Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
  • B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
  • B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
• • 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
  • 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
  • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
  • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
  • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
• • 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
• • 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
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
  • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
  • F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
• • 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
  • F04D29/08—Sealings
  • F04D29/16—Sealings between pressure and suction sides
  • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
  • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel
• • 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
  • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal 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
  • F04D29/40—Casings; Connections of working fluid
  • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
  • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49229—Prime mover or fluid pump making
  • Y10T29/49236—Fluid pump or compressor making

Definitions

• the invention relates to a turbomachine centrifugal compressor compressor cover method, a cover adapted to implement this method and a centrifugal compressor assembly provided with such a cover.
• a turbomachine can equip any type of aircraft, in particular a helicopter or an airplane.
• the configuration is said optimized in that it induces a game minimized and substantially constant between the cover and the wheel in all phases of the flight.
• the wheel cover fasteners are configured as flexible diaphragms to adapt the positioning of the cover during operation of the centrifugal compressor.
• the classically sought positioning aims to maintain a minimum clearance between the cover and the wings of the wheel in all phases of flight, either during the transient operating conditions of the compressor or during intermediate stabilized regimes.
• the temperature and pressure of the air flow in a centrifugal compressor impeller substantially increases by 30 to 40% of the leading edge at the trailing edge of the impeller.
• the effect of this differential is to tilt the radial portions of the fins near the trailing edge upstream, and thus to bring the wheel of the cover gradually, from upstream to downstream.
• an additional temperature increase in the region of these radial trailing edge portions comes from the heat radiated by the turbine of the turbomachine. This additional supply also enhances the inclination of the fins on the compressor cover.
• This inclination is furthermore also favored by the centrifugal forces which result from the high rotational speed of the impeller. These forces centrifuges also induce radial expansion, in particular for the axial portion of the cover, on the side of its leading edge.
• annular diaphragm-shaped fastener secures the lid by clamping on an annular support.
• a link in the leading edge does not allow air bleed into the lid. Indeed, the seal between the air taken and that flowing between the cover and the diffuser is not assured, which causes recirculation.
• an air sample is generally provided as a power source for the equipment of the turbine engine or the aircraft.
• a link at the trailing edge does not allow the cover to follow the movement of the impeller, particularly in its radial part, that is to say where the displacement is the most important: the game cover / impeller is sized to be at a given value to the maximum takeoff power, abbreviated PMD, of the turbomachine. But this game is not optimized in stabilized intermediate regimes and transient regimes.
• a single connection in the bend of the cover does not overcome the drawbacks of the double bonds or the link in the trailing edge because the behavior of the lid does not follow the movement of the fins, especially the upstream movement. , to limit the setting of games.
• a single-link architecture in the bend is described for example in US Patent Specification 4,264,271.
• the cover fastener here is a radial ring-shaped extension (50) attached to an annular support (42) by flanges.
• the crown can deform under the effect of pressure and temperature. This deformation makes it possible to move the concave cover so as to maintain the same distance with the wings of the wheel.
• the radial displacement of the junction (56) is strongly limited by the ring (50) which works in compression.
• this type of architecture limits the rotation of the meridian of the cover initiated naturally by the temperature gradient present on the lid.
• the present invention aims to allow a displacement of the cover so that the clearance between the cover and the wings of the wheel remains as low as possible in a wide range of deformation of the wheel.
• the invention proposes a type of attachment configuration in the middle of the lid having a particular portion. More specifically, the present invention relates to a turbomachine centrifugal compressor wheel cover fastening method, in which the cover has a concave envelope and an axisymmetric connection between a junction formed substantially in the middle of the casing and an axial fastening at the periphery, keeping the casing at a distance from the impeller.
