EP3408501B1 - Trou pour film d'air de refroidissement dans des pièces de turbine à gaz - Google Patents

Trou pour film d'air de refroidissement dans des pièces de turbine à gaz Download PDF

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Publication number
EP3408501B1
EP3408501B1 EP17715064.6A EP17715064A EP3408501B1 EP 3408501 B1 EP3408501 B1 EP 3408501B1 EP 17715064 A EP17715064 A EP 17715064A EP 3408501 B1 EP3408501 B1 EP 3408501B1
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EP
European Patent Office
Prior art keywords
section
diffusor
cooling hole
inflow
film
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.)
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Application number
EP17715064.6A
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German (de)
English (en)
Other versions
EP3408501A1 (fr
Inventor
Thomas Beck
Stefan Dahlke
Jens Dietrich
Sebastian HOHENSTEIN
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 Energy Global GmbH and Co KG
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Siemens Energy Global GmbH and Co KG
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Publication of EP3408501A1 publication Critical patent/EP3408501A1/fr
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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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent
    • 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
    • F05D2250/52—Outlet
    • 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
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • the invention relates to film cooling holes of gas turbine components to be cooled.
  • Gas turbine components that have film cooling holes can, for example, be turbine blades, ring segments or also combustion chamber components.
  • a cooling air film can be generated on surfaces of the components to be cooled over which hot gas can flow, which is intended to protect them from direct contact and thus from the thermal influences of the hot gas flowing along them.
  • the EP 0 227 578 A2 a conventional film cooling air hole with a diffuser-like area connected to a round inlet.
  • the diffuser-like area enables the cooling air flowing out to be fanned out in the lateral direction.
  • the object of this invention is to provide a film cooling hole with which particularly efficient film cooling can be achieved.
  • FIGS Figures 4 to 7 show a previously known film cooling hole 2.
  • Figures 1 to 3 show a previously known film cooling hole 2.
  • Each of the film cooling holes 2, 20 shown is formed as a through hole in a wall 14 that can be acted upon by hot gas, so that it extends from a first surface 16 of the wall 14 to a second surface 18 opposite it the wall 14 extends.
  • a hotter medium M H flows over the first surface 16, whereas the second surface 18 is exposed to a cooler medium M K during this time.
  • the hotter medium is a working medium and the cooler medium is cooling air.
  • the wall 14 can, for example, be a component part of a turbine blade of a turbomachine, a ring segment, a combustion chamber wall or the like and in this case have one or more rows with such or similar film cooling holes 2, 20.
  • the respective film cooling holes 2, 20 are arranged inclined with respect to the surfaces 16, 18.
  • Each film cooling hole 2, 20 comprises an inflow opening 22 which is arranged in the second surface 18.
  • the cooler medium can flow into the relevant film cooling hole through this inflow opening 22.
  • the medium that has flowed in leaves the relevant film cooling hole 2, 20 through an outflow opening 24 arranged in the first surface 16.
  • a first longitudinal section of the film cooling hole 2, 20, hereinafter referred to as inflow section 26, extends from inflow opening 22 to a transition point 25 and has a constant throughflow diameter d.
  • the flow rate of the emerging medium M K can be adjusted by means of this diameter d.
  • a constantly changing diffuser section 28 which extends as far as the outflow opening 24, follows immediately downstream of the transition point 25.
  • Each film cooling hole has a virtual longitudinal axis LL which extends through the center points of the inflow section 26 and extends beyond that.
  • the relevant film cooling holes 2, 20 are inclined with respect to the first surface 16 in such a way that the virtual central longitudinal axis LL - in a cross-sectional view through the relevant wall 14 - includes an acute angle of inclination ⁇ N with an upstream region 16a of the second surface 16.
  • the inflow section 26 has the length L cyl and the diffuser section 28 the length L diff , which can be combined to form a hole length L.
  • the diffuser section 28 of the film cooling hole 2, 20 comprises four individually identifiable side walls, which are hereinafter referred to as peripheral sections and which merge into one another along the circumference.
  • a first circumferential section UA H is at a smaller distance from the first surface 16 and thus faces the hotter medium M H.
