EP2025868A1 - Aube de turbine avec turbulateur à l'entrée d'air de refroidissement - Google Patents

Aube de turbine avec turbulateur à l'entrée d'air de refroidissement Download PDF

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Publication number
EP2025868A1
EP2025868A1 EP07015784A EP07015784A EP2025868A1 EP 2025868 A1 EP2025868 A1 EP 2025868A1 EP 07015784 A EP07015784 A EP 07015784A EP 07015784 A EP07015784 A EP 07015784A EP 2025868 A1 EP2025868 A1 EP 2025868A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
coolant
turbulence
blade
cooling
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Withdrawn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
EP07015784A
Other languages
German (de)
English (en)
Inventor
Hans Thermann
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP07015784A priority Critical patent/EP2025868A1/fr
Publication of EP2025868A1 publication Critical patent/EP2025868A1/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Withdrawn legal-status Critical Current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
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence

Definitions

  • the invention relates to a turbine blade with an airfoil, in which a cavity suitable for cooling the airfoil is provided, wherein the turbine blade has a feed opening for a coolant that can be supplied to the cavity.
  • Numerous turbine blades with a hollow airfoil are known from the prior art, into the cavity of which a coolant can be flowed in through a feed opening.
  • the turbine blades are known to be used for the deflection of a hot gas to convert the energy content of the hot gas into mechanical energy. Due to the high temperatures of the hot gas, the turbine blades are cooled so that they have a particularly long life despite the particularly high temperatures.
  • known cooling methods are used for cooling the turbine blades.
  • the cooling methods can be film cooling, impingement cooling or convection cooling.
  • the hollow turbine blade In the convection cooling, the hollow turbine blade is flowed through by a coolant, wherein the heat energy in the blade material is absorbed by the coolant by convection by the sweeping of the coolant on the inner surfaces of the cooling to the blade wall.
  • the coolant flowing in the turbine blade impinges perpendicularly on the blade wall to be cooled, whereby particularly good heat transfer can be achieved.
  • the film cooling, the coolant flowing inside the turbine blade exits via a plurality of film cooling holes arranged in a row, forming a protective cooling film on the surface of the outer wall to be cooled, which is exposed to the hot gas, whereby the heat input can be reduced from the hot gas into the blade material.
  • it is necessary to reduce the amount of coolant as an unnecessarily high Consumption unnecessarily lowers the efficiency of the gas turbine equipped with these turbine blades.
  • the object of the invention is therefore to provide a turbine blade mentioned above, in which the coolant is to have the highest possible effectiveness for saving the coolant.
  • the invention provides that a turbine blade of the type mentioned in or at its feed opening has a turbulence agent. Consequently, in addition to the known cooling measures in or at the inflow region, in which the coolant enters the turbine blade, for example, a turbulence grid is attached.
  • the turbulence grid is intended to generate as highly turbulent a flow as possible in the following cavity or in the coolant channel leading to the cavity. Due to the inflated turbulence of the flow, an increase in the heat transfer can be achieved in the downstream cavity of the turbine blade, which leads to a higher cooling efficiency overall. The blade can thus be cooled better. Due to the higher cooling efficiency, a coolant saving can be achieved or the turbine blade can be exposed to higher hot gas temperatures while maintaining the coolant used.
  • turbulence means are not provided in the region of the cavity suitable for cooling the airfoil - such as turbulators provided in the meander channel, for example - but they are arranged in or at the region of the feed opening for swirling the coolant.
  • the feed opening is provided in a fastening section.
  • the turbine blade is held in a mounting portion on a support structure, for example on a vane support or on a rotor of the gas turbine.
  • the supply of coolant takes place in each case via the attachment portion.
  • the feed opening is provided in the attachment portion, so that the turbulence in the coolant can be generated directly upon feeding the coolant into the turbine blade, whereby the higher heat transfer can be achieved.
  • the turbulence means at least partially covers the feed opening.
  • the turbulence agent may be formed as a turbulence grid.
  • the grid which may be formed of a wire mesh or a network of wire, can completely cover the feed opening and is, however, largely permeable to the coolant, wherein the laminar flow prior to entry can be disturbed comparatively strongly.
  • the turbulence grid represents a particularly low pressure loss variant of a turbulence means. Pressure losses are thus kept comparatively low, as a result of which overall efficient cooling of the turbine blade can be achieved.
  • due to the low additional pressure loss of the turbulence grid it is possible to retrofit existing turbine blades with such turbulence means.
  • the turbine blade also has a film and / or convection cooling, possibly also an impingement cooling.
  • the turbine blade is only convectively cooled, wherein the cavity in the airfoil may comprise, for example, meander channels.
  • the meander channels On the inside of the meander channels can further turbulence agents, such as ribs or dimple, be present.
  • the turbine blade may be configured as a blade or vane of a stationary gas turbine. In principle, the turbine blade has been produced by casting and, accordingly, in one piece. The turbulence agent can then be subsequently applied after the casting process in an additional manufacturing step. For example, the turbulence grid may be soldered or welded to the turbine blade.
  • FIG. 2 shows a turbine blade 10 according to the invention in a longitudinal section.
  • the turbine blade 10 comprises an airfoil 12, which is curved profiled aerodynamically in cross section (see. FIG. 1 ).
  • the airfoil 12 has a first platform 14 and a second platform 16.
  • the plan view of the second platform 16 is in FIG. 1 shown.
  • illustrated turbine blade 10 has a total of two cavities 18, 20, each of which a coolant can be supplied.
  • the cavities 18, 20 are disposed within the airfoil 12 such that coolant flowing therein may convectively cool the airfoil 12.
  • the Indian FIG. 2 shown on the left first cavity 18 is disposed in the region of a front edge 22 of the airfoil 12.
  • the second cavity 20 is meander-shaped and terminates at a trailing edge 24.
  • the coolant which can be supplied to the second cavity 20, leaves the turbine blade 10 at the trailing edge 24.
  • outlet openings are provided in the trailing edge 24, which connect the cavity 20 with the space surrounding the airfoil 12.
  • the coolant can be fed to the cavities 18, 20 via supply openings 26 arranged in a fastening region 25.
  • the attachment region 25 is provided on the platform side, wherein the supply openings 26 are arranged on the cold side of the platform 16.
  • a turbulence means 28 is provided in the region of the feed opening 26, whereby the inflowing coolant can be swirled immediately upon entry into the turbine blade 10.
  • the turbulence means 28 is formed as a plate 30 with two openings, over each of which a wire mesh 34 is tensioned.
  • the wire mesh 34 provides a turbulence grid for the coolant, thereby swirling the substantially uniform flow of coolant as it enters the turbine blade 10. Due to the turbulence, there already arises a heat-imparting effect, so that the heat energy present in the blade material can be transferred into the coolant in a particularly simple manner.
  • the turbine blade 10 further comprises a film and / or convection cooling in order to be able to further cool regions of the airfoil 12 which are remote from the feed opening 26.
  • the invention thus relates to a turbine blade 10 with a hollow blade 12, in the cavity 18, 20 through a supply port 26, a coolant can be flowed.
  • a turbulence means 28 is provided on or in the feed opening 26, which, for example, as a turbulence grid is trained. In this way, in particular, a turbulent air flow of coolant already generated during the inflow process can be generated.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07015784A 2007-08-10 2007-08-10 Aube de turbine avec turbulateur à l'entrée d'air de refroidissement Withdrawn EP2025868A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07015784A EP2025868A1 (fr) 2007-08-10 2007-08-10 Aube de turbine avec turbulateur à l'entrée d'air de refroidissement

