EP3408501A1 - Film cooling hole in gas turbine components - Google Patents

Film cooling hole in gas turbine components

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)
French (fr)
Other versions
EP3408501B1 (en
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
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 filed Critical Siemens AG
Publication of EP3408501A1 publication Critical patent/EP3408501A1/en
Application granted granted Critical
Publication of EP3408501B1 publication Critical patent/EP3408501B1/en
Active 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

The invention relates to a film cooling hole (20) of gas turbine components to be cooled, having an inflow section (26) with a constant flow area, to which a diffuser section (28) with a variable flow area is connected. The aim of the invention is to provide a particularly efficient film cooling. To this end, the diffuser region (26) is simply widened in the direction perpendicular to the flow direction of the hotter medium MH.

Description

Filmkühlloch in Gasturbinen - Bauteilen Film cooling hole in gas turbine components
Die Erfindung betrifft Filmkühllöcher von zu kühlenden Gasturbinen-Bauteilen. Gasturbinen-Bauteile, die Filmkühllöcher aufweisen, können beispielsweise Turbinenschaufeln, Ringsegmente oder auch Brennkammerbauteile sein. 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.
Mit Hilfe der Filmkühllöcher kann ein kühlender Luftfilm auf von Heißgas überströmbaren Flächen der zu kühlenden Bauteile erzeugt werden, welcher diese vor dem direkten Kontakt und damit vor den thermischen Einflüssen des daran entlang strömenden Heißgases schützen soll. With the aid of the film cooling holes, 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.
So offenbart beispielsweise die EP 0 227 578 A2 ein konventi- onelles Filmkühlluftloch, bei der sich an einen runde Einlass ein diffusorartiger Bereich anschließt. Durch den For example, EP 0 227 578 A2 discloses a conventional film cooling air hole, in which a diffuser-like region adjoins a round inlet. By the
diffusorartigen Bereich wird eine Auffächerung der ausströmenden Kühlluft in lateraler Richtung ermöglicht. Jedoch besteht im Zuge steigender Verbrennungstemperaturen und stei- genden Anforderungen an den Wirkungsgrad von Gasturbinen weiterhin ein besonderes Interesse an der Bereitstellung eines Filmkühllochs mit gesteigerter Kühlkapazität bei geringem Kühllufteinsatz . Aufgabe dieser Erfindung ist die Bereitstellung eines Filmkühllochs, mit dem eine besonders effiziente Filmkühlung er¬ reicht werden kann. diffuser-like area is a fanning out of the outflowing cooling air in the lateral direction allows. However, with increasing combustion temperatures and increasing demands on the efficiency of gas turbines, there continues to be a particular interest in providing a film cooling hole with increased cooling capacity with low cooling air use. Object of this invention is to provide a film cooling hole, with a particularly efficient film cooling can be ¬ he can see.
Diese Aufgabe wird mit einem Filmkühlloch gemäß Anspruch 1 gelöst. Vorteilhafte Ausgestaltungen sind in den abhängigen Ansprüchen angegeben, wobei die Merkmale der abhängigen Ansprüche in beliebiger Weise auch nur teilweise miteinander kombiniert werden können. Es zeigen: Fig. 1 ein herkömmliches Filmkühlloch mit gegenläufig ro¬ tierenden Wirbelpaaren, This object is achieved with a film cooling hole according to claim 1. Advantageous embodiments are specified in the dependent claims, wherein the features of the dependent claims can be combined in any way only partially with each other. In the drawings: Figure 1 is a conventional film cooling hole with counter ro ¬ animal vortex pairs.
