WO2011128587A1 - Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same - Google Patents
Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same Download PDFInfo
- Publication number
- WO2011128587A1 WO2011128587A1 PCT/FR2011/050846 FR2011050846W WO2011128587A1 WO 2011128587 A1 WO2011128587 A1 WO 2011128587A1 FR 2011050846 W FR2011050846 W FR 2011050846W WO 2011128587 A1 WO2011128587 A1 WO 2011128587A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- blades
- blade
- variable
- pitch
- diffuser
- Prior art date
Links
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
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
-
- 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
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- 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
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
-
- 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
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
-
- 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
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
Definitions
- the invention relates to a method of adapting the air flow rate of a turbomachine comprising a centrifugal compressor, in particular helicopter turbine engines or auxiliary power units (abbreviated as APU) to a request variable flow or mechanical or electrical power.
- the invention also relates to a diffuser equipped with variable pitch blades capable of implementing this method.
- the field of the invention is the compression of gases in turbomachinery engines and, more particularly, the adaptation of the compressed air flow to respect the performance of the engines, whether turboshaft engines or APUs, particular its specific consumption (abbreviated Cs) at partial load.
- a general problem is to meet the needs of pumping margin and to offset compression rate reductions at the intermediate speeds of the turboshaft engines, as well as variations in demand for compressed air flow and power. in the case of APUs.
- IGV inlet guide vanes
- variable setting is achieved by appropriate commands in connection with a control unit according to the physical parameters involved (rotational speed, pressures, temperatures).
- rotational speed, pressures, temperatures the ranges of wedges that the control system must cover require a control cylinder of high power, cause significant variations in the inlet and outlet diameters of the diffuser, which can generate high mechanical stresses between rotating parts (wheel) and static (radial variable valve) and decreases the efficiency at partial load (intermediate regime).
- the invention aims to overcome these disadvantages, in particular by maintaining the efficiency of the compressor to substantially reduce the Cs while ensuring a sufficient pumping margin with a better efficiency of the engine cycle at partial load. To do this, it proposes an optimized method of variable diffusion of the air flow in a centrifugal compressor of turbomachines.
- the subject of the invention is a method for diffusing variable airflow in a centrifugal compressor of turbomachine engines, consisting in providing a diffusion of air through a first annular grid of paddle blades. variable radially bordered by a second annular grid of same number of fixed-pitch blades of equivalent extension, directing the diffusion in the radial direction by coupling the blades of the two blades, each blade of the first blade being rotated away from the blade.
- Turbomachines should be understood as turbine engines, in particular helicopter turboshaft engines with a single-stage or two-stage centrifugal compressor, and APUs equipped with a centrifugal compressor of single or two-stage power.
- the radial extension of the variable pitch blades is substantially reduced by the presence of the fixed blade comprising true blades, which limits the efforts to vary their rigging and the clearance between the mobile blade and the support flange and thus the upstream / downstream recirculation, which has the effect of reducing deterioration of the pumping line and pressure losses.
- the decentralized implantation of the axis of rotation of the variable-pitch blades substantially reduces the variations in radial extension of these iso-diffusion blades: the increase in closing is less, thus favoring the efficiency, partial load and decreasing opening less also, which limits the mechanical stresses due to unsteady aerodynamic fluctuations by wheel / diffuser interaction.
- the method applying to turbomachines equipped with a power turbine, the variable-pitch radial diffusion on a centrifugal compressor, as defined above, is coupled to a wedge power turbine distributor.
- variable. Power production can be carried out according to several configurations: free power turbine - or linked, of axial or centripetal type, with or without downstream heat exchange.
- the coupling between the diffuser and the variable valve distributor makes it possible to adapt the operating line to the flow reduction, which improves the efficiency of the engine cycle (by a better pressure ratio) and therefore the Cs of the turboshaft engines. helicopters and APUs.
- the invention also relates to a turbomachine variable valve diffuser capable of implementing the method defined above, and the turbomachine equipped with such a diffuser.
