EP1505263A1 - Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération - Google Patents

Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération Download PDF

Info

Publication number
EP1505263A1
EP1505263A1 EP03018164A EP03018164A EP1505263A1 EP 1505263 A1 EP1505263 A1 EP 1505263A1 EP 03018164 A EP03018164 A EP 03018164A EP 03018164 A EP03018164 A EP 03018164A EP 1505263 A1 EP1505263 A1 EP 1505263A1
Authority
EP
European Patent Office
Prior art keywords
guide blade
trailing edge
abströmleiteinrichtung
rotation
axis
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Withdrawn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
EP03018164A
Other languages
German (de)
English (en)
Inventor
Andreas Dr. Kayser
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 EP03018164A priority Critical patent/EP1505263A1/fr
Priority to PCT/EP2004/007252 priority patent/WO2005019604A1/fr
Priority to EP04740600A priority patent/EP1651842A1/fr
Publication of EP1505263A1 publication Critical patent/EP1505263A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation
    • 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
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line

Definitions

  • the invention relates to a Abströmleit adopted in one Diffuser of a turbomachine with a baffle, the has a leading edge and a trailing edge between where a deflection is provided and the flow medium deflected from a direction of incidence and a method for changing a Abströmleit vibration.
  • a gas turbine as an example of a turbomachine is compressed air in the compressor part and heated and then in a combustion chamber with admixture of a Fuel is heated and accelerated.
  • a multi-level Turbine connects fluidically to the combustion chamber. Through the multi-stage turbine flows the flow medium, the a mixture of the burned fuel and the compressed one Air is. The movement of the flow medium generates an angular momentum on the rotor and thus eventually leads to a rotation of the rotor. The rotational energy is subsequently by means of a generator into electrical energy transformed.
  • the bearing star serves on the one hand for deflecting the flow medium and on the other as a holder for the rotatably mounted rotor.
  • the bearing star and especially the baffles rigid and made of the same material.
  • Object of the present invention is to provide a Abströmleit boots indicate with the flow losses in one Diffuser can be reduced.
  • Another task is to provide a method for changing a Abströmleit adopted in a diffuser to reduce the Specify flow losses.
  • the task directed to the outflow device is solved by a Abströmleit adopted in a diffuser a turbomachine with a guide blade, the leading edge and an outflow edge has between them Deflection is provided, which is a flow medium deflects a direction of incidence, wherein the guide sheet in terms of a course of its deflection relative to the direction of incidence is adjustable.
  • the task directed towards the method is solved by a method for changing a Abströmleit adopted 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, the one Flow medium deflects from an incident direction, wherein a Course of the deflection of the guide blade relative to Einfallsichtung is adjustable.
  • the advantage is, inter alia, that a flow a flow medium through the Abströmleit raised can be selectively changed and thereby a flow of the Lagersterns is improved.
  • Another advantage is that the Abströmleit worn during normal operation can be adjusted.
  • Another advantage is that an exhaust gas swirl is reduced and furthermore, for each load condition of the turbine or Operating condition of the turbine improves the flow.
  • the guide blade is formed such that the Turning is rotatable.
  • the Leitblatt is around a rotation axis rotatably mounted.
  • the axis of rotation runs here essentially perpendicular to the direction of incidence. Thereby is the Leitblattaerodynamik changed overall.
  • the outer shape of the deflection surface is adjustable educated.
  • the Leitblatt comprises a in the Leading edge located front part and one in the trailing edge located rear part.
  • the located in the trailing edge Rear part is rotatably mounted about a rotation axis.
  • the The axis of rotation is substantially parallel to the trailing edge educated. .
  • the rear part is in a further embodiment the invention designed such that the rear part in a flow direction directly from the leading edge to the trailing edge, is moved.
  • the length in the direction of flow a respective Leitblattes can thereby individually be changed.
  • the Leitblatt be shortened or extended in the flow direction.
