EP3022397A1 - Agencement de canaux de refroidissement dans une aube de turbine - Google Patents

Agencement de canaux de refroidissement dans une aube de turbine

Info

Publication number
EP3022397A1
EP3022397A1 EP14772098.1A EP14772098A EP3022397A1 EP 3022397 A1 EP3022397 A1 EP 3022397A1 EP 14772098 A EP14772098 A EP 14772098A EP 3022397 A1 EP3022397 A1 EP 3022397A1
Authority
EP
European Patent Office
Prior art keywords
cooling
blade
arrangement
cooling channels
turbine blade
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Withdrawn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
EP14772098.1A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Thomas Burzych
Eugen Hummel
Gordon Emanuel KUNZE
Frank PREUTEN
Thomas Alexis SCHNEIDER
Hannes Teuber
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 EP14772098.1A priority Critical patent/EP3022397A1/fr
Publication of EP3022397A1 publication Critical patent/EP3022397A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/18—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
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the invention relates to an arrangement of cooling channels in a turbine blade.
  • Turbine blades in particular blades of gas turbines, are highly stressed components. The rotation takes place during operation with a high number of revolutions. Therefore, a high mechanical load capacity is required. In addition, high temperatures occur especially in gas turbine blades during operation. It generally applies that higher temperatures of the turbine blades driving gas mixture have a favorable effect on the efficiency of the gas turbine. In order to prevent too high temperatures of the turbine blades, the turbine blades are cooled. For this purpose, cooling channels are often arranged inside the turbine blades. Sometimes the turbine blades are hit by
  • US Pat. No. 6,382,914 B1 discloses an arrangement for distributing cooling fluid in a turbine blade.
  • This arrangement provides a number of cooling channels, which extend in the interior of the turbine blade parallel to an inlet edge and paral ⁇ lel to a trailing edge of the turbine blade. At least some of the cooling channels are connected by a diagonal channel. This is to improve the cooling.
  • Further cooling devices for turbine blades are known from JP S59 231103 A, FR 1 209.752 A, GB 827 289 A and US Pat. No. 3,014,693 A.
  • 6,382,914 Bl may in some way contribute to the fact that, if the turbine blade is damaged and, consequently, a cooling channel is damaged, the cooling can be maintained to a certain extent. This is not mentioned in the documents and is actually only with knowledge of the invention described below to recognize.
  • the object of the invention is to improve the cooling in case of damage to a cooling channel on.
  • An arrangement of a plurality of cooling channels, that is to say at least two cooling channels, within a turbine blade for conveying cooling fluid is proposed.
  • the cooling fluid is usually air.
  • the cooling channels lead through the turbine blade to one or more cooling fluid outlets.
  • the turbine blade regularly has a blade foot, an airfoil tip, an inlet edge and a trailing edge.
  • the cooling channels are connected to one another at selected locations and are separated from one another in other areas such that, if the turbine blade is damaged in the region of a cooling channel, the cooling by the other cooling channels remains largely unimpaired.
  • a cooling passage generally runs from the blade root to the blade tip along the leading edge.
  • a leak caused by damage in this cooling channel causes the cooling fluid to escape there.
  • This is problematic ⁇ table as lying in the downstream of the leak portion fails cooling.
  • the cooling fluid from this cooling channel is to meander further through the turbine blade and should provide cooling. In the event of a leak, the cooling of the turbine blade then largely fails.
  • cooling channels are connected to one another at selected locations and are separated from one another in other areas. Due to the connections at selected points, cooling fluid can pass from one cooling channel into another cooling channel. If a leak had occurred in the other cooling channel upstream of the connection, cooling would be lost without the connection downstream. Through the connection, the cooling can be largely maintained downstream of the connection. But it is also necessary to separate the cooling channels in other areas from each other. Without the separation cooling fluid could pass unhindered in the event of a leak to the leak, so that the cooling would in turn be more affected.
  • At least one cooling channel in a region near the leading edge and near the sight ⁇ felfuß begins and as a diagonal channel through the Turbinenschau- fei in an area near the trailing edge and close to the
  • Blade tip leads. It should be made clear that the diagonal canal does not have to start at the root of the blade and not at the entrance, but only in this area. A beginning at the blade root and at the leading edge but should not be excluded. The same applies to the end of the diagonal channel near the trailing edge and near the blade tip. The diagonal channel allows the cooling fluid to flow well into different areas of the turbine blade and provide efficient cooling everywhere.
