EP2489837A1 - Metering insert for turbine blade and corresponding turbine blade - Google Patents

Metering insert for turbine blade and corresponding turbine blade Download PDF

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Publication number
EP2489837A1
EP2489837A1 EP11154936A EP11154936A EP2489837A1 EP 2489837 A1 EP2489837 A1 EP 2489837A1 EP 11154936 A EP11154936 A EP 11154936A EP 11154936 A EP11154936 A EP 11154936A EP 2489837 A1 EP2489837 A1 EP 2489837A1
Authority
EP
European Patent Office
Prior art keywords
throttle
blade
turbine blade
flexible sealing
sealing elements
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Withdrawn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
EP11154936A
Other languages
German (de)
French (fr)
Inventor
Fathi Ahmad
Winfried Esser
Giuseppe Gaio
Waldemar Heckel
Rudolf Küperkoch
Oliver Lüsebrink
Thorsten Mattheis
Mirko Milazar
Artur Mol
Uwe Paul
Oliver Ricken
Oliver Schneider
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 EP11154936A priority Critical patent/EP2489837A1/en
Publication of EP2489837A1 publication Critical patent/EP2489837A1/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Withdrawn legal-status Critical Current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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments

Definitions

  • the invention relates to a throttle insert according to the preamble of claim 1, as well as a turbine blade according to claim 6.
  • Turbine blades in particular those for gas turbines, must be cooled.
  • coolant is blown out through corresponding openings in the outer walls from the interior of the turbine blade to the outer surface of the blade walls.
  • the amount of blown coolant must be set as accurately as possible. This is done today via throttle inserts in the turbine blades whose throttle openings are dimensioned accordingly.
  • a generic turbine blade with a throttle insert is for example from the EP 1 717 416 A1 known and in FIG. 5 shown.
  • the turbine blade 21 has, along a blade longitudinal axis 23, a blade root 25, a platform region 27, and a blade profile 29 of a wing shape in succession.
  • the turbine blade is hollow in its interior for guiding coolant 51, preferably cooling air, so that it can withstand the high temperatures of the hot gas flowing around as the working medium of the gas turbine.
  • the blade profile 29 has a leading edge 31 for the inflowing hot gas and an outflow edge 33, at which the hot gas flowing around the blade profile 29 leaves the turbine blade 21.
  • a sheet-like throttle insert 39 is provided over approximately the full height of the blade profile 29, into which a plurality of throttle openings 41 introduced in the form of holes 43 are.
  • the throttle insert 39 may here be part of the mold for casting the turbine blade 21, which remains in the casting after casting, or it was subsequently inserted into the casting and sealed by welding, soldering or other suitable method between the pressure side wall 37 and the suction side wall 35 attached.
  • the object of the invention is to provide a throttle insert and a turbine blade, which overcome the disadvantage described above.
  • the flexible sealing elements either on one side or on the front side to the edge regions of the throttle plate.
  • FIG. 1 shows a partial section of a first embodiment of a throttle insert with a throttle plate B with throttle openings D, in which metal wool is soldered as a flexible sealing element A on one side to the edge regions of the throttle plate B.
  • FIG. 2 shows a detail of a second embodiment in which the metal wool A is applied on the front side on two opposite edge regions of the throttle plate B.
  • FIG. 3 is a training in which additional metal wool on a third edge area, here the front side, is applied.
  • FIG. 4 shows in section a section of a turbine blade with the two walls W1 and W2 of the concave curved pressure side wall and a spaced apart convexly curved suction side wall. Both walls W1 and W2 have on opposite sides at the point where the throttle insert to be introduced corresponding guide elements S1 and S2, which are designed here as guide grooves in which the throttle insert is inserted and fixed.
  • FIG. 4 also shows in enlarged detail the inserted into the guide grooves S1 and S2 and accordingly 1 to 3 trained throttle inserts.

Landscapes

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

Abstract

The insert has a throttle plate (B) with passages (D) whose dimensions determine the throttle performance of a coolant stream between compartments. Flexible sealing elements are designed as metal wools (A) that are sealably attached at edge regions of the throttle plate. Airfoil-shaped blade walls (W1, W2) form a hollow chamber for guiding a coolant stream, where the hollow chamber is bound by the blade walls of a turbine blade. Guiding elements (S1, S2) are designed in a manner such that the insert is tightly attached via the flexible sealing elements. An independent claim is also included for a turbine blade for a gas turbine.

