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
  • F04D29/40—Casings; Connections of working fluid
  • F04D29/52—Casings; Connections of working fluid for axial pumps
  • F04D29/54—Fluid-guiding means, e.g. diffusers
  • F04D29/541—Specially adapted for elastic fluid pumps
  • F04D29/542—Bladed diffusers
• • 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
  • F01D25/04—Antivibration arrangements
  • F01D25/06—Antivibration arrangements for preventing blade vibration
• • 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
  • 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
• • 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
  • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
  • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
  • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
• • 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

Definitions

• the present invention relates generally to an aircraft turbomachine, preferably of the turbojet or turboprop type.
• the invention relates to the compressor or turbine stator of such a turbomachine, and more specifically to a bladed crown sector comprising a plurality of stator vanes as well as two concentric ferrules carrying the vanes and intended to delimit radially a primary flow through the turbomachine, respectively inwardly and outwardly.
• a bladed crown generally made using several sectors arranged end to end, is generally used in the compressor or the turbine as a rectifier or distributor.
• Turbomachines generally comprise in series a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine.
• the compressors and the turbines comprise several rows of circumferentially spaced apart blades, these rows being separated by rows of blades that are also circumferentially spaced apart.
• rectifiers and distributors are subject to high dynamic loads. Indeed, the technological evolution leads to a reduction of the number of floors for equal or higher performances, which results in a higher load for each floor.
• the evolution of production technologies leads to reducing the number of parts, which leads to the reduction of the damping effect of the connections between the parts. This is the case, in particular, when adopting an abradable cartridge soldering technology that eliminates a significant source of dissipation of vibration energy.
• the object of the invention is therefore to remedy at least partially the problems mentioned above, relating to the embodiments of the prior art.
• the invention firstly relates to an assembly forming an outer ring sector, for blown crown sector intended to equip an aircraft turbomachine compressor or turbine stator, said outer shell sector comprising: on the one hand a plurality of elementary sectors spaced apart from each other in a tangential direction of said assembly, and on the other hand damping damping wedges each interposed between two elementary sectors associated with it, positioned directly following said tangential direction.
• each vibration damping wedge has a substantially identical profile to that of the elementary sectors.
• a support shims against the friction surfaces of the elementary sectors allows a perfect seal between these elements, independent of the pressure differential between the aerodynamic stream and the outside of the compressor or the turbine. Indeed, this seal is obtained by construction, with shims exerting substantially oriented efforts in the tangential direction against the friction surfaces of the elementary sectors. It is noted that this seal is further enhanced in operation, since the plating forces between the friction surfaces and the wedges are accentuated by the application, on the elementary sectors, of the tangential component of the aerodynamic forces exerted on the vanes. of stator.
• said wedge is in abutment against two plane parallel friction surfaces and facing each other in said tangential direction and respectively provided on said two elementary sectors associated with said wedge, and said wedge has two friction surfaces. complementary planes parallel to each other and cooperating respectively with the two friction surfaces of the elementary sectors.
• the planar contacts between the friction surfaces and the complementary friction surfaces make it possible to ensure a satisfactory damping of the vibrations by friction.
• the manufacture of the assembly according to the invention is greatly simplified, which provides a significant gain in terms of cost and time.
• said wedge has hooks for its maintenance on the stator of compressor or turbine, these hooks thus having the same profile than those of the brackets worn by the elementary sectors.
• the elementary sectors are spaced from each other by radial slots fully filled by said damping damping wedges.