  • the cooling ducts are joined together so that at regular cooling fluid flows through flow ⁇ the arrangement of a cooling passage in a different cooling channel. It would also be conceivable to provide this only in the event of a leak. In terms of efficient flow, it has proven to be useful to provide this in normal operation.
  • the cooling channels are separated from an inner wall of the turbine blade by a perforated plate or a device in the manner of a perforated plate, so that the cooling fluid can pass largely perpendicular to the inner wall of the turbine blade. This achieves so-called impingement cooling. This is efficient because the cooling fluid is swirled on the inner wall and after the heating as ⁇ flows.
  • At least one cooling channel begins at the blade root in a region near the inlet ⁇ edge of the turbine blade.
  • the inlet for the cooling fluid is, even with the arrangements known in the prior art, for structural reasons regularly at the blade root. Because at the leading edge that drives the turbine blade
  • a cooling duct begins in the area of the leading edge.
  • two cooling channels begin at the blade root in a region near the leading edge, which end in a region near the blade root and are connected to one another and to the diagonal channel. In this way, cooling fluid can pass from cooling fluid inlets on the display foot to the diagonal channel. If on one of the pre ⁇ called cooling passages due to a leak cooling fluid to escape, the diagonal channel can be supplied with cooling fluid through the other cooling channel continues.
  • Diagonal channel further cooling channels from, in particular cooling ⁇ channels branch off in the direction of the trailing edge and / or branch off cooling channels in the direction of the blade tip. On In this way, the distribution of the cooling fluid in the entire area of the turbine blade can be further optimized.
  • a cooling channel runs parallel to the blade tip, into which opening the above-mentioned cooling channels extending in the direction of the blade tip.
  • the blade tip ver ⁇ running parallel cooling channel can open into the same range as the diagonal channel.
  • the branching toward the trailing edge cooling channels extend far ⁇ extent perpendicular to the trailing edge.
  • the comparable towards the blade tip running cooling channels run largely parallel to the trailing edge. This also serves to further optimize the distribution of the cooling fluid. It is always important to keep in mind that a leak at one point should minimize the cooling of the turbine blade as little as possible.
  • cooling fluid outlets are provided in the region of the outlet edge through which cooling fluid can pass from the region inside the turbine blade into an area outside the turbine blade. This can be achieved in the region of the trailing edge on an outer wall, a further cooling.
  • the leaked cooling ⁇ fluid may optionally be used to drive a further Turbi ⁇ nencut.
  • at least one cooling fluid outlet is provided on the blade root in the region of the outlet edge. The cooling fluid may leave from thedefluidein-, which is normally at the blade root in the area of an edge ⁇ occurs, flow through the turbine blade and flow back to the blade root in the region of the outlet edge.
  • the exiting cooling fluid can be reused to cool additional turbine blades.
  • the figure which shows schematically an arrangement of cooling channels, the invention will be illustrated below. Evident is an arrangement 1 of cooling channels in a gas turbine blade.
  • a blade root 2 with which the turbine blade is attached to a rotor.
  • On the left is an entrance edge 3 can be seen.
  • the leading edge 3 is the area to which a gas mixture driving the turbine blade first impinges.
  • Above a blade tip 4 can be seen.
  • a trailing edge 5 is arranged.
  • the turbine ⁇ blade is not flat, but curved. In this case, the leading edge 3 and the trailing edge 5 may be straight, but also curved.
  • the blade 2 and the paddle blade tip go as curved and the rest of the shovel ⁇ area in any case.
  • the curvature is due to an aerodynamic shape of the turbine blade.
  • the turbine blade has a non-illustrated front wall, which runs trailing edge from the leading edge to the ver ⁇ and extending spaced therefrom rear wall, which leads back from the trailing edge to the leading edge.
  • the distance between the front wall and the rear wall in the region of the leading edge 3 and the trailing edge 5 is very low and increases toward the blade center.
  • a first cooling channel 6 begins at the blade root 2 and runs directly along the inlet edge 3.
  • a further cooling channel 7 extends away from the blade root 2 and is separated from the cooling channel 6.
  • the cooling channels 6 and 7 open into a region 8 which is close to the inlet edge 3 and near the blade root 2 is located.
  • the cooling ⁇ channels 6 and 7 are interconnected.
  • a diagonal channel 9 which leads into a region 10 near the trailing edge 5 and near the blade tip 4, also begins.
  • a cooling passage 11 extends parallel to the scene ⁇ felfuß 2.
  • the cooling channel 11 opens into a parallel to the off ⁇ takes edge 5 extending cooling channel 12. Following the Diago ⁇ nalkanal 9 from the area 8 near the leading edge 3 for loading ⁇ rich 10 near
  • the outlet edge 5 branch off two cooling channels 13 and 14, which run parallel to the cooling channel 11 and open into the cooling channel 12.
  • the arrangement 1 of the cooling channels 6, 7, 9, 11, 12, 13, 14, 15, 16, 17 can also be referred to as "fir tree design".

