EP1571298A1 - Aube pour turbomachine et turbomachine - Google Patents

Aube pour turbomachine et turbomachine Download PDF

Info

Publication number
EP1571298A1
EP1571298A1 EP04004893A EP04004893A EP1571298A1 EP 1571298 A1 EP1571298 A1 EP 1571298A1 EP 04004893 A EP04004893 A EP 04004893A EP 04004893 A EP04004893 A EP 04004893A EP 1571298 A1 EP1571298 A1 EP 1571298A1
Authority
EP
European Patent Office
Prior art keywords
blade
platform
adjustable
turbomachine
platforms
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Withdrawn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
EP04004893A
Other languages
German (de)
English (en)
Inventor
Christian Menke
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 EP04004893A priority Critical patent/EP1571298A1/fr
Priority to PCT/EP2005/001649 priority patent/WO2005085601A1/fr
Publication of EP1571298A1 publication Critical patent/EP1571298A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
    • 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

Definitions

  • the invention relates to a blade with an upper platform and a lower platform and one between them arranged airfoil for adjusting a flow cross-section through a turbomachine. Furthermore it concerns the invention is a turbomachine with such Shovel.
  • turbomachines z. B. turbocharger, compressor, Gas turbines generally become a fixed operating point designed so that they are at a predetermined Rated load to achieve the highest efficiency.
  • the the Turbomachine defining design parameters, such as Mass flow, rated power, absorption capacity, maximum possible Turbine inlet temperature, turbine pressure ratio and compressor pressure ratio and more, will be during the planning the turbomachine set. Then the Components calculated according to the parameters and in a fixed Body shape made.
  • the relevant components are replaced.
  • the new components differ in shape and Size mostly small compared to the original built-in and then effect the desired change of said Parameter. It is also conceivable that an operator of the machine a lower than originally planned net output achieve for a certain period of time and why would like to change the operating point of the machine to over this period the machine with improved efficiency to operate.
  • the invention is therefore based on the object, a particularly simply designed blade to change the efficiency and indicate the power output of the turbomachine. Furthermore, this is a particularly simple designed Turbomachine and a method for operating the Specify turbomachine.
  • the first object is achieved by a scoop with an upper platform and a lower one Platform and an airfoil arranged between them, wherein for setting a variable inflow area in Area of the airfoil at least one of the platforms is designed adjustable.
  • the invention is based on the consideration that a variable adjustment of a flow cross-section at a Turbomachine be possible in a simple manner should.
  • a scoop is provided indicate which, at least in a partial region of the airfoil adapted to change their inflow is.
  • the blade has at least one Platform - an upper and / or a lower platform - on, which is adjustable. An enlargement of the Flow cross section usually leads to an increase in performance.
  • the inflow area formed in the area of the blade leaf in the length increases or decreases.
  • the bucket can be adjusted symmetrically become.
  • only one of the Platforms or both are adjusted asymmetrically.
  • Prefers is the location of at least one of the platforms in one Range from 5 mm to 10 mm, in particular from 5 mm to 7 mm or from 7 mm to 9 mm, adjustable. The can both platforms symmetrical or separated from each other become.
  • the upper platform may or may and / or the lower platform adjustable about a rotation axis be arranged.
  • the end in the Platforms arranged airfoil rotated about its longitudinal axis, so that the flow cross section changes.
  • the blade is about the axis of rotation in one area rotated by +/- 10 ° of the so-called crest angle.
  • the upper one is or is Platform and / or the lower platform each with a adjustably arranged U-shaped profile, z. B. a U-shaped Ring, provided.
  • the U-shaped profile is in the art a lid placed on the platform in question, so that the legs or the circumferential ring the platform outer wall surrounds.
  • a Opening, in particular a slot, for receiving the associated End of the blade provided in the bridge of the U-shaped profile.
  • the respective platform is fixed to the turbomachine arranged, with the U-shaped profile in vertical Direction opposite the platform separately adjustable is arranged.
  • the U-shaped Profile to be arranged adjustable about a rotation axis.
  • the upper platform and / or the lower platform each with an associated adjustment Mistake.
  • the adjusting device integrated into the respective platform. This is the Adjustment to immediate temperature and Flow stresses arranged sufficiently safe.
  • Prefers is the adjustment as an actuator, as a spring element or formed as a hydraulic element. It is the platform itself or the u-shaped profile using the Adjustment device stepless or in steps in vertical Direction or about the axis of rotation movable.
  • the respective platform is advantageously with at least one opening for supplying a cooling medium in one between the respective platform and the associated one Profile formed cavity.
  • a plurality of annularly arranged to form a wave Blades a row of blades, in particular a row of vanes.
  • the guide vane row are the upper and radial outer platforms and the lower and radially inner Platforms each have an associated adjusting ring in Radial direction of the shaft formed adjustable.
  • the adjusting rings are symmetrically movable.
  • the blade is in a turbomachine for Setting a variable flow cross section used.
  • the blade for adjustment serve the swallowing capacity in a turbomachine.
  • the task directed to the methods is characterized by the features of claim 17 solved.
