EP2994614A1 - Rotor pour turbomachine thermique - Google Patents

Rotor pour turbomachine thermique

Info

Publication number
EP2994614A1
EP2994614A1 EP14731226.8A EP14731226A EP2994614A1 EP 2994614 A1 EP2994614 A1 EP 2994614A1 EP 14731226 A EP14731226 A EP 14731226A EP 2994614 A1 EP2994614 A1 EP 2994614A1
Authority
EP
European Patent Office
Prior art keywords
rotor
impeller
ribs
disk
sleeve
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.)
Withdrawn
Application number
EP14731226.8A
Other languages
German (de)
English (en)
Inventor
Karsten Kolk
Peter Schröder
Dirk Springborn
Vyacheslav Veitsman
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP14731226.8A priority Critical patent/EP2994614A1/fr
Publication of EP2994614A1 publication Critical patent/EP2994614A1/fr
Withdrawn legal-status Critical Current

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
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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
    • F04D17/02—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/266—Rotors specially for elastic fluids mounting compressor rotors on shafts
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5846—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling by injection
    • 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
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • F05D2240/61—Hollow
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a rotor for a thermal turbomachine, which is designed to guide a medium in the interior.
  • Rotors for thermal turbomachines such as axial compressor and gas turbine are known from the extensive existing state of the art in different designs.
  • welded rotors are known in which different width drums are welded together to form a monolithic rotor.
  • the object of the present invention is to provide an alternative solution in which, on the one hand, the pressure and flow losses in the interior of the rotor are further reduced and, on the other hand, is an easy, reliable and thus cost-effective solution.
  • the object directed to the invention is achieved with a rotor according to the features of claim 1.
  • Advantageous embodiments are specified in the dependent claims, the features of which can be combined according to the references.
  • the ribs are not monolithic part of one of the two rotor discs, but part of an impeller, which comprises a rib-shaped carrier plate-shaped ring on which the ribs are attached.
  • the aforementioned embodiment can be much simpler and cheaper to produce than rotor disks, in which the ribs are an integral part of the rotor disk.
  • the impeller may be made of a different material than the rotor disk itself, since the boundary conditions, such as the maximum operating temperatures, may be different.
  • the relatively complex geometry of the ribs of a rotor disk is separated from the latter since it has been recognized by the inventors that the
  • Ridges can also be arranged on a separate component - the impeller.
  • the impeller can be made mechanically from a full ring.
  • the impeller can also be assembled from individual parts - a ring and several ribs - by welding. With a complex geometry of the rib, there is also a casting method for producing the impeller.
  • a sleeve is provided which extends through the central opening of the respective rotor disc and at its first end as Stop serving collar and a first end opposite the second end, on which second end of the impeller is attached.
  • axial and “radial” and “outside” and “inside” always refer to the axis of rotation of the rotor disk or the rotor.
  • Under the interior of the rotor is also the cavity in the interior of the rotor understood den, which is bounded by the rotor disks. In other words: The holes of the first rotor disc do not count towards the rotor interior.
  • the outer edge of the rib carrier lies on a larger radius than the outer ends of the ribs, so that in the installed state, when the impeller is mounted between the hub areas of the respective rotor disks, the medium emerging from the bores because of the radially outwardly guided ribbed carrier can be better directed inward. Turbulences in the inflow regions of the flow passages can thus be avoided, which reduces pressure losses during the guidance of the medium.
