EP1589192A1 - Turbine blade with an insert for impingement cooling - Google Patents

Turbine blade with an insert for impingement cooling Download PDF

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Publication number
EP1589192A1
EP1589192A1 EP04009326A EP04009326A EP1589192A1 EP 1589192 A1 EP1589192 A1 EP 1589192A1 EP 04009326 A EP04009326 A EP 04009326A EP 04009326 A EP04009326 A EP 04009326A EP 1589192 A1 EP1589192 A1 EP 1589192A1
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EP
European Patent Office
Prior art keywords
blade
turbine blade
waveform
insert
overlap
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP04009326A
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German (de)
French (fr)
Inventor
Gernot Lang
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 AG
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
Priority to EP04009326A priority Critical patent/EP1589192A1/en
Priority to DE502005004644T priority patent/DE502005004644D1/en
Priority to US11/578,920 priority patent/US8137055B2/en
Priority to EP05731679A priority patent/EP1738060B1/en
Priority to PCT/EP2005/051487 priority patent/WO2005103452A1/en
Priority to ES05731679T priority patent/ES2308476T3/en
Publication of EP1589192A1 publication Critical patent/EP1589192A1/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated

Definitions

  • the invention relates to a cooled turbine blade, which successively a blade root, a platform area and a hollow airfoil for receiving a sheet-like Impact cooling insert comprises, which at least two in an overlap overlapping, contiguous Has sections. Furthermore, the invention relates to a gas turbine according to claim 6.
  • JP 2001-14 06 02-A discloses a cooled gas turbine blade with sheet-like impingement cooling inserts.
  • An impact-cooling insert arranged in the region of the blade trailing edge of the turbine blade and triangular in cross section is spaced from the inner surface of the outer wall and provided with impingement cooling openings.
  • the cavity enclosed by the impingement cooling insert is supplied with cooling air, which subsequently exits through the impingement cooling openings and impinges on the inner surface of the outer wall, which is flowed around hot outside, in order to cool it.
  • impact cooling inserts from two separate Parts exist successively in the cavity of a turbine blade be inserted.
  • the first part is at the radially inner platform and the second part at the radial outer platform gas-tight fixed to losses in the feed to avoid.
  • the two parts are in one overlapping flat sliding seat abut each other at the Operation of the gas turbine to allow a relative movement.
  • the object of the invention is therefore to specify a turbine blade, which saves cooling medium. It is also a task the invention for this purpose, a correspondingly improved gas turbine specify.
  • the solution of the task aimed at the turbine blade suggests that to seal the overlap area the both sections in the cross section wavy are.
  • the solution is based on the knowledge that by the undulating overlap of the two sections the Enlarged between them formed overlap area and targeted a contact area is created, where the two Sections sealingly abut each other.
  • the waveform has a rising flank between a wave trough and a wave crest and a falling flank between a wave crest and a wave trough.
  • the wave form of the two overlapping sections formed by the wave troughs and the wave crests are approximately parallel, so that contact surfaces are formed between adjacent rising flanks and / or between adjacent falling flanks, which prevent the leakage flow. This leads to a saving of cooling medium.
  • the use of such a turbine blade in a gas turbine during operation leads to an increase in efficiency.
  • there is a mechanical mobility of the two closely juxtaposed sections which are required to compensate for the thermal expansion of the material during cold start or during transient operation of the gas turbine.
  • the frequency deviates and / or the amplitude of the waveform of the first element from the second frequency or amplitude of the waveform of the second element.
  • This will certainly avoid that the waveform of the two sections in the overlap area form a parallel, meandering gap. Consequently, one between two rising or falling edge contact surface generated, the despite the different thermal material expansions or a move against each other because of the contact surface effective sealing force a particularly dense overlap area guaranteed.
  • the overlapping areas are securely sealed.
  • the embodiment in which the Frequency (and / or amplitude) of the waveform of the first element in the order of max. ⁇ 6% of the frequency (and / or amplitude) of the waveform of the second element different.
