EP1015736B1 - Aube de turbine et son utilisation - Google Patents

Aube de turbine et son utilisation Download PDF

Info

Publication number
EP1015736B1
EP1015736B1 EP98954146A EP98954146A EP1015736B1 EP 1015736 B1 EP1015736 B1 EP 1015736B1 EP 98954146 A EP98954146 A EP 98954146A EP 98954146 A EP98954146 A EP 98954146A EP 1015736 B1 EP1015736 B1 EP 1015736B1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
slot
wall
blade according
outlet
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.)
Expired - Lifetime
Application number
EP98954146A
Other languages
German (de)
English (en)
Other versions
EP1015736A1 (fr
Inventor
Michael Scheurlen
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
Publication of EP1015736A1 publication Critical patent/EP1015736A1/fr
Application granted granted Critical
Publication of EP1015736B1 publication Critical patent/EP1015736B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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

Definitions

  • the invention relates to a turbine blade that runs along a Main axis is directed and has a wall structure, wherein the wall structure has an interior for guiding cooling fluid surrounds an outer wall with an outer surface and includes an inner surface facing the interior and has an outlet for cooling fluid.
  • the invention relates continue to use such a turbine blade.
  • a gas turbine vane with a guide from Cooling gas for cooling them is described in US Pat. No. 5,419,039.
  • the guide vane is designed as a casting or composed of two castings. It has an interior to supply cooling air from the compressor Gas turbine on. Your exposed to the hot gas flow of the gas turbine, has the wall structure surrounding the air supply a load-bearing inner wall with a largely constant thickness, on which outlets for cooling air are arranged.
  • Such a Outlet is as a cool bag located on the inner wall running a cavity with an outlet opening has, which is referred to as a slot.
  • the cavity is formed by a pocket cover attached to the inner wall, the inner wall and / or the pocket cover so are designed so that between them the cavity with the Exit opening remains.
  • the inner wall is flat and the pocket cover is curved.
  • the inner wall a curvature facing the interior, so that in the curvature a depression is formed.
  • the cavity is in the curvature Cooling bag between the inside wall and the bag cover educated.
  • the pocket cover made in one piece with the inner wall as a casting.
  • the cooler bags are both in the direction of flow of the hot gas as well as perpendicular to the flow direction of the hot gas arranged along the main direction of expansion of the guide vane.
  • the blade surface is therefore of a plurality formed by pocket covers.
  • the cavities are each through which cooling air can be supplied via the air supply, that at the outlet opening into the flow of hot gas emerges and a cooling air film on the blade surface through which the blade surface is cooled.
  • the object of the invention is to provide a turbine blade with a specify coolable wall structure. There is another task in using such a turbine blade specify.
  • Cooling fluid in particular cooling air
  • the thickening facing the interior increases stability the outer wall, so that they are very thin can, which improves the cooling effect.
  • the slot preferably extends over a depth of penetration into the outer wall without penetrating it. Thereby the stability of the outer wall is further increased.
  • the slot preferably extends over the entire depth of penetration a constant cross section. This makes it production-related easy to manufacture.
  • the slot is preferably oriented parallel to the main axis. This has the advantage that when the turbine blade is used in a gas turbine, which gas turbine from one Hot gas is flowed through, the cooling fluid in the direction of flow of the hot gas emerges.
  • the outer wall is preferably made particularly thin. This results in particularly effective cooling. Because of the thickening, even an extremely thin one Outside wall for the outlet a large length-diameter ratio given and a small angle of inclination of the outlet realizable in relation to the outer wall.
  • the slot of the outlet is preferably pointed Angle ⁇ , in particular between 10 ° and 45 °, with respect to Outside wall inclined.
  • cooling air is drawn through the interior the turbine blade flows, warms and passes through the Outlet, which is designed as a slot on the outer surface is in a flow of a flowing around the turbine blade Fluids, especially a hot gas.
  • the slot of the outlet is for use of the turbine blade in a gas turbine, preferably directed along an axis, opposite the direction of flow of the fluid around the acute angle ⁇ is inclined. This ensures that cooling air flowing out of the outlet, which is proportional cool to the fluid, especially a hot gas, is forming a cold film of cooling fluid around the turbine blade. This effectively protects the turbine blade at.
  • the area of the outlet on the inner surface is preferred designed as a depression, in particular as a blind hole, which are introduced into the thickening in the area of the outlet is.
  • the slot cuts the recess, thereby the outlet is formed. This allows the slot and recess composite outlet manufacturing technology just be made.
