstream manufacturing Methods 0.000 claims description 23
- 229910052751 metal Inorganic materials 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 7
- 238000006073 displacement reaction Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 230000000717 retained effect Effects 0.000 claims description 2
- 230000035939 shock Effects 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 230000003100 immobilizing effect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
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
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
Definitions
- the invention relates to a fan rotor of an aircraft turbojet and more particularly concerns the locking of the blade roots in their respective grooves. It aims in particular the development of the system of individual locks to maintain the blades in their respective grooves. It also relates to an aircraft turbojet engine whose fan is equipped with such a rotor.
- the rotor of the fan carries a number of blades, each blade having a rib blade root engaged in a groove formed at the periphery of a wheel.
- the grooves are defined between radial protuberances provided with longitudinal lateral protrusions, covering the edges of the grooves and shaped to retain the blade roots.
- each blade root is engaged in its groove by sliding it by the upstream end thereof.
- upstream and downstream are used to denote respectively a forward or a rearward position of the engine, according to the direction of flow of the air in the blower.
- US Pat. No. 5,259,728 discloses a type of latch comprising a relatively thick metal element, for example titanium, bearing on its downstream face a damping structure constituted by a hollow honeycomb element.
- This structure is rigid enough to withstand the normal stresses of the blade root. In case of serious incident, it allows, crashing, to dampen the shock.
- the honeycomb structure made from fairly thin strip is difficult to fix (weld) on the downstream face of the thick metal element of said lock. The cost price of such a lock is also quite high.
- the invention solves these problems. More specifically, the invention relates to a fan rotor comprising fan blades attached to the periphery of a wheel, each blade having a blade root engaged in a groove of said wheel and retained therein by a latch engaged in notches made in the vicinity and on either side of the upstream end of the corresponding groove, to oppose a displacement of said blade root in the axial direction, characterized in that each said lock said main lock is associated with an additional lock separate from said main lock and spaced therefrom by a predetermined distance, said additional lock being located between said main lock and the upstream end of said blade root engaged in the groove.
- the additional lock is a thin wall.
- Said thin wall is advantageously deformable material, such as a metal plate engaged in corresponding notches formed on either side of the groove upstream thereof.
- This metal plate whose outer contour is advantageously similar to that of the main lock, may, for example, be made of stainless steel or any other metal capable of deforming without breaking, coming crashing against the downstream face of the lock main.
- the deformation of the thin plate causes neither its extraction nor the formation of debris likely to damage the neighboring blades.
- the cost of said additional lock is very low. Its thickness is low compared to the thickness of the main lock, usually of the order of 1/4 to 1/3 of the thickness of the main lock. Consequently, the corresponding notches practiced on the other of the groove are also of small width and can therefore easily be made by a machining type electroerosion wire.
- the additional lock comprises a tongue extending substantially perpendicular to its surface, upstream.
- This tongue is welded to an edge of said main lock. Accordingly, at the time of assembly, there is a single locking assembly, the spacing between the two locks being predetermined by the length of the tongue.
- This locking assembly can be implemented by introducing the two locks in their respective notches by their inner radial ends opening.
- a fixing lug protrudes upstream of said main lock, for mounting a wedge inserted between the blade root and the bottom of said groove.
- the wedge traditionally housed at the bottom of the groove, is fixed to the main latch and immobilized axially by the establishment thereof. Conversely, the wedge prevents the release of the lock.
- FIG. 1 is a partial perspective view of the fan rotor wheel showing the end of a groove
- FIG. 2 is an elevational view of the locking assembly composed of the two locks;
- FIG. 3 is a perspective view of the same locking assembly;
- FIG. 4 is a partial perspective view of the wheel, with the blade and the locking assembly in place;
- - Figure 5 is a partial view along arrow V of Figure 4, the locking assembly being fixed to the shim installed under the blade root; and - Figure 6 is a view along the arrow VI of Figure 5.
- the fan rotor 11 as shown, consists mainly of a disc constituting a wheel 13, to which are attached fan blades 15.
- Each blade comprises a blade root 17, provided with lateral ribs, engaged in a groove 18 , corresponding wheel 13.
- the latter and has at its periphery radial protuberances 20, extending over a certain length, parallel to the axis of the rotor.
