[go: up one dir, main page]
More Web Proxy on the site http://driver.im/

WO2005019604A1 - Dispositif de guidage de flux dans le diffuseur d'une turbomachine, et procede pour devier un flux - Google Patents

Dispositif de guidage de flux dans le diffuseur d'une turbomachine, et procede pour devier un flux Download PDF

Info

Publication number
WO2005019604A1
WO2005019604A1 PCT/EP2004/007252 EP2004007252W WO2005019604A1 WO 2005019604 A1 WO2005019604 A1 WO 2005019604A1 EP 2004007252 W EP2004007252 W EP 2004007252W WO 2005019604 A1 WO2005019604 A1 WO 2005019604A1
Authority
WO
WIPO (PCT)
Prior art keywords
outflow
guide
deflection surface
rotor
guide device
Prior art date
Application number
PCT/EP2004/007252
Other languages
German (de)
English (en)
Inventor
Andreas Kayser
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP04740600A priority Critical patent/EP1651842A1/fr
Publication of WO2005019604A1 publication Critical patent/WO2005019604A1/fr

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00Regulating or controlling by varying flow
    • F01D17/10Final actuators
    • F01D17/12Final actuators arranged in stator parts
    • F01D17/14Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162Final 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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162Bearing supports
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30Exhaust heads, chambers, or the like
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00Geometry
    • F05D2250/40Movement of components
    • F05D2250/41Movement of components with one degree of freedom
    • F05D2250/411Movement of components with one degree of freedom in rotation
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/70Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line

