EP3266982A1 - Aube de turbine dotee de canal de refrigerant et orifice d'evacuation - Google Patents

Aube de turbine dotee de canal de refrigerant et orifice d'evacuation Download PDF

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Publication number
EP3266982A1
EP3266982A1 EP16178150.5A EP16178150A EP3266982A1 EP 3266982 A1 EP3266982 A1 EP 3266982A1 EP 16178150 A EP16178150 A EP 16178150A EP 3266982 A1 EP3266982 A1 EP 3266982A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
coolant
outlet
channels
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Withdrawn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
EP16178150.5A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Nihal Kurt
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 EP16178150.5A priority Critical patent/EP3266982A1/fr
Priority to EP17734724.2A priority patent/EP3464825B1/fr
Priority to PCT/EP2017/066414 priority patent/WO2018007274A1/fr
Publication of EP3266982A1 publication Critical patent/EP3266982A1/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Withdrawn legal-status Critical Current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
    • F01D5/186—Film 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
    • 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
    • F05D2240/305—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 pressure side 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
    • 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
    • F05D2240/306—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 suction side 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
    • 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 a turbine blade with a blade root and an airfoil, in which, starting from an entry point, at least one radial coolant channel extends as far as an end point of the cooling channel.
  • An often used in gas turbines cooling medium is air. Part of the compressed air is taken in the compressor and fed to the gas turbine blades, bypassing the combustion chamber.
  • the cooling air is supplied to the turbine blade in one or more cooling channels extending from the blade root in the blade body to an end point of the cooling channel, to which an opening in a surface of the airfoil is arranged, through which the entire guided in the coolant passage cooling air this point is omitted for cooling the turbine blade.
  • a uniform cooling of the turbine blade is possible with such a configuration only when a large number of cooling channels are driven through the blade body, which could then possibly affect the strength of the turbine blade in large numbers.
  • An object of the invention is to provide a turbine blade which has a relatively small number allows a more uniform cooling of the turbine blade on coolant channels.
  • a turbine blade according to the invention with a blade root and an airfoil has at least one radial coolant channel in a blade body of the turbine blade, which extends from an entry point, in particular on the blade root, to an end point of the cooling channel.
  • the end point of the cooling channel is preferably arranged in the blade body.
  • At least two outlet channels are arranged on the airfoil, which in each case connect the coolant channel for conducting coolant to an outlet opening on an outer wall of the airfoil.
  • At least one outlet opening is arranged both on a front side and on a rear side of the airfoil, which is connected to the coolant channel by means of an outlet channel. This allows bilateral cooling of the airfoil, starting from a single coolant channel.
  • a plurality of outlet openings is arranged on the blade according to a preferred development, which are each connected by means of an outlet channel with the coolant channel.
  • the outlet channels are formed with a significantly smaller cross-sectional diameter than the coolant channel, in particular with a diameter ratio of 1: 5, 1:10 or higher.
  • the coolant channel is formed as a drilled blind hole and / or the outlet channel / the outlet channels are formed as through holes.
  • a drilled design of the coolant channel and / or the outlet channels allows a simple and inexpensive production of the turbine blade and in particular its cooling system.
  • the coolant channel can also be manufactured by means of electrical discharge machining (EDM, in English: spark erosive machining). For example, this may allow a greater depth of the coolant channel for larger turbine blades.
  • EDM electrical discharge machining
  • a plurality of coolant channels are arranged in the blade body, in particular two, three, five, ten or a larger plurality.
  • each of these coolant channels preferably has at least one outlet channel, in particular preferably at least two or more outlet channels.
  • the end points of at least two of these coolant channels are arranged at different radial positions of the turbine blade, in particular with respect to a radial axis of the turbine blade.
  • the coolant channels each have an outlet region in which a plurality of outlet channels, in particular all outlet channels, emanate from the coolant channel.
  • the outlet region is preferably limited to a particular radial section of the turbine blade. This embodiment allows assignment of certain radial sections of the turbine blade to certain coolant channels. In turn, this can be a cooling air be controlled for a particular radial section of the turbine blade.
  • the outlet regions of at least two of these coolant channels are arranged at different radial positions of the turbine blade, in order to allow as even cooling as possible (based on the conditions of use).
  • FIG. 1 a turbine blade 1 with a blade root 2 and an airfoil 4 is shown.
  • a blade body 6 of the turbine blade starting from in each case one entry point 8.1, 8.2 and 8.3, three coolant channels 10 extend.
  • the coolant channels 10. 1, 10. 2 and 10. 3 run in an at least substantially radial direction as far as an end point 12 of the respective coolant channel 10.
  • the coolant channels 10.1 and 10.2 extend from a - with respect to a transverse direction of the blade root 2 central entry point - away to their end points 12.
  • the coolant channel 10.3 is arranged laterally away from the center of the blade root 2, and thus follows the shape of the blade 4 in the radially inner region of the blade 4 at this axial position.
  • each of the cooling channels 10 a plurality of outlet channels 16 and 18 are arranged, wherein the outlet channels 16 respectively open at an outlet opening 20 in the outer wall 22 of the turbine blade, and thus connect the cooling channel 10 with these outlet openings 20.
  • the outlet channels 16 open onto a front side 24 of the airfoil 4, the outlet channels 18 open into outlet openings (not shown) on the rear side of the turbine blade 1.
  • the coolant channels 8 have different cross-sectional diameters x 1 , x 2 and x 3 , which allow the provision of different cooling air streams.
  • cooling air is introduced into the coolant channels 10, which then in the outlet regions 14 distributed in the individual outlet channels 16 and 18 and exits at the outlet openings 20.
  • the cooling air can selectively cool the surroundings of the outlet openings by the relatively cold cooling air cools the relatively hot outer wall 24 of the turbine blade.
  • a film cooling can be realized in which the air flowing out of the outlet openings 20 forms a "film" on the front 22 and / or the back of the airfoil 4 and thus a direct contact between the outer wall 24 and the flowing hot working fluid is prevented or at least minimized.
  • Fig. 2 is a turbine blade 1 is shown, in which by means of two exemplary marked coolant channels 10.1 and 10.2 is shown how different areas with respect to the radial axis R of the turbine blade 1 can be supplied by different coolant channels with cooling air.
  • the coolant channel 10.1 extends from its entry point 8.1 to its end point 12.1 (at the radial position of the end point 12.1, the representation of the blade 4 is cut).
  • the cooling channel 10.2 is arranged slightly offset in the flow direction of the working fluid S to the coolant channel 10.1.
  • the coolant channel 10.2 is shorter, so that the distance between the end point 12.2 and the entry point 8.2 is smaller than the distance between the end point 12.1 and the entry point 8.1.
  • Both cooling channels have an outlet region 14, wherein the outlet region 14.1 of the first cooling channel 10.1 is arranged at a radial position that is farther outward than the radial position of the outlet region 14.2 of the second coolant channel 10.2.
  • the outlet openings 20.1, at which by the connection with the cooling channel 10.1 by means of the outlet channels 16.1 cooling air can flow in the direction of arrow, arranged radially further outward than the outlet openings 20.2 of the second cooling channel 10.2.
  • the cooling mechanism according to this embodiment is due to the ability to form both the coolant channels 10 and the outlet channels 16 and 18 straight - and thus to produce as holes - manufacturing technology relatively simple and thus inexpensive to manufacture.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16178150.5A 2016-07-06 2016-07-06 Aube de turbine dotee de canal de refrigerant et orifice d'evacuation Withdrawn EP3266982A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP16178150.5A EP3266982A1 (fr) 2016-07-06 2016-07-06 Aube de turbine dotee de canal de refrigerant et orifice d'evacuation
EP17734724.2A EP3464825B1 (fr) 2016-07-06 2017-07-03 Aube de turbine dotée de canaux de refrigerant et orifices d'evacuation
PCT/EP2017/066414 WO2018007274A1 (fr) 2016-07-06 2017-07-03 Aube de turbine comprenant un canal de refroidissement et un orifice de sortie