  • the thickening on the outer wall is preferred formed as a linear increase along the slot.
  • the thickening can contain several depressions.
  • the cross section of the depression is preferably smaller than the cross section of the slot. This forms the recess a choke area and the slot an expanding one Deceleration area.
  • the throttle range is in essentially a quantity control of the cooling fluid flow achievable. Due to the widening slowdown range a reduction in the flow rate of the cooling fluid accessible so that this is immediately downstream of the outlet can lay on the outer wall.
  • the cross section of the recess is smaller than the cross section of the slot is further, the stability of the outer wall improved because the outer wall only about the diameter of the recess and not penetrated over the entire slot length becomes.
  • the height H of the slot is preferably (slot height H) and the diameter D of the depression of the same order of magnitude, especially in the range between 0.5 mm and 1 mm.
  • the Length of the slot L is preferably in Range between 1 cm and 3 cm.
  • the distance between the Slitting in the direction of the main axis is preferably in the range between 0.5 cm and 2 cm.
  • the task aimed at using the turbine blade is solved in that the turbine blade as a moving blade or guide vane in a gas turbine plant, in particular in a gas turbine in the temperatures of significantly above 1000 ° C of the hot gas flowing around the turbines, is used.
  • Such a turbine blade is preferably suitable for the Use in a gas turbine, the turbine blade from a hot gas flows around. At a temperature of the hot gas, those above the melting temperature of the base material the turbine blade is located by one with the turbine blade achievable cooling a failure of the turbine blade avoided.
  • the temperature on the outer wall, the surface temperature is through film cooling as well as cooling over the interior to a non-critical one for the turbine blade Temperature level lowered. Cooling air from the interior leads to a convective transition and heat conduction through the outer wall, creating the surface the outer wall can be cooled sufficiently.
  • the turbine blade 1 shows a turbine blade directed along a main axis 2 1 of a gas turbine shown.
  • the turbine blade 1 has a wall structure 3, which has an interior 4 surrounds for guiding cooling fluid 5, which is not shown in FIG Subareas is divided.
  • the wall structure 3 has an outer wall 6 with an outer surface 7 and one the inner surface 8 facing the interior 4.
  • the outer wall 6 has a plurality of thickenings directed towards the interior 4 11 on. For the sake of clarity, it is only one Thickening 11 shown.
  • the thickening 11 is a recess 12, which is designed as a blind hole, brought in.
  • the outer wall 6 in the area of Thicken 11 on a slot 10 the depression 12th cuts.
  • the recess 12 and the slot 10 together form an outlet 9. This allows one in the interior 4 led cooling fluid 5, cooling air, from the interior 4 to flow through the thickening 11 to the outer surface 7. Outside the turbine blade 1, the cooling air mixes 5 with the flow 13 of a flowing around the turbine blade 1 Hot gas.
  • the outlet 9 shown in FIG. 1 is enlarged in FIG shown.
  • the slot 10 with a slot height H penetrates an acute angle ⁇ over a depth of penetration E into the outer wall 6 and cuts the recess 12, the one Has diameter D.
  • the slot 10 and the recess 12 thus form the outlet 9. Characterized in that the slot 10 the has an acute angle ⁇ , it is achieved that the cooling air 5 immediately downstream of the outlet 9 to the outer wall 6 creates and thus effective film cooling of the outer wall 6 causes.
  • the choice of the diameter D can regulate the flow rate for the cooling fluid 5 be made.
  • FIG 3 shows a turbine blade 1 of a gas turbine in the Top view of the outer wall 6 (see FIG 1) is shown schematically.
  • the Flow 13 (see FIG. 1) has the direction of flow 14.
  • a plurality of slots 10 are along the major axis 2 arranged in a row. Several rows are adjacent in the direction perpendicular to the main axis 2 on the Outer surface 7 of the turbine blade 1.
  • the slots in one Row have a slot length 11, which is in the range between 1 cm and 3 cm. The distance between two slots a row is in the range between 0.5 cm and 2 cm.
  • the slots in a row are compared to the slots a directly adjacent row offset in the main axis direction arranged. This has the advantage that the areas between the slots of one row with the cooling air, the from the slots the opposite the flow direction 14 the flow 13 (see FIG 1) directly adjacent Row emerges, are cooled. This will cool the film the entire outer surface 7 guaranteed.
  • the invention is characterized by a turbine blade a wall structure in which one is exposed to hot gas Outer wall has an outlet on the outer surface the outer wall is designed as a slot, and one for Interior thickening penetrates. Through the slot a largely homogeneous flow of cooling fluid forms over the entire slot length. Because of the thickening A favorable length-diameter ratio even with an extremely thin outer wall of the outlet as well as a flat one Tilt angle of the slot of the outlet with respect to the outer wall guaranteed.

