EP0992653A1 - Composants réfroidis par couche d'air avec perçages de refroidissement à section transversale triangulaire - Google Patents

Composants réfroidis par couche d'air avec perçages de refroidissement à section transversale triangulaire Download PDF

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Publication number
EP0992653A1
EP0992653A1 EP98811012A EP98811012A EP0992653A1 EP 0992653 A1 EP0992653 A1 EP 0992653A1 EP 98811012 A EP98811012 A EP 98811012A EP 98811012 A EP98811012 A EP 98811012A EP 0992653 A1 EP0992653 A1 EP 0992653A1
Authority
EP
European Patent Office
Prior art keywords
hot gas
film cooling
film
component
cooling 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.)
Withdrawn
Application number
EP98811012A
Other languages
German (de)
English (en)
Inventor
Ewald Lutum
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 Research Ltd Switzerland
ABB Research Ltd Sweden
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Priority to EP98811012A priority Critical patent/EP0992653A1/fr
Publication of EP0992653A1 publication Critical patent/EP0992653A1/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Withdrawn legal-status Critical Current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
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/11—Two-dimensional triangular
    • 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 present invention relates to a thermally highly resilient component, which is subjected to a hot gas flow during operation, which Component exposed to at least one of the hot gas flow Hot gas side and a cold gas side not exposed to the hot gas flow has, the hot gas side in operation by a cooling film in front of the direct contact with the hot gas, which cooling film is protected from a fluid is formed, which is integrated into the component by the Hot gas and cold gas side connecting film cooling channels on the Hot gas side of the component is guided, the cross section at least one of the film cooling channels is constant over its entire length Surface and has a constant geometry.
  • Cylindrical are usually used for the transfer of the cooling medium Drilled holes in the component to be cooled, which in transverse to Main flow direction of the hot gas flow oriented rows are arranged.
  • the development towards higher hot gas temperatures has however, has led to an ever increasing amount of cooling air. This is, however the blow-out rate has risen so much that the cooling effectiveness drops drastically, this means that the amount of cooling air has to be increased disproportionately to achieve a desired absolute cooling.
  • the object of the invention is, in a thermally highly resilient component, which is subjected to a hot gas flow during operation, which Component exposed to at least one of the hot gas flow Hot gas side and a cold gas side not exposed to the hot gas flow has, the hot gas side in operation by a cooling film in front of the direct contact with the hot gas, which cooling film is protected from a fluid is formed, which is integrated into the component by the Hot gas and cold gas side connecting film cooling channels on the Hot gas side of the component is guided, the cross section at least one of the film cooling channels is constant over its entire length Surface and has a constant geometry, a geometry of Specify film cooling channels in which the cooling effectiveness even at high Blow-out rates are maintained.
  • the essence of the invention is, therefore, the film cooling channels thermally to design highly stressed components so that the replacement of the Film flow is prevented as possible. Due to the large number in Each individual component of channels to be introduced must be made Economic considerations also a simple production in as possible an operation using widely used machining methods be given.
  • this is achieved in that this film cooling channel is laterally delimited by three flat boundary surfaces.
  • the invention thus proposes a film cooling channel with a triangular shape Channel cross section before, the corners for reasons of strength and the Manufacturing will generally be rounded.
  • the cross-sectional area is kept constant over the entire channel length.
  • the channel cross section advantageously takes the form of a very flattened shape isosceles triangle, that is, two of the side of the channel bounding surfaces will enclose an angle of more than 120 °. Furthermore, the surface opposite this angle is advantageous arranged that their line of penetration with the component surface transverse to Main flow is oriented, and the outlet mouth of the film cooling channel limited upstream.
  • the resulting outlet mouth can be described as a flattened triangle, the broad base of which is oriented transversely to the hot gas flow and the tip of which points in the direction of the hot gas flow.
  • This configuration results in a number of advantageous effects: On the one hand, compared to a cylindrical film cooling channel with the same cross coverage the surface to be cooled requires significantly less cooling medium, or the overlap is significantly increased with the same coolant throughput. Experimental investigations have also shown that the cooling film lies better on the surface to be cooled, because the transverse orientation to the hot gas flow directs the coolant jet in a tangential direction with a large aerodynamic force.
  • An additional advantage of the inventive design of the film cooling channels is that secondary currents are induced in them, which efficiently counteract rapid mixing of the hot gas flow and cooling medium.