Description

Die Erfindung betrifft einen Drosseleinsatz gemäß dem Oberbegriff des Anspruchs 1, sowie eine Turbinenschaufel gemäß Anspruch 6.The invention relates to a throttle insert according to the preamble of claim 1, as well as a turbine blade according to claim 6.

Turbinenschaufeln insbesondere solche für Gasturbinen müssen gekühlt werden. Dazu wird Kühlmittel über entsprechende Öffnungen in den Außenwandungen aus dem Innern der Turbinenschaufel heraus an die außenliegende Oberfläche der Schaufelwandungen ausgeblasen. Für eine effiziente und an die Leistung der Gasturbine angepasste Kühlung der Schaufelwandungen, muss dazu die Menge an ausgeblasenem Kühlmittel möglichst exakt eingestellt werden. Dies geschieht heute über Drosseleinsätze in den Turbinenschaufeln, deren Drosselöffnungen entsprechend dimensioniert sind.Turbine blades, in particular those for gas turbines, must be cooled. For this purpose, coolant is blown out through corresponding openings in the outer walls from the interior of the turbine blade to the outer surface of the blade walls. For an efficient and adapted to the performance of the gas turbine cooling of the blade walls, to do so, the amount of blown coolant must be set as accurately as possible. This is done today via throttle inserts in the turbine blades whose throttle openings are dimensioned accordingly.

Eine gattungsgemäße Turbinenschaufel mit einem Drosseleinsatz ist beispielsweise aus der EP 1 717 416 A1 bekannt und in FIG 5 dargestellt. Die Turbinenschaufel 21 weist entlang einer Schaufellängsachse 23 aufeinander folgend einen Schaufelfuß 25, ein Plattformbereich 27 und ein im Querschnitt tragflügelförmiges Schaufelprofil 29 auf. Die Turbinenschaufel ist in ihrem Inneren zur Führung von Kühlmittel 51, vorzugsweise Kühlluft, hohl ausgebildet, damit sie den hohen Temperaturen des umströmenden Heißgases als Arbeitsmedium der Gasturbine widerstehen kann. Das Schaufelprofil 29 weist eine Anströmkante 31 für das anströmende Heißgas und eine Abströmkante 33 auf, an der das, das Schaufelprofil 29 umströmende Heißgas die Turbinenschaufel 21 verlässt. Zwischen der Anströmkante 31 und der Abströmkante 33 erstreckt sich eine konvex gebogene Saugseitenwand 35 und eine dazu beabstandete, konkav gebogene Druckseitenwand 37. Im Bereich der Abströmkante 33 ist hier ein blechförmiger Drosseleinsatz 39 über annähernd die vollständige Höhe des Schaufelprofils 29 vorgesehen, in den mehrere Drosselöffnungen 41 in Form von Bohrungen 43 eingebracht sind. Der Drosseleinsatz 39 kann hier Teil der Gießform zum Gießen der Turbinenschaufel 21 sein, welcher nach dem Gießen im Guss verbleibt, oder er wurde nachträglich in den Guss eingesetzt und durch Schweißen, Löten oder ein anderes geeignetes Verfahren zwischen der Druckseitenwand 37 und der Saugseitenwand 35 dicht befestigt. Wird ein solches Drosselblech aber auf eine solche Art und Weise fest mit den gegossenen Turbinenwandungen verbunden, kann es aufgrund der unterschiedlichen Materialeigenschaften während des Betriebs der Gasturbine aufgrund der hohen Temperaturen des Heißgases und der damit bewirkten unterschiedlichen Materialausdehnungen zu Spannungen an einer solchen Verbindung kommen. Aufgabe der Erfindung ist es, ein Drosseleinsatz und eine Turbinenschaufel bereitzustellen, die den zuvor beschriebenen Nachteil überwinden.A generic turbine blade with a throttle insert is for example from the EP 1 717 416 A1 known and in FIG. 5 shown. The turbine blade 21 has, along a blade longitudinal axis 23, a blade root 25, a platform region 27, and a blade profile 29 of a wing shape in succession. The turbine blade is hollow in its interior for guiding coolant 51, preferably cooling air, so that it can withstand the high temperatures of the hot gas flowing around as the working medium of the gas turbine. The blade profile 29 has a leading edge 31 for the inflowing hot gas and an outflow edge 33, at which the hot gas flowing around the blade profile 29 leaves the turbine blade 21. Between the leading edge 31 and the trailing edge 33 there extends a convexly curved suction side wall 35 and a concavely curved pressure side wall 37 spaced therefrom. In the region of the trailing edge 33, a sheet-like throttle insert 39 is provided over approximately the full height of the blade profile 29, into which a plurality of throttle openings 41 introduced in the form of holes 43 are. The throttle insert 39 may here be part of the mold for casting the turbine blade 21, which remains in the casting after casting, or it was subsequently inserted into the casting and sealed by welding, soldering or other suitable method between the pressure side wall 37 and the suction side wall 35 attached. However, if such a throttle plate firmly connected in such a manner with the cast turbine walls, it may lead to stresses on such a compound due to the different material properties during operation of the gas turbine due to the high temperatures of the hot gas and thus caused different material expansions. The object of the invention is to provide a throttle insert and a turbine blade, which overcome the disadvantage described above.