  • the frequencies and the amplitudes are included to choose so that the thermal expansion of material the elements do not cause mutual mechanical obstruction and thus ensure a secure sealing effect.
  • the parameters of the waveform are based on the material of the Impact cooling insert tuned.
  • the space required for the overlap area can be especially save space when the overlap area in cross section does not have more than five oscillation periods.
  • the Impact cooling insert formed in several parts.
  • the can Baffle insert forming parts from an open top Shovel tip starting in the hollow airfoil successively be inserted. After that lie the sections of the individual parts in each case in an overlapping area together, which is also referred to as a sliding seat.
  • a special easy shifting is ensured because the direction of displacement of the impact cooling insert perpendicular to the propagation of Wave runs.
  • FIG. 1 shows a perspective view of an inventive Turbine blade 1 with a platform area 2 and with one extending along a blade axis 2a Airfoil 2b.
  • the airfoil 2b has at least one Cavity 3, in which a baffle cooling insert 5 is provided. Furthermore, the airfoil 2b has one of a hot gas 7 the gas turbine flowable blade leading edge 9, from the a suction side wall 11 and a pressure side wall 13 extends to a blade trailing edge 15.
  • the turbine blade 1 may include both a vane and a blade be.
  • the inner surfaces 19 of the side walls 11, 13 enclose the cavity 3.
  • To form a gap 22 is the Surface 19 of the baffle insert 5 by means of several ribs or circular spacers 21 spaced.
  • the im Inside of the baffle inserts 5 enclosed coolant channel 23 is traversed by a cooling medium.
  • the bumpers 5 also have impingement cooling openings 25 through which flowing in the coolant channel 23 flowing cooling medium and thereafter perpendicular to the surfaces 19 of the side walls 11, 13 can bounce to cool this.
  • the baffle insert 27 is in the direction of the blade axis 2a seen from two separate parts 29, 31 formed, which each with a portion 30, 32 in an overlap area 33, 35 overlap each other.
  • the overlap area 33, 35 lies outside the middle Blade height.
  • the hot airfoil 2b expands more in the direction of the blade axis 2a than the cool one Impact cooling insert 27, is one along the blade axis 2a directed mobility of the two fixed parts 29, 31 in Overlap area 33, 35 necessary.
  • FIGS. 2 and 3 each show an alternative embodiment of the overlapping area 33, 35 in a detailed view.
  • the baffle insert 5 is under from the inner surface 19 Forming the gap 22 spaced.
  • the suction side wall 11 of the hot gas. 7 flows around.
  • the cooling medium 36 For cooling the suction side wall 11 flows out of the Coolant channel 23, the cooling medium 36 through the impingement cooling holes 25 and bounces cooling on the inner surface 19th
  • the two sections 30, 32 with an identical Waveform formed i. the waveforms of the two Sections 30, 32 of the parts 29, 31 have an identical Frequency f and an identical amplitude A on.
  • the meandering Gap 37 between the two sections 30, 32nd If a leakage reduced by turbulences can flow, compared with a leakage in a flat overlap area According to the state of the art.
  • shifted position of the sections 30, 32 can the rising flanks 39 or the falling flanks 40 of the adjacent sections 30, 32 to form a Contact surface but also close to each other.
  • a shift the two parts 29, 31 perpendicular to it is due the predetermined geometry of the airfoil 2b and the Impact cooling insert 5 not possible.
  • Fig. 3 shows the overlapping region 33 with the two opposite Sections 30, 32, which are a different Have frequency f and a different amplitude A.
  • the thermal Strains of the impingement cooling insert 5 are the rising Flanks 39 and falling edges 40 of the waveform at least a period of the two sections 30, 32 sealingly to each other so that at any time one parallel to the blade axis 2a extending contact surface 43 is present.
  • the contact surface shifts 43 within the overlap region 33, 35 of a Period to an adjacent period. Therefore, it is expedient a minimum of two periods in the overlap area 33, 35 provided to a particularly secure seal the coolant channel 23 with respect to the gap 22 to achieve.
  • baffle cooling openings Be provided 25, in particular in the field of Wave troughs or wave crests of sections 30, 32.
  • the waveform is not necessarily sinusoidal. Same one Effect is also with a waveform consisting of consecutive Semicircles or semi-ellipses achievable. About that In addition, a triangular shape, a sawtooth shape or a Rectangular shape also conceivable.

