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EP0690206B1 - Diffusor für Turbomaschine - Google Patents

Diffusor für Turbomaschine Download PDF

Info

Publication number
EP0690206B1
EP0690206B1 EP95810378A EP95810378A EP0690206B1 EP 0690206 B1 EP0690206 B1 EP 0690206B1 EP 95810378 A EP95810378 A EP 95810378A EP 95810378 A EP95810378 A EP 95810378A EP 0690206 B1 EP0690206 B1 EP 0690206B1
Authority
EP
European Patent Office
Prior art keywords
flow
diffusor
ribs
diffuser
channel
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.)
Expired - Lifetime
Application number
EP95810378A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0690206A3 (de
EP0690206A2 (de
Inventor
Franz Kreitmeier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Switzerland GmbH
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0690206A2 publication Critical patent/EP0690206A2/de
Publication of EP0690206A3 publication Critical patent/EP0690206A3/de
Application granted granted Critical
Publication of EP0690206B1 publication Critical patent/EP0690206B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the invention relates to a diffuser for an axially flow Turbo machine according to the preamble of patent claim 1.
  • Such diffusers for turbomachinery are known from GB-A-2 131 100.
  • this diffuser which is divided in two by means of a guide plate, adjoins an axial, non-ribbed part a double-curved part, the exit of which is roughly radial can be designated.
  • the diffuser points in the immediate vicinity of its outlet in both subchannels aerodynamically formed ribs, their generatrix run parallel to the machine axis. The ribs are flowed through radially.
  • This distance is such that the front edge the ribs is in a plane where there is a diffuser area ratio of preferably three prevails.
  • This first diffusion zone between the blading and the flow ribs are said to be due to total rotational symmetry remain undisturbed.
  • a second diffusion zone extends from the leading edge the thick flow ribs up to the greatest profile thickness the ribs.
  • the swirl should be in this second zone the flow can be made for the most part largely without delay.
  • a third subsequent one Diffusion zone takes the form of a straight diffuser a further delay of the almost swirl-free at the time Flow.
  • the diffuser is flowed at at idle under a speed ratio c t / c n of approximately 1.2, where c t means the tangential speed and c n the axial speed of the medium. This oblique flow leads to a drop in the pressure recovery C p .
  • the large drop in pressure recovery is due to that in the extreme conditions mentioned strong vortex between outlet blades and flow fins trains.
  • the vortex is created by the flow ribs limited to which the tangential component of the Speed is dissipated. Will be at the emerging Backflow of solid particles, e.g. water droplets in Steam turbines carried, so there can be an acute danger of Foot erosion occurs on the blades of the last row of runs.
  • the task of the invention is based on calculation methods a diffuser of the type mentioned at a given Diffuser area ratio, including the ratio of Flow cross sections at the outlet to the inlet of the diffuser is understood, with swirl-free outflow, the physical to achieve the greatest possible pressure recovery.
  • Axial-radial diffusers are already known from EP-A 581 978 known, where the kink angle idea is realized is.
  • these are multi-zone diffusers of gas turbines, as shown in FIG. 4 there are.
  • a first single-channel diffusion zone points here Bell shape.
  • a second diffusion zone which by means of 2 guide rings divided into three partial diffusers, opens into a third diffusion zone, which is only lower Delay strongly deflected. This strong redirection is caused by the arrangement of those continuing into the diffusion zone Guide rings strongly favored. This measure causes Favorable increase of the middle one related to the channel height Radius of curvature of the third diffusion zone.
  • the present invention starting from a plant, at which is a very divergent at the exit of a blading Current is present, with counter-swirl on the hub, co-rotation on the cylinder and much higher flow energy in the radially outer zone has the advantage for the first time the kink angle idea, the goal of which is the lowest possible total pressure inhomogeneity is above the bucket height at one two-channel diffuser with axial / radial deflection with Apply success.
  • a curved continuous baffle to support the diffuser flow during meridional redirection and one flow-oriented guide line in both subchannels in
  • the shape of profiled ribs is a low-loss transformation the swirling flow energy in pressure energy reached.
  • the flow ribs also take over the mechanical Support of the guide plate, thereby reducing the loss previous efforts can be dispensed with.
