EP0959228B1 - Trous de refroidissement par pellicule en agencement décalé - Google Patents

Trous de refroidissement par pellicule en agencement décalé Download PDF

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Publication number
EP0959228B1
EP0959228B1 EP98810475A EP98810475A EP0959228B1 EP 0959228 B1 EP0959228 B1 EP 0959228B1 EP 98810475 A EP98810475 A EP 98810475A EP 98810475 A EP98810475 A EP 98810475A EP 0959228 B1 EP0959228 B1 EP 0959228B1
Authority
EP
European Patent Office
Prior art keywords
holes
row
arrangement
outlet openings
diameter
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.)
Expired - Lifetime
Application number
EP98810475A
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German (de)
English (en)
Other versions
EP0959228A1 (fr
Inventor
Bernhard Dr. Weigand
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.)
General Electric Switzerland GmbH
Original Assignee
Alstom Schweiz 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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Priority to DE59808819T priority Critical patent/DE59808819D1/de
Priority to EP98810475A priority patent/EP0959228B1/fr
Priority to US09/312,061 priority patent/US6267552B1/en
Publication of EP0959228A1 publication Critical patent/EP0959228A1/fr
Application granted granted Critical
Publication of EP0959228B1 publication Critical patent/EP0959228B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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 bore arrangement for forming a cooling film a wall of a component acted upon by a hot gas stream, in particular a turbine blade or combustion chamber of a gas turbine, according to the Preamble of claim 1.
  • a test vehicle for simulating a cooling film is known at which is provided with a flat plate with holes which the blow-out openings from tubes positioned at an angle of 35 ° to the plane of the plate represent.
  • the arrangement of the holes takes the form of two with respect to the Main flow direction of staggered, laterally offset rows.
  • the test series described in this article show a significant increase of the cooling effect compared to a single row of holes.
  • This Effect is attributed to the fact that the cooling air jets emerging from the first row the cooling air jets emerging from the second row onto the surface deflect the wall to be cooled and thus improve its cooling effect.
  • the cooling film of the first row of holes over the cooling film of the row of second holes and additionally protects it against the penetration of hot gas.
  • the turbine blade known from EP 0 501 813 B1 points in a similar direction, in the case of different variants of bore arrangements for forming a cooling film be proposed in a double row.
  • One of the variants suggests two small diameter holes in the first row assign a larger diameter hole to the second row.
  • the assignments the holes in the first row to the respective holes in the second Row is given by the fact that these are flow branches of a common one Entry opening are executed.
  • the disadvantage of this solution is the high cooling air consumption caused by the high number of outlet openings of the first row is due.
  • the disadvantage is the low flexibility in the choice of the direction of the individual holes to be seen, since these start from a single, common entry bore.
  • those that emerge from the holes in the first row Cooling air jets a lateral, ie. H. Directional component perpendicular to the main flow, which in many Cases is undesirable.
  • the invention tries to avoid the disadvantages described. You are the The task is to specify a drilling arrangement of the type mentioned at the beginning, which allows a cooling film of high efficiency with reduced cooling air requirement train.
  • the number of holes in the first Row is substantially equal to or less than the number of holes in the second row.
  • a particularly effective overlay of the holes in the first row trained partial film with that of the second row results if according to a preferred variant, the holes in the first row essentially is aligned axially parallel to the bores of the second row.
  • a further improvement in the cooling effectiveness can be achieved if at least the holes in the second row in the area of the outlet openings Have axial section with a funnel-shaped cross-sectional profile.
  • the hereby achieved cross-sectional enlargement in the exit plane leads to a reduction the exit velocity of the partial cooling flows. It can be an advantage be when the axis of rotation of the funnel-shaped axial section is not coaxial to the axis of rotation of the rest of the hole, but somewhat in the direction of Main flow is inclined. As a result, the emerging cooling air jet becomes essential brought closer to the surface to be cooled.
  • a further increase in cooling capacity can be achieved if in a special one preferred variant also the holes in the first row in the area of the outlet openings have an axial section with a funnel-shaped cross-sectional profile.
