EP2863013A1 - Agencement de canaux de refroidissement dans une aube de turbine dans une structure en arc - Google Patents

Agencement de canaux de refroidissement dans une aube de turbine dans une structure en arc Download PDF

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Publication number
EP2863013A1
EP2863013A1 EP20130189517 EP13189517A EP2863013A1 EP 2863013 A1 EP2863013 A1 EP 2863013A1 EP 20130189517 EP20130189517 EP 20130189517 EP 13189517 A EP13189517 A EP 13189517A EP 2863013 A1 EP2863013 A1 EP 2863013A1
Authority
EP
European Patent Office
Prior art keywords
cooling
turbine blade
cooling fluid
blade
cooling channels
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Withdrawn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
EP20130189517
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 EP20130189517 priority Critical patent/EP2863013A1/fr
Publication of EP2863013A1 publication Critical patent/EP2863013A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • 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 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. 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.
  • the object of the invention is to mitigate this disadvantage.
  • 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 root, an airfoil tip, an inlet edge and a trailing edge.
  • the cooling channels are thereby separated from one another 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. From there, the cooling fluid should continue to meander through the turbine blade and provide cooling. In the case of a leak, this cooling of the turbine blade is then largely off.
  • cooling channels can run. Decisive are several separate cooling channels.
  • the cooling channels have connections at selected locations. It is especially important that not the entire cooling air is passed through a cooling channel, so that in case of a leak in this cooling channel, the entire cooling fails. Above all, the entire cooling air should not be led through the cooling channel, which runs along the leading edge. This cooling channel runs in a region of the turbine blade which is subject to greater thermal stress and is more susceptible to foreign body impacts since the gas or gas mixture driving the turbine first strikes there.
  • the cooling channels are separated from each other so that no, at least no immediate, connection for cooling fluid from a cooling channel into another cooling channel. Due to the extensive separation prevents cooling air flows in the event of a leak from a cooling channel without leakage in a cooling channel with leak and so the cooling is difficult. As later shown in more detail, cooling fluid outlets are often very close together. As a result, an indirect connection for cooling fluid can be created from one cooling channel to another cooling channel, but no direct connection.
  • 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 flows out again after the heating. If the cooling fluid only flow past the inner wall of the turbine blade, a film lying directly against the wall could form, in which the flow is comparatively weak.
  • heated cooling fluid would have to be used in another area for further cooling in other areas.
  • the cooling channels extend as adjacent arcs, wherein in particular three adjacent arcs are present. This results in a bow structure. Adjacent arches are structurally easy to accomplish and allow a good flow through the entire blade with cooling fluid. Since the sheets run separately, even if a sheet is damaged, the cooling remains reasonably preserved, at least in the area of the undamaged sheet (s). In the usual turbine blades, three bends have proved to be an appropriate number.
  • the cooling fluid inlets are attached to the base of the turbine blade in a region near the leading edge and the cooling fluid outlets are attached to the base of the turbine blade in a region near the trailing edge.
  • blades are attached to the blade root on a rotor. This makes it possible to install the cooling fluid inlets and the cooling fluid outlets there without problems, as is also customary in the arrangements known in the prior art. If the cooling fluid inlets are arranged near the leading edge and the cooling fluid outlets close to the trailing edge, this results in a flow which starts at the thermally stressed leading edge. Since at the leading edge, the turbine blade driving gas mixture is hottest, the thermal load of the turbine blade is highest there.
  • 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 can optionally be used to drive a further turbine stage.
  • a blade root 2 with which the turbine blade is attached to a rotor, not shown.
  • On the left is an entrance edge 3 can be seen.
  • the leading edge 3 is the area to which a turbine blade drives Gas mixture 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 root 2 and the blade tip 4 like the rest of the blade area, are curved in each case. The curvature is due to an aerodynamic shape of the turbine blade.
  • the turbine blade has a front wall, not shown, which extends from the inlet edge 3 to the outlet edge 5 and a rear wall extending at a distance therefrom, which again leads from the outlet edge 5 to the inlet edge 3.
  • 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 leading edge 3. Arrived at the blade tip 4, the cooling channel 6 continues along the blade tip 4 to the trailing edge 5. From there the cooling channel 6 extends along the trailing edge 5 back to the blade root. 2 On the way there are cooling fluid outlets 7a to 7g. At the blade root 2, the cooling channel 6 opens into a cooling fluid outlet 8.
  • a second cooling channel 9 also begins at the blade root 2 and extends next to the first cooling channel 6 on the side facing away from the leading edge 3 of the cooling channel 6. Again, in the manner of an arc, the second cooling channel 9 follows the first cooling channel 6 and runs parallel to the blade tip 4 on the Blade tip 4 opposite side of the first cooling channel 6. Finally, the second cooling channel 9 extends on the side facing away from the exit edge 5 of the first Cooling channel 6 to the blade root 2 and there opens into a cooling fluid outlet 10th
  • a third cooling channel 11 in turn begins at the blade root 2 and extends in the manner of an arc along the second cooling channel 9 respectively on the side facing away from the first cooling channel 6 and opens at the blade root 2 in a cooling fluid outlet 12th

