WO2009118234A1 - Aube pour moteur thermique rotatif - Google Patents

Aube pour moteur thermique rotatif Download PDF

Info

Publication number
WO2009118234A1
WO2009118234A1 PCT/EP2009/052533 EP2009052533W WO2009118234A1 WO 2009118234 A1 WO2009118234 A1 WO 2009118234A1 EP 2009052533 W EP2009052533 W EP 2009052533W WO 2009118234 A1 WO2009118234 A1 WO 2009118234A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
airfoil
angle
trailing edge
flow lines
Prior art date
Application number
PCT/EP2009/052533
Other languages
German (de)
English (en)
Inventor
Willy Heinz Hofmann
Michael Huber
Original Assignee
Alstom Technology Ltd
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 Alstom Technology Ltd filed Critical Alstom Technology Ltd
Priority to EP09724433A priority Critical patent/EP2268900A1/fr
Publication of WO2009118234A1 publication Critical patent/WO2009118234A1/fr
Priority to US12/892,555 priority patent/US20110038733A1/en

Links

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2250/70—Shape

Definitions

  • the present invention relates to the field of thermal machines. It relates to a blade for a rotary thermal machine according to the preamble of claim 1.
  • Fig. 1 shows a gas turbine 10 with sequential combustion, in which along a shaft 19, a compressor 11, a first combustion chamber 14, a high-pressure turbine 15, a second combustion chamber 17 and a low-pressure turbine 18 are arranged in order.
  • the compressor 1 1 and the two turbines 15 (HD), 18 (ND) are part of a rotor which rotates about the axis 19.
  • the compressor 1 1 compresses the intake air, this compressed air then flows into a plenum and from there into the first combustion chamber.
  • This combustion chamber is with Premix burners operated, as they emerge for example from EP-A1 -0 321 809, further also from EP-A2-0 704 657.
  • the compressed air flows into the premix burners where mixing with at least one fuel takes place.
  • This fuel / air mixture then flows into the first combustion chamber 14, in which this mixture passes to form a stable flame front for combustion.
  • the resulting hot gas is partially expanded in the subsequent high-pressure turbine 15 under work performance and then flows into the second combustion chamber 17, where a further fuel supply 16 takes place. Due to the high temperatures, which still has the hot gas partially released in the high-pressure turbine 15, combustion takes place in the second combustion chamber 17, which combustion is based on autoignition.
  • the hot gas reheated in the second combustion chamber 17 is then expanded in a multistage low-pressure turbine 18, in which blade rows of blades and vanes are alternately arranged in succession.
  • the low-pressure turbine 18 includes a blading 29 in which a plurality of rows of blades and vanes are arranged behind one another and alternately in the flow direction.
  • the vanes have an airfoil (22 in Fig. 2) extending radially between a cover plate (21 in Fig. 2) and a blade head (23 in Fig. 2).
  • Both ends (21, 23) of the guide blade define in the radial direction the flow cross-section of a hot gas channel through which a hot gas stream (30 in FIG. 2) flows and impeller blade 22 of the blade is supplied with corresponding flow lines, of which three flow lines in FIG located and provided with the reference numeral 26 are.
  • the flow cross section of the hot gas duct widens significantly in the flow direction in the manner of a turbine.
  • the airfoils of guide vanes in gas turbines or steam turbines are designed so that the local flow lines the flowing working medium (hot gas or steam) at the intersection with the trailing edge of the airfoil extend approximately perpendicular to the trailing edge.
  • the trailing edge can not be completely and consistently oriented perpendicular to the flow lines, because this would require a strong sweeping and tilting, for example on the blade tip, but not possible because of the space available and the assembly is, apart from the fact that such a configuration, even if accomplish this Hesse, would otherwise have serious fluidic disadvantages.
  • the invention aims to remedy this situation. It is an object of the invention to provide a blade, which has a fluidically optimal
  • Body has within the predetermined flow cross-section, and this at a maximized efficiency.
  • Essential to the invention is a shape of the airfoil, in which the
  • the angle formed by the flow lines with the trailing edge of the airfoil deviates to a limited extent from a right angle, as would be the case with a constant flow cross section, wherein the mentioned angle, ie the flow lines with the trailing edge of the airfoil, in particular, but not exclusively, smaller than 90 °, ie in certain cases the angle can be greater than 90 °.
  • a proven embodiment of the invention is characterized in that the deviation with respect to this angle, which form the flow lines with the trailing edge of the airfoil, in the range between 0 ° and -10 ° resp. + 10 ° to a right angle.
