EP1188500A1 - Vorrichtung und Verfahren zur Herstellung einer Schaufel für eine Turbine sowie entsprechend hergestellte Schaufel - Google Patents
Vorrichtung und Verfahren zur Herstellung einer Schaufel für eine Turbine sowie entsprechend hergestellte Schaufel Download PDFInfo
- Publication number
- EP1188500A1 EP1188500A1 EP00120035A EP00120035A EP1188500A1 EP 1188500 A1 EP1188500 A1 EP 1188500A1 EP 00120035 A EP00120035 A EP 00120035A EP 00120035 A EP00120035 A EP 00120035A EP 1188500 A1 EP1188500 A1 EP 1188500A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cores
- blade
- outer walls
- wall
- cavity
- 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
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C21/00—Flasks; Accessories therefor
- B22C21/12—Accessories
- B22C21/14—Accessories for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
- Y10T29/49339—Hollow blade
- Y10T29/49341—Hollow blade with cooling passage
Definitions
- the present invention relates to a device for production a shovel with two outer walls and at least a cavity for one located between the outer walls Turbine, with an outer shape and several cores for training the outer walls and the at least one cavity.
- the invention further relates to a method of manufacture a shovel with two outer walls and at least one between the cavity for a turbine arranged on the outer walls, an outer shape and a plurality of cores for forming the outer walls and the at least one cavity is provided become.
- Another object of the invention is a scoop for a turbine, in particular a gas turbine, with two outer walls and at least one arranged between the outer walls Cavity.
- Blades in particular blades for gas turbines, must cooled from the inside due to the high operating temperatures become.
- the blades have one or more Voids. With the previously known blades these cavities extend from one outer wall of the Shovel to the other outer wall. To train everyone A portion of a core is provided in the cavity. The single ones Sections are interconnected. The core will in a suitable receptacle for an outer mold for manufacture the blade is cast. The length of the Kerns can take on comparatively large values.
- the wall thickness of the outer walls be chosen as low as possible. By a slight Wall thickness can be a significant improvement in cooling to reach.
- the minimum intended wall thickness must be in each Case be greater than the wall thickness tolerance. Otherwise there is a risk that the core will shift during casting and / or deformed such that it is in contact with the outer shape comes and the manufactured blade has a hole having. In practice, therefore, a comparatively high one Wall thickness can be selected.
- the object of the present invention is therefore a simple one and inexpensive device as well as an inexpensive Process for producing a scoop with thin walls provide. It is another object of the invention to provide a blade for a turbine that Has outer walls with a much smaller wall thickness.
- each of the Cores has at least one section that differs from one assigned outer wall up to a central web of the blade extends without participating in the formation of the other outer wall to be.
- the method according to the invention is characterized in that that at least a portion of each core is supported in this way is that the distance between the outside of the section of a core and an inside of the outer shape independently on the distance between the outside of the section of the other core and the inside of the outer shape is so that Wall thicknesses of the two outer walls at least in the area of Sections are formed independently of one another.
- this task is carried out with a shovel initially mentioned type in that at least one Cavity divided into two channels by a central web is, the one channel between the one outer wall and the central bridge and the other channel between the central bridge and the other outer wall is arranged.
- the basic idea of the invention is based on the fact that the manufacture of the two outer walls of the blade at least in sections is done independently.
- At least one The vane cavity is divided into two channels by a central web divided up.
- One channel extends from the first Outer wall to the central bridge and the other channel from the central bridge to the second outer wall.
- Multiple cores are provided.
- a first core has one or more sections to form the channels between the first outer wall and the middle bridge.
- the other channels are through Sections of a second core formed which are separate from the first core is provided. Displacements and deformations of the first core, which is a change in the wall thickness of the an outer wall will not be on the second core transfer.
- the wall thicknesses of the two outer walls are therefore formed independently of one another at least in some areas.
- the inventive method provides for training of the channel serving portions of each core that a minimal wall thickness is guaranteed.
- projections are advantageously used, which are located on the Support the inside of the outer shape.
- the cores with projections for support on the outer shape are provided. They will then be beneficial to each other during casting supported and pressed against the inside of the outer shape.
- the support can be rigid, in particular wedge-shaped or elastic spacers.
- This procedure uses a minimal wall thickness for the outer walls reliably met. Shifts of the cores inward are avoided by the support against each other. For the manufacture of the cores, this means that only the outside facing the inside of the outer shape is highly precise must be manufactured. By supporting the two Cores together are the dimensional accuracy of the other outer sides of minor importance. Further is through the Support the cores to each other a higher stiffness than achieved in the known devices and methods. shifts or deformation of the cores during casting are therefore reduced. The tolerance range for the wall thickness the outer walls can therefore be significantly reduced, so that overall thinner outer walls can be provided.