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

Abstract

A turbine blade is fitted with an inner perforated baffle plate (5, 7) to direct cooling air onto the inside faces of the blade. The baffle plate is made in two parts with the main part secured to the blade near its outer tip and with the bottom part with an overlap with a shorter baffle plate fixed to the blade root platform (2). The overlap comprises interlocking corrugations with about two to five overlapping cycles. The frequencies and/or amplitudes of two overlap sections differ by about 6 percent.

Description

Die Erfindung betrifft eine gekühlte Turbinenschaufel, welche aufeinanderfolgend einen Schaufelfuß, einen Plattformbereich und ein hohles Schaufelblatt zur Aufnahme eines blechförmigen Prallkühleinsatzes umfasst, welcher zumindest zwei sich in einem Überlappungsbereich überlappende, aneinanderliegende Abschnitte aufweist. Ferner betrifft die Erfindung eine Gasturbine gemäß Anspruch 6.The invention relates to a cooled turbine blade, which successively a blade root, a platform area and a hollow airfoil for receiving a sheet-like Impact cooling insert comprises, which at least two in an overlap overlapping, contiguous Has sections. Furthermore, the invention relates to a gas turbine according to claim 6.

Aus der JP 2001-14 06 02-A ist eine gekühlte Gasturbinenschaufel mit blechförmigen Prallkühleinsätzen bekannt.
Ein im Bereich der Schaufelhinterkante der Turbinenschaufel angeordneter, im Querschnitt dreieckförmiger Prallkühleinsatz ist zur inneren Oberfläche der Außenwand beabstandet und mit Prallkühlöffnungen versehen. Beim Betrieb der Gasturbine wird der vom Prallkühleinsatz umschlossene Hohlraum mit Kühlluft gespeist, welche anschließend durch die Prallkühlöffnungen austritt und auf die innere Oberfläche der außen heiß umströmten Außenwand trifft, um diese zu kühlen.JP 2001-14 06 02-A discloses a cooled gas turbine blade with sheet-like impingement cooling inserts.
An impact-cooling insert arranged in the region of the blade trailing edge of the turbine blade and triangular in cross section is spaced from the inner surface of the outer wall and provided with impingement cooling openings. During operation of the gas turbine, the cavity enclosed by the impingement cooling insert is supplied with cooling air, which subsequently exits through the impingement cooling openings and impinges on the inner surface of the outer wall, which is flowed around hot outside, in order to cool it.

Ferner ist bekannt, dass Prallkühleinsätze aus zwei separaten Teilen bestehen, die nacheinander in den Hohlraum einer Turbinenschaufel eingeschoben werden. Das erste Teil ist an der radial inneren Plattform und das zweite Teil an der radial äußeren Plattform gasdicht fixiert, um Verluste im Einspeisebereich zu vermeiden. Die beiden Teile liegen dabei in einem sich überlappenden ebenen Schiebesitz aneinander an, um beim Betrieb der Gasturbine eine Relativbewegung zu ermöglichen.Furthermore, it is known that impact cooling inserts from two separate Parts exist successively in the cavity of a turbine blade be inserted. The first part is at the radially inner platform and the second part at the radial outer platform gas-tight fixed to losses in the feed to avoid. The two parts are in one overlapping flat sliding seat abut each other at the Operation of the gas turbine to allow a relative movement.

Beim Kaltstart oder beim transienten Betrieb der Gasturbine treten unterschiedliche thermische Dehnungen in der Gasturbinenschaufel auf, insbesondere bei der heiß umströmten Außenwand und bei dem kühleren noch nicht vollständig bzw. ungleichmäßig erwärmten Prallkühleinsatz. Diese, besonders in Richtung der Schaufelachse auftretenden Dehnungen können den Überlappungsbereich bzw. den Schiebesitz mechanisch entlasten und so einen unerwünschten Spalt zwischen den beiden aneinanderliegenden Abschnitten des Prallkühlelementes ermöglichen, durch den Kühlluft aus dem innern des Prallkühleinsatzes ungenutzt als Leckage entweichen kann.During cold start or during transient operation of the gas turbine different thermal expansions occur in the gas turbine blade on, especially in the hot-walled outer wall and in the cooler not yet complete or uneven heated baffle insert. These, especially in Direction of the blade axis occurring strains can Relieve the overlap area or the sliding seat mechanically and so an undesirable gap between the two adjacent Allow sections of the impingement cooling element unused by the cooling air from inside the impingement cooling insert as leakage can escape.

Die Aufgabe der Erfindung ist daher die Angabe einer Turbinenschaufel, welche Kühlmedium einspart. Ferner ist es Aufgabe der Erfindung hierzu eine entsprechend verbesserte Gasturbine anzugeben.The object of the invention is therefore to specify a turbine blade, which saves cooling medium. It is also a task the invention for this purpose, a correspondingly improved gas turbine specify.

Die auf die Turbinenschaufel gerichtete Aufgabe wird durch die Merkmale des Anspruchs 1 und die auf die Gasturbine gerichtete Aufgabe durch die Merkmale des Anspruchs 6 gelöst. Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben.The task directed at the turbine blade is accomplished by the features of claim 1 and directed to the gas turbine Problem solved by the features of claim 6. Advantageous embodiments are specified in the subclaims.

Die Lösung der auf die Turbinenschaufel gerichteten Aufgabe schlägt vor, dass zum Abdichten des Überlappungsbereichs die beiden Abschnitte im Querschnitt wellenförmig ausgebildet sind. Die Lösung geht dabei von der Erkenntnis aus, dass durch die wellenförmige Überlappung der beiden Abschnitte die zwischen ihnen gebildete Überlappungsfläche vergrößert und gezielt ein Kontaktbereich geschaffen wird, an dem die beiden Abschnitte dichtend aneinander anliegen.The solution of the task aimed at the turbine blade suggests that to seal the overlap area the both sections in the cross section wavy are. The solution is based on the knowledge that by the undulating overlap of the two sections the Enlarged between them formed overlap area and targeted a contact area is created, where the two Sections sealingly abut each other.

