EP1267041A2 - Gekühlte Turbinenschaufel - Google Patents
Gekühlte Turbinenschaufel Download PDFInfo
- Publication number
- EP1267041A2 EP1267041A2 EP02405389A EP02405389A EP1267041A2 EP 1267041 A2 EP1267041 A2 EP 1267041A2 EP 02405389 A EP02405389 A EP 02405389A EP 02405389 A EP02405389 A EP 02405389A EP 1267041 A2 EP1267041 A2 EP 1267041A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- edge
- cavity
- blade
- side wall
- cooling
- 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
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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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
Definitions
- This invention relates to internally cooled Blades for gas turbines and in particular on one Cooling construction for the tip area of the bucket.
- Blades for gas turbines are usually cooled, around the material of the blades from the high gas temperatures to protect and prevent its oxidation. Cooling effectively increases durability of the blades and extends their service life.
- a proven and successful cooling construction for turbine blades is internal cooling.
- a liquid or gaseous cooling fluid - in usually air drawn from the compressor of the turbine is - through channels in a cavity between the pressure side wall of the blade, the suction side Wall and a lace cap.
- the lace area includes usually the tip cap and a scraping edge, which is along the pressure side and suction side Wall extends radially away. The rubbing edge has been proportionate thin walls and is relatively far from that Cooling air is removed from inside the blade.
- the cooling channels guide from the cavity inside the blade either through the Pointed cap to a half space from the brushing edge is enclosed, or by the rubbing edge Crown of this rubbing edge.
- the liquid or gaseous Cooling fluid flows through these channels, cools the half-space and the brushing edge from the inside and - after the Exit from the outlet openings on the outer surface and finally mixes into the leakage current the gas turbine.
- a typical problem with the operation of turbines is the occasional, deliberate or accidentally rubbing the tip of the blade against the outer heat shield or against other components, which are attached to the turbine housing.
- the Rubbing the tip of the blade leads to smearing of material on the blade tip and into one Blockage or even complete blockage the outlet openings of the cooling channels on the blade tip.
- the cooling of the blade tip is then reduced or even completely interrupted and may be due to overheating to considerable damage the shovel lead.
- European patent application EP 816 636 discloses a blade for a gas turbine with a typical Scraping edge at the blade tip and cooling channels, designed for cooling the rubbing edge have been.
- the channels extend from a cavity inside the blade to the pressure side of the blade as well as through the tip cap from the brushing edge enclosed half space. If the contact edge against an outer heat shield or other component As the gas turbine rubs, material can enter the exhaust ports fall on the top cap and the channel for block the liquid or gaseous cooling fluid. About that in addition, the arrangement of the cooling channels does not provide for optimal cooling of the outermost tip of the brushing edge.
- the cooling structure cooling channels that differ from one Cavity inside the blade through the brushing edge on the suction side to the crown of the brushing edge extend on the suction side. This ensures efficient Cooling the extreme tip area. Indeed there is a high risk of rubbed material the outlet holes of the cooling channels are smeared and clogged.
- U.S. Patent 5,476,364 discloses a turbine blade without a scraping edge at the tip and with cooling channels, which extend from an inner cooling channel to Extend the pressure side of the blade tip.
- the cooling channels are at a special angle to the tip surface the shovel arranged.
- the Outlet openings of the cooling channels in particular one Cavity through a side wall parallel to the surface the shovel runs and through the side wall the outlet opening is formed. This hollowing out is to prevent the outlet opening with material is clogged by an annular shroud over the blades are rubbed off. Instead, that's supposed to rubbed material the coolant flow in one direction distract the more beneficial to the performance of the turbine is.
- This cooling structure should work provided the abraded material particles are small are. However, if the particles are larger than the cooling channel are likely to clog up.
- the aim of this invention is to provide a Blade for gas turbines with a scraping edge and a cooling structure for this scraping edge that it allows the cooling fluid to reach the extreme edge of the Touching edge can reach.
- the Cooling construction also for sufficient cooling worry after an intentional or unintentional Rub with the outer heat shield or one other turbine component has occurred and the Cooling channels due to different particles being rubbed off Size has been blocked or soiled.
- a turbine blade for a gas turbine which extends from a root to a tip and has a pressure side and a suction side, comprises a pressure-side wall, a suction-side wall and a tip cap.