  • the condition must also be met that the The area of each of the outlet openings of the first row is smaller than the area of each the outlet openings of the second row.
  • exemplary embodiments of the invention are based on a component section shown, which in particular is part of a turbine blade or combustion chamber of a gas turbine.
  • the bore arrangement shown in FIGS. 1 and 2 has a first row 1 of holes 10 on.
  • the bores 10 are arranged equidistant from one another. In the case of a turbine blade, the bores 10 can extend over the extend the entire height of the bucket.
  • Adjacent and downstream of row 1 is a second row 2 of holes 20 provided.
  • the bores 10, 20 are rotationally symmetrical executed with respect to axes of rotation 11, 21 and thus have a cylindrical Basic form.
  • the bores 10, 20 penetrate completely in the axial direction a wall 50 with the formation of inlet openings 13, 23 and outlet openings 14, 24.
  • the number of bores 10 of the first row 1 is substantially the same Number of holes 20 in the second row 2.
  • the expression “essentially equal "in this context means that due to the staggered shown here Arrangement of the holes 10 in relation to the holes 20 one of the two rows 1, 2 have an additional hole for reasons of symmetry can, but otherwise an assignment between the holes 10 of the first Row 1 and the holes 20 of the second row 2 is predetermined. In the embodiment 1, the assignment is such that the outlet openings 24 of the holes 20 with respect to the direction of the hot gas stream 100 in the The middle between the outlet openings 14 of the bores 10 is arranged. This Type of staggering has proven to be particularly beneficial in terms of effectiveness of the cooling film developing.
  • the diameter d1 of the bores 10 is smaller than the diameter d2 of the Bores 20.
  • the diameter is d1 in each case half the diameter d2. This relation ensures that the through the holes 10 emerging cooling film completely over the through the Bores 20 emerging further partial cooling film and the latter against the Wall 50 presses in the area of surface 53.
  • the comparative small diameter d1 the air consumption in relation to the achieved Extremely low cooling effect.
  • the choice of the distance is of particular importance p between the two rows 1, 2. It is correlated with the diameters d1, d2 of holes 10, 20 and should be five times the arithmetic value Do not exceed by means of the diameters d1, d2. Otherwise there is the danger of an insufficient interaction between the partial cooling films emerging from holes 10 and 20.
  • the axes of rotation 11, 21 are axially parallel aligned and somewhat inclined in the direction of the hot gas flow 100.
  • the emerging partial cooling air flows are somewhat in the direction blown onto the surface to be cooled 53 and as a result of the additional Effect of the hot gas flow 100 completely redirected.
  • both have the bores 10 'and the bores 20' axial sections 16 ', 26', the expand in a funnel shape towards outlet openings 14 ', 24'.
  • the area of the exit opening 14 ' is smaller than the area of the outlet openings 24'.
  • the funnel-shaped axial sections 16 ', 26' are not an exemplary embodiment rotationally symmetrical to the axes of rotation 11 ', 21' of the bores 10 ', 20', but rather incline towards surface 53 '.
  • FIGS. 4 to 7 are identical cylindrical bores 10 of the first row 1 as related are described with Figures 1 and 2.
  • the peculiarity lies in the Design of the bores 20 'of the second row 2', which is funnel-shaped are.
  • the embodiment shown in Figures 4 and 5 has bores 20 ' are funnel-shaped in their entire axial extent.
  • the entry openings 23 ' correspond to the variants described above circular or in the case of those shown, pointing in the direction of the main flow 100 forward tilt, elliptical.
  • the outlet openings 24 ' 4 have a trapezoidal shape with an in Direction of the hot gas stream 100 increasing width.
  • the transition from the Circular or elliptical shape of the inlet opening 23 'to the trapezoidal shape of the outlet opening 24 ' takes place continuously over the entire axial extent of the Hole 20 '. In this way, the flow is optimally designed diffuser-like cross-sectional profile.
  • the variant according to FIGS. 6 and 7 differs from the previous one through the cross-sectional profile of the bore 20 'in the axial direction. outgoing from the inlet opening 23 ', the bore is initially cylindrical.
  • the funnel-shaped axial section closes only in the vicinity of the outlet opening 24 ' 26 'on, the transition from the circular or elliptical shape to the trapezoidal shape takes place.
  • FIGS. 8 to 11 show variations of holes 10 'of the first row 1'.
  • the bores 20 'of the second row 2' are in accordance with those of the variant described above according to FIGS. 6 and 7.
