EP1163426A1 - Turbomachine blade - Google Patents

Turbomachine blade

Info

Publication number
EP1163426A1
EP1163426A1 EP00908907A EP00908907A EP1163426A1 EP 1163426 A1 EP1163426 A1 EP 1163426A1 EP 00908907 A EP00908907 A EP 00908907A EP 00908907 A EP00908907 A EP 00908907A EP 1163426 A1 EP1163426 A1 EP 1163426A1
Authority
EP
European Patent Office
Prior art keywords
blade
edge
airfoil
hole
turbomachine
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
EP00908907A
Other languages
German (de)
French (fr)
Other versions
EP1163426B1 (en
Inventor
Bent Phillipsen
Boris Mamaev
Evgeny Ryabov
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.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems 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 ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Publication of EP1163426A1 publication Critical patent/EP1163426A1/en
Application granted granted Critical
Publication of EP1163426B1 publication Critical patent/EP1163426B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the invention relates to a turbomachine blade provided with a damper wire hole according to the preamble of claim 1.
  • damper wires or other damping elements are often used, which are received in corresponding holes in the blades.
  • increased stresses occur especially at the edges of the holes.
  • the contact area that the damper wire has with the damper wire hole during operation of the turbomachine is defined by the distance between the boundary planes of the reinforcements. This distance or the length of the contact area is chosen so that both sufficient static and dynamic strength is guaranteed.
  • the invention tries to avoid all these disadvantages. It is the object of the invention to improve the efficiency of a turbomachine blade which has a reinforced hole for receiving a damping element
  • the two acute angles .alpha. And .beta. are preferably formed in a range from 5 ° to 30 °. It has been shown that with such a configuration, particularly minor disturbances in the flow occur in the area of the damping elements
  • FIG. 3 shows a section through the rotor blade, along the line III-III in FIG. 1 Only the elements essential for understanding the invention are shown. For example, the other components of the exhaust gas turbine, including its turbine wheel, are not shown
  • the turbine machine blade shown in FIG. 1, designed as a rotor blade 1, consists of a blade root 2, a platform 3 and an airfoil 4.
  • the platforms of adjacent turbine blades of the turbine wheel lie directly against one another and thus form the inner boundary of the flow channel, which is directed outwards from one Blade cover, also not shown, is completed.
  • the blade 4 has an entry edge 5, a discharge edge 6, a suction side 7 and a pressure side 8 and has a blade tip 9
  • the airfoil 4 there is a through hole 10 from the suction side 7 to the pressure side 8 for receiving a steam wire, not shown, which reduces the blade vibration occurring during operation.
  • the airfoil is also formed with an edge region 11 reinforced towards the hole 10, the edge region 11 both on the suction side 7 and on the pressure side 11 has an end surface 12, 13 which is raised in relation to the airfoil 4.
  • the end surfaces 12, 13 are at an acute angle ex of approximately 10 ° open to the leading edge 5 of the airfoil 4 and with one to the airfoil tip 9 open, acute angle ⁇ of approximately 20 ° (FIG. 2, FIG. 3)
  • both end faces 12, 13 of the reinforced edge region 11 converge in the direction of the discharge edge 6 of the airfoil 4 and in the direction of the blade root 2 in such a way that the reinforcement of the outlet-side and the blade foot-side part of the edge region 11 is significantly less than the reinforcement the part of the edge region 11 on the entrance side and the blade tip side
  • This formation of the airfoil 4 in the region of the hole 10 results in improved flow control during operation of the turbocharger or the exhaust gas turbine.
  • the working medium flowing along the airfoil 4 in a main flow direction 14 experiences, as a result of the end faces 12, 13 arranged at an acute angle to one another as described above, a significantly lower disturbance than is the case with the solutions of the prior art. Due to the improved flow guidance in the area of the turbine wheel, a higher efficiency of the turbocharger and thus ultimately also of the internal combustion engine connected to it can be achieved.
  • angles ⁇ and ⁇ between the end faces 12, 13 of the reinforced edge region 11 are each advantageously in a range from 5 ° to 30 °.
  • end surfaces 12, 13 can also have only one of the two acute angles ⁇ , ⁇ (not shown), which simplifies production but represents a certain loss in efficiency.
  • such a reinforcement of the edge region of the hole receiving the damper wire can be used for all types of damping elements, such as, for example, also in the case of binding wires, bolts, etc. and also in the case of so-called zigzag bonds.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

The invention has the aim of improving the efficiency of a turbomachine blade fitted with a reinforced hole for receiving a damping element. To this end, the raised end faces (12, 13) of the edge area (11) of the blade (4), which is reinforced in the direction of the hole (10), is configured with an acute angle alpha that is open relative to the input edge (5) of the blade and/or with an acute angle beta that is open relative to the tip (9) of the blade.