- the tip of the blade includes the tip cap and a scraping edge, which extends radially from the pressure-side and suction-side wall to a tip crown on the pressure and suction side. Together with the outer surface of the tip cap, the brushing edge forms a half-space.
- the rubbing edge comprises a cavity which extends from the half space into the rubbing edge. This cavity extends into the cooling channels, which extend from the cavity within the blade to the tip crown, so that these cooling channels are divided into a first and a second part. The first part leads from the cavity to an outlet opening in the cavity, and the second part leads from the cavity to an outlet opening on the tip crown.
- the cavity in the brushing edge provides an additional exit opening so that the cooling fluid can exit in the direction of the tip area.
- the rubbing edge with the second area of the cooling channel protects the cavity and the additional outlet opening from contact with the outer heat shield or other components and from material which is rubbed off when such contact is made.
- the exit openings on the tip crown are partially or completely blocked by the abraded material, and the cooling fluid can no longer flow through the second region of the cooling channel to the tip crown in order to cool the contact edge from the inside. Instead, the cooling fluid exits through the additional outlet opening in the cavity, flows into the half-space and from there around the contact edge to the tip crown.
- the liquid or gaseous cooling fluid can flow unhindered through the first area into the cavity and from there through the second area of the cooling channel to the tip crown, cooling the contact edge from the inside by convection.
- the cooling structure according to the invention thus ensures for cooling even if the outlet opening has been smeared. In particular, this achieves Cooling fluid the outermost edge of the rubbing edge both in cases where the outlet openings are free are, as well as in the cases where the outlet openings are blocked. In addition, the Cooling structure regardless of the size of the rubbed Material particles for cooling.
- the hollow in the contact edge on both the Pressure side as well as provided on the suction side of the blade is especially for blades suitable, the outlet openings on the top crown both on the pressure side and on the suction side the scoop have.
- the hollow in the rubbing edge is only provided on the suction side.
- the outlet openings of the cooling channels the pressure side of the lace area below the lace crown arranged.
- the blocking problem is not as serious as at the outlet openings on the top crown of the Suction side, and therefore measures to protect the Outlet openings are not absolutely necessary.
- the cavity according to the invention has a first side wall which lies substantially in the plane of the outer surface of the tip cap.
- a second side wall of the cavity extends from this first side wall of the cavity to a third side wall which is substantially parallel to the crown of the rubbing edge.
- the second side wall of the cavity is either curved or straight, with sharp corners to the first and third side walls of the cavity.
- a cavity with curved or rounded side walls is most conveniently made by casting.
- a cavity with a straight sidewall and sharp corners is more conveniently made by other methods, such as electrochemical ablation methods.
- the brushing edge comprises rounded corners or sharp, for example rectangular, corners. Sharp corners on the brushing edge are advantageous with regard to the leakage current at the blade head, since the sharp corners ensure a higher flow rate.
- Figure 1 shows a perspective view of a Blade according to the invention with a brushing edge and outlet openings of the second parts of the cooling channels on the top crown of the suction side and a hollow in the brushing edge, which is the outlet openings of the first parts of the cooling channels.
- Figure 2 shows a cross section along the line II-II the tip area of a blade according to the invention with the hollow in the brushing edge and the first and second part of a cooling channel.
- FIG. 1 shows a perspective illustration of the radially outer region of a rotor blade 1 for a gas turbine according to the invention with a pressure-side wall 2, a suction-side wall 3 and a tip cap 4 at the radial end of the blade.
- a cooling fluid - usually air, which is taken from the compressor of the turbine - circulates within the cavity 5 and cools the pressure - and suction side wall from the inside by convection.
- the figure shows in particular the tip area of the blade, which includes a brushing edge 6 and protects the tip area of the blade from damage in the event of contact with the housing of the gas turbine.
- the contact edge extends radially from the pressure and suction side walls 2 and 3 to the top crown of the pressure side 7 and the top crown of the suction side 8.
- the contact edge 6 forms a half space 9 together with the tip cap 4.
- the cooling channels extend from the cavity 5 within the Scoop through the brushing edge 6 to the tip area of the scoop. The cooling fluid flows through these cooling channels and cools the contact edge by cooling from the inside. The cooling fluid then exits the channels through the outlet openings, cools the brushing edge by flowing around the crown, and finally mixes with the gas turbine leakage.