• said damping damping wedges extend substantially in an axial or oblique direction of said assembly.
• Another object of the present invention relates to a bladed crown sector intended to equip an aircraft turbomachine compressor or turbine stator, comprising an outer ferrule sector assembly as described above, an inner ferrule sector, and a plurality of blades spaced tangentially from each other and interposed between the outer ferrule sector assembly and the inner ferrule sector.
• each elementary sector carries a single stator vane, or possibly several blades, without departing from the scope of the invention.
• the bladed crown can constitute a compressor rectifier, or a turbine distributor.
• the ring sector preferably extends over an angular extent of between 5 and 60 °, but can be up to 360 ° in order to constitute the entire bladed crown.
• the subject of the invention is also an aircraft turbine engine comprising a stator of compressor or turbine equipped with at least one sector of bladed crown as described above.
• FIG. 1 represents a schematic sectional view of a turbomachine intended to be equipped with one or more sectors of bladed crown according to the present invention
• FIG. 2 shows a sectional view showing a portion of the high pressure compressor of the turbomachine shown in Figure 1, and incorporating a bladed crown sector according to the present invention
• Fig. 3 is a perspective view of the bladed crown sector shown in the preceding figure, the sector being in the form of a preferred embodiment of the present invention
• Figure 4 shows an axial view of a portion of the bladed crown sector shown in the previous figure
• FIG. 5 represents a view of the profiles of the wedges and of the elementary sectors of the bladed crown sector shown in the preceding figures, taken along the line V-V of FIG. 4;
• FIGS. 6a to 6c show diagrammatic views of different steps of a method of manufacture of the bladed crown sector shown in the preceding figures.
• an aircraft turbojet 100 to which the invention is applicable. It comprises, from upstream to downstream, a low-pressure compressor 2, a high-pressure compressor 4, an annular combustion chamber 6, a high-pressure turbine 8 and a low-pressure turbine 10.
• FIG. 2 represents a portion of the high-pressure compressor 4.
• the compressor alternately presents in an axial direction parallel to the axis 12 of the compressor rows 14 of stator vanes and rows 16 of vanes. rotor.
• a sector of bladed crown 20 it being understood that this sector 20 preferably extends over an angular extent of between 5 and 60 °, but can be up to 360 ° in order to constitute the entire bladed crown.
• the sector 20 thus forming all or part of a turbine distributor or a compressor rectifier, comprises an inner ferrule sector 24 of inner radial delimitation of a primary annular flow 26 passing through the turbomachine, this ferrule sector 24 laying the feet of In addition to these vanes 18, the sector 20 also incorporates an outer ferrule sector assembly 28, radially outer of the primary annular flow 26, which fixes the heads of the vanes 18.
• the sector 20 also comprises known additional elements equipping the ferrule sector 24, such as an abradable radially inner coating 29 forming an annular sealing track, contacted by a sealing device 31 carried by the rotor stage 16 carrying the rotating vanes and arranged downstream of the sector 20 concerned.
• the rotating sealing device 31 is in a known manner of labyrinth or wipe type.
• the bladed crown sector 20 can be seen.
• the entire turbine distributor or compressor straightener is obtained by the end-to-end placement of a plurality of these sectors 20, each constituting an angular or circumferential portion of the crown aubagée.
• the angular sectors 20 are preferably devoid of direct rigid mechanical connections connecting them to each other, their adjacent ends being in fact simply placed opposite each other, with or without play.
• the inner ferrule sector 24 is made in one piece, and is not segmented.
• the assembly 28 forming outer shell sector 28 is segmented into elementary sectors 30 spaced from each other in the tangential direction 22, by radial or slightly oblique straight slots 32, thus creating gaps between the directly consecutive sectors 30.
• Each slot 32 is made along a median straight line between two directly consecutive blades 18, so that each elementary sector 30 fixedly carries a single stator blade 18.
• One of the two elementary sectors 30 located at the ends of the sector 20 carries an anti-rotation stop 33 protruding radially outwardly, and intended to cooperate, in a known manner, with another part of the stator of the compressor.