  • FIG 1 is a perspective view of a Prior art gas turbine 1 can be seen.
  • rotor 2 At one rotatably mounted rotor 2 is inter alia an end turbine stage 3, which includes a plurality of blades 4, mounted.
  • the one Lower part 5a and an upper part 5b Around the rotor 2 around an outer housing is arranged, the one Lower part 5a and an upper part 5b has.
  • the rotor 2 is in order a rotation axis 6 rotatably mounted.
  • a flow medium flows in operation parallel to the axis of rotation 6 in the direction the turbine stage 3.
  • the diffuser 7 After the diffuser 7 flows the flow medium under a direction of incidence by a So-called bearing star, which also serves as Abströmleit driving 8 referred to as.
  • the Abströmleit prepared 8 comprises six guide blades 9. In alternative embodiments are less or more than six guide blades 9 possible.
  • the flow medium flows at a varying outflow angle after the turbine stage 3 off.
  • the outflow angle hangs from a load attached to the rotor 2.
  • the Abströmleit driving 8 comprises a rotor-side end 10 and a stator-side end 11.
  • the rotor-side end 10 is formed such that the rotor 2 rotatably supported therein becomes.
  • FIG 2 is a perspective view of a Leitblatt 9 to see.
  • a flow medium to the guide blade 9.
  • the direction of arrival 12th depends on the outflow angle.
  • the flow medium hits initially on a leading edge 13, flows around each of a deflection 15 and then flows from a trailing edge 14 out of the gas turbine 1 out.
  • the guide blade 9 is formed such that the guide blade 9 with respect to a course of its deflection 15 is adjustable relative to the direction of incidence 12.
  • the deflection surface (15) can be rotated be.
  • the outer Shape of the deflection surface (15) to be adjustable.
  • FIG. 3 shows a cross section of the guide blade 9.
  • the viewing direction is in this case substantially perpendicular to the direction of incidence 12 in the direction of the axis of rotation 6.
  • the guide blade 9 is in this case mounted rotatably about a rotation axis 16.
  • This axis of rotation 16 is substantially perpendicular to the direction of incidence 12.
  • the axis of rotation 16 is in this embodiment substantially in the middle of the guide blade 9.
  • the axis of rotation 16 can also be attached in an alternative embodiment closer to the leading edge 13 or the trailing edge 14.
  • the guide blade 9 is rotated about the axis of rotation 16.
  • the guide blade 9 is thereby rotated about the axis of rotation 16 either clockwise 17 or counterclockwise 18.
  • a flow medium, which impinges on the guide blade 9 in the direction of arrival 12, can be deflected thereby.
  • FIG. 4 shows a second embodiment of the guide blade 9 to see.
  • the guide blade 9 comprises in this embodiment a the leading edge 13 comprehensive front part 20 and a Trailing edge 14 comprehensive rear part 19.
  • the front part 20 is rigid.
  • the front part 20 can also be rotated about a further axis of rotation be stored.
  • the rear part 19 is designed such that it is rotatably mounted about a rotation axis 21.
  • the rotation axis 21 is in this case in a front region 22 of the rear part 19th appropriate.
  • a rear portion 23 is thereby either the Clockwise 17 or counterclockwise 18 movable.
  • FIG 5 is a third embodiment of the Leitblattes 9 to see.
  • the rear part 19 in the flow direction either to the direction of incidence (represented by the Arrow 24) or against the direction of incidence (by the arrow 25).
  • the front part 20 of the Leitblattes 9 can in another alternative embodiment to another Rotary axis are rotatably mounted.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP03018164A 2003-08-08 2003-08-08 Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération Withdrawn EP1505263A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP03018164A EP1505263A1 (fr) 2003-08-08 2003-08-08 Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération
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
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 (1)

Application Number Priority Date Filing Date Title
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
EP1505263A1 true EP1505263A1 (fr) 2005-02-09

Family

ID=33547671

Family Applications (2)

Application Number Title Priority Date Filing Date
EP03018164A Withdrawn EP1505263A1 (fr) 2003-08-08 2003-08-08 Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération
EP04740600A Withdrawn EP1651842A1 (fr) 2003-08-08 2004-07-02 Dispositif de guidage dans un passage d'echappement pour une turbomachine et procede d'operation

Family Applications After (1)

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

Country Status (2)