- a plurality of outlet openings 10 of cooling channels are arranged on the brushing edge and somewhat below the tip crown 7.
- the abradable edge comprises a cavity which extends from the tip cap 4 into the abradable edge 6.
- the cavity divides the cooling channels near the suction side into a first part, which extends from the cavity 5 to the outlet openings 11 ′ in the cavity, and into a second part, which extends from the cavity to the outlet openings 11 on the tip crown 8 the suction side extends.
- Figure 2 shows the cross section along the line II-II the tip area of the blade 1 with the pressure side Wall 2 and the suction side wall 3.
- the cavity 5 is through the inner surface 12 and the inner Surface 13 of the pressure or suction side Wall and the inner surface 14 of the tip cap 4 formed.
- a cooling channel 15 extends in a first part 17 from the cavity 5 through the tip cap 4 to the outlet opening 11 'and into the cavity 16.
- the second part 18 of the channel 15 extends from the cavity 16 through the rubbing edge 6 to the outlet opening 11 on the top crown 8 of the suction side.
- the cooling fluid 20 freely to the outermost edge of the rubbing edge flow and mix into the leakage current 22.
- the cooling fluid takes a path 23 from the cavity 16 in the half space 9 and around the brushing edge Lace crown 8. In both cases, an adequate Cooling of the brushing edges including the outermost Edge reached, regardless of in what extent the second part 18 of the cooling channel is blocked is.
- the cavity 16 is here with a rounded or curved side wall formed the most appropriate is made by casting. A rectangular excavation is most economical through a cutting Shape produced. Both forms are from the standpoint the coolant flow and the effectiveness of the cooling suitable.
- the brushing edge 6 has a shape with either sharp, for example, rectangular, corners or rounded Corners. Regarding the blade tip leakage current sharp corners lead to a better flow rate.
- Another cooling channel 25 extends from the cavity 5 to the pressure side of the blade 1.
- the channel 25 leads to a Outlet opening 10 on the pressure side of the Bucket and below the tip crown 7 of the pressure side is arranged.
- the cooling fluid 26 through this Outlet opening 10 flows, flows around the brushing edge 6 around, over the top crown 7 of the pressure side in the Half space 9 and from there into leakage current 22.
- the outlet openings 10 below the top crown are arranged, they are not so susceptible to one Clogging with abraded material such as the outlet openings on the top crown of the suction side and need therefore no protection.
- the cooling channels extend over the pressure side all the way up to the top crown like this along the suction side of the blade is the case.
- the brushing edge Similar to the cooling structure on the suction side, which in the figure is specified, the brushing edge also includes a cavity on the pressure side, which is the cooling channel - in the same way as on the suction side of the Bucket divided into two parts.
- cooling channels provide the pressure side lead, as shown in the figure, for sufficient cooling of the brushing edge so that a construction with a hollow on this side is not necessary.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Gemäß der Erfindung umfasst die Anstreifkante eine Aushöhlung, die sich vom Halbraum in die Anstreifkante erstreckt. Diese Aushöhlung reicht bis in die Kühlkanäle hinein, die sich vom Hohlraum innerhalb der Schaufel bis zur Spitzenkrone erstrecken, so dass diese Kühlkanäle in einen ersten und einen zweiten Teil unterteilt werden. Der erste Teil führt vom Hohlraum zu einer Austrittsöffnung in der Aushöhlung, und der zweite Teil führt von der Aushöhlung zu einer Austrittsöffnung auf der Spitzenkrone.
Sofern es nicht zu einem Reiben mit den Turbinenkomponenten kommt, kann das flüssige oder gasförmige Kühlfluid ungehindert durch den ersten Bereich in die Aushöhlung und von dort weiter durch den zweiten Bereich des Kühlkanals zu der Spitzenkrone fließen, wobei es die Anstreifkante von innen durch Konvektion kühlt.