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP20130189517 2013-10-21 2013-10-21 Agencement de canaux de refroidissement dans une aube de turbine dans une structure en arc Withdrawn EP2863013A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20130189517 EP2863013A1 (fr) 2013-10-21 2013-10-21 Agencement de canaux de refroidissement dans une aube de turbine dans une structure en arc

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20130189517 EP2863013A1 (fr) 2013-10-21 2013-10-21 Agencement de canaux de refroidissement dans une aube de turbine dans une structure en arc

Publications (1)

Publication Number Publication Date
EP2863013A1 true EP2863013A1 (fr) 2015-04-22

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP20130189517 Withdrawn EP2863013A1 (fr) 2013-10-21 2013-10-21 Agencement de canaux de refroidissement dans une aube de turbine dans une structure en arc

Country Status (1)

Country Link
EP (1) EP2863013A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3147456A1 (fr) 2015-09-28 2017-03-29 Siemens Aktiengesellschaft Aube de turbine dote d'encoche dans le sol de couronne

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5328331A (en) * 1993-06-28 1994-07-12 General Electric Company Turbine airfoil with double shell outer wall
DE19713268A1 (de) * 1997-03-29 1998-10-01 Asea Brown Boveri Gekühlte Gasturbinenschaufel
EP0939196A2 (fr) * 1998-02-26 1999-09-01 Kabushiki Kaisha Toshiba Aube de turbine à gaz
EP1471210A1 (fr) * 2003-04-24 2004-10-27 Siemens Aktiengesellschaft Composant de turbine avec une plaque d'impact de refroidissement
US20090297361A1 (en) * 2008-01-22 2009-12-03 United Technologies Corporation Minimization of fouling and fluid losses in turbine airfoils
EP2543821A1 (fr) * 2010-03-03 2013-01-09 Mitsubishi Heavy Industries, Ltd. Pale de rotor pour turbine à gaz, son procédé de fabrication, et turbine à gaz utilisant ladite pale de rotor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5328331A (en) * 1993-06-28 1994-07-12 General Electric Company Turbine airfoil with double shell outer wall
DE19713268A1 (de) * 1997-03-29 1998-10-01 Asea Brown Boveri Gekühlte Gasturbinenschaufel
EP0939196A2 (fr) * 1998-02-26 1999-09-01 Kabushiki Kaisha Toshiba Aube de turbine à gaz
EP1471210A1 (fr) * 2003-04-24 2004-10-27 Siemens Aktiengesellschaft Composant de turbine avec une plaque d'impact de refroidissement
US20090297361A1 (en) * 2008-01-22 2009-12-03 United Technologies Corporation Minimization of fouling and fluid losses in turbine airfoils
EP2543821A1 (fr) * 2010-03-03 2013-01-09 Mitsubishi Heavy Industries, Ltd. Pale de rotor pour turbine à gaz, son procédé de fabrication, et turbine à gaz utilisant ladite pale de rotor

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3147456A1 (fr) 2015-09-28 2017-03-29 Siemens Aktiengesellschaft Aube de turbine dote d'encoche dans le sol de couronne

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