EP2268900A1 - Aube pour moteur thermique rotatif - Google Patents

Aube pour moteur thermique rotatif

Info

Publication number
EP2268900A1
EP2268900A1 EP09724433A EP09724433A EP2268900A1 EP 2268900 A1 EP2268900 A1 EP 2268900A1 EP 09724433 A EP09724433 A EP 09724433A EP 09724433 A EP09724433 A EP 09724433A EP 2268900 A1 EP2268900 A1 EP 2268900A1
Authority
EP
European Patent Office
Prior art keywords
blade
airfoil
angle
trailing edge
flow lines
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.)
Ceased
Application number
EP09724433A
Other languages
German (de)
English (en)
Inventor
Willy Heinz Hofmann
Michael Huber
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2268900A1 publication Critical patent/EP2268900A1/fr
Ceased legal-status Critical Current

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.
EP09724433A 2008-03-28 2009-03-04 Aube pour moteur thermique rotatif Ceased EP2268900A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH4672008 2008-03-28
PCT/EP2009/052533 WO2009118234A1 (fr) 2008-03-28 2009-03-04 Aube pour moteur thermique rotatif

Publications (1)

Publication Number Publication Date
EP2268900A1 true EP2268900A1 (fr) 2011-01-05

Family

ID=39870460

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09724433A Ceased EP2268900A1 (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)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BR112016014668A2 (pt) 2013-12-23 2017-08-08 Cytec Ind Inc Método para sintetizar um polímero de poliacrilonitrila, polímero de poliacrilonitrila, e, método para produzir uma fibra de carbono
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
US11629599B2 (en) 2019-11-26 2023-04-18 General Electric Company Turbomachine nozzle with an airfoil having a curvilinear trailing edge

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2899128A (en) * 1959-08-11 Vaghi

Family Cites Families (9)

* 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.
US4433955A (en) * 1981-03-26 1984-02-28 General Electric Company Turbine arrangement
GB2164098B (en) * 1984-09-07 1988-12-07 Rolls Royce Improvements in or relating to aerofoil section members for turbine engines
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
EP0916812B1 (fr) * 1997-11-17 2003-03-05 ALSTOM (Switzerland) Ltd Etage final pour turbine axial

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2899128A (en) * 1959-08-11 Vaghi

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2009118234A1 *

Also Published As

Publication number Publication date
US20110038733A1 (en) 2011-02-17
WO2009118234A1 (fr) 2009-10-01

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
EP2024606B1 (fr) Conduit d'écoulement annulaire pour une turbomachine pouvant être traversée par un courant principal dans le sens axial
EP2108784B1 (fr) Turbomachine dotée d'un composant d'injecteur de fluide
EP2260180B1 (fr) Aube directrice pour turbine a gaz
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
DE102009052142B3 (de) Axialverdichter
DE102004055439A1 (de) Strömungsarbeitsmaschine mit dynamischer Strömungsbeeinflussung
WO2009121716A1 (fr) Aube pour turbine à gaz
DE10340773A1 (de) Rotor einer Dampf- oder Gasturbine
DE102007027427A1 (de) Schaufeldeckband mit Überstand
CH701537B1 (de) Spitzendeckplatte mit Dämpfungsrippen für eine Rotorschaufel, die in eine Rotorscheibe einer Turbinenanlage einsetzbar ist.
EP3064706A1 (fr) Rangée d'aubes directrices pour une turbomachine traversée axialement
CH707459A2 (de) Innenkühlungsaufbau einer Turbinenlaufschaufel.
WO2009118234A1 (fr) Aube pour moteur thermique rotatif
DE102019008225B4 (de) Schaufel für eine rotationsmaschine oder fluidmaschine und damit ausgestattete rotationsmaschine oder fluidmaschine
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
DE102019109023B3 (de) Verdichterlaufrad mit wechselnder Beschaufelung

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

17P Request for examination filed

Effective date: 20100921

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 HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA RS

RIN1 Information on inventor provided before grant (corrected)

Inventor name: HUBER, MICHAEL

Inventor name: HOFMANN, WILLY HEINZ

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20140703

REG Reference to a national code

Ref country code: DE

Ref legal event code: R003

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

Free format text: STATUS: THE APPLICATION HAS BEEN REFUSED

18R Application refused

Effective date: 20150418