- These radial protuberances are provided with lateral bosses 22 extending above the edges of the adjacent grooves 18.
- a longitudinal shim 24 is inserted between the bottom of each groove and the blade root therein, to stabilize the position of the blade, radially.
- the upstream ends of the grooves are closed individually by locks 28.
- a lock 28 is hereinafter referred to as the main lock.
- Each main latch 28 is engaged in notches 34 formed on either side of the groove 18 that closes in the vicinity of the upstream end thereof.
- the end portions 19 of the radial protuberances 20 project upstream with respect to the upstream face 13a of the wheel 13.
- Each notch 34 is formed in this portion projecting from the adjacent radial protuberance 20.
- the notches 34 open in front of the groove and are oriented so as to converge towards each other radially outwards.
- a corresponding main latch 28 has edges 30 having the same convergence as the notches.
- each main latch 28 is associated with a deformable, thin wall additional lock 32 separate from said main latch 28 and spaced therefrom by a predetermined distance.
- the additional lock 32 is therefore interposed between the main latch 28 and the upstream end of the blade root 17 mounted in the corresponding groove.
- the additional lock 32 is a metal plate, for example made of stainless steel, engaged in corresponding notches 36 formed on either side of said groove, in the end portions 19 projecting from the adjacent radial protuberances 20.
- the notches 34 of the main latch 28 and those of the additional latch 32 open radially internally to the front of the upstream face 13a of the wheel 13.
- the additional latch 32 has substantially the same contour as the main latch 28 and the notches 36 in which it is engaged are also similar to those that host the neighboring main lock. However, they have a smaller axial length since the additional lock 32 is thinner than the main lock.
- the thickness of the additional lock will be approximately one quarter to one third of the thickness of the main lock.
- the additional latch has a tongue 38 extending substantially perpendicular to its surface toward the main latch and this tongue is welded to an edge 37 of the main latch.
- a unitary locking assembly 28, 32 to close the upstream end of each groove 18. The assembly is done by inserting the two latches simultaneously in their notches, radially outwardly.
- a bracket 40 protrudes upstream of the main lock for immobilizing the wedge 24 inserted between the blade root and the bottom of the groove.
- the fixing lug 40 is provided with a captive nut 42 and the end of the shim is pierced with a hole.
- the wedge 24 is slid into the groove 18 between the bottom wall thereof and the inner radial face of the blade root and the end of the wedge is fixed to the leg of the blade. fastening by means of a screw or the like. The screw passes through the hole in the hold and is screwed into the lock nut.
- a bracing piece 45 is interposed between the end of shim 24 and the fixing lug 40.
- the notches 36 of the additional lock are narrow and therefore they can be made by implementing a wire EDM process. This operation can be performed on an already existing rotor wheel, that is to say not originally provided for this type of lock.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0953001A FR2945329B1 (fr) | 2009-05-06 | 2009-05-06 | Rotor de soufflante d'un turboracteur d'avion |
PCT/FR2010/050747 WO2010128229A1 (fr) | 2009-05-06 | 2010-04-19 | Rotor de soufflante d'un turboreacteur d'avion |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2427658A1 true EP2427658A1 (fr) | 2012-03-14 |
EP2427658B1 EP2427658B1 (fr) | 2015-07-08 |
Family
ID=41278266
