EP0825333B1 - Aube de turbine pouvant être refroidie - Google Patents

Aube de turbine pouvant être refroidie Download PDF

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Publication number
EP0825333B1
EP0825333B1 EP97810561A EP97810561A EP0825333B1 EP 0825333 B1 EP0825333 B1 EP 0825333B1 EP 97810561 A EP97810561 A EP 97810561A EP 97810561 A EP97810561 A EP 97810561A EP 0825333 B1 EP0825333 B1 EP 0825333B1
Authority
EP
European Patent Office
Prior art keywords
blade
cooling
cavity
hollow space
channel
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
EP97810561A
Other languages
German (de)
English (en)
Other versions
EP0825333A1 (fr
Inventor
Kenneth Hall
Bernhard Dr. Weigand
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0825333A1 publication Critical patent/EP0825333A1/fr
Application granted granted Critical
Publication of EP0825333B1 publication Critical patent/EP0825333B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/187—Convection cooling
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the invention is based on a coolable blade according to the preamble of first claim.
  • Such coolable blades are known from GB 2 165 315.
  • cooling fluid is conducted from the trailing edge area of the blade to the leading edge area via turns formed by partition walls and then blown out via openings in the blade head.
  • air is blown out of the rear edge of the blade.
  • this method cannot be used for trailing edges with small radii for manufacturing reasons.
  • a large number of film cooling holes are also necessary, which makes the manufacture of the blade very complex.
  • the trailing edge blow-out can lead to a reduction in the aerodynamic efficiency of the blade, since a larger trailing edge radius is required.
  • a cooled blade is also known from DE 1 601 627, which has at its trailing edge region a radially extending cooling channel which diverges towards the tip of the blade.
  • the cooling duct is fed with cooling air via a larger inlet opening.
  • the cross-sectional area of this cooling channel is approximately the same size as that of the main channel in the middle of the blade, and even larger than that of the main channel in the area of the blade tip.
  • the heat transfer rates in the rear edge area of the blade are therefore no better than those in the central part of the blade and adequate cooling of the rear edge areas of the blade can no longer be guaranteed in the case of a blade that is subjected to high thermal loads.
  • the invention is based, with a coolable blade the task at the beginning to improve the cooling of the trailing edge area of the blade and to achieve a high aerodynamic efficiency of the blade.
  • the essence of the invention is therefore that an essentially in the trailing edge area radially extending, increasing in area with increasing radius Cooling channel is arranged, which is connected to the cavity via an inlet opening and that the cooling channel with the cavity via at least one connecting channel connected is.
  • the advantages of the invention can be seen, inter alia, in the fact that the cooling fluid guided through the cooling channel is blown out of the blade in the region of the blade head and thus has no influence on the aerodynamics of the blade. Small trailing edge radii can also be achieved, since there is no need to blow out at the trailing edge of the blade. Due to the divergent design of the cooling channel, effective cooling of the trailing edge area of the blade is achieved. The cooling of local areas can be easily adjusted by designing the divergent channel. In addition, in the case of moving blades with cover plates, the upper area, which is at high risk of creep, can be cooled particularly well towards the blade head. When using the diverging cooling channel, significantly less cooling air is required than, for example, with film cooling of the rear edge. Buckets with the diverging cooling channel can also be produced using the casting process.
  • the cooling duct is to be connected to the cavity via at least one connecting duct.
  • the connecting channels between the cavity and the cooling channel act as suction points for cooling air from the cavity and intensify the heat transfer in the trailing edge area of the cavity.
  • the cooling fluid enters the cooling channel in a jet shape and generates extremely high heat transfer coefficients.
  • a blade 10 of a turbomachine is shown, consisting from a blade 1 and a blade root 11 with which the blade 10 can be mounted. Between blade 1 and blade root 11 is common A platform 12 is arranged, which the blade root of the Shields around flowing fluids.
  • the airfoil 1 has one Front edge area 3, a rear edge area 4, a suction-side wall 5 and a pressure side wall 6, the suction side and the pressure side Wall connected to each other in the area of the front edge 3 and the rear edge 4 are, whereby a cavity 2 is formed with a cross-sectional area A2.
  • the leading edge region 3 is in each case the one flowing around the airfoil 1 Apply fluids first.
  • the cavity 2 is essentially radial Direction through the blade 10 and serves as a cooling fluid passage for a cooling fluid 20th
  • the cooling channel 7 is via connecting channels 8 with a cross-sectional area A8 and an inlet opening 9 in one
  • the airfoil center region 14 is connected to the cavity 2.
  • the inlet opening 9 of the cooling channel is also arranged at any location can be, for example, closer to the blade root or in the blade root.
  • the cooling channel 7 is in the downstream part of the Blade arranged approximately from the center 14 of the airfoil, since there the Load and danger of creep is greatest.
  • Cooling fluid 20 flows through the cavity 20 and via the inlet opening 9 and the connecting channels 8 into the cooling channel 7. This stimulates the flow circulation in the region of the trailing edge in the cavity 2. Heated cooling fluid, which tends to get stuck in the area of the rear edge due to the locally increased friction, is thereby mixed with cooler cooling fluid, especially also with the cooling fluid entering the cooling channel 7.
  • the trailing edge region is cooled by the cooling fluid passed through the cooling channel 7, the heat transfer coefficient in the cooling channel 7 increasing from the center of the airfoil to the blade head. This is due to the increasing cooling fluid mass flow in the cooling channel 7, which is brought about by the further feeding of cooling fluid via the connecting channels 8. This improves the cooling of the airfoil head 13.
  • the flow circulation in the trailing edge area of the cavity and the cooling capacity of the trailing edge area can be set by the design of the cooling channel, the inlet opening and the connecting channels.
  • the divergence angle of the cooling channel with the number of connecting channels from the cavity is adjusted so that the cooling of the blade is optimal.
  • the cross-sectional area A8 of the connecting channels 8 is smaller than the cross-sectional area A7 of the cooling channel 7 and this in turn is much smaller than the cross-sectional area A2 of the cavity 2 (A8 ⁇ A7 ⁇ A2).
  • A8 to A2 is preferably a few percent, in particular 1-5%
  • A8 to A7 is preferably several tenths, in particular 30-100%
  • A7 to A2 is preferably a few percent, in particular 1-10%.
  • the flow velocity of the fluids through the connecting channels as well as in the diverging channel 7 is much greater than that in the selected geometry Cooling duct A2.
  • By appropriate design of the cross sections A8, A7 and A2 it is achieved that the flow velocity of the fluids in the cooling channel 7 remains approximately the same or increases slightly with increasing radius.
  • FIG. 3 shows the increase in the cross-sectional area of the cooling channel 7 towards the blade head 13 and the connecting channel 8.
  • a Nusselt number Nu is defined as the ratio of the convectively dissipated to the conducted amount of heat.
  • V-shaped ribs 30 with a tip 31 and legs 32, 33 are arranged in the cavity 2 on the suction side wall.
  • the legs of the ribs are angled at an angle 34 to the main flow direction of the cooling fluid 20.
  • the angle 34 is 30 to 60 °, preferably 40 to 50 ° and in particular 45 °.
  • the ratio of rib height to cavity height is essentially the same at every point of the rib and is between 5 to 50%.
  • the tip of the rib 30 is located at the point where the rib height is at a maximum. In the areas where the cavity 2 merges into the front and rear edge area, the rib 30 tapers in order not to inhibit the passage of the cooling fluid in these areas.
  • the ribs, not shown, arranged on the inside of the pressure-side wall 6 are also V-shaped.
  • the tip is also at the point where the rib height is maximum.
  • the ribs are arranged offset on the pressure side and the suction side wall in the flow direction, so that the flow successively meets a rib 30 on the suction side 5 and a rib on the pressure side.
  • the ribs are advantageously arranged in the middle between the ribs of the opposite wall.
  • the ribs in combination with the cooling channel 7 ensure cooling of the blade, which leads to an even wall temperature distribution.
  • the Cooling fluid 20 is here from turns formed by partitions 40, 41
  • the trailing edge area of the blade is directed to the leading edge area and then Blown out through an opening 42 in the blade head 13.
  • a diverging cooling channel 7 for cooling the trailing edge area is arranged.
  • the invention is not limited to the exemplary embodiment shown and described.
  • the cavity and thus the cooling fluid passage can also be configured differently than shown, for example as a plurality of individual cooling channels.
  • the formation of the diverging cooling duct in connection with the connecting ducts between the diverging duct and the main duct is essential.
  • the cross-sectional areas A2, A7 and A8 are each measured perpendicular to the direction of flow of the fluids flowing through the cavities.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (2)