  • each of the ribs on one of the first rotor disc facing edge whose radial contour corresponds to the radial contour of the first rotor disk in the hub region.
  • the gap between the edges of the ribs and the hub contour of the first rotor disk can be kept comparatively small over the entire radial rib extension, which allows efficient guiding of the medium along the rib, without the transverse flows through one of the rib and the hub region Gap occur.
  • the impeller is screwed onto the sleeve.
  • the impeller in its central opening on an internal thread, which on a provided at the second end of the sleeve external thread is screwed.
  • the threaded end of the sleeve is first inserted into the central opening of one of the two Rotorusionm - preferably the second rotor disc - until the collar of the sleeve rests against the side surface of the hub region.
  • On the thread-side end of the impeller is screwed quasi as a nut.
  • the cylindrical portion of the sleeve is stretched, whereby a sufficient for the function sufficiently secure attachment can be ensured.
  • the so tense assembly can then be threaded as usual when stacking the rotor on the tie rod. If necessary, the assembly can be secured against loosening by caulking in the area of the central thread.
  • the impeller is formed on the second side radially inwardly between the ribs in the shape of a gutter for deflecting a flow.
  • this solution in conjunction with the screw allows a comparatively large axial Verschraubungsin with reduced rib support thickness: Due to the cuspid design of the rib support at its central opening arranged in the central opening internal thread can therefore be made longer than without a groove, resulting in a further improved screw connection continues to ensure low weight of the impeller.
  • the invention provides several advantages: First, the simplification of the manufacturing, ie the reduction of potential manufacturing errors by reducing the component complexity specify.
  • the complex geometries are no longer with the comparatively more expensive components - The rotor disks - arranged, but are realized on a separately manufactured component - the impeller.
  • the separation of the complex geometries also leads to a cost reduction of that rotor disk, with which the removal of the medium from the main flow path is realized.
  • the second rotor disk can be made classical, since the impeller takes over the function of improved flow guidance inside the rotor. Due to the structural separation, different materials can be used and combined.
  • the invention thus relates generally to a rotor for a thermal turbomachine, in particular a gas turbine, which is designed to lead in its interior a medium, for example compressor air.
  • a medium for example compressor air.
  • FIG. 1 shows a longitudinal section through a runner of a
  • FIG. 2 shows a section through the longitudinal section of a rotor according to the invention of a flow machine with an impeller arranged between two rotor disks and
  • FIG 3 shows an assembly comprising a second rotor disc, an impeller and a sleeve in an exploded view.
  • Figure 1 shows the basic schematic structure of a rotor 10 of a thermal fluid machine, which is rotatably mounted in the assembled state about its axis of rotation 13.
  • the rotor 10 of a stationary gas turbine In the embodiment shown is the rotor 10 of a stationary gas turbine.
  • the rotor 10 could also be used in an aircraft gas turbine. Due to the use in a gas turbine, the rotor 10 comprises a compressor section 12 and a turbine section 14.
  • a pipe 16 is provided between the two sections 12, 14. Both the compressor section 12 and the turbine section 14 are disk-type.
  • compressor section 12 comprises sixteen rotor disks 18 and turbine section 14 four rotor disks 18.
  • a tie rod 20 at both ends of which a so-called front hollow shaft 22 and a so-called rear hollow shaft 24 are screwed .
  • the two hollow shafts 22, 24 clamp all the rotor discs 18 and the tube 16 with each other, so that relative movements in the circumferential direction are largely avoided.