Description

Turbomaschinenschaufel Turbomachine blade
Technisches GebietTechnical field
Die Erfindung betrifft eine mit einem Dämpferdrahtloch versehene Turbomaschinenschaufel gemass dem Oberbegriff des Anspruchs 1.The invention relates to a turbomachine blade provided with a damper wire hole according to the preamble of claim 1.
Stand der TechnikState of the art
Um unzulässige Schwingungen der Schaufeln von Turbomaschinen zu vermeiden werden häufig Dämpferdrähte oder andere Dämpfungselemente eingesetzt, welche in entsprechenden Löchern der Schaufeln aufgenommen werden. Infolge der hohen Umdrehungszahlungen treten jedoch insbesondere an den Lochrändern erhöhte Spannungen auf.In order to avoid impermissible vibrations of the blades of turbomachinery, damper wires or other damping elements are often used, which are received in corresponding holes in the blades. As a result of the high number of revolutions, however, increased stresses occur especially at the edges of the holes.
Zur Vorbeugung einer frühzeitigen Materialermüdung ist es bekannt, im Lochbereich der Schaufeln entsprechende Verstärkungen vorzunehmen. Der Kontaktbereich, den der Dämpferdraht beim Betrieb der Turbomaschine zum Dämpferdrahtloch aufweist, ist durch den Abstand zwischen den Begrenzungsebenen der Verstärkungen definiert. Dieser Abstand, bzw. die Länge des Kontaktbereiches wird dabei so gewählt, dass sowohl eine ausreichende statische als auch dynamische Festigkeit gewährleistet ist.To prevent premature material fatigue, it is known to carry out appropriate reinforcements in the perforated area of the blades. The contact area that the damper wire has with the damper wire hole during operation of the turbomachine is defined by the distance between the boundary planes of the reinforcements. This distance or the length of the contact area is chosen so that both sufficient static and dynamic strength is guaranteed.
Problematisch bei einer solchen Verstärkung des Lochbereiches ist jedoch die Tatsache, dass jede Verstärkung eine Störung der Strömung im Bereich des Dämpferdrahtes hervorruft und damit den Wirkungsgrad der Beschaufelung reduziert. Dabei ist die Verringerung des Wirkungsgrades um so grösser, je grösser die Verstärkung ausgebildet wird. Darstellung der ErfindungHowever, the problem with such a reinforcement of the perforated area is the fact that each reinforcement causes a disturbance in the flow in the region of the damper wire and thus reduces the efficiency of the blading. The greater the gain, the greater the reduction in efficiency. Presentation of the invention
Die Erfindung versucht alle diese Nachteile zu vermeiden Ihr liegt die Aufgabe zugrunde, den Wirkungsgrad einer Turbomaschinenschaufel zu verbessern, welche ein verstärktes Loch zur Aufnahme eines Dampfungselementes aufweistThe invention tries to avoid all these disadvantages. It is the object of the invention to improve the efficiency of a turbomachine blade which has a reinforced hole for receiving a damping element
Erfindungsgemass wird dies dadurch erreicht, dass bei einer Vorrichtung gemass dem Oberbegriff des Anspruchs 1 , die erhabenen Endflachen des zum Loch hin verstärkten Randbereiches des Schaufelblattes mit einem zur Eintrittskante des Schaufelblattes offenen, spitzen Winkel α und/oder mit einem zur Schaufelspitze offenen, spitzen Winkel ß ausgebildet sindThis is achieved according to the invention in that in a device according to the preamble of claim 1, the raised end faces of the edge region of the airfoil reinforced towards the hole with an acute angle α open to the leading edge of the airfoil and / or with an acute angle open to the blade tip are trained
Damit konvergieren die Endflachen des verstärkten Randbereiches in Richtung der Schaufelaustrittskante sowie in Richtung des Schaufelfusses, so dass die Grosse des verstärkten Randbereiches in der Hauptstromungsrichtung des Ar- beitsfluides abnimmt In der Folge entsteht eine im Bereich des Loches aerodynamisch gunstig gestaltete Turbomaschinenschaufel mit einem verbesserten WirkungsgradThe end faces of the reinforced edge region thus converge in the direction of the blade outlet edge and in the direction of the blade root, so that the size of the reinforced edge region decreases in the main flow direction of the working fluid. As a result, a turbomachine blade with an aerodynamically favorable design with improved efficiency is created
