EP2113637A2 - Unité rotative pour un compresseur axial - Google Patents

Unité rotative pour un compresseur axial Download PDF

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Publication number
EP2113637A2
EP2113637A2 EP09004275A EP09004275A EP2113637A2 EP 2113637 A2 EP2113637 A2 EP 2113637A2 EP 09004275 A EP09004275 A EP 09004275A EP 09004275 A EP09004275 A EP 09004275A EP 2113637 A2 EP2113637 A2 EP 2113637A2
Authority
EP
European Patent Office
Prior art keywords
blade
rotating unit
axialcompressor
drive shaft
blades
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Withdrawn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
EP09004275A
Other languages
German (de)
English (en)
Other versions
EP2113637A3 (fr
Inventor
Ingo Jahns
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2113637A2 publication Critical patent/EP2113637A2/fr
Publication of EP2113637A3 publication Critical patent/EP2113637A3/fr
Withdrawn legal-status Critical Current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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage 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
    • F04D23/00—Other rotary non-positive-displacement pumps
    • F04D23/006—Creating a pulsating flow
    • 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
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid 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
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/442—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps rotating diffusers

Definitions

  • the invention relates to an axial compressor, wherein conventional stator blades are replaced by rotating units.
  • Fig. 1 shows an axial compressor in meridian section according to the prior art.
  • Today's axial compressors consist of a rotor 1 with usually several rows of rotor blades 3 and a housing 2, in which stator blades 4 are used. Each rotor blade row is preceded by a row of stator blades. The stator blades 4 build pressure by converting the kinetic energy of the fluid. Furthermore, they serve to divert fluids for the next following rotor blade row. In most cases, the front rows of stator blades are only connected to an adjusting mechanism 5, thus making it possible to adjust the guide vanes as a function of the rotational speed of the axial compressor.
  • the front stator blades 4 are adjustable via a drive train in order to deflect air or a fluid in such a way that it impinges on the following rotor blades at a favorable angle.
  • the invention has for its object to provide an axial compressor, which can build the highest possible pressure with a simple and short design and low weight.
  • an axial compressor is provided with at least one stator blade row, wherein at least one blade of the stator blade row is designed as a rotating unit, and wherein the rotating unit is completely rotatable about a drive axis.
  • the drive axis is substantially perpendicular to a Axialkompressorrotationsachse.
  • the invention replaces the prior art adjustable stator vanes with rotating units, also called novel rotating stator units, which both redirect and compress the air or fluid. Since the gasumströmten surfaces or the circumference of the interior of the axial compressor constrict by the compression of the rotor blades, conventional gear pumps or vane pumps are unsuitable. Furthermore, the compressor is annular.
  • the distances between the individual rotating units in the circumferential direction are not too large, it is advantageous to make this conical.
  • the inclination of gasumströmten surfaces is ensured by an additional tilting rotor.
  • the blades of the rotating unit and the blades of the tilting protector are designed to intermesh.
  • the rotating unit is also advantageous to connect the rotating unit to a drive via a drive shaft. Due to the intermeshing of the rotating unit and the tilting rotor, the tilting rotor is entrained when the rotating unit is driven by the drive. Both the rotating unit and the tilting rotor are mounted in the housing.
  • the tilting rotor is arranged in the housing so that a platform of the tilting protector follows the constriction of the gas-flowed area.
  • the forced rotation of the tilting protector and the inclined suspension in relation to the rotating unit result in a relative movement of the rotating unit and the tilting rotor to each other.
  • the axis of the Kipprotors and the rotating unit intersect at one point.
  • the blades of the Kipprotors are machined spherical to this point.
  • the blades of the rotating unit enter tangentially into these spherically shaped blades of the Kipprotors.
  • the webs connect the housing and the inner cover tape and form the lateral boundary for the rotating units for compression of the fluid or the air. At the same time the space between the webs serves as an inlet and outlet port for the fluid. Possible oil supply Removal of the inner cover tape can be realized via the webs.