Die Wellenform weist dabei zwischen einem Wellental und einem Wellenberg eine ansteigende Flanke und zwischen einem Wellenberg und einem Wellental eine abfallende Flanke auf. Die von den Wellentälern und von den Wellenbergen gebildete Wellenform der beiden sich überlappenden Abschnitte verlaufen annähernd parallel, so dass zwischen benachbarten ansteigenden Flanken und/oder zwischen benachbarten abfallenden Flanken jeweils Kontaktflächen gebildet werden, welche die Leckageströmung verhindern. Dies führt zu einer Einsparung von Kühlmedium. Darüber hinaus führt die Verwendung einer solchen Turbinenschaufel in einer Gasturbine beim Betrieb zu einer Wirkungsgradsteigerung.
Weiter ist eine mechanische Beweglichkeit der beiden dicht aneinanderliegenden Abschnitte gegeben, die zur Kompensation der thermischen Materialdehnung beim Kaltstart bzw. beim transienten Betrieb der Gasturbine erforderlich sind.The waveform has a rising flank between a wave trough and a wave crest and a falling flank between a wave crest and a wave trough. The wave form of the two overlapping sections formed by the wave troughs and the wave crests are approximately parallel, so that contact surfaces are formed between adjacent rising flanks and / or between adjacent falling flanks, which prevent the leakage flow. This leads to a saving of cooling medium. In addition, the use of such a turbine blade in a gas turbine during operation leads to an increase in efficiency.
Furthermore, there is a mechanical mobility of the two closely juxtaposed sections, which are required to compensate for the thermal expansion of the material during cold start or during transient operation of the gas turbine.

Nach einer vorteilhaften Weiterbildung weicht die Frequenz und/oder die Amplitude der Wellenform des ersten Elementes von der zweiten Frequenz bzw. Amplitude der Wellenform des zweiten Elementes ab. Hierdurch wird sicher vermieden, dass die Wellenform der beiden Abschnitte im Überlappungsbereich einen parallel dazu verlaufenden, mäanderförmigen Spalt bilden. Folglich wird zwingend eine zwischen zwei ansteigenden oder abfallenden Flanken liegende Kontaktfläche erzeugt, die trotz der unterschiedlichen thermischen Materialdehnungen oder eines Verschiebens gegeneinander wegen der in der Kontaktfläche wirksamen Dichtkraft einen besonders dichten Überlappungsbereich gewährleistet. Besonders beim Anfahren der Gasturbine, bei bereits heißer Turbinenschaufelaußenwand und noch vergleichsweise kühlem Prallkühleinsatz, können somit die Überlappungsbereiche sicher abgedichtet werden.According to an advantageous development, the frequency deviates and / or the amplitude of the waveform of the first element from the second frequency or amplitude of the waveform of the second element. This will certainly avoid that the waveform of the two sections in the overlap area form a parallel, meandering gap. Consequently, one between two rising or falling edge contact surface generated, the despite the different thermal material expansions or a move against each other because of the contact surface effective sealing force a particularly dense overlap area guaranteed. Especially when starting the Gas turbine, with already hot turbine blade outer wall and even comparatively cool impingement cooling, so can the overlapping areas are securely sealed.

Besonders vorteilhaft ist die Ausgestaltung, bei der sich die Frequenz (und/oder Amplitude) der Wellenform des ersten Elementes in einer Größenordnung von max. ±6% sich von der Frequenz (und/oder Amplitude) der Wellenform des zweiten Elementes unterscheidet. Die Frequenzen und die Amplituden sind dabei so zu wählen, dass die wärmebedingten Materialdehnungen der Elemente keine gegenseitige mechanische Behinderung hervorrufen und somit eine sichere Dichtwirkung gewährleisten. Ferner sind die Parameter der Wellenform auf das Material des Prallkühleinsatzes abgestimmt.Particularly advantageous is the embodiment in which the Frequency (and / or amplitude) of the waveform of the first element in the order of max. ± 6% of the frequency (and / or amplitude) of the waveform of the second element different. The frequencies and the amplitudes are included to choose so that the thermal expansion of material the elements do not cause mutual mechanical obstruction and thus ensure a secure sealing effect. Furthermore, the parameters of the waveform are based on the material of the Impact cooling insert tuned.

Der für den Überlappungsbereich benötigte Bauraum kann besonders platzsparend sein, wenn der Überlappungsbereich im Querschnitt nicht mehr als fünf Schwingungsperioden aufweist.The space required for the overlap area can be especially save space when the overlap area in cross section does not have more than five oscillation periods.

Gemäß einer besonders vorteilhaften Weiterbildung ist der Prallkühleinsatz mehrteilig ausgebildet. Somit können die den Prallkühleinsatz bildenden Teile von einer oben offenen Schaufelspitze ausgehend in das hohle Schaufelblatt nacheinander eingeschoben werden. Danach liegen die Abschnitte der einzelnen Teile jeweils in einem Überlappungsbereich aneinander, der auch als Schiebesitz bezeichnet wird. Eine besonders einfache Verschiebung ist gewährleistet, da die Verschieberichtung des Prallkühleinsatzes senkrecht zur Ausbreitung der Welle verläuft.According to a particularly advantageous embodiment of the Impact cooling insert formed in several parts. Thus, the can Baffle insert forming parts from an open top Shovel tip starting in the hollow airfoil successively be inserted. After that lie the sections of the individual parts in each case in an overlapping area together, which is also referred to as a sliding seat. A special easy shifting is ensured because the direction of displacement of the impact cooling insert perpendicular to the propagation of Wave runs.