  • this is arranged by the contact surfaces 23 Hirth gears. However, these are not shown further.
  • FIGS. 2 and 3 which on the one hand show a section of two arbitrary rotor disks 18 of the disk forming a pair of disks 25
  • Compressor section 12 of Figure 1 represent enlarged and on the other hand, an assembly of the rotor 10 in an exploded view.
  • Each rotor disk 18 has a disk web 26 which revolves endlessly about the axis of rotation 13.
  • the disk web 26 has at its radially inner end a hub region 28 with a concentric with the axis of rotation central opening 30 and at its radially outer end a rim portion 32.
  • the rim area serves for fastening rotor blades 31 (FIG. 1) and comprises collars 33 arranged on both sides, against which the adjacent rotor disks 18 adjoin one another.
  • the rotor disk 18 shown on the right in FIG. 2 is referred to below as the first rotor disk 34, which is illustrated on the left as the second rotor disk 42.
  • the first rotor disk 34 also has bores extending inwardly from the rim area through the disk web 26, which holes extend along the circumference of the disk web 26 evenly distributed. Of the holes only one is shown and labeled with the reference numeral 36.
  • the bores 36 are inclined relative to the radial direction in such a way that they penetrate the disk web 26 from one side to the other side.
  • the holes 36 open with their radially inner end in an annular surface 38, which is arranged obliquely to the radial direction of the rotor disk 34.
  • the impeller 50 comprises a plate-shaped ribbed support 52 having a first side 54 which is planarized and a second side 56 opposite the first side 54. On the second side 56, ribs 40 are distributed uniformly along the circumference. These serve as guiding elements for emerging from the holes 36 air.
  • each edge 43 of the ribs 40 facing the hub region 28 of the first rotor disk 34 is contoured so that its radial contour corresponds to the radial contour of the first rotor disk 34. Nevertheless, there is a slight gap between the edges 43 and the hub portion 28 to prevent wear.
  • the impeller 50 has a central opening 58 through which the tie rod 20 can extend.
  • a sleeve 62 is provided for secure attachment of the impeller 50. This sits in the central opening 30 of the second rotor disk 42 and has at an axial first end 63 a collar, so that the sleeve 62 can be supported laterally on the rotor disk 42. At a second end 65 of the sleeve 62, an external thread is provided. On this, the impeller 50 is screwed, which has in its central opening 58 has an internal thread.
  • the sleeve 62 is dimensioned to fit snugly or with little play in the central opening 30. With respect to the tie rod 20, its inside diameter should be slightly larger.
  • the ribs 40 are formed so that they end radially outward directly within the annular surface 38.
  • the outer edge 60 of the rib support 52 is located on a larger radius than the outer ends of the ribs 40 - with respect to the rotation axis thirteenth
  • the ribs 40 serve for flow guidance and for unwinding the air flowing out of the bores 36, which are intended to flow into the interior of the rotor 10.
  • a second rotor disk 42 adjoins on the side of the first rotor disk 34, on which the ribs 40 are provided. Because of the use of the impeller 50, the second rotor disk 42 in the hub portion 28 may be conventional.
  • the flow passages can be limited axially over the entire radial extent of the ribs 40, in which the cooling air emerging from the bores 36 and leading to the tie rod 20. This avoids turbulence of the air at the entrance of each flow passage, which improves the efficiency of the air flow.
  • An aerodynamically favorable flow guidance near the tie rod 20 can be achieved by fillets 66 which the rib support has radially inward.
  • Tie rod 20 through which the tension arm 20 guided air in the axial direction along the tie rod 20 from
  • Compressor section 12 can be performed to the turbine section 14 can.
  • disk pair 25 described above with the intermediate impeller 50 can also be used to guide the guided along the tie rod 20 air to the outside, as required for rotor disks 18 in the turbine section 14.