  • This circumferential section UA H ends on the one hand at a diffuser edge 34 on the inflow side with respect to the hotter medium M H and on the other hand merges laterally on both sides into a lateral circumferential section UA S1 , UA S2 .
  • the two lateral circumferential sections UA S1 , UA S2 each then merge into a common circumferential section UA K , which is at a smaller distance from the second surface 18 and thus faces the cooler medium M K.
  • the further circumferential section UA K thus ends at a diffuser edge 30 which is downstream in relation to the hotter medium M H and which is preferably essentially straight.
  • a distance w bc between the inflow-side diffuser edge 34 and the outflow-side diffuser edge 30 can be determined.
  • the walls of the lateral circumferential sections UA S1 , UA S2 are designed to be largely straight.
  • the increasing enlargement of the flow cross section in the diffuser section 28 of the film cooling hole 20 takes place in one dimension (lateral directions LR) alone.
  • the increase occurs of the through-flow cross-section mainly in that the lateral peripheral portions UA S1, UA S2 diverge the film cooling hole 20, whereas in the diffuser section 28, the distance between the hotter medium M H facing peripheral portion UA H and the cooler medium M K facing peripheral portion UA K at the outflow opening 24 is at most only insignificantly larger than the diameter d of the inflow section 26.
  • the detectable length L diff of the diffuser section 28 between the transition point 25 and the outflow opening 24 is greater than 7 times the diameter d of the inflow section 26. This ensures that the diffuser section is comparatively long and can therefore widen sufficiently. A comparatively broad film of cooling air can then form during operation.
  • the diffuser-like widening of the film cooling hole 20 in the diffuser section 28 immediately downstream of the transition point 25 - in a cross-sectional view through the relevant wall 14 - has a diffuser height h that is smaller than the diameter d of the inflow section 26. It is preferably smaller than 50% of the Diameter d.
  • the diffuser inlet begins with a comparatively gentle diffuser widening, which reduces the tendency of the cooling air flow to detach.
  • the diffuser-like widening of the film cooling hole 20 does not begin at that section of the circumference of the film cooling hole 20 which is closest to the second surface 18, but rather at the two lateral sections of the circumference. In this way, the flow inside the film cooling hole 20 can be fanned out with less loss, since a pressure distribution is established which is less asymmetrical, but rather more evened out.
  • a width B of the outflow opening 24 that can be detected perpendicular to the flow direction of the hotter medium M H is greater than in the case of conventional film cooling holes 2 with comparable diffuser opening ratios.
  • This has a positive effect on the counter-rotating pairs of vertebrae 23, which are usually located on the outer lateral edges of the Outflow opening 24, ie the imaginary extensions of the lateral circumferential sections UA S1 and UA S2 occur.
  • this has a first-order influence on the mixing process of cooler medium M K and hotter medium M H.
  • the distance between the two legs of the counter-rotating pairs of vertebrae 23 can be increased by the proposed design.
  • the cooler medium M K flowing out in the area of the virtual central longitudinal axis LL is less influenced by the counter-rotating vortex pairs 23, which reduces the intermixing.
  • the strength of the counter-rotating vortex pairs 23 can also be reduced as a result. As a result, this leads to an increased coverage of the first surface 16 with the desired cooling air film.
  • the greater spread ie the enlarged opening angle ⁇ 1 of the diffuser section 28 compared to the prior art in the direction perpendicular to the flow direction of the hotter medium M H (lateral direction LR)
  • a local overcooling of the first surface 16 in the central area of the virtual longitudinal axis LL immediately downstream of the diffuser edge 30 on the downstream side can be reduced.
  • the cooling can thus be made more uniform.
  • the opening angle ⁇ 1 is not greater than 12 °. It is preferably 11.5 °.
  • the diffuser edge 34 on the inflow side is preferably designed to be symmetrically curved, its central region being arranged slightly further upstream than its lateral ends. As a result, the film cooling hole 20 can be produced more easily since the inflow section is drilled and first then the contour of the diffuser section can be produced.
  • the invention relates to a film cooling hole 20 of gas turbine components to be cooled, with an inflow section 26 with a constant flow cross section, to which a diffuser section 28 with a changing flow cross section is connected.
  • the diffuser region 26 be expanded only in the lateral direction LR.