  1. Aube pouvant être refroidie (10), se composant essentiellement d'une base (11) et d'une pale (1), qui est construite à partir d'une paroi côté refoulement (6) et d'une paroi côté aspiration (5), lesquelles sont raccordées l'une à l'autre essentiellement par une région de bord arrière (4) et une région de bord avant (3) de telle sorte qu'au moins un espace creux (2) utilisé en tant que passage pour le fluide de refroidissement soit formé, l'espace creux étant alimenté en fluide de refroidissement depuis la base de l'aube et un canal de refroidissement (7) divergent s'étendant essentiellement radialement étant disposé dans la région du bord arrière (4) et s'étendant jusqu'à la tête de l'aube (13) et étant raccordé par le biais d'une ouverture d'admission (9) à l'espace creux (2), caractérisée en ce que le canal de refroidissement (7) est raccordé à l'espace creux (2) par le biais d'au moins un autre canal de raccordement (8) qui est disposé entre l'ouverture d'admission (9) et la tête de l'aube (13).
  2. Aube pouvant être refroidie selon la revendication 1, caractérisée en ce qu'au moins une nervure (30) est configurée dans l'espace creux (2), en ce qu'elle présente une pointe (31) et deux branches (32, 33) et en ce que les branches de la nervure sont inclinées suivant un angle aigu (34) par rapport à la direction principale de l'écoulement d'un fluide de refroidissement (20).
EP97810561A 1996-08-23 1997-08-08 Aube de turbine pouvant être refroidie Expired - Lifetime EP0825333B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19634237 1996-08-23
DE19634237A DE19634237A1 (de) 1996-08-23 1996-08-23 Kühlbare Schaufel