- the diffuser comprises a first annular grid of variable pitch blades radially bordered by a second annular grid of fixed pitch blades of equivalent extension, forming successive diffusion channels by coupling the blades of the two grids in radial extension.
- each blade of the first gate is driven by control means capable of exerting a proper rotation of each blade off-center with respect to its axis of rotation.
- each variable-pitch blade extends between two cups opposite and parallel and off-center with respect to the common axis of the cups coinciding with the axis of rotation;
- each blade is coupled to a drive rod which has at least one orifice in which is introduced a locking pin of a washer for adjusting the axial position of the cups;
- the rod is secured to a lever having a spherical ball received in a cylindrical housing (38) of a control ring adapted to drive in rotation about the motor axis the lever adapted to slide in the cylindrical housing;
- the cylindrical housing has a depth which is a function of the stroke of the levers, itself a function of the predetermined rotation interval of the blades; the leading edge of each variable-pitch blade is close to the peripheries of the cups, the distance from the blade to the axis of rotation being greater than or equal to half a radius;
- the diffuser upstream is a smooth diffuser, that is to say, not aubé; the inlet air duct of the diffuser located between the impeller and the variable-pitch grille is convergent, which improves the performances;
- the fixed blades of the second grid have a thicker leading edge profile than those of the first grid in order to absorb the variations of incidence; the blades with fixed wedging have a thickness sufficient to be traversed by screws allowing the passage of structural forces;
- the fixed blades have an evolutionary law of skeleton angle between the leading and trailing edges, which makes it possible to control the diffusion in the fixed grid and to optimize its aerodynamic efficiency;
- the fixed blades are wedged in azimuth with respect to the blades of the first movable grid so as to resume the wake on the extrados of the blades of this first gate to limit the pressure drops of the diffuser;
- the pitch angles of the variable blades are between +12 and - 5 ° compared to the nominal setting, which would be that of a fixed diffuser.
- FIG. 3 an overall frontal view of the upstream annular flange of the diffuser equipped with the blade grids according to the invention
- FIGS. 4a to 4c a partial schematic view in the diffuser for three wedges of movable blades, the two extreme shims. around the nominal setting, and
- upstream and downstream refer to the direction of flow of the air flow in a turbine engine.
- the centrifugal compressor 10 of a turbomachine such as a turbine engine, turbojet engine, turboprop engine or an APU, comprises a casing 12 coupled to a covering cover 14.
- radial wheel 16 last centrifugal stage of the compressor, rotatably mounted on the drive shaft 18 along the axis ⁇ .
- the flow of air F flows from the impeller 16 to the annular diffuser 19, in a converging inlet vein by radial shrinkage.
- the diffuser 19 is defined between two upstream and downstream flanges 20 and 22.
- the cover 14 is held by a fastener 23 fixed to the casing and to the upstream flange 20.
- the blades 24, forming a first annular grid are mounted in the diffuser 19.
- the cups are centered in the flanges 20 and 22 with appropriate clearances, from 0.03 to 0.05 mm in the example illustrated, on a washer 9 inserted in the centering 25 (see below with reference to FIG. ).
- Blades 28 secured to the flange 22, forming a second annular grid externally bordering the first gate are mounted on the annular flange 20 by through screws 29 housed in holes 29t. These screws also allow the passage of structural forces.
- the control of the variable blades 24 is performed by means of rods 30 integrally extending the upstream cup 17.
- rods 30 X'X axis are mounted in a cylindrical bore 32 of the upstream flange 20 and centered with a set almost zero by 30j joints mounted in grooves 30g.
- each rod 30 has a flat portion 31 articulated on a drive lever 33 clamped by two screws 35 on this flat portion 31.
- the positions of the ends 31 of the rods 30 are adjusted with appropriate play tolerances.
- the rod 30 also has a hole 30t in which a pin 36 is inserted which makes it possible to lock a washer 30u - for adjusting the axial position of the cups 17 and 27 - in a locking ring 12a formed in the casing 12.
- the pin 36 secures the rod 30 and the locking ring 12a.
- the lever 33 is driven by a control ring 34 forming a cylindrical hole 38 for housing the spherical ball 37 of the lever 33 with an adapted axial position tolerance and a contact on a generatrix of the ball joint.