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

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1898055A2 (fr) 2006-09-01 2008-03-12 United Technologies Corporation Aube statorique à géométrie variable pour un moteur à turbine à gaz
EP2644838A1 (fr) * 2012-03-27 2013-10-02 Alstom Technology Ltd Boîtier de gaz d'échappement d'une turbine à gaz
EP2746535A1 (fr) * 2012-12-20 2014-06-25 General Electric Company Conception de profil aérodynamique, à double rangée étagée, pour trame d'échappement de turbine à gaz
CN103998725A (zh) * 2011-12-14 2014-08-20 西门子能源有限公司 包括周向叶片的燃气涡轮发动机排气扩散器
EP3954875A3 (fr) * 2020-08-04 2022-05-04 MTU Aero Engines AG Aube directrice, étage de compresseur, turbomachine et procédé pour exploiter une turbomachine

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

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1898055A2 (fr) 2006-09-01 2008-03-12 United Technologies Corporation Aube statorique à géométrie variable pour un moteur à turbine à gaz
EP1898055A3 (fr) * 2006-09-01 2011-06-15 United Technologies Corporation Aube statorique à géométrie variable pour un moteur à turbine à gaz
CN103998725A (zh) * 2011-12-14 2014-08-20 西门子能源有限公司 包括周向叶片的燃气涡轮发动机排气扩散器
CN103998725B (zh) * 2011-12-14 2016-05-25 西门子能源有限公司 包括周向叶片的燃气涡轮发动机排气扩散器
EP2644838A1 (fr) * 2012-03-27 2013-10-02 Alstom Technology Ltd Boîtier de gaz d'échappement d'une turbine à gaz
EP2746535A1 (fr) * 2012-12-20 2014-06-25 General Electric Company Conception de profil aérodynamique, à double rangée étagée, pour trame d'échappement de 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
EP3954875A3 (fr) * 2020-08-04 2022-05-04 MTU Aero Engines AG Aube directrice, étage de compresseur, turbomachine et procédé pour exploiter une turbomachine
US11555500B2 (en) 2020-08-04 2023-01-17 MTU Aero Engines AG Guide vane

Also Published As

Publication number Publication date
EP1651842A1 (fr) 2006-05-03
WO2005019604A1 (fr) 2005-03-03

Similar Documents

Publication Publication Date Title
DE60133629T2 (de) Verfahren zum betrieb einer gasturbine mit verstellbaren leitschaufeln
DE602004006922T2 (de) Leitschaufelanordnung für ein Gasturbinentriebwerk
EP1219781B1 (fr) Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine
CH703553A2 (de) Profilierter axial-radialer Auslassdiffusor.
EP0417433B1 (fr) Turbine axiale
DE102008017844A1 (de) Strömungsmaschine mit Fluid-Injektorbaugruppe
DE102009044024A1 (de) System und Verfahren zum Beeinflussen einer Turbinenabgastemperatur
DE102009059224B4 (de) Gegenstrom-Hochdruck-Niederdruck-Dampfturbine
WO1999063204A1 (fr) Turbine a gaz ainsi que procede pour le refroidissement d'un etage de turbine
DE2853340A1 (de) Vorrichtung zum erzeugen eines vorwirbels am verdichtereingang eines turbinen-triebwerkes
DE2454054A1 (de) Innentriebwerk bzw. gasgenerator fuer gasturbinentriebwerke
EP3064706A1 (fr) Rangée d'aubes directrices pour une turbomachine traversée axialement
EP2165077A1 (fr) Dispositif de fourniture d'air destiné en particulier à un système de fourniture d'air des cellules à combustible
CH703666A2 (de) Einrichtung mit einer Turbine, einem Diffusor und einem Nabenströmungspfadprofil.
DE19850732A1 (de) Axialturbine
DE102011054307A1 (de) Endstück für Turbinenlaufschaufel-Deckband
DE2412242C2 (de) Mantelstromtriebwerk
EP1505263A1 (fr) Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération
DE102010044819B4 (de) Axialturbine und ein Verfahren zum Abführen eines Stroms von einer Axialturbine
DE112016005055T5 (de) Verfahren und vorrichtung zur inbetriebnahme einer gasturbine
DE2743111C2 (de) Fahrzeug-Gasturbinenanlage
EP1715224A1 (fr) Joint d'étanchéité de turbomachine
WO2009080439A1 (fr) Plaque de protection contre l'érosion pour aubes mobiles
DE102010040823A1 (de) Turbolader
EP1561909A1 (fr) Diffuseur, turbomachine et procédé de récupération de pression dans une turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK

AKX Designation fees paid
REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20050810