Landscapes

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

Claims (7)

  1. Pièce (12) refroidie d'une turbine,
    comprenant une paroi (14), qui est délimitée par une première surface (16) et par une deuxième surface (18) opposée à la première surface (16), la première surface (16) étant prévue pour être parcourue par un fluide (MH) assez chaud qui peut passer d'une partie (16a) en amont à une partie (16b) en aval, et la deuxième surface (18) étant prévue pour venir en contact avec un fluide (MK) assez froid,
    comprenant au moins un trou (20) de refroidissement pelliculaire, incliné par rapport à la deuxième surface (18), pour le passage du fluide (MK) assez froid à travers la paroi vers la deuxième surface (16),
    dans laquelle le trou (20) de refroidissement pelliculaire concerné comprend :
    - une ouverture (22) d'entrée, qui est disposée dans la deuxième surface (18) et par laquelle le fluide (MK) assez froid peut pénétrer dans le trou (20) de refroidissement pelliculaire,
    - une ouverture (24) de sortie, qui est disposée dans la première surface (16) et par laquelle le fluide (MK) assez froid, qui peut passer à l'intérieur du trou (20) de refroidissement pelliculaire, peut quitter le trou (20) de refroidissement pelliculaire,
    - un axe (LL) longitudinal central virtuel, qui s'étend, par une longueur (L) de trou, de l'ouverture (22) d'entrée à l'ouverture (24) de sortie,
    - quatre parties de pourtour, qui se confondent l'une après l'autre successivement suivant un pourtour tangentiel à l'axe longitudinal :
    * une partie (UAH) de pourtour tournée vers le milieu assez chaud,
    * une première partie (UAS1) de pourtour latérale,
    * une partie (UAK) de pourtour tournée vers le fluide assez froid et
    * une deuxième partie (UAS2) de pourtour latérale,
    - une partie (26) d'entrée disposée entre l'ouverture (22) d'entrée et un point (25) de transition et ayant une section transversale de passage constante et
    - une partie (28) de diffuseur allant, du point (25) de transition à l'ouverture (24) de sortie et ayant un élargissement de type en diffuseur du trou (20) de refroidissement pelliculaire et ayant une section transversale de passage croissant dans ce sens,
    - un bord (30) de diffuseur en aval, où la partie (UAK) de pourtour tournée vers le fluide assez froid est voisine de la deuxième surface (16),
    - un bord (34) de diffuseur en amont où la partie (UAH) de pourtour tournée vers le fluide assez chaud est voisine de la deuxième surface (16) et
    - une distance (Wbc) entre le bord (34) de diffuseur en amont et le bord (30) de diffuseur en aval, l'inclinaison du trou (20) de refroidissement pelliculaire par rapport à la première surface (16) étant telle que l'axe (LL) longitudinal central virtuel - considéré en section transversale dans la paroi (14) concernée - fait avec la partie (16a) en amont de la deuxième surface (16) un angle (αN) d'inclinaison aigu et dans laquelle la partie (UAK) de pourtour tournée vers le fluide (MK) assez froid fait avec l'axe (LL) longitudinal virtuel - considéré suivant une section transversale de la paroi (14) concernée - un angle (α3) de recoupement,
    dans laquelle,
    l'angle (α3) de recoupement a une valeur plus petite que 1°, caractérisée,
    en ce que l'élargissement de type en diffuseur du trou (20) de refroidissement pelliculaire dans la partie de diffuseur immédiatement en aval du point (25) de transition - considéré dans la section transversale de la paroi (14) concernée a une hauteur (h) de diffusion qui est plus petite que le diamètre (d) de la partie (26) d'entrée.
  2. Pièce (12) suivant la revendication 1,
    dans laquelle la longueur (Ldiff), pouvant être relevée entre le point (25) de transition et l'ouverture (24) de sortie, de la partie (28) de diffuseur est plus grande que 7 fois le diamètre (d) de la partie (26) d'entrée.
  3. Pièce (12) suivant l'une des revendications 1 ou 2,
    dans laquelle les parties (UAS1, UAS2) latérales de pourtour de la partie (28) de diffuseur sont en ligne droite en projection perpendiculaire à la première surface (16) et celles-ci font avec l'axe (LL) longitudinal central virtuel un angle (β1) d'ouverture d'au moins 11,5°.
  4. Pièce (12) suivant l'une des revendications 1, 2 ou 3,
    dans laquelle le bord (30) de diffuseur en aval est sensiblement droit.
  5. Pièce (12) suivant l'une des revendications précédentes,
    dans laquelle le bord (34) de diffuseur en amont est incurvé.
  6. Pièce (12) suivant l'une des revendications précédentes,
    dans laquelle la distance (Wbc) correspond sensiblement au diamètre (d) de la partie (26) d'entrée divisée par le sinus de l'angle (αN) d'inclinaison : Wbc = d / sin (αN).
  7. Pièce (12) suivant l'une des revendications précédentes, comprenant une pluralité de trous (20) de refroidissement pelliculaire disposés en une rangée ou en plusieurs rangées.
EP17715064.6A 2016-03-23 2017-03-22 Trou pour film d'air de refroidissement dans des pièces de turbine à gaz Active EP3408501B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016204824.4A DE102016204824A1 (de) 2016-03-23 2016-03-23 Filmkühllöcher in Gasturbinen - Bauteilen
PCT/EP2017/056834 WO2017162743A1 (fr) 2016-03-23 2017-03-22 Trou pour film d'air de refroidissement dans des pièces de turbine à gaz