- the control ring 34 is centered on sectors having needle bearings 39.
- the control ring 34 rotated about the motor axis ⁇ by a rod (not shown), rotates the levers 33 which slide in the cylindrical housing 38 through their ball joint 37.
- the depth of the housing 38 is a function of the stroke of the levers 33, itself a function of the rotation interval of the blades 24.
- This architecture is particularly suitable for rotation blades up to + 12 ° with a 50% section closure, and up to -5 ° with a 20% section opening.
- a movable blade 24 is shown between the parallel cups 17, 27 and secured by welding 21 to them, so that the blade extends parallel to the axis X'X cups opposite.
- the leading edge 24c of the blade 24 is flush with the outer circumferences 17c and 27c of the cups, the thickness of the blade 24 being relatively thin, 2 mm in the illustrated example.
- the distance between the blade 24 and the axis X'X of the rod 30 is equal to about 80% of the radius of the cups in the illustrated example.
- the rod 30 also has the cylindrical centering grooves 30g and the locking hole 30t of the adjusting washer of the axial position of the cups 17 and 27. Its flat portion 31 is traversed by holes 30a for receiving the mounting screws 35. to the control lever.
- FIG. 3 illustrates the upstream annular flange 20 equipped with annular gates G1 and G2, mounted respectively mobile and fixed and composed of blades 24 and 28.
- the blades 28 have a substantially thicker profile in the leading edge Ba than that of the blades 24, respectively 0.5 and 2.5 mm, to preserve a good resistance to variations in incidence during the rotation of the movable blades 24.
- the skeleton angle law of the blades 28 between the leading edges BA and LF leakage is scalable, to optimize the aerodynamic efficiency of the fixed gate by a maximum recovery of static pressure.
- the blades 28 of the fixed gate have a maximum thickness of 7 mm in the example shown, for fixing the flange 20 of the diffuser by screws housed in the holes 29t, while allowing the passage structural efforts.
- the air flow F flows along a fixed blade 28 in radial extension of a movable blade 24 and between two adjacent blades of the same type, mobile or fixed. Thanks to the off-centering of the mobile blades 24 with respect to the axes of rotation X'X of their cups 17, the variations of the radial extensions formed by these movable blades 24 are limited compared to variations of extensions that should be made of centered blades. This limitation makes it possible to improve the performance of a centrifugal compressor: it makes it possible to move the operating line away from the pumping line, by shifting towards lower flow rates, and to raise this operating line close to the yield maxima. higher diets.
- the radial extensions of the movable blades 24 with respect to the fixed blades 28 are illustrated by the diagrams of Figures 4a to 4c, which also appear, in dashed lines, the cups 17, 27 of the blades.
- the nominal setting of 0 ° corresponds to a flow of the reference air flow F for which the adjustment of the mobile blades 24 with respect to the fixed blades 28 is adapted to stable intermediate speeds.
- FIG. 4a illustrates the case of a closure of 25% associated with a setting of 6 °, the neck section then being 75% of the section Sb.
- the calibration setting can also go down to -5 °.
- FIG. 4c illustrates the case of an opening of 2.5 °, the section at the neck being then a relative value of 1 10%.
- the fixed blades 28 are wedged in azimuth with respect to the blades 24 of the first movable gate G1 so as to resume the wake on the extrados Ex of the blades of this first gate G1.
- the radial extensions of the blades 24, limited by the presence of the fixed blades 28, allow to maintain control games between the cups 17 and 27 of the blades 24 and the flanges 20 and 22, as shown in Figure 5.
- the values of the clearances remain less than or equal to 0.02 mm (for J1 or J2), 0.10 mm (for J3) and 0.25 mm (for J4).
- the clearance (set J1 and J2) of the blade 24 on the washer 9 remains about 0.03 mm or slightly higher.