• An elastically deformable portion in bending is arranged on said link outside the junction to the envelope, so that the distance between the casing and the wheel is kept constant with minimum clearances at intermediate and transient levels.
• the presence of such a portion ensures a substantially constant distance in operation, which allows adjustment of the games to intermediate and transient regimes minimized, and a behavior of the fastener that remains as close to the behavior of the wheel to these intermediate and transitional regimes.
• the deformable portion is arranged near the attachment of the connection and the connection is joined to the casing in a substantially radial configuration with respect to the curvature of the casing at the junction.
• the invention also relates to a cover for implementing the method above, the cover having a concave envelope having an inner face arranged at a distance from the compressor equipped with a wheel provided with fins by a fastener having a junction end formed substantially in the middle of the casing and another end fixed to a casing of the turbomachine.
• a fastener comprises an axially symmetrical diaphragm of generally frustoconical configuration which has an arm profile coupled to the fastening end to the casing by a double-angled joint of right angles and obtuse at rest, this articulation being arranged closer to the fixing end only from the junction end to the casing.
• the distance between the inner face of the casing and the upper edges of the fins is thus able to be kept constant during operation and adjusted with a minimum clearance setting at the intermediate and transient regimes.
• the diaphragm comprises an axial annular connection between a radial fixing ring and the double-elbow joint;
• the double-elbow joint is formed in the rest position by a radial hinge ring coupled, on the one hand, to the axial annular connection along a substantially straight bend and, on the other hand, to the frustoconical arm. according to an obtuse angle bend;
• the profile of the arm may be substantially rectilinear at rest and substantially scalable thickness increasing towards the junction end;
• the arm has on average a thickness substantially smaller than that of the envelope of the lid.
• the invention also relates to an assembly of a cover as described above and a centrifugal compressor turbomachine.
• the cover is configured to remain on the one hand at a constant distance from the compressor and, on the other hand, to attach to the casing of the turbomachine.
• FIG. 1 a longitudinal view of a turbomachine equipped with a centrifugal compressor cover according to the invention
• FIG. 3 a partial front view of the cover and the compressor according to the plane III-III of FIG. 1, and
• FIG. 4 shows the sectional view according to FIG. 2 while the compressor is in operation, showing the positions of the cover and compressor operating relative to those at rest in Figure 2 which appear in dashed lines.
• the terms of the "axial”, “axisymmetric”, “upstream” and “downstream” type refer to locations along or of revolution around the central axis X'X of rotation of the turbomachine according to the direction of this central axis.
• the term “radial” refers to locations orthogonal to this central axis.
• the elements having the same reference signs in different figures relate to identical elements.
• an example of an aircraft turbine engine 1 mainly comprises, arranged upstream and downstream about the central axis of rotation X'X, an axial compressor 10 with three stages, a centrifugal compressor. 12, combustion chambers 14, a linked turbine 16 with two stages and a free turbine 18 also with two stages.
• F1 air flow is compressed by the passage of compressors 10 and 12 in ducts 2, and then mixed with the fuel in the chambers 14 to provide by combustion of the kinetic energy to the turbines 16 and 18.
• the stages of the turbine 16 drives the compressors 10 and 12 via a transmission shaft 3 and the free turbine 18 transmits power via a through shaft 4 to the aircraft equipment (pump alternators, air conditioning).
• the turbomachine is protected by a housing 6.
• the turbomachine is a turbine engine and the aircraft a helicopter.
• the free turbines drive the equipment, in particular the rotor of the propeller, via a power transmission gearbox 7 equipped with appropriate gearboxes.
• the centrifugal compressor 12 is equipped with axial fins 20 formed on a wheel 22 to drive the flow of air F1 and compress when the compressor rotates at high speed.
• the duct 2 in which the flow F1 flows is limited at the level of the centrifugal compressor by the fins 20 and the inside face 51 of a concave envelope 50.
• This envelope 50 is held by an extension forming a fastener 8 fixed to the casing 6 by flanges 61.
• the envelope 50 and the fastener 8 form the cover 5.
• the flow of compressed air F1 is then conveyed to the combustion chambers 14 via diffusers 19.
• the fastener 8 of the cover 5 originates substantially in the middle of the concave face of the lid, for example, as illustrated, at the junction end point 83 where the curvature of the lid is the strongest.
• the fastener 8 is then substantially radial to the envelope 50 with respect to the curvature of the cover at the point of contact.
• the configuration of this fastener 8 is illustrated more particularly by the views in partial and frontal section of the lid and the centrifugal compressor of FIGS. 2 and 3. In these figures, at least partially appear the fins 20 of the impeller, the duct 2, the compressor centrifuge 12 and the shafts 3 and 4.
• the envelope 50 has a leading edge BA, substantially axial and a trailing edge BF downstream substantially radial.