Fig. 2 das herkömmliche Filmkühlloch in einem Querschnitt, Fig. 3 das herkömmliche Filmkühlloch in einer Draufsicht, 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 ein erfindungsgemäßes Filmkühlloch in einer perspektivischen Ansicht, Fig. 5 das erfindungsgemäße Filmkühlloch mit gegenläufig rotierenden Wirbelpaaren, einen Querschnitt durch eine das erfindungsgemäße Filmkühlloch aufweisende Bauteilwand und eine zur ersten Oberfläche senkrechte Draufsicht auf das erfindungsgemäße Filmkühlloch. 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.
Die Erfindung und das erfindungsgemäße Filmkühlloch 20 sind in den Figuren 4 bis 7 dargestellt, wohingegen die Figuren 1 bis 3 ein vorbekanntes Filmkühlloch 2 zeigen. Sowohl bei der Darstellung der Erfindung als auch bei der Darstellung des Standes der Technik sind identische Merkmale mit den gleichen Bezugszeichen versehen. The invention and the film cooling hole 20 according to the invention are shown in FIGS. 4 to 7, whereas FIGS. 1 to 3 show a previously known film cooling hole 2. Both in the illustration of the invention and in the presentation of the prior art, identical features are provided with the same reference numerals.
Jedes der gezeigten Filmkühllöcher 2, 20 ist in einer heißgasbeaufschlagbaren Wand 14 als Durchgangsloch ausgebildet, so dass es sich von einer ersten Oberfläche 16 der Wand 14 zu einer dieser gegenüberliegenden zweiten Oberfläche 18 der Wand 14 erstreckt. Die erste Oberfläche 16 ist bei be¬ stimmungsgemäßen Einsatz der Erfindung von einem heißeren Medium MH überströmt, wohingegen die zweite Oberfläche 18 wäh¬ renddessen einem kühleren Medium MK ausgesetzt ist. Üblicher- weise handelt es sich bei dem heißeren Medium um ein Arbeits¬ medium und bei dem kühleren Medium um Kühlluft. Die Wand 14 kann beispielsweise ein Bestandteil einer Turbinenschaufel einer Turbomaschine, eines Ringsegments, einer Brennkammer¬ wand oder dergleichen sein und dabei eine oder mehrere Reihen mit derartigen oder ähnlichen Filmkühllöcher 2, 20 aufweisen. 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
Die betreffenden Filmkühllöcher 2, 20 sind gegenüber den Oberflächen 16, 18 geneigt angeordnet. Jedes Filmkühlloch 2, 20 umfasst eine Einströmöffnung 22, welche in der zweiten Oberfläche 18 angeordnet ist. Durch diese Einströmöffnung 22 kann das kühlere Medium in das betreffende Filmkühlloch einströmen. Das eingeströmte Medium verlässt das betreffende Filmkühlloch 2, 20 durch eine in der ersten Oberfläche 16 angeordnete Ausströmöffnung 24. 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.
Wie aus den Figuren 3 und 7 hervorgeht, reicht ein erster Längsabschnitt des Filmkühllochs 2, 20, nachfolgend Einström¬ abschnitt 26 genannt, von der Einströmöffnung 22 bis zu einem Übergangspunkt 25 und weist dabei einen konstanten Durchströ- mungsdurchmesser d auf. Mittels dieses Durchmessers d ist die Durchflussmenge an austretendem Medium MK einstellbar. Ab dem Übergangspunkt 25 ändert sich neben der Größe des As is apparent from the Figures 3 and 7, extends a first longitudinal portion of the film cooling hole 2, 20, hereinafter inflow ¬ portion called 26 from the inflow port 22 up to a transition point 25 and thereby has a constant throughflow mung diameter d. By means of this diameter d, the flow rate of escaping medium M K is adjustable. From the transition point 25 changes in addition to the size of
durchströmbaren Querschnitts des Filmkühllochs auch dessen Kontur. In Bezug auf das das Filmkühlloch durchströmende küh- lere Medium MK folgt mithin unmittelbar stromab des Übergangspunkt 25 ein sich stetig verändernder Diffusorabschnitt 28, welcher sich bis zur Ausströmöffnung 24 erstreckt. Jedes Filmkühlloch besitzt eine virtuelle Längsachse LL, wel¬ che sich durch die Mittelpunkte des Einströmabschnitts 26 er¬ streckt und darüber hinaus verlängert. Die betreffenden Film¬ kühllöcher 2, 20 sind gegenüber der ersten Oberfläche 16 der- art geneigt, dass die virtuelle zentrale Längsachse LL - in einer Querschnittbetrachtung durch die betreffende Wand 14 - mit einem stromauf liegenden Bereich 16a der zweiten Oberfläche 16 einen spitzen Neigungswinkel N einschließt. Längs der virtuellen Längsachse LL betrachtet weisen derpermeable cross section of the film cooling hole and its contour. With respect to the cooler medium M K flowing through the film cooling hole, a continuously 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, 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