- the invention is not limited to the examples described and shown. It is for example possible to set the pitch of the mobile blades by only mechanical adjustment, individual or centralized, or by electrical, electronic control with or without digital control.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2794825A CA2794825C (en) | 2010-04-14 | 2011-04-13 | Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same |
PL11730371.9T PL2558728T5 (en) | 2010-04-14 | 2011-04-13 | Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same |
CN201180018458.4A CN102834622B (en) | 2010-04-14 | 2011-04-13 | The adjusting method of air-flow and the diffuser of the described method of enforcement in turbogenerator centrifugal compressor |
RU2012148378/06A RU2564158C2 (en) | 2010-04-14 | 2011-04-13 | Method of air flow rate regulation in centrifugal compressor of turbo-machine and diffuser for its implementation |
EP11730371.9A EP2558728B2 (en) | 2010-04-14 | 2011-04-13 | Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same |
KR1020127025210A KR20130079326A (en) | 2010-04-14 | 2011-04-13 | Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same |
JP2013504319A JP2013524099A (en) | 2010-04-14 | 2011-04-13 | Method for adapting the air flow of a turbine engine with a centrifugal compressor and a diffuser for its implementation |
US13/640,978 US20130034425A1 (en) | 2010-04-14 | 2011-04-13 | Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1052827A FR2958967B1 (en) | 2010-04-14 | 2010-04-14 | METHOD FOR ADJUSTING TURBOMACHINE AIR FLOW WITH CENTRIFUGAL COMPRESSOR AND DIFFUSER THEREFOR |
FR1052827 | 2010-04-14 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011128587A1 true WO2011128587A1 (en) | 2011-10-20 |
Family
ID=43067161
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2011/050846 WO2011128587A1 (en) | 2010-04-14 | 2011-04-13 | Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same |
Country Status (10)
Country | Link |
---|---|
US (1) | US20130034425A1 (en) |
EP (1) | EP2558728B2 (en) |
JP (2) | JP2013524099A (en) |
KR (1) | KR20130079326A (en) |
CN (1) | CN102834622B (en) |
CA (1) | CA2794825C (en) |
FR (1) | FR2958967B1 (en) |
PL (1) | PL2558728T5 (en) |
RU (1) | RU2564158C2 (en) |
WO (1) | WO2011128587A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
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WO2014154997A1 (en) * | 2013-03-28 | 2014-10-02 | Turbomeca | Radial or mixed-flow compressor diffuser having vanes |
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US9546669B2 (en) | 2013-01-11 | 2017-01-17 | Hamilton Sundstrand Corporation | Compressor housing for an air cycle machine |
CN103925246B (en) * | 2013-01-11 | 2017-06-09 | 哈米尔顿森德斯特兰德公司 | For the compressor housing of air cycle machine |
JP2014152637A (en) * | 2013-02-05 | 2014-08-25 | Mitsubishi Heavy Ind Ltd | Centrifugal compressor |
GB2513666B (en) * | 2013-05-03 | 2015-07-15 | Dyson Technology Ltd | Compressor |
DE102015220333A1 (en) * | 2015-10-19 | 2017-04-20 | Rolls-Royce Deutschland Ltd & Co Kg | Device for adjusting a gap between the housing of an impeller and the impeller in a centrifugal compressor and a turbomachine |
US10458429B2 (en) | 2016-05-26 | 2019-10-29 | Rolls-Royce Corporation | Impeller shroud with slidable coupling for clearance control in a centrifugal compressor |
US10718222B2 (en) | 2017-03-27 | 2020-07-21 | General Electric Company | Diffuser-deswirler for a gas turbine engine |
BE1025194B1 (en) * | 2017-05-05 | 2018-12-07 | Safran Aero Boosters S.A. | TURBULENCE SENSOR IN A TURBOMACHINE COMPRESSOR |