Vorzugsweise sind die beiden spitzen Winkel α und ß in einem Bereich von 5° bis 30° ausgebildet Es hat sich gezeigt, dass bei einer solchen Ausgestaltung besonders geringe Störungen der Strömung im Bereich der Dampfungselemente auftretenThe two acute angles .alpha. And .beta. Are preferably formed in a range from 5 ° to 30 °. It has been shown that with such a configuration, particularly minor disturbances in the flow occur in the area of the damping elements
Kurze Beschreibung der ZeichnungBrief description of the drawing
In der Zeichnung ist ein Ausfuhrungsbeispiel der Erfindung anhand einer Laufschaufel der Abgasturbine eines Turboladers dargestelltIn the drawing, an exemplary embodiment of the invention is shown using a rotor blade of the exhaust gas turbine of a turbocharger
Es zeigenShow it
Fig 1 eine saugseitige Seitenansicht der Laufschaufel,1 is a suction side view of the blade,
Fig 2 einen Schnitt durch die Laufschaufel, entlang der Linie ll-ll in Fig 1 ,2 shows a section through the rotor blade, along the line II-II in FIG. 1,
Fig 3 einen Schnitt durch die Laufschaufel, entlang der Linie lll-lll in Fig 1 Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt Nicht dargestellt sind beispielsweise die weiteren Bauteile der Abgasturbme, ein- schlfesslich ihres Turbinenrades3 shows a section through the rotor blade, along the line III-III in FIG. 1 Only the elements essential for understanding the invention are shown. For example, the other components of the exhaust gas turbine, including its turbine wheel, are not shown
Weg zur Ausführung der ErfindungWay of carrying out the invention
Die in Fig 1 dargestellte, als Laufschaufel 1 ausgebildete Turbomaschinenschaufel besteht aus einem Schaufelfuss 2, einer Plattform 3 und einem Schaufelblatt 4 Die Plattformen benachbarter Turbmenschaufeln des nicht dargestellten Turbinenrades liegen unmittelbar aneinander an und bilden so die innere Begrenzung des Stromungskanals, welcher nach aussen von einer ebenfalls nicht dargestellten Schaufelabdeckung abgeschlossen wird Das Schaufelblatt 4 besitzt eine Eintrittskante 5, eine Austnttskante 6, eine Saugseite 7 sowie eine Druckseite 8 und weist eine Schaufelspitze 9 aufThe turbine machine blade shown in FIG. 1, designed as a rotor blade 1, consists of a blade root 2, a platform 3 and an airfoil 4. The platforms of adjacent turbine blades of the turbine wheel (not shown) lie directly against one another and thus form the inner boundary of the flow channel, which is directed outwards from one Blade cover, also not shown, is completed. The blade 4 has an entry edge 5, a discharge edge 6, a suction side 7 and a pressure side 8 and has a blade tip 9
Im Schaufelblatt 4 ist ein von der Saugseite 7 zur Druckseite 8 durchgehendes Loch 10 zur Aufnahme eines nicht dargestellten Dampferdrahtes angeordnet, welcher die im Betrieb auftretenden Schaufelschwingungeπ reduziert Das Schaufelblatt ist zudem mit einem zum Loch 10 hin verstärkten Randbereich 11 ausgebildet, wobei der Randbereich 11 sowohl auf der Saugseite 7 als auch auf der Druckseite 11 eine gegenüber dem Schaufelblatt 4 erhabene Endflache 12, 13 besitzt Die Endflachen 12, 13 sind mit einem zur Eintrittskante 5 des Schaufelblattes 4 offenen, spitzen Winkel ex von etwa 10° und mit einem zur Schaufelspitze 9 offenen, spitzen Winkel ß von etwa 20°ausgebιldet (Fig 2, Fig 3)In the airfoil 4 there is a through hole 10 from the suction side 7 to the pressure side 8 for receiving a steam wire, not shown, which reduces the blade vibration occurring during operation. The airfoil is also formed with an edge region 11 reinforced towards the hole 10, the edge region 11 both on the suction side 7 and on the pressure side 11 has an end surface 12, 13 which is raised in relation to the airfoil 4. The end surfaces 12, 13 are at an acute angle ex of approximately 10 ° open to the leading edge 5 of the airfoil 4 and with one to the airfoil tip 9 open, acute angle β of approximately 20 ° (FIG. 2, FIG. 3)