Einströmabschnitt 26 die Länge Lcyi und der Diffusorabschnitt 28 die Länge Ldiff auf, die sich zu einer zur Lochlänge L zu¬ sammenfassen lassen. Insbesondere der Diffusorabschnitt 28 des Filmkühllochs 2, 20 umfasst vier einzeln identifizierbare Seitenwände, die nach¬ folgend als Umfangsabschnitte bezeichnet werden und längs des Umlaufs ineinander übergehen. Ein erster Umfangsabschnitt UAH weist einen geringeren Abstand zur ersten Oberfläche 16 auf und ist damit dem heißeren Medium MH zugewandt. Dieser Um- fangsabschnitt UAH endet einerseits an einer in Bezug auf das heißere Medium MH anströmseitigen Diffusorkante 34 und geht andererseits lateral beidseitig in jeweils einen seitlichen Umfangsabschnitt UASi, UAS2 über. Die beiden seitlichen Um- fangsabschnitte UASi, UAS2 gehen jeweils dann in einen gemein¬ samen Umfangsabschnitt UAK über, der einen geringeren Abstand zur zweiten Oberfläche 18 aufweist und damit dem kühleren Me¬ dium MK zugewandt ist. Der weitere Umfangsabschnitt UAK endet somit an einer in Bezug auf das heißere Medium MH Inflow section 26, the length L cy i and the diffuser section 28, the length L d i ff , which can be summarized to one to the hole length L to ¬ . In particular, 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. On the one hand, 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.
abströmseitigen Diffusorkante 30, die vorzugsweise im Wesent¬ lichen geradlinig ist. Insgesamt lässt sich ein Abstand wbc zwischen anströmseitiger Diffusorkante 34 und abströmseitige Diffusorkante 30 ermitteln. In dem gezeigten Ausführungsbeispiel sind die Wände der seit¬ lichen Umfangsabschnitte UASi, UAS2 weitestgehend geradlinig ausgestaltet . In einer Querschnittbetrachtung (vgl. Fig. 1) schließt der dem kühleren Medium zugewandte Umfangsabschnitt UAK mit der virtuellen Längsachse LL einen so genannten Rücklagewinkel CX3 ein. Bei senkrechter Projektion (gemäß Fig. 3) auf die erste Oberfläche 16 kann ein Öffnungswinkel ßi jeweils zwischen den seitlichen Umfangsabschnitten UASi, UAS2 des 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. In the shown embodiment, since the walls of the peripheral portions ¬ union UA S i, UA S 2 are arranged largely in a straight line. In a cross-sectional view (see Fig. 1), the cooler medium facing peripheral portion UA K with the virtual longitudinal axis LL includes a so-called reserve angle CX3. In perpendicular projection (of FIG. 3) on the first surface 16, an opening angle can SSI each between the lateral peripheral portions UA S i, S 2 of the UA
Diffusorabschnitts 28 und mit der virtuellen zentralen Längs¬ achse LL erfasst werden. Diffuser section 28 and be detected with the virtual central longitudinal ¬ LL.
Erfindungsgemäß ist vorgesehen, dass die im Diffusorabschnitt 28 des Filmkühllochs 20 zunehmende Vergrößerung des Durch¬ strömungsquerschnitts allein in einer Dimension (Lateralrichtungen LR) erfolgt. Dazu ist vorgesehen, dass der Rücklage- Winkel CX3 einen Wert zwischen 1° und 0° aufweist. Mithin er- folgt die Zunahme des Durchströmungsquerschnitts hauptsäch¬ lich dadurch, dass die seitlichen Umfangsabschnitte UASi, UAS2 des Filmkühllochs 20 divergieren, wohingegen im According to the invention, it is provided that 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. For this purpose, it is provided that 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
Diffusorabschnitt 28 der Abstand zwischen dem dem heißeren Medium MH zugewandten Umfangsabschnitt UAH und dem dem kühle- ren Medium MK zugewandten Umfangsabschnitt UAK an der 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