Diese Aufgabe wird mit dem Drosseleinsatz mit den Merkmalen des Anspruchs 1, sowie der Turbinenschaufel mit den Merkmalen des Anspruchs 6 gelöst.This object is achieved with the throttle insert with the features of claim 1, and the turbine blade with the features of claim 6.

Dadurch, dass an Randbereichen des Drosselblechs flexible Dichtelemente, wie beispielsweise Metallwolle, zum Abdichten angebracht sind, können sich Turbinenschaufelwandungen und Drosselblech unterschiedlich ausdehnen, ohne dass es zu Spannungskräften an der Verbindung zwischen den Stützelementen der Wandungen und des Drosseleinsatzes kommt.Characterized in that at the edge regions of the throttle plate flexible sealing elements, such as metal wool, are attached for sealing, Turbinenschaufelwandungen and throttle plate can expand differently, without causing tension forces on the connection between the support elements of the walls and the throttle insert.

Je nach Geometrie der Turbinenschaufel kann es dabei vorteilhaft sein, die flexiblen Dichtelemente entweder einseitig oder stirnseitig an den Randbereichen des Drosselblechs anzubringen.Depending on the geometry of the turbine blade, it may be advantageous to attach the flexible sealing elements either on one side or on the front side to the edge regions of the throttle plate.

Besonders vorteilhaft ist bei einer Turbinenschaufel für eine Gasturbine mit tragflügelförmig ausgebildeten Schaufelwandungen die Ausbildung der Führungselemente als Führungsnuten, da dann der Drosseleinsatz in Richtung der Schaufellängsachse eingeschoben werden kann und an Schaufelfuß oder Schaufelkopf nur an einer einzigen Stelle fest fixiert werden muss. Seitlich wird der Drosseleinsatz über die flexiblen Dichtelemente dicht in die Führungsnuten eingebracht und selbst schon fixiert.Particularly advantageous is in a turbine blade for a gas turbine with airfoil-shaped blade walls, the formation of the guide elements as guide grooves, since then the throttle insert can be inserted in the direction of the blade longitudinal axis and blade root or blade head only has to be firmly fixed in one place. Laterally, the throttle insert is introduced via the flexible sealing elements tightly into the guide grooves and already fixed.

Die Erfindung soll nun anhand der nachfolgenden Figuren beispielhaft erläutert werden. Es zeigen:

FIG 1
schematisch eine erste erfindungsgemäße Ausführung eines Drosseleinsatzes,
FIG 2
schematisch eine zweite erfindungsgemäße Ausführung eines Drosseleinsatzes,
FIG 3
schematisch eine dritte erfindungsgemäße Ausführung eines Drosseleinsatzes,
FIG 4
ein Schnittbild einer erfindungsgemäß ausgebildeten Turbinenschaufel mit Drosseleinsatz,
FIG 5
ein Schnitt durch eine aus dem Stand der Technik bekannte Turbinenschaufel mit Drosseleinsatz.
The invention will now be explained by way of example with reference to the following figures. Show it:
FIG. 1
schematically a first embodiment of a throttle insert according to the invention,
FIG. 2
schematically a second embodiment of a throttle insert according to the invention,
FIG. 3
schematically a third embodiment of a throttle insert according to the invention,
FIG. 4
a sectional view of an inventively designed turbine blade with throttle insert,
FIG. 5
a section through a known from the prior art turbine blade with throttle insert.

FIG 1 zeigt einen Teilausschnitt eines ersten Ausführungsbeispiels eines Drosseleinsatzes mit einem Drosselblech B mit Drosselöffnungen D, bei dem Metallwolle als flexibles Dichtelement A einseitig an den Randbereichen des Drosselblechs B aufgelötet ist. FIG. 1 shows a partial section of a first embodiment of a throttle insert with a throttle plate B with throttle openings D, in which metal wool is soldered as a flexible sealing element A on one side to the edge regions of the throttle plate B.