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07015784A EP2025868A1 (fr) 2007-08-10 2007-08-10 Aube de turbine avec turbulateur à l'entrée d'air de refroidissement

Publications (1)

Publication Number Publication Date
EP2025868A1 true EP2025868A1 (fr) 2009-02-18

Family

ID=39125199

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07015784A Withdrawn EP2025868A1 (fr) 2007-08-10 2007-08-10 Aube de turbine avec turbulateur à l'entrée d'air de refroidissement

Country Status (1)

Country Link
EP (1) EP2025868A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8864438B1 (en) * 2013-12-05 2014-10-21 Siemens Energy, Inc. Flow control insert in cooling passage for turbine vane
EP3199760A1 (fr) * 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Aube de turbine dotée d'un élément d'étranglement

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE853534C (de) * 1943-02-27 1952-10-27 Maschf Augsburg Nuernberg Ag Luftgekuehlte Gasturbinenschaufel
US3645243A (en) * 1969-10-27 1972-02-29 Nils C Ohlsson Fuel mixing and vaporizing device for internal combustion engines
US4550707A (en) * 1983-09-07 1985-11-05 Alain Kervagoret Method for improving the performance of an internal combustion engine, device for implementing the method, and internal combustion engine equipped with said device
EP0160291A1 (fr) * 1984-04-30 1985-11-06 Klöckner-Humboldt-Deutz Aktiengesellschaft Ailette refroidie de turbine
EP0340149A1 (fr) * 1988-04-25 1989-11-02 United Technologies Corporation Moyens de dépoussiérage pour une aube refroidie par de l'air
US5779447A (en) * 1997-02-19 1998-07-14 Mitsubishi Heavy Industries, Ltd. Turbine rotor
WO2002057691A1 (fr) * 2001-01-16 2002-07-25 Technologies Echangeurs Gaz-Air (T.E.G.A) Inc. Systeme echangeur thermique a gaz souple
DE10237341A1 (de) * 2002-08-14 2004-02-26 Siemens Ag Modell, Berechnung und Anwendung periodisch erzeugter Kantenwirbel im Turbomaschinenbau
US20050084370A1 (en) * 2003-07-29 2005-04-21 Heinz-Jurgen Gross Cooled turbine blade

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE853534C (de) * 1943-02-27 1952-10-27 Maschf Augsburg Nuernberg Ag Luftgekuehlte Gasturbinenschaufel
US3645243A (en) * 1969-10-27 1972-02-29 Nils C Ohlsson Fuel mixing and vaporizing device for internal combustion engines
US4550707A (en) * 1983-09-07 1985-11-05 Alain Kervagoret Method for improving the performance of an internal combustion engine, device for implementing the method, and internal combustion engine equipped with said device
EP0160291A1 (fr) * 1984-04-30 1985-11-06 Klöckner-Humboldt-Deutz Aktiengesellschaft Ailette refroidie de turbine
EP0340149A1 (fr) * 1988-04-25 1989-11-02 United Technologies Corporation Moyens de dépoussiérage pour une aube refroidie par de l'air
US5779447A (en) * 1997-02-19 1998-07-14 Mitsubishi Heavy Industries, Ltd. Turbine rotor
WO2002057691A1 (fr) * 2001-01-16 2002-07-25 Technologies Echangeurs Gaz-Air (T.E.G.A) Inc. Systeme echangeur thermique a gaz souple
DE10237341A1 (de) * 2002-08-14 2004-02-26 Siemens Ag Modell, Berechnung und Anwendung periodisch erzeugter Kantenwirbel im Turbomaschinenbau
US20050084370A1 (en) * 2003-07-29 2005-04-21 Heinz-Jurgen Gross Cooled turbine blade

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8864438B1 (en) * 2013-12-05 2014-10-21 Siemens Energy, Inc. Flow control insert in cooling passage for turbine vane
EP3199760A1 (fr) * 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Aube de turbine dotée d'un élément d'étranglement

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