Ausströmöffnung 24 höchstens nur unwesentlich größer wird als der Durchmesser d des Einströmabschnitts 26.  Outflow opening 24 is at most only slightly larger than the diameter d of the inflow 26th
Damit wird das Gebiet-Verhältnis (area-ratio) vergrößert: für einen gegebenen Massenstrom an kühlerem Medium durch das betreffende Filmkühlloch 20 kann die Strömungsgeschwindigkeit an der Ausströmöffnung 24 des Filmkühllochs 20 im Vergleich zu einem konventionellen Filmkühlloch 2 reduziert werden, wodurch die Tendenz des austretenden Strahls an kühlerem Medium MK zur Ablösung von der ersten Oberfläche 16 reduziert werden kann . Thus, 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.
Bevorzugt ist die zwischen dem Übergangspunkt 25 und der Ausströmöffnung 24 erfassbare Länge Ldiff des Preferably, the detectable between the transition point 25 and the discharge opening 24 length L diff of
Diffusorabschnitts 28 größer als der 7-fache Durchmesser d des Einströmabschnitts 26. Damit wird erreicht, dass der Diffusorabschnitt vergleichse lang ist und sich somit hinrei¬ chend aufweiten kann. Im Betrieb kann sich dann ein ver- gleichsweise breiter Kühlluftfilm ausbilden. Diffuser portion 28 is larger than the 7-times the diameter d of the flow-in portion 26. This ensures that the diffuser section vergleichse is long and thus can expand rea ¬ accordingly. During operation, a comparatively wide cooling air film can then form.
Mit besonderem Vorteil weist der Diffusorabschnitt 28 unmit¬ telbar stromab des Übergangspunkts 25 - in einer Querschnitt¬ betrachtung durch die betreffende Wand 14 - eine Diffusorhöhe h aufweist, die kleiner ist als der Durchmesser d des With particular advantage, the diffuser portion 28 UNMIT ¬ telbar downstream of the transition point 25 - in a cross-sectional ¬ viewing through the respective wall 14 - having a diffuser height h which is smaller than the diameter d of
Einströmabschnitts 26. Vorzugsweise ist sie kleiner als 50% des Durchmessers d. Dadurch beginnt der Diffusoreingang mit einer vergleichsweise sachten Diffusoraufweitung, was die Neigung der Kühlluftströmung zu Ablösungen verringert. Zudem beginnt die diffusorartige Aufweitung des Filmkühllochs 20 nicht an demjenigen Abschnitt des Umfangs des Filmkühllochs 20, welches der zweiten Oberfläche 18 am nächsten ist, son¬ dern an den beiden seitlichen Abschnitten des Umfangs. Damit kann eine verlustärmere Auffächerung der Strömung im Inneren des Filmkühllochs 20 erreicht, da sich eine Druckverteilung einstellt, die weniger asymmetrisch, sondern eher Einströmabschnitts 26. Preferably, it is less than 50% of the diameter d. As a result, the diffuser inlet begins with a comparatively gentle diffuser expansion, which reduces the tendency of the cooling air flow to detach. In addition, 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. Thus, 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
vergleichmäßigt ist. is evened.
Gleichfalls ist eine zur Strömungsrichtung des heißeren Medi- ums MH senkrecht erfassbare Breite B der Ausströmöffnung 24 größer als bei konventionellen Filmkühllöchern 2 mit vergleichbaren Diffusoröffnungsverhältnissen . Dies beeinflusst die gegenläufig rotierenden Wirbelpaare 23 positiv, welche gewöhnlich an den äußeren seitlichen Rändern der Ausströmöffnung 24, d.h. den gedachten Verlängerungen der seitlichen Umfangsabschnitten UASi und UAS2 auftreten. Gleichzeitig hat dies einen Einfluss erster Ordnung auf den Mi- schungsprozess von kühlerem Medium MK und heißerem Medium MH. Wie in Figur 5 gezeigt, kann der Abstand der beiden Schenkel der gegenläufig rotierenden Wirbelpaare 23 durch das vorge¬ schlagene Design vergrößert werden. Dadurch wird das im Be¬ reich der virtuellen zentralen Längsachsse LL ausströmende kühlere Medium MK weniger durch die gegenläufig rotierenden