- the cores can be on one or both ends in one receptacle the outer shape in the longitudinal direction of the blade.
- a Fixation in the longitudinal direction alone is sufficient if the support in the transverse direction by the projections on the Cores done. As a result, the position of the cores during the Manufacture of the wax tool and casting ensured.
- the outer walls are advantageous for forming several cavities connected by several ribs. This gives targeted cooling of individual areas of the blade with increased strength.
- a cavity is on an entry edge and / or an exit edge of the blade free from the center bar.
- the reason for this is that in the area an increased cooling effect is required at the leading edge is. That would be in the confluence area of the Mittelstegs Cooling effect impaired. This applies analogously to the Trailing edge.
- the wall thickness of the central web is larger than the wall thickness of the outer walls. The required The blade's strength is then from the center bar and, if necessary, the ribs. The wall thickness the outer walls can be reduced accordingly.
- Figure 1 shows a schematic longitudinal section through a Gas turbine 10 with a housing 11 and a rotor 12. On the housing 11 are guide vanes 13 and 12 rotor blades on the rotor 14 attached.
- the turbine 10 is in the direction of arrow 15 from flows through a hot medium, in particular a gas. by virtue of this flow, the rotor 12 rotates by one Axis 16 offset from the housing 11.
- the blades 13, 14 must due to the high prevailing temperature from the inside be cooled.
- FIG. 2 shows a cross section through a moving blade 14 the turbine 10.
- the guide vanes 13 are essentially constructed similarly.
- the blade 14 has two outer walls 17, 18, which are connected by three ribs 19, 20, 21.
- the ribs 19, 20, 21 are approximately perpendicular to the outer walls 17, 18.
- the outer walls 17, 18 go at both ends into an entry edge 22 or an exit edge 23 over. The flow against the blade 14 according to the direction of the arrow 15 takes place from the leading edge 22 to the trailing edge 23.
- the wall thickness D of the central web 28 is greater than the wall thickness d the outer walls.
- the central web 28 runs from the front rib 19 over the middle rib 20 to the rear Rib 21. It is approximately in the axial profile center of the rotor blade 14 arranged.
- the center bar 28 provides with the ribs 19, 20, 21 the strength required for operation the blade 14 ready.
- the outer walls 17, 18 can therefore be made thin.
- Figure 3 shows a cross section through an inventive Device 29 for making a blade 13, 14. It is an outer mold 30 is provided with two molded parts 31, 32 which according to the direction of arrow 33 apart and on each other too can be moved. Between the two molded parts 31, 32 two separate cores 34, 35 are used.
- the first core 34 has three sections 36a, 37a, 38a.
- the sections 36a, 37a serve to form the Channels 26a, 27a.
- the section 38a forms the cavity 24 in the Area of the leading edge 22.
- the second core 35 is substantially similar in sections 36b, 37b, 38b. Again, there are two sections 36b, 37b are provided for forming the channels 26b, 27b.
- the Cavity 25 in the region of the trailing edge 23 is through the Section 38b formed.
- the individual sections 36ab, 37ab, 38ab of the cores 34, 35 are interconnected.
- the sections 36ab, 37ab to form the channels 26a, 26b, 27a, 27b have projections 39 for support on an inner side 40 of the outer shape 30.
- the protrusions 39 taper themselves and are conical. You set the minimum distance between the inside 40 of the outer shape and one each assigned outside 46a, 47a, 46b, 47b of the sections 36a, 36b, 37a, 37b ready. This distance corresponds essentially the wall thickness d of the outer walls 17, 18. Die Wall thickness D of the central web 28 is determined by the distance between sections 36a, 37a and sections 36b, 37b established.
- FIGs 4 and 5 show the storage of the cores 34, 35 in of the device 29.
- Each of the cores 34, 35 points to both Ends projections 41, 42 for attachment in a dashed line Shown 43 of the device according to the invention 29 on.
- the two cores 34, 35 are spacers 44, 45 supported against each other.
- the protrusions 39 will hereby pressed against the inside 40 of the outer mold 30.
- the use of rigid spacers 44 and in Figure 5 the use of elastic, especially springy trained spacer 45 shown.
- the minimum Wall thickness d of the outer walls 17, 18 ensured that the cores 34, 35 with the projections 39 on the inside Support 40. Because of the taper of the protrusions 39 there is only a punctiform opening in the outer walls 17, 18 of the finished blade 13, 14. A shift the cores 34, 35 are moved towards each other by the spacers 44, 45 prevented. This ensures that the desired Wall thickness d of the outer walls 17, 18 reliably maintained becomes. The tolerances of the wall thickness that have occurred so far d can be reduced significantly. The wall thickness d can therefore be constructively compared to the known blades 13, 14 and devices 29 reduced become.