Publications (2)

Publication Number Publication Date
EP3408501A1 EP3408501A1 (fr) 2018-12-05
EP3408501B1 true EP3408501B1 (fr) 2021-03-17

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ID=58464510

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Application Number Title Priority Date Filing Date
EP17715064.6A Active EP3408501B1 (fr) 2016-03-23 2017-03-22 Trou pour film d'air de refroidissement dans des pièces de turbine à gaz

Country Status (4)

Country Link
US (1) US20190078443A1 (fr)
EP (1) EP3408501B1 (fr)
DE (1) DE102016204824A1 (fr)
WO (1) WO2017162743A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114719290B (zh) * 2022-03-17 2023-03-31 西北工业大学 一种放气方案可调的扩压器结构及应用

Family Cites Families (8)

* 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
US4726735A (en) 1985-12-23 1988-02-23 United Technologies Corporation Film cooling slot with metered flow
US4684323A (en) * 1985-12-23 1987-08-04 United Technologies Corporation Film cooling passages with curved corners
EP0945593B1 (fr) * 1998-03-23 2003-05-07 ALSTOM (Switzerland) Ltd Trou de refroidissement pelliculaire
DE19960797C1 (de) * 1999-12-16 2001-09-13 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Öffnung in einem metallischen Bauteil
US8672613B2 (en) * 2010-08-31 2014-03-18 General Electric Company Components with conformal curved film holes and methods of manufacture
US9422815B2 (en) * 2012-02-15 2016-08-23 United Technologies Corporation Gas turbine engine component with compound cusp cooling configuration
CN104747242A (zh) * 2015-03-12 2015-07-01 中国科学院工程热物理研究所 一种离散气膜冷却孔

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
WO2017162743A1 (fr) 2017-09-28
DE102016204824A1 (de) 2017-09-28
US20190078443A1 (en) 2019-03-14
EP3408501A1 (fr) 2018-12-05

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