• the assembly 28 also comprises, housed between the elementary sectors 30 directly consecutive vibration damping wedges 34.
• each vibration damping wedge 34 is housed between two parallel flat friction surfaces 38 facing one another in the tangential direction 22, and respectively provided on the tangential ends facing each other of the two associated elementary sectors. at the hold.
• each shim 34 has two complementary flat friction surfaces 40, parallel to each other, and also parallel and in contact with the two flat friction surfaces 38 with which they cooperate, respectively.
• Each shim 34 is thus sandwiched between two directly consecutive elementary sectors 30, in having a complementarity of shape with that of the friction surfaces 38.
• the contact between the two friction surfaces 38, 40 of each pair is obtained preferably as soon as the wedge 34 is placed between its two associated elementary sectors 30.
• the wedges 34 thus exert, with their complementary flat friction surfaces 40, substantially oriented efforts in the tangential direction against the friction surfaces 38 of the elementary sectors. These efforts are moreover reinforced in operation by the additional application, on the elementary sectors, of the tangential component of the aerodynamic forces exerted on the stator vanes.
• profile of shims 34 is substantially identical to the profile of the elementary sectors, this same profile corresponding to that of the outer shell sector.
• profile here means the overall shape of the element seen in the tangential direction 22, although a sectional view has been shown in Figure 5.
• each shim 34 has, like the elementary sectors 30, a lower surface 46 serving as external radial delineation of the vein.
• the annular overall surface of delimitation of the vein, composed of the succession of these surfaces 46 provided on the wedges 34 and the sectors 30, is therefore substantially continuous from a point of view aerodynamic, since there is no step between the successive surfaces 46.
• each shim 34 and sector 30 includes hooks for its retention on another part of the compressor stator, and more specifically a holding hook 48 projecting forwards, and a holding hook 50 protruding towards the rear.
• the hooks 48, 50 are respectively housed in annular slots 52, 54 provided in another part of the stator of the compressor, to ensure the attachment of the sector 20 on the other part of the stator.
• each shim 34 allows the transmission of tangential forces between the two elementary sectors 30 between which it is interposed.
• the material used for the elementary sectors 30 and the material used for the wedges 34 are substantially of the same nature, preferably metallic, and chosen so that the wedges are used primarily with respect to the elementary sectors 30.
• the ratio between the extent in the tangential direction of each shim, and the extent in the tangential direction of each elementary sector, these extents also corresponding to the thicknesses is between 0.5 and 1.
• FIGS. 6a to 6c schematize a method of manufacturing the bladed crown sector 20.
• a one-piece assembly 100 is produced by casting or by machining, forming the inner ferrule sector 24, the outer ferrule sector 28, and the stator vanes 18.
• By simple and inexpensive machining it is then proceeded to the realization of the radial straight slots 32 on the outer ferrule sector 28, so as to obtain the elementary sectors 30, such as that this has been schematized in Figure 6b.
• these slots 32 can be obtained by simply cutting the sector 28.
• Figure 6c shows the final step of placing the vibration damping wedges 34 in the slots 32 forming the friction surfaces, by simply sliding the wedges in their respective holes.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

Priority Applications (7)

Applications Claiming Priority (2)

Publications (2)

Family

ID=41800367

Family Applications (1)

Country Status (9)

Cited By (1)

Families Citing this family (15)

Citations (1)

Family Cites Families (12)

• 2009
  • 2009-07-31 FR FR0955439A patent/FR2948736B1/fr active Active
• 2010
  • 2010-07-29 WO PCT/EP2010/061037 patent/WO2011012679A2/fr active Application Filing
  • 2010-07-29 RU RU2012107522/06A patent/RU2537997C2/ru not_active IP Right Cessation
  • 2010-07-29 CA CA2769217A patent/CA2769217A1/en not_active Abandoned
  • 2010-07-29 JP JP2012522172A patent/JP5697667B2/ja not_active Expired - Fee Related
  • 2010-07-29 EP EP10739591.5A patent/EP2459884B1/fr active Active
  • 2010-07-29 BR BR112012002304A patent/BR112012002304A2/pt not_active IP Right Cessation
  • 2010-07-29 US US13/386,496 patent/US20120128482A1/en not_active Abandoned
  • 2010-07-29 CN CN2010800340319A patent/CN102472297A/zh active Pending

Patent Citations (1)

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