- Another advantage is that the wall thickness d of the outer walls 17, 18 no longer depend on each other. A shift or deformation of the core 34 does not result in a change the wall thickness d of the outer wall 18. Also a shift or deformation of the core 35 does not result in a change the wall thickness d of the outer wall 17.
- Figure 6 shows schematically a plan view of Figure 5.
- Die individual sections 36a, 36b, 37a, 37b, 38a, 38b of the cores 34, 35 are rigidly connected to one another as shown.
- the Cores 34, 35 are connected to one another via the elastic spacers 45 supported and are pressed against the inside 40. If several spacers 45 are distributed over the whole Length of cores 34, 35 can be used, shifts and deformations during casting be reduced.
- the desired ones are first of all Cores 34, 35 in a suitable, not shown Mold preformed and then fired. You will afterwards inserted into the outer mold 30 provided. The tabs 39 of sections 36a, 36b, 37a, 37b of the two cores 34, 35 become to rest on the inside 40 of the outer shape 30 brought. For this purpose, either rigid or elastic Spacers 44, 45 between the two cores 34, 35 introduced. Then the two cores 34, 35 in the Recordings 43 fixed.
- a suitable material for example Poured in wax. After the wax solidifies the outer shape is removed and the wax body with a Provide protective layer.
- This protective layer can, as well the cores 34, 35 consist of a ceramic material.
- the wax tool provided with the protective layer is again burned. Then in the space between the Protective layer and the cores 34, 35 the pourable material introduced for the blade 13, 14. After freezing this The protective layer and the cores 34, 35 become material removed in a suitable manner, for example with an acid or lye rinsed out.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
- Casting Devices For Molds (AREA)
Abstract
Description
- Figur 1
- einen schematischen Längsschnitt durch eine Gasturbine;
- Figur 2
- einen Querschnitt durch eine Laufschaufel der Turbine;
- Figur 3
- einen Querschnitt durch die erfindungsgemäß vorgesehene Vorrichtung zur Herstellung der Schaufel;
- Figur 4
- eine schematische Seitenansicht der Lagerung der Kerne in der erfindungsgemäßen Vorrichtung;
- Figur 5
- eine Ansicht ähnlich Figur 4 in weiterer Ausgestaltung; und
- Figur 6
- eine Draufsicht auf Figur 5.
Claims (13)
- Vorrichtung zur Herstellung einer Schaufel (13; 14) mit zwei Außenwänden (17, 18) und mindestens einem zwischen den Außenwänden (17, 18) angeordneten Hohlraum (24; 25; 26; 27) für eine Turbine (10), insbesondere einer Schaufel nach einem der Ansprüche 10 bis 13, mit einer Außenform (30) und mehreren Kernen (34, 35) zur Ausbildung der Außenwände (17, 18) und des mindestens eines Hohlraums (24; 25; 26; 27), dadurch gekennzeichnet, dass jeder der Kerne (34, 35) mindestens einen Abschnitt (36a; 36b; 37a; 37b) aufweist, der sich von einer zugeordneten Außenwand (17; 18) bis zu einem Mittelsteg (28) der Schaufel (13; 14) erstreckt, ohne an der Ausbildung der anderen Außenwand (18; 17) beteiligt zu sein.
- Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Kerne (34, 35) zur Abstützung an der Außenform (30) mit Vorsprüngen (39) versehen sind.
- Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, dass die Vorsprünge (39) sich ausgehend von den Kernen (34, 35) verjüngen, insbesondere konisch ausgebildet sind.
- Vorrichtung nach Anspruch 2 oder 3, dadurch gekennzeichnet, dass die Kerne (34, 35) mittels starrer, insbesondere keilförmiger, oder elastischer Abstandshalter (44; 45) aneinander abgestützt sind.
- Vorrichtung nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Kerne (34, 35) an einem oder beiden Enden in einer Aufnahme (43) der Außenform (30) in Längsrichtung der Schaufel (13; 14) fixiert sind.
- Verfahren zur Herstellung einer Schaufel (13; 14) mit zwei Außenwänden (17, 18) und mindestens einem zwischen den Außenwänden (17, 18) angeordneten Hohlraum (24; 25; 26; 27) für eine Turbine (10), insbesondere einer Schaufel nach einem der Ansprüche 10 bis 13, wobei eine Außenform (30) und mehrere Kerne (34, 35) zur Ausbildung der Außenwände (17, 18) und des mindestens eines Hohlraums (24; 25; 26; 27) bereitgestellt werden, dadurch gekennzeichnet, dass mindestens ein Abschnitt (36a; 36b; 37a; 37b) jedes Kerns (34, 35) derart abgestützt wird, dass der Abstand zwischen der Außenseite (46a; 46b) des Abschnitts (36a; 36b) des einen Kerns (34) und der Innenseite (40) der Außenform (30) unabhängig von dem Abstand zwischen der Außenseite (47a; 47b) des Abschnitts (37a; 37b) des anderen Kerns (35) und der Innenseite (40) der Außenform (30) ist, so dass Wandstärken (d) der beiden Außenwände (17, 18) zumindest im Bereich der Abschnitte (36a; 36b; 37a; 37b) unabhängig voneinander ausgebildet werden.