Definitions

  • the invention relates to an outflow guide device in a diffuser of a turbomachine with a guide blade, which has a leading edge and a trailing edge, between which a deflection surface is provided and which deflects a flow medium from an incident direction, and a method for changing an outflow guide device.
  • a gas turbine as an example of a turbomachine
  • intake air is compressed and heated in the compressor part and then strongly heated and accelerated in a combustion chamber with the addition of a fuel.
  • a multi-stage turbine connects to the combustion chamber in terms of flow.
  • the flow medium which is a mixture of the burned fuel and the compressed air, flows through the multi-stage turbine.
  • the movement of the flow medium creates an angular momentum on the rotor and thus ultimately leads to a rotation of the rotor.
  • the rotational energy is then converted into electrical energy using a generator.
  • the flow medium flows in a diffuser past a bearing star, which has several guide blades.
  • the bearing star serves on the one hand for deflecting the flow medium and on the other hand as a holder for the rotatably mounted rotor.
  • the bearing star and in particular the guide blades are usually made rigid and of the same material.
  • Such a bearing star arrangement is described in document DE 39 42 203.
  • the bearing star arrangement there relates to a turbine engine.
  • the object of the present invention is to provide an outflow guiding device with which flow losses in a diffuser can be reduced.
  • Another object is to provide a method for changing an outflow guide device in a diffuser to reduce the flow losses.
  • the object directed to the outflow guiding device is achieved by an outflow guiding device
  • Turbomachine with a guide blade which has a leading edge and a trailing edge between which a deflecting surface is provided which deflects a flow medium from an incident direction
  • the outflow guiding device being mountable in a diffuser
  • the outflow guiding device comprising a rotor-side end and a stator-side end and the rotor-side End is designed to support a rotor
  • the guide blade being adjustable with respect to the course of its deflection surface relative to the direction of incidence.
  • the object directed towards the method is achieved by a method for changing an outflow guide device of a turbomachine with a guide blade, which has a leading edge and a trailing edge between which a deflection surface is provided which deflects a flow medium from an incident direction, the outflow guide device in a diffuser is installed, a rotor-side end and a stator-side end being provided for the outflow guiding device and the rotor-side end supporting the rotor, a course of the deflection surface of the guide blade being adjustable relative to the incident sighting.
  • the advantage can be seen, inter alia, in the fact that a flow of a flow medium through the outflow guiding device can be changed in a targeted manner, and thereby an inflow of the Lagersterns is improved.
  • Another advantage is that the outflow guiding device can be adjusted during the intended operation.
  • Another advantage is that an exhaust gas swirl is reduced and, furthermore, the flow is improved for each load state of the turbine or operating state of the turbine.
  • the guide blade is preferably designed in such a way that the deflection surface can be rotated.
  • the guide sheet is rotatably mounted about an axis of rotation.
  • the axis of rotation is essentially perpendicular to the direction of incidence. This changes the overall aerodynamics of the blade.
  • the outer shape of the deflection surface is preferably designed to be adjustable.
  • the guide sheet comprises a front part located in the leading edge and a rear part located in the trailing edge.
  • the rear part located in the trailing edge is rotatably supported about an axis of rotation.
  • the axis of rotation is essentially parallel to the trailing edge.
  • the front part which is usually very solid, can be rigidly installed in the diffuser.
  • the rear part which is rotatably supported, improves the inflow through the outflow guide device due to the changeable aerodynamics.
  • the rear part is preferably designed in such a way that the rear part is moved in a flow direction that runs directly from the leading edge to the trailing edge.
  • the length in the flow direction of a respective guide sheet can hereby be changed individually.
  • the guide sheet can be shortened or lengthened in the direction of flow.
  • Figure 1 is a perspective view of a prior art power stage of a gas turbine
  • FIG. 2 shows a perspective illustration of a guide sheet of an outflow guide device belonging to the prior art
  • Figure 3 is a cross-sectional view of a guide sheet in a first embodiment
  • Figure 4 is a cross-sectional view of a guide sheet in a second embodiment
  • Figure 5 is a cross-sectional view of a guide sheet in a third embodiment.
  • FIG. 1 shows a perspective illustration of a gas turbine 1 belonging to the prior art.
  • An end turbine stage 3 which comprises a plurality of moving blades 4, is attached to a rotatably mounted rotor 2.
  • An outer housing is arranged around the rotor 2 and has a lower part 5a and an upper part 5b.
  • the rotor 2 is rotatably mounted about an axis of rotation 6.
  • a flow medium flows parallel to the axis of rotation 6 in the direction of the turbine stage 3.
  • the flow medium flows into the diffuser 7.
  • the flow medium flows through an incident direction through a so-called bearing star, which is also referred to as a discharge guide device 8.
  • the outflow guide device 8 comprises six guide blades 9. In alternative embodiments, fewer or more than six guide blades 9 are possible.
  • the flow medium flows out at a varying outflow angle after turbine stage 3.
  • the outflow angle depends on a load attached to the rotor 2.
  • the outflow guiding device 8 comprises a rotor-side end 10 and a stator-side end 11.
  • the rotor-side end 10 is designed such that the rotor 2 is rotatably mounted therein.
  • Figure 2 is a perspective view of a
  • a flow medium flows to the guide blade 9 in an incident direction 12.
  • the incident direction 12 depends on the outflow angle.
  • the flow medium is true 'first to a leading edge 13, flows around a respective environmental guide surface 15 and then flows from a trailing edge 14 from the gas turbine 1 out.
  • the guide sheet 9 is designed such that the guide sheet 9 can be adjusted with respect to the course of its deflecting surface 15 relative to the direction of incidence 12.
  • This configuration of the guide blade 9 minimizes losses which are caused by non-optimal flow against the guide blade 9 as a result of the load-dependent varying outflow angle.
  • the deflection surface (15) can be rotatable.
  • the outer shape of the deflection surface (15) can be adjustable.
  • a first embodiment is shown in FIG. 3.
  • a cross section of the guide leaf 9 can be seen in FIG. The viewing direction is essentially perpendicular to the direction of incidence 12 in the direction of the axis of rotation 6.
  • the guide blade 9 is in this case rotatably mounted about an axis of rotation 16.
  • This axis of rotation 16 is essentially perpendicular to the direction of incidence 12.
  • the axis of rotation 16 lies essentially in the center of the guide blade 9.
  • the axis of rotation 6 can also be attached closer to the leading edge 13 or the trailing edge 14.
  • the guide sheet 9 is rotated about the axis of rotation 16.
  • the guide sheet 9 is rotated about the axis of rotation 16 either clockwise 17 or counterclockwise 18.
  • a flow medium that impinges on the guide blade 9 in the direction of incidence 12 can thereby be deflected.
  • the guide sheet 9 comprises a front part 20 comprising the leading edge 13 and a rear part 19 comprising the trailing edge 14.
  • the front part 20 is of rigid construction.
  • the front part 20 can also be rotatably supported about a further axis of rotation.
  • the rear part 19 is designed such that it is rotatably mounted about an axis of rotation 21.
  • the axis of rotation 21 is attached in a front region 22 of the rear part 19.
  • a rear region 23 can thereby be moved either clockwise 17 or counterclockwise 18.
  • a third embodiment of the guide sheet 9 can be seen in FIG.
  • the rear part 19 is moved in the flow direction either to the direction of incidence (represented by arrow 24) or counter to the direction of incidence (represented by arrow 25).
  • the front part 20 of the guide sheet 9 can be rotatably mounted about an additional axis of rotation in an alternative embodiment.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Abstract