• the fastener 8 is composed of one end forming a radial ring 82 fixed to the casing by flanges (see FIG. 1), and an axially symmetrical diaphragm 80 of generally frustoconical configuration.
• the ring 82 is arranged substantially radially opposite the end of the leading edge BA of the envelope 50.
• the diaphragm 80 comes to the end 83 to integrate with the envelope 50 with a suitable mechanical reinforcement 84.
• the diaphragm 80 is in turn composed of an axial annular connection 8a coupled to a rectilinear frustoconical arm 8b, via a double bent joint.
• the adjustable length of the axial connection 8a advantageously provides a degree of freedom of adaptation to the position imposed by the fixing flanges 61.
• the joint is formed, as shown in the rest position, by the assembly of a radial crown 8c of articulation with, firstly, the axial annular connection 8a - according to a bend 8d d ' substantially straight angle - and, on the other hand, the rectilinear arm 8b - according to an 8th elbow obtuse angle - about 140 ° in the example.
• the arm 8b preferably has a substantially scalable thickness "E" which increases between the elbow 8e and its end 83.
• this thickness is on average lower, for example from 1, 5 to 3
• This thin arm thickness makes it possible to reduce the play consumption between the inner face 51 of the envelope 50 and the upper edges 21 of the fins 20 during the stabilized flight regimes.
• arm thickness that is too low can increase game consumptions during transients. A compromise is therefore obtained on all intermediate regimes, without risk of severe contact between the casing 50 and the edges of fins 21, this thickness of intermediate arm can also be scalable.
• the variation of the height H of the radial articulation ring 8c leads to the same compromise: the height H is increased to reduce the game consumption on all stabilized speeds, but this increase is limited to secure the risk of contact between the lid and the fins. Thus, increasing the height H by 25% reduces the thickness of the envelope 50 by 20%.
• Figure 4 illustrates in section the position of the cover 5 (in solid lines) when the compressor and therefore the fins 20 are in operation, as well as the position of the cover (in dashed lines) and fins 20 of the compressor in rest. according to Figure 2.
• the housing and the fixing of the lid also undergo the effects of pressure and temperature.
• the casing and the fastening of the lid have been shown in FIG. 4 in the same position as that of the Figure 2.
• the fins 20 move upstream (arrow A) on the side of its trailing edge BF, and in radial extension (R arrow) for the axial portion 50a (substantially parallel to the axis X'X) of the casing 50 on the side of its leading edge BA. Thanks to the bending of the radial ring 8c and the arm 8b of the fastener 8 - in other words thanks to the variation of the articulation angles of the elbows 8d and 8e - the inner face 51 of the envelope 50 follows the displacements undergone by the fins 20.
• the thickness "E”, in its mean and in its variation up to the junction 83, and the length "L" of the arm 8b can advantageously be adjusted so as to also allow an appropriate flexion of the arm depending on the configuration of the compressor.
• the behavior of the lid remaining very close to that of the wheel, the game setting is adjusted to a minimum.
• the invention is not limited to the embodiment described and shown. It is for example possible to provide the double-elbow joint in a more advanced position towards the center of the fastener, while preferably remaining closer to the crown fixing the housing than the cover. Several joints may also be provided around radial crown of suitable dimensions. Moreover, the obtuse angle of the frustoconical arm at rest can preferably vary within a range of between 120 and 150 °.
• a slightly curved arm, concave or convex, or a radial crown also slightly concave or convex.
• the dimensional characteristics of the arm 8b namely its thickness "E", in its evolution not necessarily linear to the junction, and its length "L", for example 3 to 4 times higher than that of the rest of the fastener , can be adjusted in addition to the characteristics of the double-elbow joint to adjust the proper bending of the entire attachment.
• other types of elastically deformable portion may be provided: use of different materials for the portion and the arm, portion having corrugations and / or perforated material, any other shape and other suitable treatment.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Priority Applications (9)

Applications Claiming Priority (2)

Publications (1)

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ID=44022910

Family Applications (1)

Country Status (11)

Cited By (2)

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Citations (5)

Family Cites Families (8)

• 2010
  • 2010-10-21 FR FR1058587A patent/FR2966529B1/fr active Active
• 2011
  • 2011-10-20 WO PCT/FR2011/052448 patent/WO2012052687A1/fr not_active Ceased
  • 2011-10-20 KR KR1020137008702A patent/KR101819778B1/ko not_active Expired - Fee Related
  • 2011-10-20 US US13/880,245 patent/US9409228B2/en active Active
  • 2011-10-20 CA CA2813692A patent/CA2813692C/fr not_active Expired - Fee Related
  • 2011-10-20 EP EP11785734.2A patent/EP2630336B1/fr active Active
  • 2011-10-20 RU RU2013117811/06A patent/RU2570310C2/ru active
  • 2011-10-20 PL PL11785734T patent/PL2630336T3/pl unknown
  • 2011-10-20 JP JP2013534370A patent/JP5916742B2/ja active Active
  • 2011-10-20 CN CN201180050194.0A patent/CN103201461B/zh active Active
  • 2011-10-20 ES ES11785734.2T patent/ES2668570T3/es active Active

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