  • the deviation of the angle that the flow lines with the trailing edge of the Formed over the largest portion of the height of the airfoil in the range between O ° and -5 ° and possibly between O ° and + 5 ° the deviations within the angular range must not be uniform over the entire blade length, ie the flow lines must do not have the same size deviation within certain flow sections along the blade length. Also, an oscillating deviation within the underlying angular range along the entire blade length is possible.
  • FIG. 2 shows a perspective side view of a guide blade, for example for use in a gas turbine according to FIG. 1, and furthermore according to a preferred embodiment of the invention, FIG.
  • Fig. 3 shows the deviation of the angle
  • Trailing edge of a comparable to Fig. 2 blade form from the right angle above the blade height when the blade has a completely rectangular “stacking" and Fig. 4 shows the deviation of the angle, the flow lines with the
  • Trailing edge of the blade shown in Fig. 2 form, from the right angle to the blade height according to an embodiment of the invention.
  • FIG. 2 shows a typical vane conventionally used in a turbine of a gas turbine group, for example in the low pressure turbine of a gas turbine with sequential combustion, as shown in FIG.
  • the guide vane 20 comprises a relatively strongly curved airfoil 22 in the space that extends in the longitudinal direction (in the radial direction relative to the rotor of the gas turbine) between a vane head 23 and a cover plate 21 and in the flow direction of the hot gas stream 30 of a
  • Leading edge 27 extends to a trailing edge 28. Between the two edges 27 and 28, the airfoil 22 is bounded to the outside by a suction side 31 and an (opposite) pressure side (not visible in Fig. 2).
  • the hot gas stream 30 flows from the leading edge 27 to the trailing edge 28 on the airfoil 22 along flow lines 26, of which three such flow lines are shown by way of example in FIG. are symbolized.
  • the flow lines 26 At their intersection with the trailing edge 28, the flow lines 26 each form an angle ⁇ which changes in the radial direction and thus establishes a dependence on the height h of the airfoil 22.
  • this angle ⁇ over the entire height of the airfoil 22 is equal to 90 °, this would correspond to a complete right-angled filling ("filling orthogonal stacking") of the blade, accordingly the value 0 would result for the deviation ⁇ -90 ° from the right angle. as shown in the diagram of Fig. 3, in which the function ⁇ -90 ° (h) is shown.
  • this fully right-angled threading is replaced by a less stringent "softened" orthogonal stacking, in which the angle ⁇ remains close to a right angle but can deviate to a limited extent from it.
  • the diagram corresponding to Fig. 3 for such a "softened" right-angled threading is shown in Fig. 4.
  • the deviation ⁇ -90 ° of the angle ⁇ from the right angle is in the negative range ( ⁇ 0) and in the present example is all to one Angular range between 0 and -10 ° limited ..
  • the deviation starts with a maximum value of almost -10 °, then goes back to zero within a very short distance and remains in the present example over most of the height below -5 ° .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une aube (20) de moteur thermique rotatif, notamment une aube directrice de turbine basse pression de turbine à gaz, à combustion séquentielle. Cette aube comprend une pale (22) s'étendant sensiblement dans le sens radial et parcourue en périphérie par un milieu de travail, ladite pale étant délimitée dans le sens d'écoulement par une arête avant (27) et par une arête arrière (28). Les exigences concurrentielles relevant de la technique d'écoulement et de la structure au niveau de l'aube, en cas de forte inclinaison de l'écoulement peuvent être satisfaites du fait que la pale (22) est conformée de sorte que l'angle (a) que les lignes d'écoulement (26) forment avec l'arête arrière (28) de la pale (22) s'écarte dans une mesure limitée de l'angle droit.
PCT/EP2009/052533 2008-03-28 2009-03-04 Aube pour moteur thermique rotatif WO2009118234A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP09724433A EP2268900A1 (fr) 2008-03-28 2009-03-04 Aube pour moteur thermique rotatif
US12/892,555 US20110038733A1 (en) 2008-03-28 2010-09-28 Blade for a rotating thermal machine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH00467/08 2008-03-28
CH4672008 2008-03-28

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US12/892,555 Continuation US20110038733A1 (en) 2008-03-28 2010-09-28 Blade for a rotating thermal machine

Publications (1)

Publication Number Publication Date
WO2009118234A1 true WO2009118234A1 (fr) 2009-10-01

Family

ID=39870460

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2009/052533 WO2009118234A1 (fr) 2008-03-28 2009-03-04 Aube pour moteur thermique rotatif

Country Status (3)

Country Link
US (1) US20110038733A1 (fr)
EP (1) EP2268900A1 (fr)
WO (1) WO2009118234A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3828390A1 (fr) * 2019-11-26 2021-06-02 General Electric Company Buse de turbomachine avec une surface portante dotée d'un bord de fuite curviligne