Landscapes

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

Abstract

L'invention concerne globalement un rotor (10), destiné à une turbomachine thermique, en particulier une turbine à gaz, qui est configuré pour guider un fluide, par exemple de l'air de suralimentation, dans sa partie intérieure. Selon l'invention, pour pouvoir guider ce fluide avec peu de pertes à l'écoulement dans la partie intérieure tout en donnant un rotor (10) qui peut être fabriqué de manière relativement simple et économique, une roue à aubes (50) fabriquée séparément est disposée entre les zones de moyeu voisines l'une de l'autre des deux disques de rotor (34, 42), et un manchon (62) servant à fixer la roue à aubes (50) à l'un des deux disques de rotor (34, 42) s'étend à travers l'orifice central (30) du disque de rotor (34, 42) concerné, comprenant à sa première extrémité (63) une collerette (64) qui sert de butée et une deuxième extrémité (65), située à l'opposé de la première extrémité (63), à laquelle la roue à aubes (50) est fixée.
EP14731226.8A 2013-07-17 2014-06-16 Rotor pour turbomachine thermique Withdrawn EP2994614A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14731226.8A EP2994614A1 (fr) 2013-07-17 2014-06-16 Rotor pour turbomachine thermique

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP13176862.4A EP2826958A1 (fr) 2013-07-17 2013-07-17 Rotor pour une turbomachine thermique
EP14731226.8A EP2994614A1 (fr) 2013-07-17 2014-06-16 Rotor pour turbomachine thermique
PCT/EP2014/062518 WO2015007443A1 (fr) 2013-07-17 2014-06-16 Rotor pour turbomachine thermique

Publications (1)

Publication Number Publication Date
EP2994614A1 true EP2994614A1 (fr) 2016-03-16

Family

ID=48803411

Family Applications (2)

Application Number Title Priority Date Filing Date
EP13176862.4A Withdrawn EP2826958A1 (fr) 2013-07-17 2013-07-17 Rotor pour une turbomachine thermique
EP14731226.8A Withdrawn EP2994614A1 (fr) 2013-07-17 2014-06-16 Rotor pour turbomachine thermique

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP13176862.4A Withdrawn EP2826958A1 (fr) 2013-07-17 2013-07-17 Rotor pour une turbomachine thermique

Country Status (5)

Country Link
US (1) US20160195110A1 (fr)
EP (2) EP2826958A1 (fr)
JP (1) JP2016524095A (fr)
CN (1) CN105392963B (fr)
WO (1) WO2015007443A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2826957A1 (fr) 2013-07-17 2015-01-21 Siemens Aktiengesellschaft Rotor pour une turbomachine thermique
WO2017026908A1 (fr) * 2015-08-13 2017-02-16 Siemens Aktiengesellschaft Système d'élimination de turbulences destiné à un système de refroidissement, et système de refroidissement d'une turbomachine
KR101896436B1 (ko) * 2017-04-12 2018-09-10 두산중공업 주식회사 보강디스크를 포함하는 압축기 및 이를 포함하는 가스터빈
CN108425708B (zh) * 2018-04-28 2023-08-01 南京航空航天大学 一种复合式减涡器结构
CN110081027A (zh) * 2019-04-29 2019-08-02 南京航空航天大学 一种用于压气机的翅片式减涡器引气系统
GB201917397D0 (en) 2019-11-29 2020-01-15 Siemens Ag Method of assembling and disassembling a gas turbine engine module and an assembly therefor

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Publication number Priority date Publication date Assignee Title
GB2207465B (en) * 1987-07-18 1992-02-19 Rolls Royce Plc A compressor and air bleed arrangement
DE19617539B4 (de) 1996-05-02 2006-02-09 Alstom Rotor für eine thermische Turbomaschine
DE19852604A1 (de) * 1998-11-14 2000-05-18 Abb Research Ltd Rotor für eine Gasturbine
FR2834753B1 (fr) * 2002-01-17 2004-09-03 Snecma Moteurs Disque de compresseur axial de turbomachine a prelevement d'air centripete
US7344354B2 (en) * 2005-09-08 2008-03-18 General Electric Company Methods and apparatus for operating gas turbine engines
DE102007031712A1 (de) * 2007-07-06 2009-01-08 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung und Verfahren zum Einspannen von beschaufelten Rotorscheiben eines Strahltriebwerkes
FR2930589B1 (fr) * 2008-04-24 2012-07-06 Snecma Prelevement d'air centripete dans un rotor de compresseur d'une turbomachine
FR2930588B1 (fr) * 2008-04-24 2010-06-04 Snecma Rotor de compresseur d'une turbomachine comportant des moyens de prelevement d'air centripete
US9145771B2 (en) * 2010-07-28 2015-09-29 United Technologies Corporation Rotor assembly disk spacer for a gas turbine engine
US20130199207A1 (en) * 2012-02-03 2013-08-08 General Electric Company Gas turbine system

Non-Patent Citations (1)

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Title
See references of WO2015007443A1 *

Also Published As

Publication number Publication date
CN105392963A (zh) 2016-03-09
JP2016524095A (ja) 2016-08-12
EP2826958A1 (fr) 2015-01-21
CN105392963B (zh) 2017-03-15
WO2015007443A1 (fr) 2015-01-22
US20160195110A1 (en) 2016-07-07

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