EP3408501A1 - 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

Info

Publication number
EP3408501A1
EP3408501A1 EP17715064.6A EP17715064A EP3408501A1 EP 3408501 A1 EP3408501 A1 EP 3408501A1 EP 17715064 A EP17715064 A EP 17715064A EP 3408501 A1 EP3408501 A1 EP 3408501A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
film cooling
cooling hole
inflow
section
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.)
Granted
Application number
EP17715064.6A
Other languages
German (de)
English (en)
Other versions
EP3408501B1 (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
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
Publication of EP3408501A1 publication Critical patent/EP3408501A1/fr
Application granted granted Critical
Publication of EP3408501B1 publication Critical patent/EP3408501B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 having film cooling holes may be, for example, turbine blades, ring segments or combustion chamber components.
  • a cooling air film can be produced on areas of the components to be cooled which can be overflowed by hot gas, which should protect them from direct contact and thus from the thermal influences of the hot gas flowing therealong.
  • EP 0 227 578 A2 discloses a conventional film cooling air hole, in which a diffuser-like region adjoins a round inlet.
  • Object of this invention is to provide a film cooling hole, with a particularly efficient film cooling can be ⁇ he can see.
  • Figure 1 is a conventional film cooling hole with counter ro ⁇ animal vortex pairs.
  • FIG. 2 shows the conventional film cooling hole in a cross section
  • FIG. 3 shows the conventional film cooling hole in a plan view
  • FIG. 4 shows a film cooling hole according to the invention in a perspective view
  • FIG. 5 shows the film cooling hole according to the invention with counter-rotating swirl pairs, a cross section through a component wall having the film cooling hole according to the invention and a top view, perpendicular to the first surface, of the film cooling hole according to the invention.
  • FIGS. 4 to 7 show a previously known film cooling hole 2.
  • FIGS. 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 to be charged with hot gas, so as to extend from a first surface 16 of the wall 14 to a second surface 18 opposite thereto the wall 14 extends.
  • the first surface 16 is overflowed at be ⁇ humor proper use of the invention from a hotter medium M is H, whereas the second surface 18 currencies ⁇ rend which a cooler medium M is exposed to K.
  • Customarily as it concerns with the hotter medium is a work ⁇ medium and the cooler medium is cooling air.
  • the wall 14 can, for example, one component of a turbine blade of a turbomachine, of a ring segment, a combustion chamber wall ⁇ or the like while one or more rows with such or similar film cooling holes 2, have twentieth
  • the respective film cooling holes 2, 20 are inclined relative to the surfaces 16, 18.
  • Each film cooling hole 2, 20 comprises an inflow opening 22, which is arranged in the second surface 18. Through this inflow opening 22, the cooler medium can flow into the relevant film cooling hole. The inflowing medium leaves the relevant film cooling hole 2, 20 through an outflow opening 24 arranged in the first surface 16.
  • each film cooling hole has a virtual longitudinal axis LL, wel ⁇ che to he stretches ⁇ through the centers of the flow-in portion 26 and extends beyond it.
  • the film in question ⁇ cooling holes 2, 20 are opposed to the first surface 16 DER art inclined so that the virtual central longitudinal axis LL - in a cross-sectional view through the respective wall 14 - having an upstream region 16a of the second surface 16 form an acute angle of inclination N including , Viewed along the virtual longitudinal axis LL have the
  • the diffuser portion 28 of the film cooling hole 2, 20 comprises four individually identifiable side walls, which are called peripheral portions according to the following ⁇ and along the circulation merge into one another.
  • a first peripheral portion UA H has a smaller distance to the first surface 16 and thus faces the hotter medium M H.
  • this peripheral portion UA H terminates at a diffuser edge 34 upstream of the hotter medium M H and, on the other hand, transitions laterally on both sides into a respective lateral peripheral portion UA S i, UA S 2.
  • the two lateral circumferential portions UA S i, S 2 UA will then in each case in a common ⁇ seed peripheral portion UA K above, which has a smaller distance from the second surface 18 and is therefore facing the cooler Me ⁇ medium M, K.
  • the further peripheral portion UA K thus ends at a with respect to the hotter medium M H.
  • the diffuser downstream edge 30 that is straight preferably in materiality ⁇ union. Overall, a distance w bc between inflow-side diffuser edge 34 and outflow-side diffuser edge 30 can be determined.
  • the cooler medium facing peripheral portion UA K with the virtual longitudinal axis LL includes a so-called reserve angle CX3.
  • an opening angle can SSI each between the lateral peripheral portions UA S i, S 2 of the UA
  • Diffuser section 28 and be detected with the virtual central longitudinal ⁇ LL.
  • the increasing in the diffuser section 28 of the film cooling hole 20 enlargement of the flow cross ⁇ section alone in one dimension (lateral directions LR) takes place.
  • the reserve angle CX3 has a value between 1 ° and 0 °. Consequently, the increase in the flow cross-section is mainly effected by the fact that the lateral circumferential sections UA S , UA S 2 of the film cooling hole 20 diverge, whereas in FIG
  • 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 slightly larger than the diameter d of the inflow 26th
  • the area ratio is increased: for a given mass flow of cooler medium through the film cooling hole 20 concerned, the flow velocity at the outflow opening 24 of the film cooling hole 20 can be reduced compared to a conventional film cooling hole 2, thereby increasing the tendency of the exiting Jet in cooler medium M K for detachment from the first surface 16 can be reduced.
  • Diffuser portion 28 is larger than the 7-times the diameter d of the flow-in portion 26. This ensures that the diffuser section weakenedse is long and thus can expand rea ⁇ accordingly. During operation, a comparatively wide cooling air film can then form.
  • Einströmabitess 26 Preferably, it is less than 50% of the diameter d.
  • the diffuser inlet begins with a comparatively gentle diffuser expansion, which reduces the tendency of the cooling air flow to detach.
  • the diffuser-like expansion of the film cooling hole 20 does not begin at the portion of the periphery of the film cooling hole 20, which is closest to the second surface 18, son ⁇ countries on the two lateral portions of the periphery.
  • a loss-less fanning of the flow inside the film cooling hole 20 can be achieved, since a pressure distribution sets, the less asymmetrical, but rather
  • a perpendicular to the flow direction of the hotter medium M H detectable width B of the outflow opening 24 is greater than in conventional film cooling holes 2 with comparable diffuser opening ratios.
  • the distance between the two legs of the counter-rotating vortex pairs 23 can be increased by the pre ⁇ knocked design.
  • Characterized in the effluent Be ⁇ area of the virtual central L Kunststoffsachsse LL cooler medium M K is less influenced by the counter-rotating vortex pairs 23, which reduces the mixing. Also, the strength of the counter-rotating vortex pairs 23 can be reduced. As a result, this leads to egg ⁇ ner enlarged coverage of the first surface 16 with the desired cooling air film.
  • Diffuser section 28 in the direction of flow of the hotter medium M H vertical direction (lateral direction LR) to a more uniform distribution of the cooler medium M K at the discharge opening 24.
  • Diffuser edge 30 can be reduced. Overall, so that the cooling can be made uniform. For this reason is the
  • Opening angle ßi not greater than 12 °. Preferably, it is 11.5 °.
  • the inflow-side diffuser edge 34 is designed symmetrically curved, wherein its central region is arranged slightly further upstream than its mallli ⁇ chen ends.
  • the film cooling hole 20 can be produced more easily, since first the inflow drilled and 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, at which a diffuser section 28 with a changing flow cross section follows.
  • a diffuser section 28 with a changing flow cross section follows.