Wirbelpaare 23 beeinflusst, was die Durchmischung reduziert. Auch die Stärke der gegenläufig rotierenden Wirbelpaare 23 kann dadurch reduziert werden. Im Ergebnis führt dies zu ei¬ ner vergrößerten Abdeckung der ersten Oberfläche 16 mit dem gewünschten Kühlluftfilm. Similarly, 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. This positively affects the counter-rotating vortex pairs 23, which are usually at the outer lateral edges of the Outflow opening 24, ie the imaginary extensions of the lateral peripheral sections UA S i and UA S 2 occur. At the same time, this has a first-order influence on the mixing process of cooler medium M K and hotter medium M H. As shown in Figure 5, 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 Längsachsse 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.
Weiter führt die größere Spreizung, d.h. der im Vergleich zum Stand der Technik vergrößerte Öffnungswinkel ßi des Further, the larger spread, i. the enlarged in comparison to the prior art opening angle ßi of
Diffusorabschnitts 28 in zur Strömungsrichtung des heißeren Mediums MH senkrechter Richtung (Lateralrichtung LR) zu einer gleichmäßigeren Verteilung des kühleren Mediums MK an der Ausströmöffnung 24. Damit kann ein lokales Überkühlen der ersten Oberfläche 16 im zentralen Bereich der virtuellen Längsachse LL unmittelbar stromab der abströmseitigen 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. Thus, a local overcooling of the first surface 16 in the central region of the virtual longitudinal axis LL immediately downstream of the downstream
Diffusorkante 30 reduziert werden. Insgesamt kann damit die Kühlung vergleichmäßigt werden. Aus diesem Grunde ist derDiffuser edge 30 can be reduced. Overall, so that the cooling can be made uniform. For this reason is the
Öffnungswinkel ßi nicht größer als 12°. Vorzugsweise liegt er bei 11,5°. Opening angle ßi not greater than 12 °. Preferably, it is 11.5 °.
Vorzugsweise ist die anströmseitige Diffusorkante 34 symmet- risch gekrümmt ausgestaltet, wobei dessen mittlerer Bereich geringfügig weiter stromauf angeordnet ist als seine seitli¬ chen Enden. Hierdurch lässt sich das Filmkühlloch 20 einfacher produzieren, da zuerst der Einströmabschnitt gebohrt und anschließend die Kontur des Diffusorabschnitts hergestellt werden kann. Preferably, the inflow-side diffuser edge 34 is designed symmetrically curved, wherein its central region is arranged slightly further upstream than its seitli ¬ chen ends. As a result, 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.
Alle vorgenannten Vorteile führen insgesamt zu einem Anstieg der adiabatischen Filmkühlungwirksamkeit verglichen mit konventionellen Filmkühllöchern. Insbesondere weiter stromab des Filmkühllochs ist die durchschnittliche Filmkühlwirksamkeit des erfindungsgemäßen Filmkühllochs der Wirksamkeit von her¬ kömmlichen Filmkühllöchern überlegen. All of the above advantages result in an overall increase in adiabatic film cooling efficiency compared to conventional film cooling holes. In particular, further downstream of the film cooling hole, the average film cooling effectiveness of the film cooling hole according to the invention of the efficacy of her ¬ conventional film cooling holes is superior.
Insgesamt betrifft die Erfindung ein Filmkühlloch 20 von zu kühlenden Gasturbinen-Bauteilen, mit einem Einströmabschnitt 26 mit einem konstanten Durchströmungsquerschnitt, an dem sich ein Diffusorabschnitt 28 mit einem sich verändernden Durchströmungsquerschnitt anschließt. Um eine besondere effi¬ ziente Filmkühllung bereitzustellen, wird vorgeschlagen, dass die Aufweitung des Diffusorbereichs 26 lediglich in lateraler Richtung LR erfolgt. Overall, 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. In order to provide a special effi ¬ cient film cooling, it is proposed that the expansion of the diffuser region 26 takes place only in the lateral direction LR.