FIG 2 zeigt ausschnittsweise ein zweites Ausführungsbeispiel, bei dem die Metallwolle A stirnseitig auf zwei gegenüberliegenden Randbereichen des Drosselblechs B aufgebracht ist. FIG. 2 shows a detail of a second embodiment in which the metal wool A is applied on the front side on two opposite edge regions of the throttle plate B.

FIG 3 ist eine Weiterbildung bei der zusätzlich Metallwolle auf einen Dritten Randbereich, hier stirnseitig, aufgebracht ist. FIG. 3 is a training in which additional metal wool on a third edge area, here the front side, is applied.

FIG 4 zeigt im Schnitt einen Ausschnitt aus einer Turbinenschaufel mit den beiden Wandungen W1 und W2 der konkav gebogene Druckseitenwand und einer dazu beabstandeten konvex gebogenen Saugseitenwand. Beide Wandungen W1 und W2 weisen an gegenüberliegenden Seiten an der Stelle an der der Drosseleinsatz eingebracht werden soll entsprechende Führungselemente S1 und S2 auf, die hier als Führungsnuten ausgebildet sind in die der Drosseleinsatz einschiebbar und fixierbar ist. FIG 4 zeigt zudem in vergrößerten Ausschnitten die in die Führungsnuten S1 und S2 eingesetzten und entsprechend FIG 1 bis 3 ausgebildeten Drosseleinsätze. FIG. 4 shows in section a section of a turbine blade with the two walls W1 and W2 of the concave curved pressure side wall and a spaced apart convexly curved suction side wall. Both walls W1 and W2 have on opposite sides at the point where the throttle insert to be introduced corresponding guide elements S1 and S2, which are designed here as guide grooves in which the throttle insert is inserted and fixed. FIG. 4 also shows in enlarged detail the inserted into the guide grooves S1 and S2 and accordingly 1 to 3 trained throttle inserts.

Claims (8)

Drosseleinsatz zum Unterteilen eines kühlmitteldurchströmten Hohlraums einer Turbinenschaufel in zwei Teilräume, wobei der Hohlraum durch Schaufelwandungen der Turbinenschaufel begrenzt ist, und wobei der Drosseleinsatz ein Drosselblech (B) mit Durchführungen (D) aufweist, deren Gesamtgröße eine Drosselleistung des Kühlmittelstroms zwischen den Teilräumen bestimmt
dadurch gekennzeichnet, dass an Randbereichen des Drosselblechs (B) flexible Dichtelemente (A) zum Abdichten angebracht sind.A throttle insert for dividing a coolant flowed through cavity of a turbine blade into two partial spaces, wherein the cavity is defined by blade walls of the turbine blade, and wherein the throttle insert a throttle plate (B) with passages (D) whose total size determines a throttle performance of the coolant flow between the subspaces
characterized in that at the edge regions of the throttle plate (B) flexible sealing elements (A) are mounted for sealing. Drosseleinsatz nach Anspruch 1,
dadurch gekennzeichnet, dass die flexiblen Dichtelemente (A) an den Randbereichen einseitig auf dem Drosselblech (B) angebracht sind.Throttle insert according to claim 1,
characterized in that the flexible sealing elements (A) at the edge regions on one side of the throttle plate (B) are mounted. Drosseleinsatz nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass die flexiblen Dichtelemente (A) an den Randbereichen stirnseitig auf dem Drosselblech (B) angebracht sind.Throttle insert according to claim 1 or 2,
characterized in that the flexible sealing elements (A) at the edge regions are frontally mounted on the throttle plate (B). Drosseleinsatz nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, dass die flexiblen Dichtelemente (A) Metallwolle ist.Throttle insert according to one of claims 1 to 3,
characterized in that the flexible sealing elements (A) is metal wool. Drosseleinsatz nach Anspruch 4,
dadurch gekennzeichnet, dass die Metallwolle (A) an den Randbereichen aufgelötet ist.Throttle insert according to claim 4,
characterized in that the metal wool (A) is soldered to the edge regions. Turbinenschaufel für eine Gasturbine mit tragflügelförmig ausgebildeten Schaufelwandungen (W1,W2), die einen Hohlraum zur Führung eines Kühlmittelstroms ausbilden, mit einem im Hohlraum angebrachten und den Hohlraum unterteilenden Drosseleinsatz nach einem der Ansprüche 1 bis 5, wobei an den Schaufelwandungen (W1,W2) Führungselemente (S1,S2) so ausgebildet sind, dass der Drosseleinsatz über die flexiblen Dichtelemente dicht daran anbringbar ist.Turbine blade for a gas turbine having airfoil-shaped blade walls (W1, W2) forming a cavity for guiding a coolant flow, having a cavity-mounted and cavity dividing throttle insert according to one of claims 1 to 5, wherein on the blade walls (W1, W2) Guiding elements (S1, S2) are formed are that the throttle insert on the flexible sealing elements can be attached tightly thereto. Turbinenschaufel nach Anspruch 6,
dadurch gekennzeichnet, dass die Führungselemente (S1,S2) in Schaufellängsachse an den beiden gegenüberliegenden Schaufelwandungen (W1,W2) als Führungsnuten ausgebildet sind, in die der Drosseleinsatz in Richtung der Schaufellängsachse eingeschoben und über die flexiblen Dichtelemente in den Führungsnuten dicht fixiert ist.Turbine blade according to claim 6,
characterized in that the guide elements (S1, S2) in the blade longitudinal axis on the two opposite Schaufelwandungen (W1, W2) are formed as guide grooves, in which the throttle insert is inserted in the direction of the blade longitudinal axis and tightly fixed in the guide grooves via the flexible sealing elements. Turbinenschaufel nach Anspruch 7,
dadurch gekennzeichnet, dass der eingeschobene Drosseleinsatz im Bereich des Schaufelfußes oder Schaufelkopfes fest fixiert ist.Turbine blade according to claim 7,
characterized in that the inserted throttle insert is firmly fixed in the region of the blade root or blade head.
EP11154936A 2011-02-18 2011-02-18 Metering insert for turbine blade and corresponding turbine blade Withdrawn EP2489837A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11154936A EP2489837A1 (en) 2011-02-18 2011-02-18 Metering insert for turbine blade and corresponding turbine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11154936A EP2489837A1 (en) 2011-02-18 2011-02-18 Metering insert for turbine blade and corresponding turbine blade

