EP3167195A1 - Return stage of a multi-stage turbocompressor or turboexpander having rough wall surfaces - Google Patents
Return stage of a multi-stage turbocompressor or turboexpander having rough wall surfacesInfo
- Publication number
- EP3167195A1 EP3167195A1 EP15774561.3A EP15774561A EP3167195A1 EP 3167195 A1 EP3167195 A1 EP 3167195A1 EP 15774561 A EP15774561 A EP 15774561A EP 3167195 A1 EP3167195 A1 EP 3167195A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- section
- flow
- rough
- feedback stage
- stage
- 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
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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
-
- 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
- F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/12—Multi-stage pumps
- F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
-
- 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
- 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
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- 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
- F05D2250/60—Structure; Surface texture
- F05D2250/63—Structure; Surface texture coarse
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/516—Surface roughness
Definitions
- Return stage not only the function of deflecting the process fluid from the flow direction radially outward in an axial flow direction and the other impeller, but also at least partially retard the flow of the process fluid and thus increase the pressure according to Bernulli.
- the return step is hereby simultaneously formed regularly as a diffuser in a radially outward dishes ⁇ th flow path and as a constrictor in a radially inward flow path at the inlet of the process fluid to the other impeller.
- Return step is unmoved relative to the impellers and re ⁇ regularly change in the feedback stage provided Leit ⁇ shovel the swirl and thus the flow direction of the process zessfluids in preparation for the subsequent entry into the subsequent compaction.
- This sophisticated aerodyna ⁇ mix objective of the return step requires careful fluid dynamic design to minimize pressure losses and efficiency optimization. Nevertheless, due to the flow of radial diffusers and confusers of the recirculation stage at the surfaces wetted by the flow, friction-induced and basically unavoidable pressure losses occur which reduce the efficiency of the turbomachine.
- the local frictional pressure losses are dependent on the local flow velocity and the Loka ⁇ len roughness or roughness of the surface Strömungsbenetzen.
- large pressure losses occur where the lo- flow velocities and at the same time the local roughness of the overflowed surfaces are large.
- the invention has made it starting from the prior art described, the object of the surface of the flow-guiding areas of the return step so as to ge ⁇ Stalten that compared to the known solutions, a reduced or optionally consistent manufacturing expense while improving efficiency of the Turboverdich ⁇ ters.
- return step is an annularly extending around the rotation axis component.
- This component can be divided in the circumferential direction or formed undivided.
- a divided in the circumferential direction training is provided so that a parting line of the return stage or the return stages is formed, which ensures a separation of the rotor without disassembly of the rotor in a divided feedback stage made possible.
- the return stage is generally formed axially divided, wherein a blade bottom separates the radially outwardly guided branch of the flow channel of a radially inwardly guided branch downstream of the 180 ° deflection of the flow and the ⁇ this blade bottom is attached to an intermediate floor of the return stage, wherein the intermediate floor on the one hand the flow-guide used in the feedback stage and the other part of the attachment of the return step to the other components of the turbo compressor, for example, to an inner housing or on an internally bundle of the turbocompressor together ⁇ comprehensive support.
- a first portion extends radially and has a ra ⁇ Diale opening to an upstream impeller at a first end of the first section on.
- a fourth portion adjacent radially radially with a first end of the fourth section at a second end of the - upstream in Fal ⁇ le of the turbocompressor - third portion at.
- the fourth section directs the flow to ⁇ et wa 90 ° in axial direction and with a second end of the fourth section it has an axial opening to the two ⁇ th downstream impeller on.
- the rough areas are preferably provided at different positions, which are specified in detail below.
- a first rough region in the first section is disposed on the axial boundary surface which is axially further from the third section than the other axial boundary surface.
- a third rough region is directly adjacent to the second rough region in the third section and extending between 5% to 40% along the flow channel .
- a fourth rough region is located in the fourth section on the radially outer boundary surface.