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10723700.0A Active EP2427658B1 (fr) | 2009-05-06 | 2010-04-19 | Rotor de soufflante d'un turboreacteur d'avion |
Country Status (9)
Country | Link |
---|---|
US (1) | US8899935B2 (fr) |
EP (1) | EP2427658B1 (fr) |
JP (1) | JP5497157B2 (fr) |
CN (1) | CN102422026B (fr) |
BR (1) | BRPI1013848A2 (fr) |
CA (1) | CA2760470A1 (fr) |
FR (1) | FR2945329B1 (fr) |
RU (1) | RU2525817C2 (fr) |
WO (1) | WO2010128229A1 (fr) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8840375B2 (en) * | 2011-03-21 | 2014-09-23 | United Technologies Corporation | Component lock for a gas turbine engine |
GB201317161D0 (en) | 2013-09-27 | 2013-11-06 | Rolls Royce Plc | Retainer plate |
GB201318623D0 (en) | 2013-10-22 | 2013-12-04 | Rolls Royce Plc | Retainer plate |
FR3057908B1 (fr) * | 2016-10-21 | 2019-11-22 | Safran Aircraft Engines | Ensemble rotatif d'une turbomachine muni d'un systeme de maintien axial d'une aube |
RU2659416C1 (ru) * | 2017-04-07 | 2018-07-02 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Рабочее колесо компрессора газотурбинного двигателя |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3395891A (en) * | 1967-09-21 | 1968-08-06 | Gen Electric | Lock for turbomachinery blades |
FR2502690B1 (fr) | 1981-03-27 | 1985-09-13 | Snecma | Dispositif de verrouillage d'aubes de soufflante et de fixation de capot avant d'un turboreacteur |
FR2535793B1 (fr) | 1982-11-08 | 1987-04-10 | Snecma | Dispositif de verrouillage axial d'aubes de soufflante |
FR2535794A1 (fr) * | 1982-11-08 | 1984-05-11 | Snecma | Dispositif de retenue axiale et radiale d'aubes de soufflante |
SU1130693A1 (ru) * | 1983-04-11 | 1984-12-23 | Производственное объединение "Брянский машиностроительный завод" им.В.И.Ленина | Устройство дл осевой фиксации рабочих лопаток турбомашины |
US5259728A (en) * | 1992-05-08 | 1993-11-09 | General Electric Company | Bladed disk assembly |
US5350279A (en) * | 1993-07-02 | 1994-09-27 | General Electric Company | Gas turbine engine blade retainer sub-assembly |
US5984639A (en) * | 1998-07-09 | 1999-11-16 | Pratt & Whitney Canada Inc. | Blade retention apparatus for gas turbine rotor |
FR2886336B1 (fr) * | 2005-05-26 | 2007-08-24 | Snecma Moteurs Sa | Perfectionnement a une roue aubagee de rotor pour renforcer le verrouillage des aubes |
FR2889264B1 (fr) | 2005-07-29 | 2007-11-02 | Snecma | Verrouillage des aubes dans un rotor de soufflante |
FR2900437B1 (fr) | 2006-04-27 | 2008-07-25 | Snecma Sa | Systeme de retention des aubes dans un rotor |
-
2009
- 2009-05-06 FR FR0953001A patent/FR2945329B1/fr active Active
-
2010
- 2010-04-19 US US13/318,502 patent/US8899935B2/en active Active
- 2010-04-19 RU RU2011149487/06A patent/RU2525817C2/ru not_active IP Right Cessation
- 2010-04-19 BR BRPI1013848A patent/BRPI1013848A2/pt not_active IP Right Cessation
- 2010-04-19 WO PCT/FR2010/050747 patent/WO2010128229A1/fr active Application Filing
- 2010-04-19 JP JP2012509073A patent/JP5497157B2/ja not_active Expired - Fee Related
- 2010-04-19 CA CA2760470A patent/CA2760470A1/fr not_active Abandoned
- 2010-04-19 CN CN201080020196.0A patent/CN102422026B/zh active Active
- 2010-04-19 EP EP10723700.0A patent/EP2427658B1/fr active Active
Non-Patent Citations (1)
Title |
---|
See references of WO2010128229A1 * |
Also Published As
Publication number | Publication date |
---|---|
US20120045341A1 (en) | 2012-02-23 |
FR2945329A1 (fr) | 2010-11-12 |
RU2011149487A (ru) | 2013-06-20 |
CN102422026B (zh) | 2014-08-20 |
RU2525817C2 (ru) | 2014-08-20 |
CA2760470A1 (fr) | 2010-11-11 |
US8899935B2 (en) | 2014-12-02 |
EP2427658B1 (fr) | 2015-07-08 |
JP2012526231A (ja) | 2012-10-25 |
BRPI1013848A2 (pt) | 2016-04-12 |
FR2945329B1 (fr) | 2011-06-03 |
JP5497157B2 (ja) | 2014-05-21 |
WO2010128229A1 (fr) | 2010-11-11 |
CN102422026A (zh) | 2012-04-18 |
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