  • the described shape of the film cooling openings can be easily produced as there are no cross-sectional transitions to be worked into the material.
  • the additional manufacturing effort compared to cylindrical bores is right low.
  • devices for electrochemical Drilling the film cooling channels after replacing the dies without further changes continue to be used, in particular remain the manufacturing steps are identical.
  • Laser drilling is also no change to existing fixtures necessary.
  • FIG. 1 is an example of a film-cooled component Turbine blade 10 shown. This is in the direction of the arrows from one Hot gas flow 8 flows around. Through the interior 11, which by webs 20th is divided, the blade is supplied with cooling medium. This is through Film cooling channels 30 guided to the outside of the blade and forms there a cooling film. As can be seen in the drawing, the channels 30 in arranged transversely to the inflow 8 rows to one possible to ensure complete wetting of the surface 14 to be cooled.
  • the illustration of a blade with the cooling medium through the interior is not a limitation here.
  • an element over which hot gas flows only on one side for example a Combustion chamber segment to be cooled in this way.
  • the Film cooling channels then do not connect an interior with one Outside space, but an area not exposed to hot gas cooling surface.
  • FIG. 2 shows the geometry of a design according to the invention Shown film cooling channel 30 which is in a plane perpendicular to Coolant flow 35 is cut.
  • the film cooling channel is through three adjacent flat boundary surfaces 301, 302 and 303 laterally limited. The transitions are for reasons of production and strength rounded between two boundary surfaces.
  • the boundary surfaces include angles A, B and C, one of which is the Angle, here the angle C, preferably greater than 120 °, is selected from Reasons discussed below. Likewise, angles A and B are made fluid-mechanical considerations preferably chosen to be the same size.
  • FIG. 3 shows a section of a film-cooled component 10, which with film cooling openings 30 according to the invention is provided in a Top view of the hot gas side 14, as well as a side view in section Z-Z.
  • the surface 14 to be cooled is in the direction of the arrow by a Hot gas flow 8 overflows.
  • the film cooling channel 30 opens onto the Hot gas side 14; the channel mouth is through the penetration lines 311, 312, 313 of the boundary surfaces 301, 302, 303 defined. Because of the generally large angle of attack D of the channel against the normal 141 the hot gas side 14 are the angles A, B and C on the hot gas side strongly distorted as the angles A ', B' and C '.
  • the film cooling channel is advantageously in such a way in the component to be cooled incorporated that the penetration line 311 of the surface which corresponds to the angle C opposite, the mouth of the channel 30 on the to be cooled
  • Component surface 14 upstream of the hot gas flow limited, and transverse to Flow direction of the hot gas is arranged.
  • the mouth thus receives essentially the shape of a triangle with rounded corners that through the edges 311, 312 and 313 is formed, being more expedient Forming the film cooling channel 30 the edge 311 a very wide base forms, and which with a tip enclosing the angle C 'in Main flow direction shows.
  • angles A and B. it is also advantageous to use the angles A and B. to choose the same size, which in the preferred shown Configuration of the film cooling channel symmetrical to the main flow direction of the hot gas. If this symmetry is not given, they take effect aerodynamic forces also asymmetrical on the coolant jet and deflect it laterally.
  • Fig. 4 are a series of cylindrical film cooling channels and a series compared film cooling channels according to the invention. Clear The lateral coverage is recognizable in the embodiment according to the invention the surface to be cooled with a constant cross-sectional area of the channels significantly increased, which of course improves the cooling effectiveness.
  • the advantageous effects were verified by measurements, the results of which are shown qualitatively in FIG. 5.
  • the adiabatic cooling effectiveness ⁇ ad relates the temperature gradient between the surface to be cooled and the hot gas to the temperature gradient between the coolant and hot gas.
  • the blowout rate M can be interpreted as a volume-specific pulse ratio of coolant flow and hot gas flow.
  • the measured values are plotted for different values X / D, where X represents a distance downstream of the blow-out point and D represents a hydraulically equivalent diameter of the film cooling channel.
  • X represents a distance downstream of the blow-out point
  • D represents a hydraulically equivalent diameter of the film cooling channel.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98811012A 1998-10-08 1998-10-08 Composants réfroidis par couche d'air avec perçages de refroidissement à section transversale triangulaire Withdrawn EP0992653A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP98811012A EP0992653A1 (fr) 1998-10-08 1998-10-08 Composants réfroidis par couche d'air avec perçages de refroidissement à section transversale triangulaire

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98811012A EP0992653A1 (fr) 1998-10-08 1998-10-08 Composants réfroidis par couche d'air avec perçages de refroidissement à section transversale triangulaire

Publications (1)