- a preferred embodiment of the invention provides that the rough areas each extend over the entire circumference of the flow channel.
- the radial turbo fluid energy machine is a turbo compressor flows through a process fluid sections in the Rei ⁇ hen graphic fourth section, the third section, the second from ⁇ section, the first section.
- the first portion of the flow channel may include vanes to direct the flow to the downstream conditions.
- the rough regions have an average roughness 20ym ⁇ Rz, particularly preferably 30ym ⁇ Rz.
- the non-rough areas a medium rough ⁇ ness 20ym> Rz, more preferably to 10ym> ref.
- the local surface roughness is to be adapted to the local Strömungsge ⁇ speed vice versa according to the invention.
- the region-specific surface roughness according to the invention provides that the loading ⁇ rich high flow velocities, the strömungsbenetze surface with a smaller roughness is executed as in the Be ⁇ rich smaller flow rates.
- a preferred application of the invention provides that the return stage has a bladed radial diffuser or, in the case of the radial turbine, a bladed radial confuser.
- the return stage has a blade-less radial diffuser or, in the case of the radial turbine, a blade-less radial confuser.
- the speed level in the radial diffuser ⁇ relationship, in the radial constrictor is the annular space inside diameter - that the impeller outer diameter - the highest and decreases with increasing radius - so outwardly - from.
- the wetted surfaces to be machined surface of the annular space walls with the radius becomes larger.
- Figure 1 is a schematic representation of a longitudinal section through a turbocompressor according to the invention.
- FIG. 1 shows a schematic longitudinal section through a return stage RS from a first impeller IMP1 to a second impeller IMP2 of a turbocompressor TCO.
- the two impellers IMP1, IMP2 are components of a Ro ⁇ R tors, wherein the impeller IMP1, are non-positively mounted on egg ⁇ ner extending along an axis X shaft SH IMP2.
- the rotor R is surrounded by flow-carrying stationary components, of which a feedback stage RS is shown here.
- a multi-stage turbomachine includes in the
- the return stage comprises a blade bottom SB and an intermediate bottom ZB, which are firmly connected to one another by means of guide vanes V forming a flow channel between them.
- the return stages RS are designed to be divided in the circumferential direction, so that a division of the return stage in a parting line makes it possible to remove the rotor from the structure of the return stages.
- the rotor is radially inserted during assembly or removed radially during disassembly.
- the return stages RS have to the rotor R at different points shaft seals SHS, which should prevent the unused degradation of pressure differences or Beipassströmungen in operation.
- the first section S1 extends essentially radially and has a radial opening to the first impeller IMP1 at a first end S1E1 of the first section S1.
- the second section S2 adjoins a first end S2E1 of the second section S2 at a second end S1E2 of the first section Sl and directs the flow through the channel CH by about 180 ° from one radial direction to the opposite
- the flow is deflected from radially outward in a direction radially inward.
- the third section S3 closes S3 adjacent to the second end of the second section S2 S2E2 with a first En ⁇ de S3E1 of the third section.
- This section ver ⁇ runs substantially radially and leads in case of Turbover- dichters TCO the flow from radially outside to radially inside.
- the fourth portion radially adjoins a first end S4E1 of the fourth portion S4 radially at a second end S3E2 of the third portion S3 and diverts the flow by about 90 ° in the direction of the second impeller IMP2.
- a second end S4E2 of the fourth section S4 adjoins the second impeller IMP2.
- a first rough region RZ1 is located in the first section S1 on that axial boundary surface which is axially further away from the third section S3 than the other axial boundary surface.
- a second rough area RZ2 is located on the radially inner boundary surface of the second section S2 be ⁇ ginnend at the second end of the second section S2 S2E2.
- This second rough region RZ2 extends between 30% -70% of the extent along the flow channel of the second section S2.
- a third rough area RZ3 is adjacent to the second rough area RZ2 to S3 in the third section and extends between 5% -40% CH S3 along the flow channel in drit ⁇ th section.