Somit konvergieren beide Endflachen 12, 13 des verstärkten Randbereiches 11 in Richtung der Austnttskante 6 des Schaufelblattes 4 sowie in Richtung des Schau- felfusses 2 dergestalt, dass die Verstärkung des austrittseitigen und des schaufel- fussseitigen Teils des Randbereiches 11 deutlich geringer ausgebildet ist als die Verstärkung des emtrittseitigen und des schaufelspitzenseitigen Teils des Randbereiches 11 Diese Ausbildung des Schaufelblattes 4 im Bereich des Loches 10 hat eine verbesserte Strömungsführung beim Betrieb des Turboladers bzw. der Abgasturbine zur Folge. Insbesondere erfährt das in einer Hauptströmungsrichtung 14 am Schaufelblatt 4 entlangströmende Arbeitsmedium infolge der, wie oben beschrieben, spitzwinklig zueinander angeordneten Endflächen 12, 13 eine deutlich geringere Störung als dies bei den Lösungen des Standes der Technik der Fall ist. Aufgrund der verbesserten Strömungsführung im Bereich des Turbinenrades kann ein höherer Wirkungsgrad des Turboladers und damit letztlich auch der mit diesem verbundenen Brennkraftmaschine erzielt werden.Thus, both end faces 12, 13 of the reinforced edge region 11 converge in the direction of the discharge edge 6 of the airfoil 4 and in the direction of the blade root 2 in such a way that the reinforcement of the outlet-side and the blade foot-side part of the edge region 11 is significantly less than the reinforcement the part of the edge region 11 on the entrance side and the blade tip side This formation of the airfoil 4 in the region of the hole 10 results in improved flow control during operation of the turbocharger or the exhaust gas turbine. In particular, the working medium flowing along the airfoil 4 in a main flow direction 14 experiences, as a result of the end faces 12, 13 arranged at an acute angle to one another as described above, a significantly lower disturbance than is the case with the solutions of the prior art. Due to the improved flow guidance in the area of the turbine wheel, a higher efficiency of the turbocharger and thus ultimately also of the internal combustion engine connected to it can be achieved.
Je nach Ausbildung des Schaufelblattes 4 und entsprechend den Einsatzbedingungen des Turboladers hat es sich gezeigt, dass die Winkel α und ß zwischen den Endflächen 12, 13 des verstärkten Randbereiches 11 vorteilhaft jeweils in einem Bereich von 5° bis 30° ausgebildet sind.Depending on the design of the airfoil 4 and on the conditions of use of the turbocharger, it has been shown that the angles α and β between the end faces 12, 13 of the reinforced edge region 11 are each advantageously in a range from 5 ° to 30 °.
Natürlich können die Endflächen 12, 13 auch nur einen der beiden spitzen Winkel α, ß aufweisen (nicht dargestellt), was zwar die Fertigung vereinfacht, aber einen gewissen Wirkungsgradverzicht darstellt.Of course, the end surfaces 12, 13 can also have only one of the two acute angles α, β (not shown), which simplifies production but represents a certain loss in efficiency.
Selbstverständlich kann eine solchermassen ausgebildete Verstärkung des Randbereiches des den Dämpferdraht aufnehmenden Loches für alle Arten von Dämpfungselementen verwendet werden, wie beispielsweise auch bei Bindedrähten, Bolzen usw. und auch bei sogenannten Zick-Zack-Bindungen. Of course, such a reinforcement of the edge region of the hole receiving the damper wire can be used for all types of damping elements, such as, for example, also in the case of binding wires, bolts, etc. and also in the case of so-called zigzag bonds.
BezugszeichenlisteReference list
Turbomaschinenschaufel, LaufschaufelTurbomachine blade, rotor blade
SchaufelfussBlade root
Plattformplatform
SchaufelblattAirfoil
EintrittskanteLeading edge
AustrittskanteTrailing edge
SaugseiteSuction side
DruckseitePrinted page
SchaufelspitzeBlade tip
Lochhole
RandbereichEdge area
EndflächeEnd face
EndflächeEnd face
Hauptströmungsrichtung Main flow direction