Publication Number Publication Date
EP0992653A1 true EP0992653A1 (fr) 2000-04-12

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EP98811012A Withdrawn EP0992653A1 (fr) 1998-10-08 1998-10-08 Composants réfroidis par couche d'air avec perçages de refroidissement à section transversale triangulaire

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EP (1) EP0992653A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SG90121A1 (en) * 1999-04-05 2002-07-23 Gen Electric A method for improving the cooling effectiveness of a geseous coolant stream which flows through a substrate, and related articles of manufacture
EP2343435A1 (fr) * 2009-11-25 2011-07-13 Honeywell International Inc. Composant de moteur à turbine à gaz à refroidissement par film amélioré
US8371814B2 (en) 2009-06-24 2013-02-12 Honeywell International Inc. Turbine engine components
US8628293B2 (en) 2010-06-17 2014-01-14 Honeywell International Inc. Gas turbine engine components with cooling hole trenches
US9650900B2 (en) 2012-05-07 2017-05-16 Honeywell International Inc. Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations
WO2018024759A1 (fr) * 2016-08-02 2018-02-08 Siemens Aktiengesellschaft Procédé de fabrication d'une structure de conduit et constituants
US10113433B2 (en) 2012-10-04 2018-10-30 Honeywell International Inc. Gas turbine engine components with lateral and forward sweep film cooling holes
US11021965B2 (en) 2016-05-19 2021-06-01 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3527543A (en) 1965-08-26 1970-09-08 Gen Electric Cooling of structural members particularly for gas turbine engines
US3623711A (en) * 1970-07-13 1971-11-30 Avco Corp Combustor liner cooling arrangement
EP0290370A1 (fr) * 1987-05-04 1988-11-09 United Technologies Corporation Paroi métallique mince et refroidissable
US4887663A (en) * 1988-05-31 1989-12-19 United Technologies Corporation Hot gas duct liner
EP0375175A1 (fr) * 1988-12-23 1990-06-27 ROLLS-ROYCE plc Composants refroidis pour turbomachines
US5000005A (en) * 1988-08-17 1991-03-19 Rolls-Royce, Plc Combustion chamber for a gas turbine engine
EP0648918A1 (fr) 1993-10-15 1995-04-19 United Technologies Corporation Passage pour le refroidissement des parois minces par pellicule

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3527543A (en) 1965-08-26 1970-09-08 Gen Electric Cooling of structural members particularly for gas turbine engines
US3623711A (en) * 1970-07-13 1971-11-30 Avco Corp Combustor liner cooling arrangement
EP0290370A1 (fr) * 1987-05-04 1988-11-09 United Technologies Corporation Paroi métallique mince et refroidissable
US4887663A (en) * 1988-05-31 1989-12-19 United Technologies Corporation Hot gas duct liner
US5000005A (en) * 1988-08-17 1991-03-19 Rolls-Royce, Plc Combustion chamber for a gas turbine engine
EP0375175A1 (fr) * 1988-12-23 1990-06-27 ROLLS-ROYCE plc Composants refroidis pour turbomachines
EP0648918A1 (fr) 1993-10-15 1995-04-19 United Technologies Corporation Passage pour le refroidissement des parois minces par pellicule

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SG90121A1 (en) * 1999-04-05 2002-07-23 Gen Electric A method for improving the cooling effectiveness of a geseous coolant stream which flows through a substrate, and related articles of manufacture
US8371814B2 (en) 2009-06-24 2013-02-12 Honeywell International Inc. Turbine engine components
EP2343435A1 (fr) * 2009-11-25 2011-07-13 Honeywell International Inc. Composant de moteur à turbine à gaz à refroidissement par film amélioré
US8529193B2 (en) 2009-11-25 2013-09-10 Honeywell International Inc. Gas turbine engine components with improved film cooling
US8628293B2 (en) 2010-06-17 2014-01-14 Honeywell International Inc. Gas turbine engine components with cooling hole trenches
US9650900B2 (en) 2012-05-07 2017-05-16 Honeywell International Inc. Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations
US10113433B2 (en) 2012-10-04 2018-10-30 Honeywell International Inc. Gas turbine engine components with lateral and forward sweep film cooling holes
US11021965B2 (en) 2016-05-19 2021-06-01 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions
US11286791B2 (en) 2016-05-19 2022-03-29 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions
WO2018024759A1 (fr) * 2016-08-02 2018-02-08 Siemens Aktiengesellschaft Procédé de fabrication d'une structure de conduit et constituants

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