  • the advantages achieved by the invention are in particular in that by a shovel with adjustable platforms in a particularly simple manner, the flow cross-section a turbomachine during operation of these changeable is.
  • the respective blade in particular its blade and / or their platforms
  • the adjusting device by means of the adjusting device be brought into a desired position, the one Operating requirements corresponding flow cross-section, in particular the minimum flow cross-section of the flow path, causes.
  • the bucket during operation the turbomachine adjusted, in particular twisted become. It can be a larger operating area, even in the Part load range, with optimized efficiency and optimized Performance to be driven.
  • a refilling is safely avoided by blades.
  • the blade 1 shows a blade 1 with an upper platform 2a and a lower platform 2b and arranged between them Blade sheet 4.
  • the blade 1 is part, for example a blade row of a turbomachine, not shown, z. B. a compressor, a gas turbine.
  • a variable flow cross section Qs of Turbomachine in the region of the airfoil 4 is at least one of the platforms 2a or 2b adjustable. With the adjustment of the platforms changes at the same time the inflow surface of the airfoil that can be flown by the hot gas.
  • the platforms 2a or 2b are both Platforms 2a and 2b made adjustable.
  • je According to the type and function of the bucket 1, only one of the Platforms 2a and 2b be designed adjustable.
  • the platform in question is 2a or 2b in the vertical direction along the arrow P1 arranged adjustable.
  • the two platforms 2a and 2b are symmetrical and synchronous to the adjustment of the flow cross section Qs moves.
  • the respective platform 2a or 2b are moved separately.
  • the two platforms 2a and 2b about a rotation axis D in particular about the longitudinal axis of Shovel 1, adjustable.
  • the two Platforms 2a and 2b moved symmetrically and synchronously.
  • Rotation of the blade 1 about the axis of rotation D becomes the airfoil 4, which end to the respective platform 2a or 2b is arranged, rotated, so that the flow cross-section Qs changes along the arrow P3.
  • each platform 2a, 2b one or more adjusting devices 6 may be provided.
  • the respective adjusting device 6 is as an actuator, spring element or hydraulic Element formed.
  • the nature and structure of the Adjustment 6 are significantly determined by the shape the relevant blade 1, in particular of their platforms 2a, 2b, and the airfoil 4. Preferred is the adjustment 6 integrated into the respective platform 2a, 2b.
  • the respective platform 2a, 2b with an adjustable arranged U-shaped profile 8a and 8b provided.
  • the respective U-shaped profile 8a, 8b, z. B. a U-shaped ring is, like the platform 2a, 2b itself, in the vertical direction adjustable along the arrow P1 and / or about the axis of rotation D, so that the flow cross-section Qs along the Arrows P2 or P3 changes accordingly.
  • FIG. 2 shows, by way of example, a cross-section through a blade 1 with the parameters characterizing it, such as depression angle ⁇ s , minimum principal axis of inertia ⁇ , maximum principal axis of inertia ⁇ , direction of axial velocity a, direction of circumferential velocity u, shear center Q and center of gravity S.
  • the platforms 2a and 2b or the associated u-shaped Profiles 8a and 8b become the intermediate airfoil 4 also rotated around the area concerned, so that resulting from the position of the airfoil Flow cross section Qs changes.
  • the platforms 2a and 2b and the associated U-shaped profiles 8a and 8b respectively in one Range from -2.5 mm to +2.5 mm compared to a middle one Basic adjustment adjustable, so that both adjustable Platforms your distance to each other on an order of magnitude from 0-10 mm.
  • the blade 1 in area 14 between the respective platform 2a or 2b and the associated profile 8a and 8b with a sealing element 12 be provided.
  • the blade 1, in particular the respective platform 2a, 2b, with at least one Opening 14 for supplying a cooling medium in between the relevant platform 2a or 2b and the associated Profile 8a and 8b formed cavity H be provided.
  • a cooling medium for example, cold air is used.
  • the above-described blade 1 with an adjustable inflow surface by the adjustment of the platforms 2a, 2b and / or the profiles 8a, 8b in the vertical direction or in order a rotation axis is preferably suitable for turbomachines and their adjustment of the swallowing capacity.
  • the absorption capacity of a gas turbine is thereby of the smallest flow cross-section Qs determines which in the flow path the mass flow of the gas turbine is located.
  • the flow path The mass flow is the path in which the sucked Air through the compressor and in the one to one Hot gas burned fuel-compressor air mixture in the Turbine flows, with the smallest flow cross section of Flow path is usually in the region of the guide vane ring the first turbine stage is located.
  • the guide vanes have the first turbine stage, the adjustment of the platforms 2b, 2a on, leaving the gas turbine in different operating range operated with optimized efficiency and optimized performance can be. This adjustment can be unique the operation of the gas turbine and / or during operation be made.
  • the vanes of subsequent turbine stages in particular those of the second Turbine stage to equip with adjustable platforms.
  • FIG. 3 shows a cross section through a blade row R with a plurality of radially arranged to a shaft blades 1 a not shown turbomachine with a flow cross-section Qs.
  • the respective blade 1 is over the lower platform 2b is arranged on the fastening ring 16.
  • the upper platform 2a and the lower platform 2b are respectively provided with the U-shaped profile 8a and 8b.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
EP04004893A 2004-03-02 2004-03-02 Aube pour turbomachine et turbomachine Withdrawn EP1571298A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP04004893A EP1571298A1 (fr) 2004-03-02 2004-03-02 Aube pour turbomachine et turbomachine
PCT/EP2005/001649 WO2005085601A1 (fr) 2004-03-02 2005-02-17 Turbine a gaz stationnaire a flux axial