  • baffle with the inner and outer flow ribs and the associated inner and outer diffuser rings as self-supporting half-shells with horizontal Partition plane are formed, so it facilitates achieved mechanical integrity of the baffle a simple Assembly / disassembly of the diffuser and access to the Blading.
  • the ratio of rib distance a from the outlet the blading to rib division t is at least 0.5. This measure also results in full utilization the working ability of the fluid.
  • the ratio of rib chord s to rib pitch t is at least 1, it ensures that the sensitive Diffuser flow free of detachment in the swirl-free flow direction is redirected and that a contribution to the desired Delay is made.
  • the curvature of the Velcro line of the ribs is advantageous with regard to bumpless entry and axial Outflow selected. This guarantees the desired high Pressure recovery as well as a certain insensitivity Partial load.
  • the main components are the outer casing 1, the inner casing 2 and the rotor 3.
  • the outer housing consists of several, unspecified parts, as a rule only screwed or welded together at the place of installation become.
  • the inner housing consists of the inflow housing 4 in the form of a torus and the downstream guide vane supports 5, which is equipped with the guide vanes 6 are.
  • Outer housing, inner housing and blade carriers are horizontally divided and on separating flanges 41 (Fig. 3) with each other screwed. That is in the plane of these separating flanges Inner housing supported by support arms in the outer housing.
  • the rotor 3 equipped with the blades 7 is out Shaft washers and shaft ends with integrated coupling flanges welded together. It is not shown by means of Bearings supported in bearing housings.
  • the path of the steam leads from a steam pipe over the Steam feed-through in the outer casing 1 into the inner casing 2.
  • the torus ensures that the steam is guided to the well both floods of blading reached.
  • the steam passes energy to the rotor 3 via an annular ring Diffuser 11 in the evaporation chamber 30 of the outer housing 1 before going down (in the drawing) to the capacitor flows out.
  • Axial flow through shaft seals 13 on the Carrier bushings in the outer housing prevent entry of air in the exhaust steam.
  • the kink angle idea is not realized here.
  • the opening angle of the blading is greatly reduced.
  • For only local support of the deflection is two axially staggered baffles recognizable, those with the above disadvantageous struts on the diffuser inner walls and - Outside walls must be attached.
  • the flow-limiting outer walls of the diffuser are formed by the diffuser outer ring 25 and the diffuser inner ring 24.
  • the former is with the blade carrier 3 (like indicated) screwed.
  • the latter is made up of several parts.
  • the closest to the blading is at least approximate Ring part 24A extending in the axial direction. That is followed by a deflecting ring part 24B, which in one passes even more diverting ring portion 24C.
  • the parts 24A and 24B are welded together. Between Axial play is provided for parts 24B and 24C.
  • the housing of the shaft seal 13 is attached. Downstream is the ring portion 24C via a flange with the rear, essentially vertical Baffle 31 connected. The baffle is in turn vapor tight connected to the outer housing 1.
  • the diffuser is turned by means of a deflecting baffle 60 divided into two sub-channels, an inner channel 50 and one Outer duct 51.
  • This baffle is for manufacturing reasons also made in three parts; a first part 60A, a strongly deflecting middle part 60B and a vertically running one Part 60C. The three parts are a whole welded together.
  • the area ratios of the two subchannels 50, 51 are taking into account the total pressure profile respectively the flow energies behind the last blade 7A fixed.
  • a larger area ratio is chosen if, for example, large kinetic energies are implemented must become what can be the case in the outer channel; accordingly, a smaller area is chosen for the inner channel if smaller energies are to be implemented there.
  • the outer channel is 50 and the inner channel 51 the same areas are provided, namely from the diffuser inlet up to the diffuser outlet. So that are the different Angle of attack for the guide plate part 60B and the diffuser inner ring 24B, 24C.
  • the baffle part 60A is like this employed that the flow flows smoothly. Of course can deviate from the solutions shown Diffuser inner ring 24 and the baffle 60 also with steady Curvature.
  • the diffuser is therefore solely based on fluid technology Aspects. The considerations must lead to a homogeneous total pressure profile over the entire canal height. The two kink angles will be therefore determined based on the total flow in the Blading and in the diffuser.
  • the implementation takes place the kink angle aN on the hub by a suitable Collar 80 arranged on the runner 3 extends over the axial length of the first flow Diffuser inner ring 24A.
  • a suitable Collar 80 arranged on the runner 3 extends over the axial length of the first flow Diffuser inner ring 24A.