Publications (2)

Publication Number Publication Date
EP0825333A1 EP0825333A1 (fr) 1998-02-25
EP0825333B1 true EP0825333B1 (fr) 2001-05-23

Family

ID=7803585

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810561A Expired - Lifetime EP0825333B1 (fr) 1996-08-23 1997-08-08 Aube de turbine pouvant être refroidie

Country Status (6)

Country Link
US (1) US5934874A (fr)
EP (1) EP0825333B1 (fr)
JP (1) JP4152458B2 (fr)
CN (1) CN1105228C (fr)
CZ (1) CZ267997A3 (fr)
DE (2) DE19634237A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103089335A (zh) * 2013-01-21 2013-05-08 上海交通大学 适用于涡轮叶片后部冷却腔的w形肋通道冷却结构
US10400608B2 (en) * 2016-11-23 2019-09-03 General Electric Company Cooling structure for a turbine component
US11248471B2 (en) 2020-01-22 2022-02-15 General Electric Company Turbine rotor blade with angel wing with coolant transfer passage between adjacent wheel space portions by additive manufacture
US11242760B2 (en) 2020-01-22 2022-02-08 General Electric Company Turbine rotor blade with integral impingement sleeve by additive manufacture
US11492908B2 (en) 2020-01-22 2022-11-08 General Electric Company Turbine rotor blade root with hollow mount with lattice support structure by additive manufacture
US11220916B2 (en) 2020-01-22 2022-01-11 General Electric Company Turbine rotor blade with platform with non-linear cooling passages by additive manufacture

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3171631A (en) * 1962-12-05 1965-03-02 Gen Motors Corp Turbine blade
GB1070130A (en) * 1966-01-31 1967-05-24 Rolls Royce Aeofoil shaped blade for a fluid flow machine such as a gas turbine engine
SU364747A1 (ru) * 1971-07-08 1972-12-28 Охлаждаемая лопатка турбол1ашины
US4288201A (en) * 1979-09-14 1981-09-08 United Technologies Corporation Vane cooling structure
GB2165315B (en) * 1984-10-04 1987-12-31 Rolls Royce Improvements in or relating to hollow fluid cooled turbine blades
JPS62501304A (ja) * 1984-10-10 1987-05-21 ポ−ル　マリウス　エイ ガスタ−ビンエンジン
US4820123A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US5122033A (en) * 1990-11-16 1992-06-16 Paul Marius A Turbine blade unit
US5695321A (en) * 1991-12-17 1997-12-09 General Electric Company Turbine blade having variable configuration turbulators
US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket

Also Published As

Publication number Publication date
CZ267997A3 (cs) 1998-03-18
DE59703585D1 (de) 2001-06-28
CN1177676A (zh) 1998-04-01
US5934874A (en) 1999-08-10
JP4152458B2 (ja) 2008-09-17
DE19634237A1 (de) 1998-02-26
EP0825333A1 (fr) 1998-02-25
JPH1089007A (ja) 1998-04-07
CN1105228C (zh) 2003-04-09

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