  • FIGS. 8 and 9 show a modification in which the outlet opening 14 ' is also trapezoidal, the funnel-shaped axial section 16 ' is restricted to an area adjacent to the outlet opening 14 '.
  • the exemplary embodiment according to FIGS. 10 and 11 has bores 10 ', the outlet openings widened transversely to the direction of the hot gas stream 100 are executed.
  • the transition from the circular or elliptical shape of the entrance opening 13 'to the elongated hole shape of the outlet opening 14' takes place continuously along the axial extension of the bore 10 '.
  • the exemplary embodiments according to FIGS. 4 to 11 have in common that even in the case of less high-precision, for example by means of a laser beam Holes, a cooling film is formed that is highly efficient and stable over large Run lengths is.
  • the surfaces of the outlet openings 14 'of the bores 10 ' are chosen to be much smaller than the areas of the outlet openings 24' the bores 20 '.
  • the efficiency of the film cooling was demonstrated in a concrete test vehicle of a turbine profile can be demonstrated.
  • the diameter d1 was 0.35 mm
  • the diameter d2 was 0.50 mm.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Groupement de lumières destiné à générer une lame de refroidissement sur la paroi d'un élément mécanique exposée à un flux de gaz chaud, en particulier d'une aube de turbine ou d'une chambre de combustion d'une turbine à gaz, comprenant une première rangée de lumières et une seconde rangée de lumières en aval de la première rangée, le diamètre des lumières de la première rangée étant plus petit que le diamètre des lumières de la seconde rangée, caractérisé en ce que le nombre des lumières (10, 10') de la première rangée (1, 1') est sensiblement égal ou inférieur au nombre des lumières (20, 20') de la seconde rangée (2, 2').
  2. Groupement de lumières suivant la revendication 1, caractérisé en ce que les orifices de sortie (24, 24') des lumières (20, 20') de la seconde rangée (2, 2') sont décalés latéralement par rapport à la direction du flux de gaz chaud (100) ou disposés en position médiane entre des orifices de sortie (14, 14') des lumières (10, 10') de la première rangée (1, 1').
  3. Groupement de lumières suivant la revendication 1 ou 2, caractérisé en ce que les lumières (20, 20') de la seconde rangée (2, 2') sont orientées à axes parallèles par rapport aux lumières (10, 10') de la première rangée (1, 1').
  4. Groupement de lumières suivant l'une des revendications qui précèdent, caractérisé en ce que le diamètre (d1, d1') des lumières (10, 10') de la première rangée est plus grand que ou égal à la moitié du diamètre (d2, d2') des lumières (20, 20') de la seconde rangée (2, 2').
  5. Groupement de lumières suivant l'une des revendications qui précèdent, caractérisé en ce que la distance (p) séparant les deux rangées (1, 2, 1', 2') est inférieure ou égale au quintuple de la moyenne arithmétique des diamètres (d1', d2') des lumières (10, 20, 10', 20') des première et seconde rangées (1, 2, 1', 2').
  6. Groupement de lumières suivant l'une des revendications qui précèdent, caractérisé en ce que les lumières (20') de la seconde rangée (2') présentent une partie axiale (26') de section transversale en forme d'entonnoir dans la zone des orifices de sortie (24').
  7. Groupement de lumières suivant la revendication 6, caractérisé en ce que les lumières (10') de la première rangée (1') présentent une partie axiale (16') de section transversale en forme d'entonnoir dans la zone de l'orifice de sortie (14'), l'aire de chacun des orifices de sortie (14') de la première rangée (1) étant plus petite que l'aire de chacun des orifices de sortie (26') de la seconde rangée (2').
  8. Groupement de lumières suivant la revendication 6 ou 7, caractérisé en ce que les parties axiales (16') en forme d'entonnoir sont produites par laser.
  9. Groupement de lumières suivant l'une des revendications 6 à 8, caractérisé en ce que les orifices de sortie (24') et/ou les orifices de sortie (14') présentent une forme de trapèze en vue de dessus, avec une largeur croissante dans la direction du flux de gaz chaud (100).
  10. Groupement de lumières suivant l'une des revendications qui précèdent, caractérisé en ce que les orifices de sortie (24') et/ou les orifices de sortie (14') présentent, en vue de dessus, la forme de boutonnières orientées transversalement à la direction du flux de gaz chaud (100).
EP98810475A 1998-05-20 1998-05-20 Trous de refroidissement par pellicule en agencement décalé Expired - Lifetime EP0959228B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE59808819T DE59808819D1 (de) 1998-05-20 1998-05-20 Gestaffelte Anordnung von Filmkühlungsbohrungen
EP98810475A EP0959228B1 (fr) 1998-05-20 1998-05-20 Trous de refroidissement par pellicule en agencement décalé
US09/312,061 US6267552B1 (en) 1998-05-20 1999-05-17 Arrangement of holes for forming a cooling film