Die Erfindung wird anhand von Zeichnungen näher erläutert. Dabei zeigt:

Fig. 1
eine perspektivische Ansicht einer Turbinenschaufel mit einem Prallkühleinsatz,
Fig. 2
die Detailansicht eines Überlappungsbereichs des Prallkühleinsatzes der Turbinenschaufel gemäß Fig. 1 und
Fig. 3
die Detailansicht eines alternativen Überlappungsbereichs des Prallkühleinsatzes der Turbinenschaufel gemäß Fig. 1.
The invention will be explained in more detail with reference to drawings. Showing:
Fig. 1
a perspective view of a turbine blade with an impact cooling insert,
Fig. 2
the detailed view of an overlap region of the impingement cooling insert of the turbine blade of FIG. 1 and
Fig. 3
the detailed view of an alternative overlap region of the impingement cooling insert of the turbine blade according to FIG. 1.

Gasturbinen und deren Arbeitsweisen sind allgemein bekannt. Fig. 1 zeigt eine perspektivische Ansicht einer erfindungsgemäße Turbinenschaufel 1 mit einem Plattformbereich 2 und mit einem sich entlang einer Schaufelachse 2a erstreckenden Schaufelblatt 2b. Das Schaufelblatt 2b weist zumindest einen Hohlraum 3 auf, in dem ein Prallkühleinsatz 5 vorgesehen ist. Ferner weist das Schaufelblatt 2b eine von einem Heißgas 7 der Gasturbine anströmbare Schaufelvorderkante 9 auf, von der aus sich eine Saugseitenwand 11 und eine Druckseitenwand 13 zu einer Schaufelhinterkante 15 erstreckt. Die Turbinenschaufel 1 kann sowohl eine Leitschaufel als auch eine Laufschaufel sein. Gas turbines and their ways of working are well known. Fig. 1 shows a perspective view of an inventive Turbine blade 1 with a platform area 2 and with one extending along a blade axis 2a Airfoil 2b. The airfoil 2b has at least one Cavity 3, in which a baffle cooling insert 5 is provided. Furthermore, the airfoil 2b has one of a hot gas 7 the gas turbine flowable blade leading edge 9, from the a suction side wall 11 and a pressure side wall 13 extends to a blade trailing edge 15. The turbine blade 1 may include both a vane and a blade be.

Die inneren Oberflächen 19 der Seitenwände 11, 13 umschließen den Hohlraum 3. Unter Bildung eines Zwischenraums 22 ist die Oberfläche 19 vom Prallkühleinsatz 5 mittels mehrerer rippe-oder kreisförmiger Abstandselemente 21 beabstandet. Der im Inneren der Prallkühleinsätze 5 umschlossene Kühlmittelkanal 23 ist von einem Kühlmedium durchströmbar. Die Prallkühleinsätze 5 weisen ferner Prallkühlöffnungen 25 auf, durch welche das im Kühlmittelkanal 23 strömende Kühlmedium strömen und danach senkrecht auf die Oberflächen 19 der Seitenwände 11, 13 prallen kann, um diese zu kühlen.The inner surfaces 19 of the side walls 11, 13 enclose the cavity 3. To form a gap 22 is the Surface 19 of the baffle insert 5 by means of several ribs or circular spacers 21 spaced. The im Inside of the baffle inserts 5 enclosed coolant channel 23 is traversed by a cooling medium. The bumpers 5 also have impingement cooling openings 25 through which flowing in the coolant channel 23 flowing cooling medium and thereafter perpendicular to the surfaces 19 of the side walls 11, 13 can bounce to cool this.

Der Prallkühleinsatz 27 ist in Richtung der Schaufelachse 2a gesehen dabei aus zwei separaten Teilen 29, 31 gebildet, welche sich jeweils mit einem Abschnitt 30, 32 in einem Überlappungsbereich 33, 35 aneinanderliegend überlappen. Der Überlappungsbereich 33, 35 liegt dabei außerhalb der mittleren Schaufelblatthöhe.The baffle insert 27 is in the direction of the blade axis 2a seen from two separate parts 29, 31 formed, which each with a portion 30, 32 in an overlap area 33, 35 overlap each other. The overlap area 33, 35 lies outside the middle Blade height.

Der in der Fig. 1 dargestellte untere Teil 31 des Prallkühleinsatzes ist an der unteren Plattform und der obere Teil 29 an einer nicht dargestellten oberen Plattform im Anschlussbereich gasdicht zur Vermeidung von Leckagen fixiert.The illustrated in Fig. 1 lower part 31 of the impingement cooling insert is at the lower platform and the upper part 29 on an upper platform, not shown, in the connection area gas-tight to prevent leaks.

Da beim Betrieb des Gasturbine sich das heiße Schaufelblatt 2b in Richtung der Schaufelachse 2a mehr dehnt als der kühle Prallkühleinsatz 27, ist eine entlang der Schaufelachse 2a gerichtete Beweglichkeit der beiden fixierten Teile 29, 31 im Überlappungsbereich 33, 35 notwendig.Since during operation of the gas turbine, the hot airfoil 2b expands more in the direction of the blade axis 2a than the cool one Impact cooling insert 27, is one along the blade axis 2a directed mobility of the two fixed parts 29, 31 in Overlap area 33, 35 necessary.