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Publication Number Publication Date
EP2489837A1 true EP2489837A1 (en) 2012-08-22

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3023586A1 (en) * 2014-11-21 2016-05-25 Siemens Aktiengesellschaft Hollow blade body, inserted fin and hollow blade
EP3101230A1 (en) * 2015-05-29 2016-12-07 General Electric Company Turbine component having surface cooling channels and method of forming same
US10364685B2 (en) * 2016-08-12 2019-07-30 Gneral Electric Company Impingement system for an airfoil
US10408062B2 (en) * 2016-08-12 2019-09-10 General Electric Company Impingement system for an airfoil
US10436048B2 (en) * 2016-08-12 2019-10-08 General Electric Comapny Systems for removing heat from turbine components
US10443397B2 (en) * 2016-08-12 2019-10-15 General Electric Company Impingement system for an airfoil

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1717416A1 (en) 2005-04-25 2006-11-02 Siemens Aktiengesellschaft Turbine blade, use of the blade and manufacturing method thereof
EP1947295A1 (en) * 2007-01-18 2008-07-23 Siemens Aktiengesellschaft Vane plug of an axial turbine vane

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1717416A1 (en) 2005-04-25 2006-11-02 Siemens Aktiengesellschaft Turbine blade, use of the blade and manufacturing method thereof
EP1947295A1 (en) * 2007-01-18 2008-07-23 Siemens Aktiengesellschaft Vane plug of an axial turbine vane

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3023586A1 (en) * 2014-11-21 2016-05-25 Siemens Aktiengesellschaft Hollow blade body, inserted fin and hollow blade
WO2016078851A1 (en) * 2014-11-21 2016-05-26 Siemens Aktiengesellschaft Hollow blade body, insertion rib, and hollow blade
CN107002496A (en) * 2014-11-21 2017-08-01 西门子股份公司 Hollow blade body, insertion rib and hollow blade
EP3101230A1 (en) * 2015-05-29 2016-12-07 General Electric Company Turbine component having surface cooling channels and method of forming same
US9752440B2 (en) 2015-05-29 2017-09-05 General Electric Company Turbine component having surface cooling channels and method of forming same
US10364685B2 (en) * 2016-08-12 2019-07-30 Gneral Electric Company Impingement system for an airfoil
US10408062B2 (en) * 2016-08-12 2019-09-10 General Electric Company Impingement system for an airfoil
US10436048B2 (en) * 2016-08-12 2019-10-08 General Electric Comapny Systems for removing heat from turbine components
US10443397B2 (en) * 2016-08-12 2019-10-15 General Electric Company Impingement system for an airfoil

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