- a fourth rough region RZ4 extends in the fourth section S4 on the radially outer boundary surface.
- the harsh preparation ⁇ che RZ1-RZ 3 are extra roughened designed by the boundary surfaces of the flow channel SFA CH or the other Regions of the boundary surface SFA against the rough areas RZ1-RZ4 are provided with a lower surface roughness, for example by means of polishing.
- both a roughening of the rough areas RZ1-RZ4 and a polishing of the other boundary surfaces SFA is provided in order to achieve the erfindungsze the effect.
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102014219821.6A DE102014219821A1 (en) | 2014-09-30 | 2014-09-30 | Return step |
PCT/EP2015/072208 WO2016050669A1 (en) | 2014-09-30 | 2015-09-28 | Return stage of a multi-stage turbocompressor or turboexpander having rough wall surfaces |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3167195A1 true EP3167195A1 (en) | 2017-05-17 |
EP3167195B1 EP3167195B1 (en) | 2018-07-11 |
Family
ID=54249461
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15774561.3A Not-in-force EP3167195B1 (en) | 2014-09-30 | 2015-09-28 | Return channel of a multistage turbocompressor or turboexpander with rough wall surfaces |
Country Status (6)
Country | Link |
---|---|
US (1) | US20170292536A1 (en) |
EP (1) | EP3167195B1 (en) |
CN (1) | CN107076159A (en) |
DE (1) | DE102014219821A1 (en) |
RU (1) | RU2661916C1 (en) |
WO (1) | WO2016050669A1 (en) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102015219556A1 (en) | 2015-10-08 | 2017-04-13 | Rolls-Royce Deutschland Ltd & Co Kg | Diffuser for radial compressor, centrifugal compressor and turbo machine with centrifugal compressor |
DE102016208265A1 (en) | 2016-05-13 | 2017-11-16 | Siemens Aktiengesellschaft | Return stage, radial turbocompressor |
GB2558917B (en) * | 2017-01-19 | 2021-02-10 | Gkn Aerospace Sweden Ab | Transition duct of a multi-stage compressor with areas of different surface roughness |
JP6935312B2 (en) | 2017-11-29 | 2021-09-15 | 三菱重工コンプレッサ株式会社 | Multi-stage centrifugal compressor |
DE102018100336A1 (en) | 2018-01-09 | 2019-07-11 | Man Truck & Bus Ag | Piston for an internal combustion engine |
US11098730B2 (en) | 2019-04-12 | 2021-08-24 | Rolls-Royce Corporation | Deswirler assembly for a centrifugal compressor |
JP2021032106A (en) * | 2019-08-22 | 2021-03-01 | 三菱重工業株式会社 | Vaned diffuser and centrifugal compressor |
CN110750845B (en) * | 2019-11-13 | 2024-04-05 | 中国科学院工程热物理研究所 | Method for improving sealing efficiency of disc cavity based on end wall rough area |
CN112412884A (en) * | 2020-05-09 | 2021-02-26 | 北京理工大学 | Roughness stability expanding method, stability expanding structure and roughness stability expanding centrifugal compressor |
US11286952B2 (en) | 2020-07-14 | 2022-03-29 | Rolls-Royce Corporation | Diffusion system configured for use with centrifugal compressor |
US11441516B2 (en) | 2020-07-14 | 2022-09-13 | Rolls-Royce North American Technologies Inc. | Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features |
DE102020118650A1 (en) | 2020-07-15 | 2022-01-20 | Ventilatorenfabrik Oelde, Gesellschaft mit beschränkter Haftung | centrifugal fan |