Claims

Patentansprüche : Claims:
Gekühltes Bauteil (12) für eine Turbine, Cooled component (12) for a turbine,
mit einer Wand (14), die von einer ersten Oberfläche (16) und einer der ersten Oberfläche (16) gegenüberliegende zweite Oberfläche (18) begrenzt ist, wobei die erste Ober¬ fläche (16) vorgesehen ist von einem heißeren Medium (MH), welches von einem stromaufliegenden Bereich (16a) zu einem stromabliegenden Bereich (16b) strömbar ist, umströmt zu werden, und wobei die zweite Oberfläche (18) vorgesehen ist mit einem kühleren Medium (MK) in Kontakt zu kommen, mit zumindest einem zur zweiten Oberfläche (18) geneigten Filmkühlloch (20) zur Durchleitung des kühleren Mediums (MK) durch die Wand zur zweiten Oberfläche (16), with a wall (14) extending from a first surface (16) and one of the first surface (16) opposite second surface (18) is limited, wherein the first upper ¬ surface (16) is provided (from a hotter medium M H ), which is flowable from an upstream portion (16a) to a downstream portion (16b) to be flowed around, and wherein the second surface (18) is intended to come into contact with a cooler medium (M K ) with at least one to the second surface (18) inclined film cooling hole (20) for the passage of the cooler medium (M K ) through the wall to the second surface (16),
wobei das betreffende Filmkühlloch (20) umfasst:  wherein the film cooling hole (20) comprises:
- eine in der zweiten Oberfläche (18) angeordnete  - One in the second surface (18) arranged
Einströmöffnung (22), durch welche das kühlere Medium (MK) in das Filmkühlloch (20) einströmbar ist, Inflow opening (22), through which the cooler medium (M K ) can be flowed into the film cooling hole (20),
- eine in der ersten Oberfläche (16) angeordnete  - One in the first surface (16) arranged
Ausströmöffnung (24), durch welche das im Inneren des Filmkühllochs (20) strömbare kühlere Medium (MK) das Film¬ kühlloch (20) verlassen kann, Outflow opening (24) through which flowable the inside of the film-cooling hole (20) cooler medium (M K) can leave the film ¬ cooling hole (20),
- eine virtuelle zentrale Längsachse (LL) , die sich mit einer Lochlänge (L) von der Einströmöffnung (22) bis zu der Ausströmöffnung (24) erstreckt,  a virtual central longitudinal axis (LL) extending with a hole length (L) from the inflow opening (22) to the outflow opening (24),
- vier Umfangsabschnitte, die entlang eines zur Längsachse tangentialen Umlaufs aufeinanderfolgend nacheinander inei¬ nander übergehen: - Four peripheral sections, which merge successively successively inei ¬ nander along a tangential to the longitudinal axis circulation:
* einen dem heißeren Medium zugewandten Umfangsab- schnitt (UAH), * a peripheral portion (UA H ) facing the hotter medium,
* einen ersten seitlichen Umfangsabschnitt (UASi) , * a first lateral peripheral portion (UA S i),
* einen dem kühleren Medium zugewandten Umfangsab- schnitt (UAK) und * a peripheral wall facing the cooler medium cut (UA K ) and
* einen zweiten seitlichen Umfangsabschnitt (UAS2),* a second lateral peripheral portion (UA S2 ),
- einen zwischen der Einströmöffnung (22) und einem Übergangspunkt (25) angeordneten Einströmabschnitt (26) mit einem konstanten Durchströmungsquerschnitt und - One between the inflow opening (22) and a transition point (25) arranged inflow section (26) having a constant flow cross-section and