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04004893A EP1571298A1 (fr) 2004-03-02 2004-03-02 Aube pour turbomachine et turbomachine

Publications (1)

Publication Number Publication Date
EP1571298A1 true EP1571298A1 (fr) 2005-09-07

Family

ID=34745986

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04004893A Withdrawn EP1571298A1 (fr) 2004-03-02 2004-03-02 Aube pour turbomachine et turbomachine

Country Status (2)

Country Link
EP (1) EP1571298A1 (fr)
WO (1) WO2005085601A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008065447A1 (fr) * 2006-12-01 2008-06-05 Parsons Brinckerhoff Limited Dispositif de régulation d'écoulement
US7900431B2 (en) 2005-11-04 2011-03-08 Parsons Brinckerhoff Limited Process and plant for power generation
DE102010063701A1 (de) * 2010-12-21 2012-06-21 Robert Bosch Gmbh Verfahren und Vorrichtung zur Nutzung von Abwärme einer Wärmekraftmaschine
EP2474709A1 (fr) * 2011-01-05 2012-07-11 Siemens Aktiengesellschaft Anneau statorique aubagé pour une turbine à vapeur doté d'un dispositif d'ajustement précis de la capacité de débit et procédé associé

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR667306A (fr) * 1928-02-02 1929-10-15 Rateau Soc Dispositif de réglage des conditions de marche des machines centrifuges
US4557665A (en) * 1982-05-28 1985-12-10 Helset Engineering Company Limited Variable inlet area turbine
EP1128025A2 (fr) * 2000-02-25 2001-08-29 Man Nutzfahrzeuge Ag Turbomachine radiale

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB737473A (en) * 1952-10-03 1955-09-28 Napier & Son Ltd Turbines and like machines having adjustable guide blades
GB743782A (en) * 1952-11-07 1956-01-25 Power Jets Res & Dev Ltd Nozzle assemblies for bladed fluid flow machines such as turbines and compressors