US11578654B2 (en) | 2020-07-29 | 2023-02-14 | Rolls-Royce North American Technologies Inc. | Centrifical compressor assembly for a gas turbine engine |
CN111997937B (en) * | 2020-09-21 | 2021-11-30 | 江西省子轩科技有限公司 | Compressor with interstage stator |
CN113107872B (en) * | 2021-05-11 | 2023-02-03 | 内蒙古兴洋科技股份有限公司 | Centrifugal compressor for electronic high-purity gas |
FR3127517A1 (en) * | 2021-09-27 | 2023-03-31 | Safran | Secondary stream cavity surface between a fixed wheel and a moving wheel of an improved turbomachine |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2419669A (en) * | 1942-05-08 | 1947-04-29 | Fed Reserve Bank | Diffuser for centrifugal compressors |
CA1252075A (en) * | 1983-09-22 | 1989-04-04 | Dresser Industries, Inc. | Diffuser construction for a centrifugal compressor |
DE4319628A1 (en) * | 1993-06-15 | 1994-12-22 | Klein Schanzlin & Becker Ag | Structured surfaces of fluid machine components |
US6092766A (en) * | 1995-12-12 | 2000-07-25 | Ulrich Laroche | Process for forming a surface for contact with a flowing fluid and body with such surface regions |
RU2275533C2 (en) * | 2001-06-29 | 2006-04-27 | ОАО Самарский научно-технический комплекс им. Н.Д. Кузнецова | Multistage centrifugal compressor |
ITMI20022753A1 (en) * | 2002-12-23 | 2004-06-24 | Nuovo Pignone Spa | HIGH PRESSURE CENTRIFUGAL COMPRESSOR WITH IMPROVED EFFICIENCY |
RU2265141C1 (en) * | 2004-04-12 | 2005-11-27 | Кожевин Виталий Валерьевич | Multistage compressor |
EP1878879A1 (en) * | 2006-07-14 | 2008-01-16 | Abb Research Ltd. | Turbocharger with catalytic coating |
DE102007005384A1 (en) * | 2007-02-02 | 2008-08-07 | Rolls-Royce Deutschland Ltd & Co Kg | Turbomachine and rotor blade of a turbomachine |
DE102009019061A1 (en) * | 2009-04-27 | 2010-10-28 | Man Diesel & Turbo Se | Multistage centrifugal compressor |
JP5316365B2 (en) * | 2009-10-22 | 2013-10-16 | 株式会社日立プラントテクノロジー | Turbo fluid machine |
JP2011132877A (en) * | 2009-12-24 | 2011-07-07 | Mitsubishi Heavy Ind Ltd | Multistage radial turbine |
CN103244461B (en) * | 2012-02-14 | 2016-03-30 | 珠海格力电器股份有限公司 | Low denseness vane diffuser and manufacture method thereof |
EP2749771B1 (en) * | 2012-12-27 | 2020-04-22 | Thermodyn | Device for generating a dynamic axial thrust to balance the overall axial thrust of a radial rotating machine |
WO2014115417A1 (en) * | 2013-01-28 | 2014-07-31 | 三菱重工業株式会社 | Centrifugal rotation machine |
-
2014
- 2014-09-30 DE DE102014219821.6A patent/DE102014219821A1/en not_active Withdrawn
-
2015
- 2015-09-28 EP EP15774561.3A patent/EP3167195B1/en not_active Not-in-force
- 2015-09-28 WO PCT/EP2015/072208 patent/WO2016050669A1/en active Application Filing
- 2015-09-28 CN CN201580052792.XA patent/CN107076159A/en active Pending
- 2015-09-28 RU RU2017114608A patent/RU2661916C1/en not_active IP Right Cessation
- 2015-09-28 US US15/512,766 patent/US20170292536A1/en not_active Abandoned
Also Published As
Publication number | Publication date |
---|---|
WO2016050669A1 (en) | 2016-04-07 |
EP3167195B1 (en) | 2018-07-11 |
CN107076159A (en) | 2017-08-18 |
DE102014219821A1 (en) | 2016-03-31 |
RU2661916C1 (en) | 2018-07-23 |
US20170292536A1 (en) | 2017-10-12 |
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