In einer bevorzugten Ausführungsform der Erfindung ist die zweite Seitenwand der Aushöhlung entweder gekrümmt oder gerade, mit scharfen Ecken zur ersten und dritten Seitenwand der Aushöhlung. Eine Aushöhlung mit gekrümmten oder gerundeten Seitenwänden wird am zweckmäßigsten durch Guss hergestellt. Eine Aushöhlung mit einer geraden Seitenwand und scharfen Ecken wird zweckmäßiger durch andere Verfahren, wie zum Beispiel durch elektrochemische Abtragungsmethoden, hergestellt.
Scharfe Ecken an der Anstreifkante sind hinsichtlich des Leckstroms an dem Schaufelkopf vorteilhaft, da die scharfen Ecken eine höhere Durchflusszahl gewährleisten.
Die Abbildung zeigt insbesondere den Spitzenbereich der Schaufel, die eine Anstreifkante 6 umfasst und den Spitzenbereich der Schaufel vor Schäden im Falle einer Berührung mit dem Gehäuse der Gasturbine schützt. Die Anstreifkante erstreckt sich radial von der druck- und saugseitigen Wand 2 und 3 zur Spitzenkrone der Druckseite 7 beziehungsweise der Spitzenkrone der Saugseite 8. Die Anstreifkante 6 bildet zusammen mit der Spitzenkappe 4 einen Halbraum 9. Die Kühlkanäle erstrecken sich von dem Hohlraum 5 innerhalb der Schaufel durch die Anstreifkante 6 bis zum Spitzenbereich der Schaufel. Das Kühlfluid strömt durch diese Kühlkanäle und kühlt die Anstreifkante durch Kühlung von innen. Das Kühlfluid tritt dann aus den Kanälen durch die Austrittsöffnungen, kühlt die Anstreifkante, indem es um die Krone strömt, und vermischt sich schließlich mit dem Leckstrom der Gasturbine. Auf der Druckseite der Schaufel 1 sind mehrere Austrittsöffnungen 10 von Kühlkanälen auf der Anstreifkante und etwas unterhalb der Spitzenkrone 7 angeordnet. Mehrere zusätzliche Austrittsöffnungen 11 der Kühlkanäle sind auf der Spitzenkrone der Saugseite 8 angeordnet. Gemäß der Erfindung umfasst die Anstreifkante eine Aushöhlung, die sich von der Spitzenkappe 4 in die Anstreifkante 6 erstreckt. Die Aushöhlung unterteilt die Kühlkanäle in der Nähe der Saugseite in einen ersten Teil, der sich von dem Hohlraum 5 zu den Austrittsöffnungen 11' in der Aushöhlung erstreckt, und in einen zweiten Teil, der sich von der Aushöhlung zu den Austrittsöffnungen 11 auf der Spitzenkrone 8 der Saugseite erstreckt.
- 1
- Laufschaufel
- 2
- druckseitige Wand
- 3
- saugseitige Wand
- 4
- Spitzenkappe
- 5
- Hohlraum
- 6
- Anstreifkante
- 7
- Spitzenkrone auf der Druckseite
- 8
- Spitzenkrone auf der Saugseite
- 9
- Halbraum
- 10
- Austrittsöffnung des Kühlkanals auf der Druckseite
- 11
- Austrittsöffnung des Kühlkanals auf der Saugseite
- 11'
- Austrittsöffnung innerhalb der Aushöhlung an der Anstreifkante an der Saugseite
- 12
- Innere Oberfläche der druckseitigen Wand
- 13
- Innere Oberfläche der saugseitigen Wand
- 14
- Innere Oberfläche der Spitzenkappe
- 15
- Kühlkanal auf der Saugseite
- 16
- Aushöhlung in der Anstreifkante
- 17
- Erster Teil des Kühlkanals auf der Saugseite
- 18
- Zweiter Teil des Kühlkanals auf der Saugseite
- 20
- Kühlmittelstrom auf der Saugseite durch die Spitzenkrone
- 22
- Leckstrom der Gasturbine
- 23
- Kühlmittelstrom auf der Saugseite der Schaufel in den Halbraum und um die Spitzenkrone der Saugseite herum
- 25
- Kühlkanal auf der Druckseite
- 26
- Kühlmittelstrom auf der Druckseite
Claims (6)