Landscapes

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

Claims (12)

  1. Aube (1) de turbine, qui est dirigée le long d'un axe (2) principal et qui a une structure (3) de paroi, la structure (3) de paroi entourant une chambre (4) intérieure de passage de fluide (5) de refroidissement, comprenant une paroi (6) extérieure ayant une surface (7) extérieure et une surface (8) intérieure tournée vers la chambre (4) intérieure, ainsi qu'une sortie (9) pour du fluide (5) de refroidissement, la sortie (9) étant constituée sur la surface (7) extérieure sous la forme d'une fente (10), caractérisée en ce que la paroi (6) extérieure a un épaississement (11) qui est dirigé vers la chambre (4) intérieure et que la sortie (9) traverse.
  2. Aube de turbine suivant la revendication 1, caractérisée en ce que la fente (10) s'étend sur une profondeur (E) de pénétration dans la paroi (6) extérieure sans la traverser.
  3. Aube de turbine suivant la revendication 2, caractérisée en ce que la fente (10) a sur toute la profondeur (E) de pénétration une section transversale constante.
  4. Aube de turbine suivant l'une des revendications précédentes, caractérisée en ce que la fente (10) est dirigée parallèlement à l'axe (2) principal.
  5. Aube de turbine suivant l'une des revendications précédentes, caractérisée en ce que la fente (10) fait un angle α aigu avec la surface (7) extérieure, notamment dans l'intervalle compris entre 10° et 45°.
  6. Aube de turbine suivant l'une des revendications précédentes, caractérisée en ce que l'épaississement (11 ) a une cavité (12) dans la zone de la sortie (9).
  7. Aube de turbine suivant la revendication 6, caractérisée en ce que la cavité (12) est en forme de trou borgne.
  8. Aube de turbine suivant la revendication 6 ou 7, caractérisée en ce que la fente (10) coupe la cavité (12).
  9. Aube de turbine suivant la revendication 8, caractérisée en ce que la section transversale de la cavité (12) est inférieure à la section transversale de la fente (10).
  10. Aube de turbine suivant la revendication 9, caractérisée en ce que la fente (10) a une hauteur (H) et la cavité a un diamètre (D), et la hauteur (H) de la fente est du même ordre de grandeur que le diamètre (D), en étant comprise notamment entre 0,5 mm et 1,0 mm.
  11. Aube de turbine suivant l'une des revendications précédentes, qui est une aube mobile ou une aube directrice pour une turbine à gaz.
  12. Utilisation d'une aube de turbine suivant l'une des revendications précédentes dans une installation de turbine à gaz.
EP98954146A 1997-09-18 1998-09-08 Aube de turbine et son utilisation Expired - Lifetime EP1015736B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19741231 1997-09-18
DE19741231 1997-09-18
PCT/DE1998/002657 WO1999014465A1 (fr) 1997-09-18 1998-09-08 Aube de turbine et son utilisation

Publications (2)

Publication Number Publication Date
EP1015736A1 EP1015736A1 (fr) 2000-07-05
EP1015736B1 true EP1015736B1 (fr) 2003-11-19

Family

ID=7842852

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98954146A Expired - Lifetime EP1015736B1 (fr) 1997-09-18 1998-09-08 Aube de turbine et son utilisation

Country Status (4)

Country Link
EP (1) EP1015736B1 (fr)
JP (1) JP2001516834A (fr)
DE (1) DE59810230D1 (fr)
WO (1) WO1999014465A1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10236676A1 (de) * 2002-08-09 2004-02-19 Rolls-Royce Deutschland Ltd & Co Kg Turbinenschaufel für eine Gasturbine mit zumindest einer Kühlungsausnehmung
JP5039837B2 (ja) * 2005-03-30 2012-10-03 三菱重工業株式会社 ガスタービン用高温部材
BR112014026360A2 (pt) * 2012-04-23 2017-06-27 Gen Electric aerofólio de turbina e pá de turbina
US9957814B2 (en) 2014-09-04 2018-05-01 United Technologies Corporation Gas turbine engine component with film cooling hole with accumulator
US10982552B2 (en) * 2014-09-08 2021-04-20 Raytheon Technologies Corporation Gas turbine engine component with film cooling hole
US20170306764A1 (en) * 2016-04-26 2017-10-26 General Electric Company Airfoil for a turbine engine
FR3111661B1 (fr) * 2020-06-22 2022-11-04 Safran Aircraft Engines Aube de turbine avec système de refroidissement
US11486259B1 (en) 2021-11-05 2022-11-01 General Electric Company Component with cooling passage for a turbine engine
CN114382553B (zh) * 2021-12-26 2024-06-18 西北工业大学 涡轮叶片中弦区用高堵塞比肋片层板冷却结构及冷却方法