JP6888688B2 (en) * | 2017-11-01 | 2021-06-16 | 株式会社Ihi | Centrifugal compressor |
EP3620658A1 (en) * | 2018-09-04 | 2020-03-11 | Siemens Aktiengesellschaft | Lid of a turbomachine housing, turbomachine housing with a lid, turbomachine and method for the manufacture of a lid |
US10989219B2 (en) | 2019-02-04 | 2021-04-27 | Honeywell International Inc. | Diffuser assemblies for compression systems |
CN112983846A (en) | 2019-12-02 | 2021-06-18 | 开利公司 | Centrifugal compressor and method for operating a centrifugal compressor |
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-
2010
- 2010-04-14 FR FR1052827A patent/FR2958967B1/en active Active
-
2011
- 2011-04-13 EP EP11730371.9A patent/EP2558728B2/en active Active
- 2011-04-13 US US13/640,978 patent/US20130034425A1/en not_active Abandoned
- 2011-04-13 JP JP2013504319A patent/JP2013524099A/en active Pending
- 2011-04-13 PL PL11730371.9T patent/PL2558728T5/en unknown
- 2011-04-13 WO PCT/FR2011/050846 patent/WO2011128587A1/en active Application Filing
- 2011-04-13 KR KR1020127025210A patent/KR20130079326A/en not_active Application Discontinuation
- 2011-04-13 RU RU2012148378/06A patent/RU2564158C2/en not_active IP Right Cessation
- 2011-04-13 CA CA2794825A patent/CA2794825C/en not_active Expired - Fee Related
- 2011-04-13 CN CN201180018458.4A patent/CN102834622B/en active Active
-
2016
- 2016-11-04 JP JP2016215929A patent/JP6483074B2/en not_active Expired - Fee Related
Patent Citations (7)
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US3029067A (en) * | 1956-05-31 | 1962-04-10 | Garrett Corp | Variable area nozzle means for turbines |
US3588270A (en) * | 1968-08-20 | 1971-06-28 | Escher Wyss Ltd | Diffuser for a centrifugal fluid-flow turbomachine |
US3957392A (en) * | 1974-11-01 | 1976-05-18 | Caterpillar Tractor Co. | Self-aligning vanes for a turbomachine |
FR2485102A1 (en) * | 1980-05-30 | 1981-12-24 | Neyrpic | Distribution control vanes appts. for high head water turbine - uses pair of thin blades in place of single heavy vane for more precise control of water flow and better sealing |
EP0458142A1 (en) * | 1990-05-19 | 1991-11-27 | Mtu Motoren- Und Turbinen-Union MàNchen Gmbh | Device for adjusting the front vanes of a radial diffuser |
US5207559A (en) | 1991-07-25 | 1993-05-04 | Allied-Signal Inc. | Variable geometry diffuser assembly |
EP0589745A1 (en) | 1992-09-25 | 1994-03-30 | TURBOMECA, Société dite: | Inlet control system of a turbomachine |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014154997A1 (en) * | 2013-03-28 | 2014-10-02 | Turbomeca | Radial or mixed-flow compressor diffuser having vanes |
FR3003908A1 (en) * | 2013-03-28 | 2014-10-03 | Turbomeca | DIFFUSER WITH FINES OF A RADIAL OR MIXED COMPRESSOR |
US9890792B2 (en) | 2013-03-28 | 2018-02-13 | Turbomeca | Radial or mixed-flow compressor diffuser having vanes |
Also Published As
Publication number | Publication date |
---|---|
PL2558728T3 (en) | 2019-10-31 |
EP2558728B2 (en) | 2022-10-12 |
EP2558728A1 (en) | 2013-02-20 |
FR2958967A1 (en) | 2011-10-21 |
JP2013524099A (en) | 2013-06-17 |
PL2558728T5 (en) | 2023-02-06 |
FR2958967B1 (en) | 2013-03-15 |
EP2558728B1 (en) | 2019-07-24 |
CN102834622B (en) | 2016-02-10 |
KR20130079326A (en) | 2013-07-10 |
CA2794825C (en) | 2018-06-12 |
CN102834622A (en) | 2012-12-19 |
RU2012148378A (en) | 2014-05-20 |
CA2794825A1 (en) | 2011-10-20 |
JP2017061936A (en) | 2017-03-30 |
JP6483074B2 (en) | 2019-03-13 |
RU2564158C2 (en) | 2015-09-27 |
US20130034425A1 (en) | 2013-02-07 |
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