Claims

Patentansprüche claims
1. Turbomaschinenschaufel mit Schaufelblatt, welches eine Eintrittskante (5), eine Austrittskante (6), eine Saugseite (7), eine Druckseite (8) sowie eine Schaufelspitze (9) aufweist und mit einem durchgehenden Loch (10) zur Aufnahme eines Dämpfungselementes für die Schaufelschwiπgungen ausgestattet ist, wobei das Schaufelblatt (4) mit einem zum Loch (10) hin verstärkten Randbereich (11 ) ausgebildet ist und der Randbereich (11 ) sowohl auf der Saugseite (7) als auch auf der Druckseite (8) eine erhabene Endfläche (12, 13) besitzt, dadurch gekennzeichnet, dass die Endflächen (12, 13) mit einem zur Eintrittskante (5) des Schaufelblattes (4) offenen, spitzen Winkel (α) und/oder mit einem zur Schaufelspitze (9) offenen, spitzen Winkel (ß) ausgebildet sind.1. Turbomachine blade with an airfoil, which has an inlet edge (5), an outlet edge (6), a suction side (7), a pressure side (8) and a blade tip (9) and with a through hole (10) for receiving a damping element for the blade vibrations is equipped, the blade (4) being formed with an edge region (11) reinforced towards the hole (10) and the edge region (11) both on the suction side (7) and on the pressure side (8) having a raised end face (12, 13), characterized in that the end faces (12, 13) have an acute angle (α) which is open to the leading edge (5) of the airfoil (4) and / or which is open to the blade tip (9) Angle (ß) are formed.
2. Turbomaschinenschaufel nach Anspruch 1 , dadurch gekennzeichnet, dass der Winkel α in einem Grössenbereich von 5° < α < 30° ausgebildet ist.2. Turbomachine blade according to claim 1, characterized in that the angle α is formed in a size range of 5 ° <α <30 °.
3. Turbomaschinenschaufel nach Anspruch 1 , dadurch gekennzeichnet, dass der Winkel ß in einem Grössenbereich von 5° < α < 30° ausgebildet ist. 3. Turbomachine blade according to claim 1, characterized in that the angle β is formed in a size range of 5 ° <α <30 °.
EP00908907A 1999-03-24 2000-03-23 Turbomachine blade Expired - Lifetime EP1163426B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19913265 1999-03-24
DE19913265A DE19913265A1 (en) 1999-03-24 1999-03-24 Turbomachine blade
PCT/CH2000/000171 WO2000057030A1 (en) 1999-03-24 2000-03-23 Turbomachine blade

Publications (2)

Publication Number Publication Date
EP1163426A1 true EP1163426A1 (en) 2001-12-19
EP1163426B1 EP1163426B1 (en) 2003-06-18

Family

ID=7902195

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00908907A Expired - Lifetime EP1163426B1 (en) 1999-03-24 2000-03-23 Turbomachine blade

Country Status (8)

Country Link
US (1) US6520741B1 (en)
EP (1) EP1163426B1 (en)
JP (1) JP4531268B2 (en)
KR (1) KR100718859B1 (en)
CN (1) CN1171005C (en)
DE (2) DE19913265A1 (en)
TW (1) TW440654B (en)
WO (1) WO2000057030A1 (en)

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KR101324249B1 (en) * 2011-12-06 2013-11-01 삼성테크윈 주식회사 Turbine impeller comprising a blade with squealer tip
US20140215998A1 (en) * 2012-10-26 2014-08-07 Honeywell International Inc. Gas turbine engines with improved compressor blades
WO2015085078A1 (en) * 2013-12-05 2015-06-11 United Technologies Corporation Hollow blade having internal damper
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GB201511416D0 (en) 2015-06-30 2015-08-12 Napier Turbochargers Ltd Turbomachinery rotor blade
WO2019057655A1 (en) * 2017-09-20 2019-03-28 Sulzer Turbo Services Venlo B.V. Assembly of vane units
CN107514292A (en) * 2017-09-30 2017-12-26 南京赛达机械制造有限公司 A kind of torsion fracture resistant turbine blade
CN114396315A (en) * 2021-12-27 2022-04-26 哈尔滨工程大学 Sawtooth crown turbine blade with hybrid cooling-sealing structure

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Also Published As

Publication number Publication date
KR100718859B1 (en) 2007-05-16
JP2002540335A (en) 2002-11-26
TW440654B (en) 2001-06-16
US6520741B1 (en) 2003-02-18
EP1163426B1 (en) 2003-06-18
CN1359445A (en) 2002-07-17
WO2000057030A1 (en) 2000-09-28
CN1171005C (en) 2004-10-13
KR20020004969A (en) 2002-01-16
JP4531268B2 (en) 2010-08-25
DE19913265A1 (en) 2000-09-28
DE50002590D1 (en) 2003-07-24

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