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98810475A EP0959228B1 (fr) 1998-05-20 1998-05-20 Trous de refroidissement par pellicule en agencement décalé

Publications (2)

Publication Number Publication Date
EP0959228A1 EP0959228A1 (fr) 1999-11-24
EP0959228B1 true EP0959228B1 (fr) 2003-06-25

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ID=8236102

Family Applications (1)

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EP98810475A Expired - Lifetime EP0959228B1 (fr) 1998-05-20 1998-05-20 Trous de refroidissement par pellicule en agencement décalé

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US (1) US6267552B1 (fr)
EP (1) EP0959228B1 (fr)
DE (1) DE59808819D1 (fr)

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US7074006B1 (en) 2002-10-08 2006-07-11 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Endwall treatment and method for gas turbine
US7008186B2 (en) * 2003-09-17 2006-03-07 General Electric Company Teardrop film cooled blade
US7223072B2 (en) * 2004-01-27 2007-05-29 Honeywell International, Inc. Gas turbine engine including airfoils having an improved airfoil film cooling configuration and method therefor
US7165940B2 (en) * 2004-06-10 2007-01-23 General Electric Company Method and apparatus for cooling gas turbine rotor blades
GB0424593D0 (en) * 2004-11-06 2004-12-08 Rolls Royce Plc A component having a film cooling arrangement
US7186085B2 (en) * 2004-11-18 2007-03-06 General Electric Company Multiform film cooling holes
US7883320B2 (en) * 2005-01-24 2011-02-08 United Technologies Corporation Article having diffuser holes and method of making same
US7415827B2 (en) 2005-05-18 2008-08-26 United Technologies Corporation Arrangement for controlling fluid jets injected into a fluid stream
US20080005903A1 (en) * 2006-07-05 2008-01-10 United Technologies Corporation External datum system and film hole positioning using core locating holes
US8052378B2 (en) * 2009-03-18 2011-11-08 General Electric Company Film-cooling augmentation device and turbine airfoil incorporating the same
US20100239409A1 (en) * 2009-03-18 2010-09-23 General Electric Company Method of Using and Reconstructing a Film-Cooling Augmentation Device for a Turbine Airfoil
US8684691B2 (en) 2011-05-03 2014-04-01 Siemens Energy, Inc. Turbine blade with chamfered squealer tip and convective cooling holes
US9410435B2 (en) * 2012-02-15 2016-08-09 United Technologies Corporation Gas turbine engine component with diffusive cooling hole
US9279330B2 (en) 2012-02-15 2016-03-08 United Technologies Corporation Gas turbine engine component with converging/diverging cooling passage
EP2861909A2 (fr) 2012-06-13 2015-04-22 General Electric Company Paroi de moteur de turbine à gaz
US20140075947A1 (en) * 2012-09-18 2014-03-20 United Technologies Corporation Gas turbine engine component cooling circuit
EP2964891B1 (fr) 2013-03-05 2019-06-12 Rolls-Royce North American Technologies, Inc. Agencement de composant pour moteur à turbine à gaz
US9874110B2 (en) 2013-03-07 2018-01-23 Rolls-Royce North American Technologies Inc. Cooled gas turbine engine component
US20160153282A1 (en) * 2014-07-11 2016-06-02 United Technologies Corporation Stress Reduction For Film Cooled Gas Turbine Engine Component
US10247011B2 (en) * 2014-12-15 2019-04-02 United Technologies Corporation Gas turbine engine component with increased cooling capacity
CN105626161A (zh) * 2015-12-25 2016-06-01 中国航空工业集团公司沈阳发动机设计研究所 一种冷却强度径向不均匀的涡轮叶片
DE102017207863A1 (de) * 2017-05-10 2018-11-15 MTU Aero Engines AG Komponente für eine Strömungsmaschine
US10539026B2 (en) 2017-09-21 2020-01-21 United Technologies Corporation Gas turbine engine component with cooling holes having variable roughness
JP6943706B2 (ja) * 2017-09-22 2021-10-06 三菱パワー株式会社 タービン翼及びガスタービン

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FR2725474B1 (fr) 1984-03-14 1996-12-13 Snecma Aube de distributeur de turbine refroidie
US4726735A (en) * 1985-12-23 1988-02-23 United Technologies Corporation Film cooling slot with metered flow
US4676719A (en) * 1985-12-23 1987-06-30 United Technologies Corporation Film coolant passages for cast hollow airfoils
GB2227965B (en) * 1988-10-12 1993-02-10 Rolls Royce Plc Apparatus for drilling a shaped hole in a workpiece
US5326224A (en) 1991-03-01 1994-07-05 General Electric Company Cooling hole arrangements in jet engine components exposed to hot gas flow
US5816777A (en) * 1991-11-29 1998-10-06 United Technologies Corporation Turbine blade cooling
US5374162A (en) * 1993-11-30 1994-12-20 United Technologies Corporation Airfoil having coolable leading edge region
JPH07279612A (ja) * 1994-04-14 1995-10-27 Mitsubishi Heavy Ind Ltd 重質油焚き用ガスタービン冷却翼
US5586859A (en) * 1995-05-31 1996-12-24 United Technologies Corporation Flow aligned plenum endwall treatment for compressor blades

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Publication number Publication date
US6267552B1 (en) 2001-07-31
EP0959228A1 (fr) 1999-11-24
DE59808819D1 (de) 2003-07-31

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