  • the axis of the rotating unit is also designed cone-shaped. The volume between the blades of the rotating unit and the webs is thus narrowed.
  • the blades of the rotating unit are arranged spirally on the circumference of the rotating unit.
  • air or fluid is conveyed and compressed from the radially inner regions to the radially outer regions.
  • the use of the axial compressor according to the invention already builds up more pressure at the front stage of the compressor. As a result, fewer compression stages are required to build up the same pressure. Consequently, the compressor can be made shorter and lighter.
  • Fig. 2 shows an axial compressor in the meridian section with an axial compressor rotation axis 27, a rotor 1 and an inner space 22.
  • the rotor 1 includes rotor blades 3.
  • the axial compressor is externally bounded by a housing 2.
  • a left rotating unit 6 and a right rotating unit 6th displayed.
  • the rotating units may also be referred to as novel rotating stator units. These each consist of a blade 8, a drive shaft 10 and a drive 11, which is designed here as a gear. A drive via individual electric motors is also conceivable.
  • the drive axis 26 extends.
  • the rotating unit 6 is completely rotatable about its drive axis 26.
  • the rotating unit 6 is mounted above in the housing 2.
  • the seal against the rotor 1 is in the right rotating unit 6 in Fig. 2 shown, but hidden in the left rotating unit 6 or not required.
  • Fig. 3 shows a rotating unit 6 according to a first embodiment with a bearing 12, a tilt rotor 7, blades 8 and the drive shaft 10. It can be seen how the drive shaft 10 is mounted on the bearing 12, which is designed as a rolling bearing in the housing. The tilting rotor 7 is also mounted on roller bearings relative to the housing and a further roller bearing relative to the drive shaft 10.
  • Fig. 4 shows a detail of the rotating unit according to the first embodiment.
  • the tilting rotor 7 with a platform 13 and tilt rotor blades 9 can be seen.
  • Fig. 4 arcuate portions 16 of the tilt rotor blades 9.
  • the dashed line 29 denotes a rotation axis of the Kipprotors. From this axis of rotation of the Kipprotors 29 and the drive axle 26 results in the pivot point 14th
  • Fig. 5 shows the tilt rotor 7 of the first embodiment in detail, it can be seen how the blades 8 of the rotating unit engage in pockets 28 of the tilt rotor blades 7. Thus, vane ends 19 and tipper rotor blade ends 21 overlap.
  • Fig. 6 shows a rotating unit according to a second embodiment.
  • the blades 8 of the rotating unit form at their ends pockets 20 which receive the tilt rotor blades 9.
  • Fig. 8 shows a 3-D view of the rotating unit according to the second embodiment in the region of a rotor hub, thereby It is easy to see how the pocket 20 of the bucket 8 receives the tipping rotor blade ends 21 of the tipping rotor blades 9.
  • Fig. 9 shows a detailed view of the rotating unit according to the second embodiment in a perspective view.
  • Fig. 10 shows two rotating units 6.
  • two rotating units 6 can be seen within a row of stator blades 18.
  • webs 17 are arranged, which connect the housing 2 with an inner cover tape 15. These webs form the lateral boundary, and thus a closed space 23, for the rotating units 6 for compressing the air or the fluid.
  • the space between the webs 17 serves as an inlet and outlet port for the fluid. Any supply and removal of the inner cover tape 15 can be realized via the webs.
  • the formation of webs as a lateral boundary is present in all embodiments.
  • the internal geometry follows the blades of the Kipprotors 7 and the rotating unit. 9
  • FIGS. 11 and 12 show a rotating unit according to a third embodiment. It is easy to see how the drive shaft 10 is designed conical. The conical shape of the drive shaft 10 allows additional compression by the centrifugal forces. For the same reason, the blade 8 of the rotating unit 6 is conically shaped. Alternatively, the blades 8 may also be spirally disposed on the periphery of the drive shaft 10 to convey and compress air from the radially inner region to the outer regions of the axial compressor. Furthermore, as already in Fig. 10 the tilt rotor 7 spherically 25 formed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP09004275.5A 2008-04-30 2009-03-25 Unité rotative pour un compresseur axial Withdrawn EP2113637A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102008021683A DE102008021683A1 (de) 2008-04-30 2008-04-30 Rotierende Einheit für einen Axialkompressor

Publications (2)

Publication Number Publication Date
EP2113637A2 true EP2113637A2 (fr) 2009-11-04
EP2113637A3 EP2113637A3 (fr) 2015-04-01

Family

ID=40527396

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09004275.5A Withdrawn EP2113637A3 (fr) 2008-04-30 2009-03-25 Unité rotative pour un compresseur axial

Country Status (3)