Abstract

L'invention concerne un agencement (1) de plusieurs canaux de refroidissement (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) à l'intérieur d'une aube de turbine, permettant de transporter du fluide de refroidissement. Les canaux de refroidissement (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) mènent à un ou plusieurs orifices de sortie (18, 19a à19g) en traversant l'aube de turbine, laquelle aube comprenant un pied d'aube (2), une pointe d'aube (4), un bord d'attaque (3) et un bord de fuite (5). Les canaux de refroidissement (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) sont reliés les uns aux autres à des endroits sélectionnés (8, 10) et s'étendent séparément les uns des autres dans d'autres zones, de telle sorte que, lorsque l'aube de turbine est endommagée dans la zone d'un canal de refroidissement (6, 7, 9, 11, 12, 13, 14, 15, 16, 17), le refroidissement continue à s'effectuer dans une large mesure sans perturbations au moyen des autres canaux de refroidissement (6, 7, 9, 11, 12, 13, 14, 15, 16, 17). Au moins un canal de refroidissement commence dans une zone (8) proche du bord d'attaque (3) et proche du pied d'aube (2), et mène, sous la forme d'un canal diagonal (9) qui traverse l'aube de turbine, dans une zone (10) proche du bord de fuite (5) et de la pointe d'aube (4).
EP14772098.1A 2013-09-25 2014-09-17 Agencement de canaux de refroidissement dans une aube de turbine Withdrawn EP3022397A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14772098.1A EP3022397A1 (fr) 2013-09-25 2014-09-17 Agencement de canaux de refroidissement dans une aube de turbine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP13185944.9A EP2853689A1 (fr) 2013-09-25 2013-09-25 Agencement de canaux de refroidissement dans une aube de turbine
PCT/EP2014/069747 WO2015044007A1 (fr) 2013-09-25 2014-09-17 Agencement de canaux de refroidissement dans une aube de turbine
EP14772098.1A EP3022397A1 (fr) 2013-09-25 2014-09-17 Agencement de canaux de refroidissement dans une aube de turbine

Publications (1)

Publication Number Publication Date
EP3022397A1 true EP3022397A1 (fr) 2016-05-25

Family

ID=49303737

Family Applications (2)

Application Number Title Priority Date Filing Date
EP13185944.9A Withdrawn EP2853689A1 (fr) 2013-09-25 2013-09-25 Agencement de canaux de refroidissement dans une aube de turbine
EP14772098.1A Withdrawn EP3022397A1 (fr) 2013-09-25 2014-09-17 Agencement de canaux de refroidissement dans une aube de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP13185944.9A Withdrawn EP2853689A1 (fr) 2013-09-25 2013-09-25 Agencement de canaux de refroidissement dans une aube de turbine

Country Status (5)

Country Link
US (1) US20160208622A1 (fr)
EP (2) EP2853689A1 (fr)
JP (1) JP2016533446A (fr)
CN (1) CN105593471A (fr)
WO (1) WO2015044007A1 (fr)

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Publication number Priority date Publication date Assignee Title
FR3037830B1 (fr) * 2015-06-29 2024-02-16 Snecma Ensemble de moulage d'une aube de turbomachine, comprenant une portion en relief de grande section
US10544684B2 (en) * 2016-06-29 2020-01-28 General Electric Company Interior cooling configurations for turbine rotor blades
FR3057906B1 (fr) * 2016-10-20 2019-03-15 Safran Aircraft Engines Aube de turbomachine a refroidissement optimise
US10422229B2 (en) * 2017-03-21 2019-09-24 United Technologies Corporation Airfoil cooling
US10697301B2 (en) * 2017-04-07 2020-06-30 General Electric Company Turbine engine airfoil having a cooling circuit
US11644046B2 (en) * 2018-01-05 2023-05-09 Aurora Flight Sciences Corporation Composite fan blades with integral attachment mechanism
EP3832069A1 (fr) * 2019-12-06 2021-06-09 Siemens Aktiengesellschaft Aube de turbine pour turbine à gaz fixe

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Also Published As

Publication number Publication date
WO2015044007A1 (fr) 2015-04-02
JP2016533446A (ja) 2016-10-27
US20160208622A1 (en) 2016-07-21
CN105593471A (zh) 2016-05-18
EP2853689A1 (fr) 2015-04-01

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