Fig. 2 und Fig. 3 zeigen jeweils eine alternative Ausgestaltung des Überlappungsbereichs 33, 35 in einer Detailansicht.FIGS. 2 and 3 each show an alternative embodiment of the overlapping area 33, 35 in a detailed view.

Der Prallkühleinsatz 5 ist von der inneren Oberfläche 19 unter Bildung des Zwischenraumes 22 beabstandet. Beim Betrieb der Gasturbine wird die Saugseitenwand 11 von dem Heißgas 7 umströmt. Zur Kühlung der Saugseitenwand 11 strömt aus dem Kühlmittelkanal 23 das Kühlmedium 36 durch die Prallkühlöffnungen 25 hindurch und prallt kühlend auf die innere Oberfläche 19.The baffle insert 5 is under from the inner surface 19 Forming the gap 22 spaced. During operation the gas turbine, the suction side wall 11 of the hot gas. 7 flows around. For cooling the suction side wall 11 flows out of the Coolant channel 23, the cooling medium 36 through the impingement cooling holes 25 and bounces cooling on the inner surface 19th

In Fig. 2 sind die beiden Abschnitte 30, 32 mit einer identischen Wellenform ausgebildet, d.h. die Wellenformen der beiden Abschnitte 30, 32 der Teile 29, 31 weisen eine identische Frequenz f und eine identische Amplitude A auf. Durch den mäanderförmigen Spalt 37 zwischen den beiden Abschnitten 30, 32 kann eine durch Verwirbelungen verminderte Leckage strömen, verglichen mit einer Leckage bei einem ebenen Überlappungsbereich nach dem Stand der Technik. Bei einer in Bezug auf Fig. 2 nach links oder rechts zueinander, also entlang der Schaufelachse 2a, verschobenen Position der Abschnitte 30, 32 können die ansteigenden Flanken 39 oder die abfallenden Flanken 40 der benachbarten Abschnitte 30, 32 unter Bildung einer Kontaktfläche aber auch dicht aneinander anliegen. Eine Verschiebung der beiden Teile 29, 31 senkrecht dazu ist aufgrund der vorgegebenen Geometrie des Schaufelblattes 2b und des Prallkühleinsatzes 5 nicht möglich.In Fig. 2, the two sections 30, 32 with an identical Waveform formed, i. the waveforms of the two Sections 30, 32 of the parts 29, 31 have an identical Frequency f and an identical amplitude A on. Through the meandering Gap 37 between the two sections 30, 32nd If a leakage reduced by turbulences can flow, compared with a leakage in a flat overlap area According to the state of the art. With reference to FIG. 2 to the left or right to each other, ie along the blade axis 2a, shifted position of the sections 30, 32 can the rising flanks 39 or the falling flanks 40 of the adjacent sections 30, 32 to form a Contact surface but also close to each other. A shift the two parts 29, 31 perpendicular to it is due the predetermined geometry of the airfoil 2b and the Impact cooling insert 5 not possible.

Fig. 3 zeigt den Überlappungsbereich 33 mit den beiden gegenüberliegenden Abschnitten 30, 32, welche eine unterschiedliche Frequenz f und eine unterschiedliche Amplitude A aufweisen. Hierdurch ist zwischen den beiden Abschnitten 30, 32 ein Spiel in Richtung des Pfeils 41, also parallel zur Schaufelachse 2a, möglich, ohne das die Dichtwirkung des Überlappungsbereiches 33 abnimmt. Unabhängig von den thermischen Dehnungen des Prallkühleinsatzes 5 liegen die ansteigenden Flanken 39 bzw. abfallenden Flanken 40 der Wellenform zumindest einer Periode der beiden Abschnitte 30, 32 dichtend aneinander an, so dass jederzeit eine zur Schaufelachse 2a parallel verlaufende Kontaktfläche 43 vorhanden ist.Fig. 3 shows the overlapping region 33 with the two opposite Sections 30, 32, which are a different Have frequency f and a different amplitude A. As a result, between the two sections 30, 32 a Play in the direction of the arrow 41, ie parallel to the blade axis 2a, possible, without the sealing effect of the overlap region 33 decreases. Regardless of the thermal Strains of the impingement cooling insert 5 are the rising Flanks 39 and falling edges 40 of the waveform at least a period of the two sections 30, 32 sealingly to each other so that at any time one parallel to the blade axis 2a extending contact surface 43 is present.

Bei auftretenden Materialdehnungen bzw. Verschiebungen der Abschnitte 30, 32 gegeneinander verlagert sich die Kontaktfläche 43 innerhalb des Überlappungsbereichs 33, 35 von einer Periode zu einer benachbarten Periode. Daher ist zweckmäßigerweise eine Mindestanzahl von zwei Perioden im Überlappungsbereich 33, 35 vorgesehen, um eine besonders sichere Abdichtung des Kühlmittelkanals 23 gegenüber dem Zwischenraum 22 zu erzielen.At occurring material expansions or shifts of Sections 30, 32 against each other, the contact surface shifts 43 within the overlap region 33, 35 of a Period to an adjacent period. Therefore, it is expedient a minimum of two periods in the overlap area 33, 35 provided to a particularly secure seal the coolant channel 23 with respect to the gap 22 to achieve.