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
MY182047A (en) 2013-12-23 2021-01-18 Cytec Ind Inc Method for producing carbon fibers from polyacrylonitrile (pan) polymers with low pol ydispersity index (pdi)
PL415835A1 (pl) * 2016-01-18 2017-07-31 General Electric Company Zespół łopatki sprężarki do gazowego silnika turbinowego i sposób kontrolowania strumienia przecieku przez uszczelnienia wokół zespołu łopatki sprężarki do gazowego silnika turbinowego
US11566530B2 (en) 2019-11-26 2023-01-31 General Electric Company Turbomachine nozzle with an airfoil having a circular trailing edge

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US850200A (en) * 1905-11-28 1907-04-16 Gen Electric Turbine bucket and nozzle.
GB2095764A (en) * 1981-03-26 1982-10-06 Gen Electric Turbine arrangement
GB2164098A (en) * 1984-09-07 1986-03-12 Rolls Royce Improvements in or relating to aerofoil section members for turbine engines
EP0916812A1 (fr) * 1997-11-17 1999-05-19 Asea Brown Boveri AG Etage final pour turbine axial

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2899128A (en) * 1959-08-11 Vaghi
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
DE4228879A1 (de) * 1992-08-29 1994-03-03 Asea Brown Boveri Axialdurchströmte Turbine
CH687269A5 (de) * 1993-04-08 1996-10-31 Abb Management Ag Gasturbogruppe.
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner
US5488825A (en) * 1994-10-31 1996-02-06 Westinghouse Electric Corporation Gas turbine vane with enhanced cooling

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US850200A (en) * 1905-11-28 1907-04-16 Gen Electric Turbine bucket and nozzle.
GB2095764A (en) * 1981-03-26 1982-10-06 Gen Electric Turbine arrangement
GB2164098A (en) * 1984-09-07 1986-03-12 Rolls Royce Improvements in or relating to aerofoil section members for turbine engines
EP0916812A1 (fr) * 1997-11-17 1999-05-19 Asea Brown Boveri AG Etage final pour turbine axial

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP2268900A1 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3828390A1 (fr) * 2019-11-26 2021-06-02 General Electric Company Buse de turbomachine avec une surface portante dotée d'un bord de fuite curviligne
US11629599B2 (en) 2019-11-26 2023-04-18 General Electric Company Turbomachine nozzle with an airfoil having a curvilinear trailing edge

Also Published As

Publication number Publication date
EP2268900A1 (fr) 2011-01-05
US20110038733A1 (en) 2011-02-17

Similar Documents

Publication Publication Date Title
EP2025945B1 (fr) Machine de traitement des écoulements dotée d'un creux de paroi de canal de ceinture
DE60133629T2 (de) Verfahren zum betrieb einer gasturbine mit verstellbaren leitschaufeln
EP1609999B1 (fr) Turbo machine
EP2108784B1 (fr) Turbomachine dotée d'un composant d'injecteur de fluide
EP1659293B1 (fr) Turbomachine
DE602004001531T2 (de) Statorschaufel mit Doppelkrümmung
EP2024606B1 (fr) Conduit d'écoulement annulaire pour une turbomachine pouvant être traversée par un courant principal dans le sens axial
EP2255072B1 (fr) Aube directrice pour turbine à gaz et turbine à gaz dotée d'une aube directrice de ce type
EP0916812B1 (fr) Etage final pour turbine axial
EP2132414B1 (fr) Agencement en feuillure
DE102012000915B4 (de) Axialturbine
EP2320030B1 (fr) Rotor et aube de rotor pour une turbomachine axiale
EP2260180A2 (fr) Aube directrice pour turbine a gaz
DE3334880A1 (de) Mehrstufiger radialverdichter, radialrad und verfahren zum verdichten eines fluids
WO2009121716A1 (fr) Aube pour turbine à gaz
DE10340773A1 (de) Rotor einer Dampf- oder Gasturbine
DE102007027427A1 (de) Schaufeldeckband mit Überstand
EP3064706A1 (fr) Rangée d'aubes directrices pour une turbomachine traversée axialement
EP2226511A2 (fr) Turbomachine de travail dotée d'une arrivée de fluide
DE102010017105A1 (de) Rotorschaufeln für Turbinenanlagen
DE102014100087A1 (de) Innenaufbau einer Turbinenlaufschaufel
EP2268900A1 (fr) Aube pour moteur thermique rotatif
DE102017212311A1 (de) Umströmungsanordung zum Anordnen im Heißgaskanal einer Strömungsmaschine
EP1571341B1 (fr) Ventilateur extracteur à étages multiples
DE102010044819A1 (de) Axialturbine und ein Verfahren zum Abführen eines Stroms von einer Axialturbine

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 09724433

Country of ref document: EP

Kind code of ref document: A1

DPE1 Request for preliminary examination filed after expiration of 19th month from priority date (pct application filed from 20040101)
WWE Wipo information: entry into national phase

Ref document number: 2009724433

Country of ref document: EP

NENP Non-entry into the national phase

Ref country code: DE