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16178150.5A EP3266982A1 (fr) 2016-07-06 2016-07-06 Aube de turbine dotee de canal de refrigerant et orifice d'evacuation

Publications (1)

Publication Number Publication Date
EP3266982A1 true EP3266982A1 (fr) 2018-01-10

Family

ID=56360314

Family Applications (2)

Application Number Title Priority Date Filing Date
EP16178150.5A Withdrawn EP3266982A1 (fr) 2016-07-06 2016-07-06 Aube de turbine dotee de canal de refrigerant et orifice d'evacuation
EP17734724.2A Active EP3464825B1 (fr) 2016-07-06 2017-07-03 Aube de turbine dotée de canaux de refrigerant et orifices d'evacuation

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP17734724.2A Active EP3464825B1 (fr) 2016-07-06 2017-07-03 Aube de turbine dotée de canaux de refrigerant et orifices d'evacuation

Country Status (2)

Country Link
EP (2) EP3266982A1 (fr)
WO (1) WO2018007274A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1598522A1 (fr) * 2004-05-21 2005-11-23 Siemens Aktiengesellschaft Composants d'une turbine à vapeur, procédé pour refroidir une turbine à vapeur et leur utilisation
DE102005044182A1 (de) * 2004-09-15 2006-03-16 General Electric Co. Kühlsystem für die Hinterkanten von Turbinenschaufelblättern
EP2284364A2 (fr) * 2009-08-13 2011-02-16 Siemens Aktiengesellschaft Arrangement de protection d'érosion dans une turbine à vapeur

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2349187A (en) * 1941-03-08 1944-05-16 Westinghouse Electric & Mfg Co Vibration dampener

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1598522A1 (fr) * 2004-05-21 2005-11-23 Siemens Aktiengesellschaft Composants d'une turbine à vapeur, procédé pour refroidir une turbine à vapeur et leur utilisation
DE102005044182A1 (de) * 2004-09-15 2006-03-16 General Electric Co. Kühlsystem für die Hinterkanten von Turbinenschaufelblättern
EP2284364A2 (fr) * 2009-08-13 2011-02-16 Siemens Aktiengesellschaft Arrangement de protection d'érosion dans une turbine à vapeur

Also Published As

Publication number Publication date
WO2018007274A1 (fr) 2018-01-11
EP3464825A1 (fr) 2019-04-10
EP3464825B1 (fr) 2020-12-16

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