Je nach Anforderung können zur gleichmäßigeren Kühlung der Seitenwände 11, 13 auch im Überlappungsbereich 33, 35 Prallkühlöffnungen 25 vorgesehen sein, insbesondere im Bereich der Wellentäler oder Wellenberge der Abschnitte 30, 32.Depending on the requirements, the more even cooling can be achieved Side walls 11, 13 also in the overlap region 33, 35 baffle cooling openings Be provided 25, in particular in the field of Wave troughs or wave crests of sections 30, 32.

Die Wellenform ist nicht zwingend sinusförmig. Eine gleiche Wirkung ist auch mit einer Wellenform bestehend aus aufeinanderfolgenden Halbkreisen oder Halbellipsen erzielbar. Darüber hinaus ist eine Dreiecksform, eine Sägezahnform oder eine Rechteckform ebenfalls denkbar.The waveform is not necessarily sinusoidal. Same one Effect is also with a waveform consisting of consecutive Semicircles or semi-ellipses achievable. About that In addition, a triangular shape, a sawtooth shape or a Rectangular shape also conceivable.

Durch die verbesserte Dichtwirkung des Prallkühleinsatzes 5 im Vergleich zu den ebenen Anlageflächen aus dem Stand der Technik kann eine Kühllufteinsparung erzielt werden, die bei einer Verwendung der Turbinenschaufel in einer Gasturbine zu einer Wirkungsgradsteigerung führt. Gleichfalls ist die erfindungsgemäße wellenförmige Überlappung auf jedes prallgekühlte Bauteil einer Gasturbine mit einem Prallkühlblech, z. B. auf einen der Laufschaufel außen gegenüberliegenden Führungsring oder auf ein Brennkammerhitzeschild, übertragbar.Due to the improved sealing effect of the impact cooling insert 5 Compared to the flat contact surfaces from the state of Technique can be achieved with a cooling air saving a use of the turbine blade in a gas turbine to an increase in efficiency leads. Likewise, the inventive Wavy overlap on each impact-cooled Component of a gas turbine with an impingement cooling plate, z. B. on one of the blade outside opposite Guide ring or on a combustion chamber heat shield, transferable.

Claims (6)

Turbinenschaufel (1), insbesondere Leitschaufel für eine Gasturbine,
welche aufeinanderfolgend einen Schaufelfuß, einen Plattformbereich (2) und ein hohles Schaufelblatt (2b) zur Aufnahme eines blechförmigen Prallkühleinsatzes (5, 27) umfasst,
welcher zumindest zwei sich in einem Überlappungsbereich (33, 35) überlappende, aneinanderliegende Abschnitte (30, 32) aufweist,
dadurch gekennzeichnet, dass zum Abdichten des Überlappungsbereichs (33, 35) die beiden Abschnitte (30, 32) im Überlappungsbereich (33, 35) im Querschnitt wellenförmig ausgebildet sind.Turbine blade (1), in particular guide vane for a gas turbine,
which successively comprises a blade root, a platform region (2) and a hollow blade (2b) for receiving a sheet-like impingement cooling insert (5, 27),
which has at least two adjoining sections (30, 32) overlapping in an overlapping area (33, 35),
characterized in that for sealing the overlap region (33, 35), the two sections (30, 32) in the overlapping region (33, 35) are formed in a wave-shaped cross-section. Turbinenschaufel (1) nach Anspruch 1,
dadurch gekennzeichnet, dass die Frequenz (f) und/oder die Amplitude (A) der Wellenform des ersten Abschnitts (30) von der Frequenz (f) und/oder Amplitude (A) der Wellenform des zweiten Abschnitts (32) abweicht.Turbine blade (1) according to claim 1,
characterized in that the frequency (f) and / or the amplitude (A) of the waveform of the first section (30) deviates from the frequency (f) and / or amplitude (A) of the waveform of the second section (32). Turbinenschaufel (1) nach Anspruch 2,
dadurch gekennzeichnet, dass die Frequenz (f) und/oder Amplitude (A) der Wellenform des ersten Abschnitts (30) in einer Großenordnung von ±6% sich von der Frequenz (f) und/oder Amplitude (A) der Wellenform des zweiten Abschnitts (32) unterscheidet.Turbine blade (1) according to claim 2,
characterized in that the frequency (f) and / or amplitude (A) of the waveform of the first section (30) is on the order of ± 6% of the frequency (f) and / or amplitude (A) of the waveform of the second section (32) differs. Turbinenschaufel (1) nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, dass der Überlappungsbereich (33, 35) nicht mehr als 5 Schwingungsperioden aufweist. Turbine blade (1) according to one of claims 1 to 3,
characterized in that the overlap region (33, 35) has no more than 5 oscillation periods. Turbinenschaufel (1) nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, dass der Prallkühleinsatz (5) mehrteilig ausgebildet ist.Turbine blade (1) according to one of claims 1 to 3,
characterized in that the impact cooling insert (5) is designed in several parts. Gasturbine mit einer Turbinenschaufel (1) nach einem der Ansprüche 1 bis 5.Gas turbine with a turbine blade (1) according to one of Claims 1 to 5.
EP04009326A 2004-04-20 2004-04-20 Turbine blade with an insert for impingement cooling Withdrawn EP1589192A1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP04009326A EP1589192A1 (en) 2004-04-20 2004-04-20 Turbine blade with an insert for impingement cooling
DE502005004644T DE502005004644D1 (en) 2004-04-20 2005-04-01 TURBINE BUCKET WITH A BUMPER INSERT
US11/578,920 US8137055B2 (en) 2004-04-20 2005-04-01 Turbine blade with an impingement cooling insert
EP05731679A EP1738060B1 (en) 2004-04-20 2005-04-01 Turbine blade with an impact cooling insert
PCT/EP2005/051487 WO2005103452A1 (en) 2004-04-20 2005-04-01 Turbine blade with an impact cooling insert
ES05731679T ES2308476T3 (en) 2004-04-20 2005-04-01 TURBINE SHOVEL WITH A REFRIGERATION INSERT BY REBOUND.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04009326A EP1589192A1 (en) 2004-04-20 2004-04-20 Turbine blade with an insert for impingement cooling