La présente invention concerne un dispositif de guidage de flux dans le diffuseur (7) d'une turbomachine, comprenant au moins une lame de guidage (9) qui présente un arête d'arrivée de flux (13) et une arête de départ de flux (14) entre lesquelles s'étend une surface de déflexion (15) qui dévie un flux par rapport à sa direction d'arrivée (12), la/les lame(s) de guidage pouvant subir un réglage de l'allure de sa/leur surface de déflexion (15) par rapport à la direction d'arrivée (12).
PCT/EP2004/007252 2003-08-08 2004-07-02 Dispositif de guidage de flux dans le diffuseur d'une turbomachine, et procede pour devier un flux WO2005019604A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04740600A EP1651842A1 (fr) 2003-08-08 2004-07-02 Dispositif de guidage dans un passage d'echappement pour une turbomachine et procede d'operation

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP03018164.8 2003-08-08
EP03018164A EP1505263A1 (fr) 2003-08-08 2003-08-08 Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération

Publications (1)

Publication Number Publication Date
WO2005019604A1 true WO2005019604A1 (fr) 2005-03-03

Family

ID=33547671

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2004/007252 WO2005019604A1 (fr) 2003-08-08 2004-07-02 Dispositif de guidage de flux dans le diffuseur d'une turbomachine, et procede pour devier un flux

Country Status (2)

Country Link
EP (2) EP1505263A1 (fr)
WO (1) WO2005019604A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7632064B2 (en) 2006-09-01 2009-12-15 United Technologies Corporation Variable geometry guide vane for a gas turbine engine
US9032721B2 (en) * 2011-12-14 2015-05-19 Siemens Energy, Inc. Gas turbine engine exhaust diffuser including circumferential vane
EP2644838A1 (fr) * 2012-03-27 2013-10-02 Alstom Technology Ltd Boîtier de gaz d'échappement d'une turbine à gaz
US9422864B2 (en) 2012-12-20 2016-08-23 General Electric Company Staggered double row, slotted airfoil design for gas turbine exhaust frame
DE102020209792A1 (de) 2020-08-04 2022-02-10 MTU Aero Engines AG Leitschaufel

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH247831A (de) * 1942-11-26 1947-03-31 Jendrassik Georg Turbine für heisses Arbeitsmittel.
US2934895A (en) * 1958-09-15 1960-05-03 Curtiss Wright Corp Dual cycle engine distributor construction
US2945672A (en) * 1956-10-05 1960-07-19 Marquardt Corp Gas turbine unit
US3285567A (en) * 1963-11-29 1966-11-15 Bristol Siddeley Engines Ltd Axial flow turbines and compressors
US3563669A (en) * 1969-07-10 1971-02-16 Gen Motors Corp Variable area nozzle
US4292802A (en) * 1978-12-27 1981-10-06 General Electric Company Method and apparatus for increasing compressor inlet pressure
FR2526485A1 (fr) * 1982-05-07 1983-11-10 Snecma Roue directrice d'entree de soufflante de turboreacteur permettant le demontage unitaire des aubes mobiles, et procede pour la mise en oeuvre
EP0094296A1 (fr) * 1982-05-04 1983-11-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif de réglage de la perte de charge d'au moins un des flux dans un turboréacteur multiflux
US4972671A (en) * 1988-05-11 1990-11-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbo-engine air intake grill
US4989406A (en) * 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
US5259187A (en) * 1993-02-05 1993-11-09 General Electric Company Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH247831A (de) * 1942-11-26 1947-03-31 Jendrassik Georg Turbine für heisses Arbeitsmittel.
US2945672A (en) * 1956-10-05 1960-07-19 Marquardt Corp Gas turbine unit
US2934895A (en) * 1958-09-15 1960-05-03 Curtiss Wright Corp Dual cycle engine distributor construction
US3285567A (en) * 1963-11-29 1966-11-15 Bristol Siddeley Engines Ltd Axial flow turbines and compressors
US3563669A (en) * 1969-07-10 1971-02-16 Gen Motors Corp Variable area nozzle
US4292802A (en) * 1978-12-27 1981-10-06 General Electric Company Method and apparatus for increasing compressor inlet pressure
EP0094296A1 (fr) * 1982-05-04 1983-11-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif de réglage de la perte de charge d'au moins un des flux dans un turboréacteur multiflux
FR2526485A1 (fr) * 1982-05-07 1983-11-10 Snecma Roue directrice d'entree de soufflante de turboreacteur permettant le demontage unitaire des aubes mobiles, et procede pour la mise en oeuvre
US4972671A (en) * 1988-05-11 1990-11-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbo-engine air intake grill
US4989406A (en) * 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
US5259187A (en) * 1993-02-05 1993-11-09 General Electric Company Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes

Also Published As

Publication number Publication date
EP1505263A1 (fr) 2005-02-09
EP1651842A1 (fr) 2006-05-03

Similar Documents

Publication Publication Date Title
DE60133629T2 (de) Verfahren zum betrieb einer gasturbine mit verstellbaren leitschaufeln
DE602004006922T2 (de) Leitschaufelanordnung für ein Gasturbinentriebwerk
EP1659293B1 (fr) Turbomachine
DE3530769C2 (de) Schaufel für ein Gasturbinentriebwerk
DE102008017844A1 (de) Strömungsmaschine mit Fluid-Injektorbaugruppe
DE112012002692B4 (de) Vorrichtung und Verfahren zur Reduzierung des Luftmassenflusses zur emissionsarmen Verbrennung über einen erweiterten Bereich in einwelligen Gasturbinen
DE102007025006A1 (de) Doppelwellen-Gasturbine
CH703553A2 (de) Profilierter axial-radialer Auslassdiffusor.
DE2454054A1 (de) Innentriebwerk bzw. gasgenerator fuer gasturbinentriebwerke
DE2853340A1 (de) Vorrichtung zum erzeugen eines vorwirbels am verdichtereingang eines turbinen-triebwerkes
DE102009043833A1 (de) Relativpositionierung von Turbinenschaufelblättern
EP3064706A1 (fr) Rangée d'aubes directrices pour une turbomachine traversée axialement
CH701537A2 (de) Spitzendeckplatte mit Dämpfungsrippen.
DE102017111721A1 (de) Auslassdiffusor
WO2009080439A1 (fr) Plaque de protection contre l'érosion pour aubes mobiles
EP0999349A2 (fr) Turbine axiale
WO2005019604A1 (fr) Dispositif de guidage de flux dans le diffuseur d'une turbomachine, et procede pour devier un flux
DE102010044819B4 (de) Axialturbine und ein Verfahren zum Abführen eines Stroms von einer Axialturbine
DE102011053929A1 (de) Turbinenblattspitzenabdeckung zur Verwendung bei einem Spitzenabstandssteuerungssystem
DE3707723C2 (fr)
DE102019008225A1 (de) Schaufel und damit ausgestattete maschine
EP2268900A1 (fr) Aube pour moteur thermique rotatif
DE102010040823A1 (de) Turbolader
DE102006010863B4 (de) Turbomaschine, insbesondere Verdichter
DE3807574A1 (de) Windenergiegewinnungsanlage sowie verfahren zur gewinnung von windenergie

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE EG ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NA NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): BW GH GM KE LS MW MZ NA SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LU MC NL PL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG

121 Ep: the epo has been informed by wipo that ep was designated in this application
WWE Wipo information: entry into national phase

Ref document number: 2004740600

Country of ref document: EP

WWP Wipo information: published in national office

Ref document number: 2004740600

Country of ref document: EP

WWW Wipo information: withdrawn in national office

Ref document number: 2004740600

Country of ref document: EP