Country Link
US (1) US8251646B2 (fr)
EP (1) EP2113637A3 (fr)
DE (1) DE102008021683A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102777410A (zh) * 2012-06-28 2012-11-14 南京航空航天大学 无尾桨反扭矩系统气动性能综合试验平台用压气机
EP3064719A1 (fr) * 2015-03-04 2016-09-07 Siemens Aktiengesellschaft Rangée d'aubes directrices pour une turbomachine traversée axialement
EP3109408A1 (fr) * 2015-06-25 2016-12-28 Rolls-Royce Deutschland Ltd & Co KG Dispositif de stator pour une turbomachine comprenant un dispositif de carter et plusieurs aubes directrices
US10344616B2 (en) 2015-06-25 2019-07-09 Rolls-Royce Deutschland Ltd & Co Kg Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012092543A1 (fr) * 2010-12-30 2012-07-05 Rolls-Royce North America Technologies, Inc. Aube variable pour moteur à turbine à gaz
US9670877B2 (en) * 2013-07-15 2017-06-06 United Technologies Corporation Link arm drag reducing device

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB978658A (en) 1962-05-31 1964-12-23 Rolls Royce Gas turbine by-pass engines

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE496713A (fr) * 1949-07-01
GB755527A (en) * 1953-10-15 1956-08-22 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in axial flow elastic fluid turbines
US4086042A (en) * 1976-06-17 1978-04-25 Westinghouse Electric Corporation Rotary compressor and vane assembly therefor
US4278398A (en) * 1978-12-04 1981-07-14 General Electric Company Apparatus for maintaining variable vane clearance
US4239450A (en) * 1979-05-17 1980-12-16 Buffalo Forge Company Adjusting mechanism for variable inlet vane
DE3731902A1 (de) * 1987-09-23 1989-04-06 Mtu Muenchen Gmbh Fluegelgitter fuer gasfoermige stroemungsmittel
US4950129A (en) * 1989-02-21 1990-08-21 General Electric Company Variable inlet guide vanes for an axial flow compressor
DE4237031C1 (de) * 1992-11-03 1994-02-10 Mtu Muenchen Gmbh Verstellbare Leitschaufel
FR2723614B1 (fr) * 1994-08-10 1996-09-13 Snecma Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.
FR2742799B1 (fr) * 1995-12-20 1998-01-16 Snecma Palier d'extremite interne d'aube pivotante
JPH09280199A (ja) 1996-04-12 1997-10-28 Mitsubishi Heavy Ind Ltd 回転軸流機械
FR2817906B1 (fr) * 2000-12-12 2003-03-28 Snecma Moteurs Volet redresseur de turbomachine et son procede de realisation
FR2835295B1 (fr) * 2002-01-29 2004-04-16 Snecma Moteurs Dispositif de commande d'aube a angle de calage variable a liaison par pincement pour redresseur de compresseur de turbomachine
US7628579B2 (en) * 2005-07-20 2009-12-08 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
EP1867877A1 (fr) 2006-06-16 2007-12-19 Ansaldo Energia S.P.A. Compresseur d'une turbine à gaz
FR2913052B1 (fr) * 2007-02-22 2011-04-01 Snecma Commande des aubes a angle de calage variable

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB978658A (en) 1962-05-31 1964-12-23 Rolls Royce Gas turbine by-pass engines

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102777410A (zh) * 2012-06-28 2012-11-14 南京航空航天大学 无尾桨反扭矩系统气动性能综合试验平台用压气机
CN102777410B (zh) * 2012-06-28 2014-09-03 南京航空航天大学 无尾桨反扭矩系统气动性能综合试验平台用压气机
EP3064719A1 (fr) * 2015-03-04 2016-09-07 Siemens Aktiengesellschaft Rangée d'aubes directrices pour une turbomachine traversée axialement
EP3109408A1 (fr) * 2015-06-25 2016-12-28 Rolls-Royce Deutschland Ltd & Co KG Dispositif de stator pour une turbomachine comprenant un dispositif de carter et plusieurs aubes directrices
US10344616B2 (en) 2015-06-25 2019-07-09 Rolls-Royce Deutschland Ltd & Co Kg Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes

Also Published As

Publication number Publication date
EP2113637A3 (fr) 2015-04-01
US8251646B2 (en) 2012-08-28
US20090274547A1 (en) 2009-11-05
DE102008021683A1 (de) 2009-11-05

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