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4314442A (en) * 1978-10-26 1982-02-09 Rice Ivan G Steam-cooled blading with steam thermal barrier for reheat gas turbine combined with steam turbine
US4672727A (en) * 1985-12-23 1987-06-16 United Technologies Corporation Method of fabricating film cooling slot in a hollow airfoil
US4859147A (en) * 1988-01-25 1989-08-22 United Technologies Corporation Cooled gas turbine blade
US5405242A (en) 1990-07-09 1995-04-11 United Technologies Corporation Cooled vane
GB2262314A (en) * 1991-12-10 1993-06-16 Rolls Royce Plc Air cooled gas turbine engine aerofoil.
US5651662A (en) * 1992-10-29 1997-07-29 General Electric Company Film cooled wall
US5458461A (en) * 1994-12-12 1995-10-17 General Electric Company Film cooled slotted wall
DE59806535D1 (de) * 1997-02-20 2003-01-16 Siemens Ag Turbinenschaufel sowie deren verwendung in einer gasturbinenanlage

Also Published As

Publication number Publication date
WO1999014465A1 (fr) 1999-03-25
EP1015736A1 (fr) 2000-07-05
JP2001516834A (ja) 2001-10-02
DE59810230D1 (de) 2003-12-24

Similar Documents

Publication Publication Date Title
DE3789514T2 (de) Gekühlte Gasturbinenschaufel.
EP1745195B1 (fr) Aube de turbomachine
DE1946535C3 (de) Bauteil für ein Gasturbinentriebwerk
DE2718661C2 (de) Leitschaufelgitter für eine axial durchströmte Gasturbine
DE60213328T2 (de) Gekühlte hohle Schaufelspitzenabdeckung einer Turbinenschaufel
EP0964981B1 (fr) Aube de turbine et son utilisation dans un systeme de turbine a gaz
DE69932688T2 (de) Kühlungsöffnungen für Gasturbinenkomponenten
DE69302614T2 (de) Gekühlte Schaufel für eine Turbomaschine
DE69505882T2 (de) Kühlung für die Blattspitzen einer Turbine
DE69714960T3 (de) Wirbelelementkonstruktion für Kühlkanäle eines Gasturbinenrotorschaufelblattes
DE2358521C2 (de) Gasturbinenschaufel mit gewelltem Austrittskantenbereich
DE69211317T2 (de) Kühlkanäle mit Turbulenzpromotoren für Gasturbinenschaufeln
DE60015233T2 (de) Turbinenschaufel mit interner Kühlung
DE60014170T2 (de) Statorschaufel einer Gasturbine
DE1476796C3 (de) Aus einem hochfesten Material integral hergestelltes Bauteil einer Gasturbinenanlage
DE69729980T2 (de) Turbinenschaufelkühlung
DE2703815A1 (de) Hohlschaufel fuer ein gasturbinentriebwerk
DE102006004437A1 (de) Plattform einer Laufschaufel einer Gasturbine, Verfahren zur Herstellung einer Laufschaufel, Dichtungsplatte und Gasturbine
EP1013884A2 (fr) Aube de turbine avec plateforme refroidie
DE2555049A1 (de) Gekuehlte turbinenschaufel
EP1267039A1 (fr) Configuration de refroidissement du bord de fuite d'une aube
DE1601550B2 (de) Kuehlbare wand mit porositaet, insbesondere fuer schaufeln oder leitflaechen in einer gasturbine
EP1015736B1 (fr) Aube de turbine et son utilisation
DE2406277A1 (de) Einrichtung zur kuehlfilmbildung fuer brennkammern
DE2657471A1 (de) Kuehlschlitzanordnung im mantel eines brenners

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: 20000317

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH DE FR GB IT LI

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE FR GB IT LI

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REF Corresponds to:

Ref document number: 59810230

Country of ref document: DE

Date of ref document: 20031224

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20040211

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20040930

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20040930

26N No opposition filed

Effective date: 20040820

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20050906

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20050912

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20051121

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20060930

Year of fee payment: 9

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070403

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20060908

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20070531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20060908

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20061002

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070908