- einen von dem Übergangspunkt (25) bis zur  - one from the transition point (25) to the
Ausströmöffnung (24) angeordneten Diffusorabschnitt (28) mit einem in dieser Richtung zunehmenden Durchströmungsquerschnitt, Outflow opening (24) arranged diffuser section (28) with an increasing in this direction flow cross-section,
- eine abströmseitigen Diffusorkante (30), an der der dem kühleren Medium zugewandte Umfangsabschnitt (UAK) an die zweite Oberfläche (16) angrenzt, a downstream diffuser edge (30), at which the peripheral portion (UA K ) facing the cooler medium adjoins the second surface (16),
- eine anströmseitigen Diffusorkante (34), an der der dem heißeren Medium zugewandte Umfangsabschnitt (UAH) an die zweite Oberfläche (16) angrenzt und - An inflow-side diffuser edge (34) on which the hotter medium facing peripheral portion (UA H ) adjacent to the second surface (16) and
- einen Abstand (wbc) zwischen anströmseitiger - A distance (w bc ) between upstream
Diffusorkante (34) und abströmseitige Diffusorkante (30), wobei die Neigung des Filmkühllochs (20) gegenüber der ersten Oberfläche (16) derart ist, dass die virtuelle zentrale Längsachse (LL) - in einer Querschnittbetrachtung durch die betreffende Wand (14) - mit dem stromauf liegen¬ den Bereich (16a) der zweiten Oberfläche (16) einen spitzen Neigungswinkel ( N) einschließt, und The diffuser edge (34) and downstream diffuser edge (30), wherein the inclination of the film cooling hole (20) relative to the first surface (16) is such that the virtual central longitudinal axis (LL) - in a cross-sectional view through the wall (14) - with the upstream region ¬ the region (16a) of the second surface (16) includes an acute angle of inclination ( N ), and
wobei der dem kühleren Medium (MK) zugewandte Umfangsab- schnitt (UAK) mit der virtuellen Längsachse (LL) - in ei¬ ner Querschnittbetrachtung durch die betreffende Wand (14)wherein the cooler medium (M K) facing Umfangsab- cut (UA K) with the virtual longitudinal axis (LL) - ei in ¬ ner cross-sectional view through the respective wall (14)
- einen Rücklage-Winkel (0(3) einschließt, - includes a reserve angle (0 ( 3 ),
dadurch gekennzeichnet, dass characterized in that
der Rücklage-Winkel (0(3) einen Wert kleiner als 1° auf- weist. the reserve angle (0 (3) has a value less than 1 °.
2. Bauteil (12) nach Anspruch 1, 2. Component (12) according to claim 1,
bei dem die zwischen dem Übergangspunkt (25) und der Ausströmöffnung (24) erfassbare Länge (Ldiff) des wherein the between the transition point (25) and the outflow opening (24) detectable length (L d i ff ) of
Diffusorabschnitts (28) größer ist als der 7-fache  Diffuser section (28) is greater than 7 times
Durchmesser (d) des Einströmabschnitts (26).  Diameter (d) of the inflow section (26).
3. Bauteil (12) nach Anspruch 1 oder 2, 3. component (12) according to claim 1 or 2,
bei dem die seitlichen Umfangsabschnitte (UASi, UAS2) des Diffusorabschnitts (28) bei senkrechter Projektion zur ersten Oberfläche (16) geradlinig ausgestaltet sind und diese mit der virtuellen zentralen Längsachse (LL) einen Öffnungswinkel (ßi) von mindestens 11,5° einschließen. in which the lateral peripheral sections (UA S i, UA S 2) of the diffuser section (28) are configured in a straight line when projecting perpendicular to the first surface (16) and the virtual central longitudinal axis (LL) has an opening angle (βi) of at least 11, Enclose 5 °.