Landscapes

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

Abstract

La présente invention concerne un trou pour film d'air de refroidissement (20) dans des pièces de turbine à gaz à refroidir, qui présente un segment d'entrée (26) à section transversale d'écoulement constante prolongé par un segment diffuseur (28) à section transversale d'écoulement se modifiant. Selon l'invention, pour obtenir un refroidissement par film particulièrement efficace, l'élargissement de la zone de diffuseur (28) a lieu uniquement dans la direction perpendiculaire à la direction d'écoulement du milieu plus chaud MH.
EP17715064.6A 2016-03-23 2017-03-22 Trou pour film d'air de refroidissement dans des pièces de turbine à gaz Not-in-force 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 true EP3408501A1 (fr) 2018-12-05
EP3408501B1 EP3408501B1 (fr) 2021-03-17

Family

ID=58464510

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17715064.6A Not-in-force 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
US4684323A (en) * 1985-12-23 1987-08-04 United Technologies Corporation Film cooling passages with curved corners
US4726735A (en) 1985-12-23 1988-02-23 United Technologies Corporation Film cooling slot with metered flow
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

Also Published As

Publication number Publication date
WO2017162743A1 (fr) 2017-09-28
US20190078443A1 (en) 2019-03-14
DE102016204824A1 (de) 2017-09-28
EP3408501B1 (fr) 2021-03-17

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