- Schaufel (1) für eine Gasturbine, bestehend aus einer druckseitigen Wand (2) und einer saugseitigen Wand (3), einer Spitzenkappe (4), einem Hohlraum (5), der durch die innere Oberfläche (12, 13, 14) der druckseitigen Wand (2), der saugseitigen Wand (3) und der Spitzenkappe (4) gebildet wird, und einer Anstreifkante (6), der sich radial von der druckseitigen und saugseitigen Wand (2, 3) erstreckt, einem Halbraum(9), der durch die äußere Oberfläche der Spitzenkappe (4) und der Anstreifkantes(6) gebildet wird, und Kühlkanälen (15, 25), die vom Hohlraum (5) zur Anstreifkante(6) führen;
dadurch gekennzeichnet, dass die Anstreifkante(6) eine Aushöhlung aufweist, die sich vom Halbraum(9) in die Anstreifkante erstreckt, so dass die Aushöhlung (16) den Kühlkanal in einen ersten Teil und einen zweiten Teil unterteilt, wobei der erste Teil eine Austrittsöffnung in der Aushöhlung aufweist, durch ein Kühlfluid in den Halbraum(9) und um die Anstreifkante (6) fließen kann, und der zweite Teil eine Austrittsöffnung auf der Spitzenkrone der Anstreifkantes aufweist. - Schaufel (1) nach Anspruch 1,
dadurch gekennzeichnet, dass sich die Aushöhlung in der Anstreifkante (6) sowohl entlang der Druckseite als auch entlang der Saugseite der Schaufel (1) erstreckt. - Schaufel (1) nach Anspruch 1,
dadurch gekennzeichnet, dass sich die Aushöhlung (16) in der Anstreifkante (6) entlang der Saugseite der Schaufel (1) erstreckt. - Schaufel (1) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass die Aushöhlung (16) eine erste Seitenwand aufweist, die im wesentlichen in der Ebene der äußeren Oberfläche der Spitzenkappe(4) liegt, und eine zweite Seitenwand, die sich von der ersten Seitenwand zu einer dritten Seitenwand erstreckt, wobei die dritte Seitenwand im wesentlichen parallel zu der Spitzenkrone (8) der Anstreifkante verläuft. - Schaufel (1) nach Anspruch 4,
dadurch gekennzeichnet, dass die zweite Seitenwand der Aushöhlung (16) entweder gekrümmt oder gerade verläuft und scharfe Ecken zu der ersten und der dritten Seitenwand aufweist. - Schaufel (1) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass die Anstreifkante (6) gerundete Ecken oder scharfe, beispielsweise rechteckige, Ecken umfasst.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US877083 | 1997-06-17 | ||
US09/877,083 US6527514B2 (en) | 2001-06-11 | 2001-06-11 | Turbine blade with rub tolerant cooling construction |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1267041A2 true EP1267041A2 (de) | 2002-12-18 |
EP1267041A3 EP1267041A3 (de) | 2004-09-29 |
EP1267041B1 EP1267041B1 (de) | 2006-06-28 |
Family
ID=25369214
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02405389A Expired - Lifetime EP1267041B1 (de) | 2001-06-11 | 2002-05-14 | Gekühlte Turbinenschaufel |
Country Status (3)
Country | Link |
---|---|
US (1) | US6527514B2 (de) |
EP (1) | EP1267041B1 (de) |
DE (1) | DE50207362D1 (de) |
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Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4142824A (en) * | 1977-09-02 | 1979-03-06 | General Electric Company | Tip cooling for turbine blades |
EP0816636A1 (de) * | 1994-04-21 | 1998-01-07 | Mitsubishi Jukogyo Kabushiki Kaisha | Kühlung für die Blattspitzen einer Turbine |
US5927946A (en) * | 1997-09-29 | 1999-07-27 | General Electric Company | Turbine blade having recuperative trailing edge tip cooling |
DE19944923A1 (de) * | 1999-09-20 | 2001-03-22 | Asea Brown Boveri | Turbinenschaufel für den Rotor einer Gasturbine |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE794195A (fr) | 1972-01-18 | 1973-07-18 | Bbc Sulzer Turbomaschinen | Aube directrice refroidie pour des turbines a gaz |