  • the underside of the collar and the front edge of the Diffuser inner ring 24A configured accordingly.
  • Fig. 2 shows that the inner flow ribs 71 with the Diffuser inner ring 24B and with the front baffle part 60A are connected, for example by welding. Shown is also how the radially flowed flow ribs 71 in Outer channel 51 are attached. A suspension variant is shown, those for absorbing both tensile forces as well of compressive forces is suitable.
  • On both sides of the Flow ribs are here the same base plates 14 provided, which in the known hammerhead type or dovetail type in corresponding turns of the Diffuser outer ring 25 and the vertically extending part 60C of the guide plate.
  • the system forms guide plate 60 A, B, C with the inner and outer flow ribs 71, 70 and the associated inner (24A, B) and outer (25) diffuser rings one self-supporting unit.
  • these are units designed as half-shells with a horizontal parting plane. These half-shells are screwed together in the Parting plane over inner flanges 26 (Fig. 3). The parting plane 26 lies at the level of the machine axis.
  • the lower half-shell can (not shown) on the housing of the shaft seal 13 be attached.
  • This training facilitates access to the blading.
  • Removing an end blade 7A is as follows first of all, the exhaust hood (part of the Outer housing 1) together with the upper housing Shaft seal 13 lifted off. After that, after loosening the Flange screws of the diffuser inner ring and the screw connection the upper half shell of the diffuser outer ring self-supporting unit as a whole.
  • the number of radially flowed outer flow ribs in the present case, 70 is fifty (50) pieces. This 3 even number has the advantage that in the horizontal parting plane are not ribs.
  • the large number on flow ribs 70 is also advantageous, among other things, because this results in a low radial height or little influence on the installation space for diffuser and exhaust steam is achieved.
  • the number of inner flow ribs 71 is in the present Case eighteen (18) pieces. 3 shows, are also at this even number in the horizontal parting plane no ribs present. This number as well as the fluidic Formation of the ribs 70, 71 are now the following Considerations:
  • the distance a of the leading edge 72 becomes the inner one Flow ribs 71 in relation to the exit of the blading for rib division t - which measure for the number of ribs is set.
  • This ratio is at least 0.5, so interference with the last run 7A blading can be largely avoided.
  • the flow ribs have a supporting function, so a minimum cross-section should not be undercut.
  • a minimum chord length should also not be undercut. If the ratio of the rib chord s to the rib pitch t is at least 1 and the ratio of the maximum profile thickness d max of the flow ribs to the chord s to be described later is approximately 0.15, both tasks can be performed.
  • the arrangement of the flow ribs is now subject to following criteria: To gain access to blading enable is the diffusion zone with a horizontal Provide parting plane, i.e. the diffuser inner ring, the Diffuser outer ring and the baffle are split.
  • the ratio of the greatest profile thickness d max of the flow ribs to the rib chord s should not exceed 0.15 and is kept largely constant over the rib height.
  • the flow ribs are curved.
  • the curvature of the Velcro line of the ribs is there in terms of bumpless entry and axial Outflow selected, which is usually a variable Curvature leads above the height of the ribs.
  • the diagonally flowed through inner ribs 71 can be a basic one Have taper. That is the thought of one the ratio of the tendon to the redirection task Division (s / t). This configuration is the starting point which is then cut in sections above the height of the ribs is adapted to the actual flow.
  • the leading edges 72 of the ribs are so above the rib height oriented that they cut perpendicularly from the streamlines become. This leads to leading edges, which by no means must be aligned radially or axially.
  • the new diffuser insert is a has great efficiency potential; they are pressure recovery coefficients up to 60% possible.
  • the articulation angle idea together with the flow-oriented ribs for low loss Conversion of the swirl energy into pressure energy and the swirl-free flow of the two rows of fins sets Minimum of residual energy safe.
  • the inner Channel 50 only partially for the actual diffusion process is needed.
  • the downstream part in the area of the baffle 31 increases the free cross section in the parting plane and thus serves to reduce the harmful rotational asymmetry.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP95810378A 1994-06-29 1995-06-08 Diffusor für Turbomaschine Expired - Lifetime EP0690206B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4422700A DE4422700A1 (de) 1994-06-29 1994-06-29 Diffusor für Turbomaschine
DE4422700 1994-06-29