Publications (1)

Publication Number Publication Date
EP1589192A1 true EP1589192A1 (en) 2005-10-26

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EP05731679A Not-in-force EP1738060B1 (en) 2004-04-20 2005-04-01 Turbine blade with an impact cooling insert

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EP05731679A Not-in-force EP1738060B1 (en) 2004-04-20 2005-04-01 Turbine blade with an impact cooling insert

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US (1) US8137055B2 (en)
EP (2) EP1589192A1 (en)
DE (1) DE502005004644D1 (en)
ES (1) ES2308476T3 (en)
WO (1) WO2005103452A1 (en)

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WO2008081486A1 (en) * 2007-01-04 2008-07-10 Ansaldo Energia S.P.A. Spacer for gas turbine blade insert
CN100420542C (en) * 2006-06-22 2008-09-24 上海电气电站设备有限公司 Assembly art of inlay type welded clapboard
EP3293356A1 (en) * 2016-09-06 2018-03-14 Rolls-Royce Deutschland Ltd & Co KG Blade for turbomachine comprising a movably supported impingement baffle and corresponding assembly method

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US8777569B1 (en) * 2011-03-16 2014-07-15 Florida Turbine Technologies, Inc. Turbine vane with impingement cooling insert
US9719372B2 (en) 2012-05-01 2017-08-01 General Electric Company Gas turbomachine including a counter-flow cooling system and method
US10100659B2 (en) 2014-12-16 2018-10-16 Rolls-Royce North American Technologies Inc. Hanger system for a turbine engine component
US9879554B2 (en) 2015-01-09 2018-01-30 Solar Turbines Incorporated Crimped insert for improved turbine vane internal cooling
DE102016207162A1 (en) 2016-04-27 2017-11-02 Siemens Aktiengesellschaft Coolant distributor for a blade of several part inserts
PL232314B1 (en) 2016-05-06 2019-06-28 Gen Electric Fluid-flow machine equipped with the clearance adjustment system
US10309246B2 (en) 2016-06-07 2019-06-04 General Electric Company Passive clearance control system for gas turbomachine
US10605093B2 (en) 2016-07-12 2020-03-31 General Electric Company Heat transfer device and related turbine airfoil
US10392944B2 (en) 2016-07-12 2019-08-27 General Electric Company Turbomachine component having impingement heat transfer feature, related turbomachine and storage medium
US10767487B2 (en) * 2016-11-17 2020-09-08 Raytheon Technologies Corporation Airfoil with panel having flow guide
JP6655589B2 (en) * 2017-11-29 2020-02-26 三菱重工業株式会社 Measuring system, processing system, measuring method and program
CN111764967B (en) * 2020-07-06 2022-10-14 中国航发湖南动力机械研究所 Turbine blade trailing edge cooling structure

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CN100420542C (en) * 2006-06-22 2008-09-24 上海电气电站设备有限公司 Assembly art of inlay type welded clapboard
WO2008081486A1 (en) * 2007-01-04 2008-07-10 Ansaldo Energia S.P.A. Spacer for gas turbine blade insert
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Also Published As

Publication number Publication date
ES2308476T3 (en) 2008-12-01
EP1738060B1 (en) 2008-07-09
US8137055B2 (en) 2012-03-20
DE502005004644D1 (en) 2008-08-21
US20080260537A1 (en) 2008-10-23
WO2005103452A1 (en) 2005-11-03
EP1738060A1 (en) 2007-01-03

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