4. Bauteil (12) nach Anspruch 1, 2 oder 3, 4. component (12) according to claim 1, 2 or 3,
bei dem die abströmseitige Diffusorkante (30) im Wesent¬ lichen gerade ist. in which the downstream diffuser edge (30) in the materiality ¬ union is straight.
5. Bauteil (12) nach einem der vorangehenden Ansprüche, bei dem die anströmseitige Diffusorkante (34) gekrümmt ist . 5. component (12) according to any one of the preceding claims, wherein the inflow-side diffuser edge (34) is curved.
6. Bauteil (12) nach einem der vorangehenden Ansprüche, bei dem der Abstand (wbc) im Wesentlichen dem Durchmesser (d) des Einströmabschnitts (26) geteilt durch den Sinus des Neigungswinkel ( N) entspricht: wbc = d / sind ( N) . Bauteil (12) nach einem der vorangehenden Ansprüche, bei dem der Diffusorabschnitt (28) unmittelbar stromab des Übergangspunkts (25) - in einer Querschnittbetrachtung durch die betreffende Wand (14) - eine Diffusorhöhe (h) aufweist, die kleiner ist als der Durchmesser (d) des Einströmabschnitts (26). A member (12) according to any one of the preceding claims, wherein the distance (w bc ) substantially corresponds to the diameter (d) of the inflow portion (26) divided by the sine of the pitch angle ( N ): w bc = d / ( N ). A member (12) according to any one of the preceding claims wherein the diffuser portion (28) immediately downstream of the transition point (25) has a diffuser height (h) smaller than the diameter (cross-sectional view through the wall (14)). d) of the inflow section (26).
Bauteil (12) nach einem der vorangehenden Ansprüche, mit einer Vielzahl entsprechender Filmkühllöcher (20), angeordnet in ein oder mehreren Reihen. Component (12) according to one of the preceding claims, with a plurality of respective film cooling holes (20) arranged in one or more rows.
EP17715064.6A 2016-03-23 2017-03-22 Film cooling hole in gas turbine components Active EP3408501B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016204824.4A DE102016204824A1 (en) 2016-03-23 2016-03-23 Film cooling holes in gas turbine components
PCT/EP2017/056834 WO2017162743A1 (en) 2016-03-23 2017-03-22 Film cooling hole in gas turbine components

Publications (2)

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

Family

ID=58464510

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17715064.6A Active EP3408501B1 (en) 2016-03-23 2017-03-22 Film cooling hole in gas turbine components

Country Status (4)

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

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114719290B (en) * 2022-03-17 2023-03-31 西北工业大学 Diffuser structure with adjustable air discharge scheme and application

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
DE59808269D1 (en) * 1998-03-23 2003-06-12 Alstom Switzerland Ltd Film cooling hole
DE19960797C1 (en) * 1999-12-16 2001-09-13 Mtu Aero Engines Gmbh Method for producing an opening in a metallic component
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 (en) * 2015-03-12 2015-07-01 中国科学院工程热物理研究所 Straggling air film cooling hole

Also Published As

Publication number Publication date
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DE102016204824A1 (en) 2017-09-28
US20190078443A1 (en) 2019-03-14
WO2017162743A1 (en) 2017-09-28

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