Publications (3)

Publication Number Publication Date
EP0690206A2 EP0690206A2 (de) 1996-01-03
EP0690206A3 EP0690206A3 (de) 1997-08-13
EP0690206B1 true EP0690206B1 (de) 2000-03-01

Family

ID=6521771

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810378A Expired - Lifetime EP0690206B1 (de) 1994-06-29 1995-06-08 Diffusor für Turbomaschine

Country Status (5)

Country Link
US (2) US5588799A (zh)
EP (1) EP0690206B1 (zh)
JP (1) JPH0842306A (zh)
CN (1) CN1116271A (zh)
DE (2) DE4422700A1 (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10255389A1 (de) * 2002-11-28 2004-06-09 Alstom Technology Ltd Niederdruckdampfturbine mit Mehrkanal-Diffusor

Families Citing this family (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4422700A1 (de) * 1994-06-29 1996-01-04 Abb Management Ag Diffusor für Turbomaschine
SE509521C2 (sv) * 1997-06-05 1999-02-08 Abb Stal Ab Utloppsanordning för en strömningsmaskin
DE10037684A1 (de) 2000-07-31 2002-02-14 Alstom Power Nv Niederdruckdampfturbine mit Mehrkanal-Diffusor
US7021561B2 (en) * 2001-12-18 2006-04-04 Becton, Dickinson And Company Spray device and method
US7207403B2 (en) * 2003-10-08 2007-04-24 Pride Mobility Products Corporation Transportable power wheelchair
JP4541813B2 (ja) * 2004-09-17 2010-09-08 株式会社日立製作所 蒸気タービン低圧排気室
JP4619849B2 (ja) * 2005-03-31 2011-01-26 株式会社日立製作所 タービン排気装置
GB2445952B (en) 2007-01-25 2011-07-20 Siemens Ag A gas turbine engine
US8109720B2 (en) * 2009-03-31 2012-02-07 General Electric Company Exhaust plenum for a turbine engine
US8161749B2 (en) * 2009-04-07 2012-04-24 General Electric Company Cooled exhaust hood plates for reduced exhaust loss
EP2295732A1 (en) * 2009-09-14 2011-03-16 Alstom Technology Ltd Axial turbine and method for discharging a flow from an axial turbine
US8439633B2 (en) * 2010-01-04 2013-05-14 General Electric Company Hollow steam guide diffuser having increased pressure recovery
JP5422470B2 (ja) * 2010-04-05 2014-02-19 株式会社東芝 軸流タービン
US8475125B2 (en) 2010-04-13 2013-07-02 General Electric Company Shroud vortex remover
US20120034064A1 (en) * 2010-08-06 2012-02-09 General Electric Company Contoured axial-radial exhaust diffuser
US8628297B2 (en) 2010-08-20 2014-01-14 General Electric Company Tip flowpath contour
US8591184B2 (en) * 2010-08-20 2013-11-26 General Electric Company Hub flowpath contour
US8708639B2 (en) * 2010-10-11 2014-04-29 The Coca-Cola Company Turbine bucket shroud tail
US20120186261A1 (en) * 2011-01-20 2012-07-26 General Electric Company System and method for a gas turbine exhaust diffuser
RU111580U1 (ru) * 2011-02-11 2011-12-20 Альстом Текнолоджи Лтд Выпускное устройство для модуля паровой турбины
JP5951187B2 (ja) 2011-03-29 2016-07-13 三菱重工業株式会社 タービン排気構造及びガスタービン
KR101408140B1 (ko) * 2011-12-30 2014-06-17 두산중공업 주식회사 가스터빈 압축기의 반경방향 디스윌러 베인의 고정구조
JP6012222B2 (ja) * 2012-03-30 2016-10-25 三菱重工業株式会社 静翼セグメント、これを備える軸流流体機械及びその静翼連結方法
EP2690253A1 (de) * 2012-07-27 2014-01-29 Siemens Aktiengesellschaft Niederdruck-Turbine
US20140037439A1 (en) * 2012-08-02 2014-02-06 General Electric Company Turbomachine exhaust diffuser
JP5996657B2 (ja) * 2012-08-29 2016-09-21 川崎重工業株式会社 ガスタービン装置
JP6033154B2 (ja) 2013-03-29 2016-11-30 三菱重工業株式会社 軸流回転機械、及びディフューザ
CN105065068B (zh) * 2015-08-13 2016-07-20 德阳东汽电站机械制造有限公司 一种用于汽轮机排汽缸的导流环
DE102015218493A1 (de) * 2015-09-25 2017-03-30 Siemens Aktiengesellschaft Niederdrucksystem und Dampfturbine
US10287920B2 (en) 2015-11-24 2019-05-14 General Electric Company System of supporting turbine diffuser
US10036267B2 (en) 2015-11-24 2018-07-31 General Electric Company System of supporting turbine diffuser outlet
US10041365B2 (en) * 2015-11-24 2018-08-07 General Electric Company System of supporting turbine diffuser
US10041377B2 (en) * 2015-11-24 2018-08-07 General Electric Company System and method for turbine diffuser
US10036283B2 (en) 2015-11-24 2018-07-31 General Electric Company System and method for diffuser AFT plate assembly
DE102017108368B4 (de) * 2016-05-11 2025-02-13 General Electric Technology Gmbh System und Verfahren für eine Diffusorrückplattenanordnung
JP6731359B2 (ja) * 2017-02-14 2020-07-29 三菱日立パワーシステムズ株式会社 排気ケーシング、及びこれを備える蒸気タービン
JP6745233B2 (ja) * 2017-02-28 2020-08-26 三菱重工業株式会社 タービン及びガスタービン
CN107605540B (zh) * 2017-09-18 2020-01-31 东方电气集团东方汽轮机有限公司 双分流透平进汽导流结构
JP7254472B2 (ja) * 2018-09-28 2023-04-10 三菱重工業株式会社 蒸気タービンの排気室、蒸気タービン及び蒸気タービンの換装方法
CN113123838B (zh) * 2019-12-30 2023-05-30 上海汽轮机厂有限公司 一种排汽缸及其应用的汽轮机
JP7368260B2 (ja) 2020-01-31 2023-10-24 三菱重工業株式会社 タービン
CN111520195B (zh) * 2020-04-03 2022-05-10 东方电气集团东方汽轮机有限公司 一种汽轮机低压进汽室导流结构及其参数设计方法
US11808174B2 (en) * 2020-04-23 2023-11-07 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbine and turbocharger including the turbine