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR667306A (fr) * 1928-02-02 1929-10-15 Rateau Soc Dispositif de réglage des conditions de marche des machines centrifuges
US4557665A (en) * 1982-05-28 1985-12-10 Helset Engineering Company Limited Variable inlet area turbine
EP1128025A2 (fr) * 2000-02-25 2001-08-29 Man Nutzfahrzeuge Ag Turbomachine radiale

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7900431B2 (en) 2005-11-04 2011-03-08 Parsons Brinckerhoff Limited Process and plant for power generation
WO2008065447A1 (fr) * 2006-12-01 2008-06-05 Parsons Brinckerhoff Limited Dispositif de régulation d'écoulement
US8206089B2 (en) 2006-12-01 2012-06-26 Parsons Brinckerhoff Limited Flow control device
DE102010063701A1 (de) * 2010-12-21 2012-06-21 Robert Bosch Gmbh Verfahren und Vorrichtung zur Nutzung von Abwärme einer Wärmekraftmaschine
DE102010063701B4 (de) * 2010-12-21 2019-02-07 Robert Bosch Gmbh Verfahren und Vorrichtung zur Nutzung von Abwärme einer Wärmekraftmaschine
EP2474709A1 (fr) * 2011-01-05 2012-07-11 Siemens Aktiengesellschaft Anneau statorique aubagé pour une turbine à vapeur doté d'un dispositif d'ajustement précis de la capacité de débit et procédé associé
WO2012092996A1 (fr) * 2011-01-05 2012-07-12 Siemens Aktiengesellschaft Couronne d'aubes directrices pour une turbine à vapeur présentant un ajustage précis du débit de dimensionnement et procédé associé
CN103282605A (zh) * 2011-01-05 2013-09-04 西门子公司 用于蒸汽轮机的、能够精细调节最大通流量的导向叶片环和相关的方法
CN103282605B (zh) * 2011-01-05 2015-08-05 西门子公司 用于蒸汽轮机的、能够精细调节最大通流量的导向叶片环和相关的方法

Also Published As

Publication number Publication date
WO2005085601A1 (fr) 2005-09-15

Similar Documents

Publication Publication Date Title
DE69718673T2 (de) Kühlbare schaufelstruktur für eine gasturbine
DE112006002658B4 (de) Turbomaschinenschaufel
EP1394364B1 (fr) Turbosoufflante et son anneau de guidage
DE602004006323T2 (de) Verfahren zur Herstellung einer Turbine mit Turbinenschaufeln unterschiedlicher Resonanzfrequenzen samt einer solchen Turbine
EP3611387B1 (fr) Roue à aubes d'une turbomachine
EP2455584B1 (fr) Turbine à gaz avec des moyens de contrôle de refroidisment comprenant partialement des alliages à mémoire de forme
DE4309636C2 (de) Radialdurchströmte Abgasturboladerturbine
EP2989298B1 (fr) Turbocompresseur à gaz d'échappement
DE2953300C1 (de) Abdampfstutzen einer Turbine
EP3269941B1 (fr) Grille d'aube réglable pour turbomachines
EP3064706A1 (fr) Rangée d'aubes directrices pour une turbomachine traversée axialement
EP1012445B1 (fr) Aube pour une turbomachine, et turbine a vapeur
EP1557536A1 (fr) Turbine à gaz avec rotor axialement déplaçable
DE60019965T2 (de) Axialturbine für gase
WO2005085601A1 (fr) Turbine a gaz stationnaire a flux axial
EP0532907A1 (fr) Turbine axiale
EP2404038B1 (fr) Rotor à aubage intégral et procede de fabrication d'un rotor à aubage intégral
WO2014012725A1 (fr) Diffuseur parallèle pour une machine à fluide
DE3413304A1 (de) Verstellbare leitbeschaufelung fuer eine turbomaschine
DE10029807C1 (de) Abgasturbolader für eine Brennkraftmaschine
DE60026849T2 (de) Leitschaufel für eine abgasturboladerturbine
DE10352789B4 (de) Gasturbine
EP3298285A1 (fr) Aube directrice pour un diffuseur d'un compresseur centrifuge
WO2012130879A1 (fr) Augmentation du rendement d'un étage régulateur d'une turbine à action
EP0408956B1 (fr) Roue ouverte à ailettes

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 PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK

AKX Designation fees paid
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: 20060308

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566