US4236870A (en) | 1977-12-27 | 1980-12-02 | United Technologies Corporation | Turbine blade |
US4474532A (en) | 1981-12-28 | 1984-10-02 | United Technologies Corporation | Coolable airfoil for a rotary machine |
JPS62271902A (ja) | 1986-01-20 | 1987-11-26 | Hitachi Ltd | ガスタ−ビン冷却翼 |
DE3603350A1 (de) | 1986-02-04 | 1987-08-06 | Walter Prof Dipl Ph Sibbertsen | Verfahren zur kuehlung thermisch belasteter bauelemente von stroemungsmaschinen, vorrichtung zur durchfuehrung des verfahrens sowie ausbildung thermisch belasteter schaufeln |
US5140127A (en) | 1989-09-20 | 1992-08-18 | Rolls-Royce Plc | Laser barrier material |
US5476364A (en) | 1992-10-27 | 1995-12-19 | United Technologies Corporation | Tip seal and anti-contamination for turbine blades |
GB9514447D0 (en) | 1995-07-14 | 1995-09-13 | Rolls Royce Plc | Laser barrier material and method |
US6231307B1 (en) * | 1999-06-01 | 2001-05-15 | General Electric Company | Impingement cooled airfoil tip |
-
2001
- 2001-06-11 US US09/877,083 patent/US6527514B2/en not_active Expired - Lifetime
-
2002
- 2002-05-14 EP EP02405389A patent/EP1267041B1/de not_active Expired - Lifetime
- 2002-05-14 DE DE50207362T patent/DE50207362D1/de not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4142824A (en) * | 1977-09-02 | 1979-03-06 | General Electric Company | Tip cooling for turbine blades |
EP0816636A1 (de) * | 1994-04-21 | 1998-01-07 | Mitsubishi Jukogyo Kabushiki Kaisha | Kühlung für die Blattspitzen einer Turbine |
US5927946A (en) * | 1997-09-29 | 1999-07-27 | General Electric Company | Turbine blade having recuperative trailing edge tip cooling |
DE19944923A1 (de) * | 1999-09-20 | 2001-03-22 | Asea Brown Boveri | Turbinenschaufel für den Rotor einer Gasturbine |
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FR2934008A1 (fr) * | 2008-07-21 | 2010-01-22 | Turbomeca | Aube creuse de roue de turbine comportant une nervure |
WO2010010284A1 (fr) * | 2008-07-21 | 2010-01-28 | Turbomeca | Aube creuse de roue de turbine comportant une nervure, roue et turbomachine associees |
RU2503820C2 (ru) * | 2008-07-21 | 2014-01-10 | Турбомека | Полая лопатка для ротора турбины, при этом лопатка включает в себя ребро |
US8647071B2 (en) | 2008-07-21 | 2014-02-11 | Turbomeca | Hollow turbine wheel vane comprising a rib and associated wheel and turbomachine |
EP2960433A1 (de) * | 2014-05-08 | 2015-12-30 | United Technologies Corporation | Gasturbinenschaufelblatt mit gewinkelten Kühlkanälen |
US9957808B2 (en) | 2014-05-08 | 2018-05-01 | United Technologies Corporation | Airfoil leading edge film array |
CN106089315A (zh) * | 2015-04-28 | 2016-11-09 | 西门子股份公司 | 用于燃气涡轮的转子叶片 |
EP3199763A1 (de) * | 2015-12-07 | 2017-08-02 | General Electric Company | Schaufel und zugehöriges herstellungsverfahren |
US10227876B2 (en) | 2015-12-07 | 2019-03-12 | General Electric Company | Fillet optimization for turbine airfoil |
US10822957B2 (en) | 2015-12-07 | 2020-11-03 | General Electric Company | Fillet optimization for turbine airfoil |
CN108412555A (zh) * | 2018-03-15 | 2018-08-17 | 哈尔滨工业大学 | 阵列的凹腔射流改善叶顶泄漏流动及换热的涡轮动叶片 |
CN108412555B (zh) * | 2018-03-15 | 2019-06-04 | 哈尔滨工业大学 | 阵列的凹腔射流改善叶顶泄漏流动及换热的涡轮动叶片 |
Also Published As
Publication number | Publication date |
---|---|
EP1267041A3 (de) | 2004-09-29 |
DE50207362D1 (de) | 2006-08-10 |
US6527514B2 (en) | 2003-03-04 |
US20020197159A1 (en) | 2002-12-26 |
EP1267041B1 (de) | 2006-06-28 |
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