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1302282A (en) * 1916-06-23 1919-04-29 British Westinghouse Electric Steam-turbine.
DE834474C (de) * 1950-07-01 1952-04-15 Maschf Augsburg Nuernberg Ag Axial beaufschlagte Kreiselrad-Stroemungsmaschine, insbesondere Gas- oder Luftturbine mit Austrittsdiffusor
GB1050879A (zh) * 1965-01-28
US3400911A (en) * 1967-12-04 1968-09-10 Hitachi Ltd Structure of exhaust chamber in gas turbines
CH484358A (de) * 1968-02-15 1970-01-15 Escher Wyss Ag Abströmgehäuse einer axialen Turbomaschine
US3802187A (en) * 1972-06-01 1974-04-09 Avco Corp Exhaust system for rear drive engine
US4013378A (en) * 1976-03-26 1977-03-22 General Electric Company Axial flow turbine exhaust hood
JPS5520607U (zh) * 1978-07-26 1980-02-08
SU857516A1 (ru) * 1978-11-27 1981-08-23 Харьковский Ордена Ленина Политехнический Институт Им. В.И.Ленина Выхлопной патрубок осевой турбины
US5203674A (en) * 1982-11-23 1993-04-20 Nuovo Pignone S.P.A. Compact diffuser, particularly suitable for high-power gas turbines
IT1153351B (it) * 1982-11-23 1987-01-14 Nuovo Pignone Spa Diffusore compatto perfezionato, particolarmente adatto per turbine a gas di grande potenza
CH672004A5 (zh) * 1986-09-26 1989-10-13 Bbc Brown Boveri & Cie
FR2612250B1 (fr) * 1986-12-18 1991-04-05 Vibrachoc Sa Dispositif d'echappement d'une turbine a gaz, comportant un diffuseur de jets
JPS6478706A (en) * 1987-09-17 1989-03-24 Honda Motor Co Ltd Turret head replacing device
JPH01178706A (ja) * 1988-01-06 1989-07-14 Hitachi Ltd 軸流タービン用排気室
DE59204947D1 (de) * 1992-08-03 1996-02-15 Asea Brown Boveri Mehrzoniger Diffusor für Turbomaschine
US5362203A (en) * 1993-11-01 1994-11-08 Lamson Corporation Multiple stage centrifugal compressor
DE4422700A1 (de) * 1994-06-29 1996-01-04 Abb Management Ag Diffusor für Turbomaschine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10255389A1 (de) * 2002-11-28 2004-06-09 Alstom Technology Ltd Niederdruckdampfturbine mit Mehrkanal-Diffusor

Also Published As

Publication number Publication date
US5588799A (en) 1996-12-31
US5707208A (en) 1998-01-13
EP0690206A3 (de) 1997-08-13
DE4422700A1 (de) 1996-01-04
DE59507868D1 (de) 2000-04-06
CN1116271A (zh) 1996-02-07
JPH0842306A (ja) 1996-02-13
EP0690206A2 (de) 1996-01-03

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