- Verfahren nach Anspruch 6, dadurch gekennzeichnet, dass die beiden Kerne (34, 35)über Vorsprünge (39) an der Innenseite (40) der Außenform (30) abgestützt werden, um eine minimale Wandstärke (d) der Außenwände (17, 18) sicherzustellen.
- Verfahren nach Anspruch 6 oder 7, dadurch gekennzeichnet, dass die beiden Kerne (34, 35) aneinander abgestützt und gegen die Innenseite (40) der Außenform (30) gedrückt werden.
- Verfahren nach Anspruch 8, dadurch gekennzeichnet, dass die beiden Kerne (34, 35) mittels starrer oder elastischer Abstandshalter (44; 45) aneinander abgestützt werden.
- Schaufel für eine Turbine (10), insbesondere eine Gasturbine, mit zwei Außenwänden (17, 18) und mindestens einem zwischen den Außenwänden (17, 18) angeordneten Hohlraum (24; 25; 26; 27), dadurch gekennzeichnet, dass mindestens ein Hohlraum (25; 27) durch einen Mittelsteg (28) in zwei Kanäle (26a, 26b; 27a, 27b) aufgeteilt ist, wobei der eine Kanal (26a; 27a) zwischen der einen Außenwand (17) und dem Mittelsteg (28) und der andere Kanal (26b; 27b) zwischen dem Mittelsteg (28) und der anderen Außenwand (18) angeordnet ist.
- Schaufel nach Anspruch 10, dadurch gekennzeichnet, dass die Außenwände (17, 18) zur Bildung mehrerer Hohlräume (24, 25, 26, 27) über mehrere Rippen (19, 20, 21) miteinander verbunden sind.
- Schaufel nach Anspruch 11, dadurch gekennzeichnet, dass ein Hohlraum (24; 25) an einer Eintrittskante (22) und/oder einer Austrittskante (23) der Schaufel (13; 14) frei von dem Mittelsteg (28) ist.
- Schaufel nach einem der Ansprüche 10 bis 12, dadurch gekennzeichnet, dass die Wandstärke (D) des Mittelstegs (28) größer ist als die Wandstärke (d) der Außenwände (17, 18).
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00120035A EP1188500B1 (de) | 2000-09-14 | 2000-09-14 | Vorrichtung und Verfahren zur Herstellung einer Schaufel für eine Turbine sowie entsprechend hergestellte Schaufel |
DE50013334T DE50013334D1 (de) | 2000-09-14 | 2000-09-14 | Vorrichtung und Verfahren zur Herstellung einer Schaufel für eine Turbine sowie entsprechend hergestellte Schaufel |
US10/239,792 US6805535B2 (en) | 2000-09-14 | 2001-09-13 | Device and method for producing a blade for a turbine and blade produced according to this method |
PCT/EP2001/010600 WO2002022291A1 (de) | 2000-09-14 | 2001-09-13 | Vorrichtung und verfahren zur herstellung einer schaufel für eine turbine sowie entsprechend hergestellte schaufel |
CNB018027393A CN1213823C (zh) | 2000-09-14 | 2001-09-13 | 制造涡轮叶片的方法和装置 |
JP2002526531A JP4350372B2 (ja) | 2000-09-14 | 2001-09-13 | タービン翼とその製造方法および製造装置 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00120035A EP1188500B1 (de) | 2000-09-14 | 2000-09-14 | Vorrichtung und Verfahren zur Herstellung einer Schaufel für eine Turbine sowie entsprechend hergestellte Schaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1188500A1 true EP1188500A1 (de) | 2002-03-20 |
EP1188500B1 EP1188500B1 (de) | 2006-08-16 |
Family
ID=8169834
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00120035A Expired - Lifetime EP1188500B1 (de) | 2000-09-14 | 2000-09-14 | Vorrichtung und Verfahren zur Herstellung einer Schaufel für eine Turbine sowie entsprechend hergestellte Schaufel |
Country Status (6)
Country | Link |
---|---|
US (1) | US6805535B2 (de) |
EP (1) | EP1188500B1 (de) |
JP (1) | JP4350372B2 (de) |
CN (1) | CN1213823C (de) |
DE (1) | DE50013334D1 (de) |
WO (1) | WO2002022291A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2874186A1 (fr) * | 2004-08-12 | 2006-02-17 | Snecma Moteurs Sa | Procede de fabrication par moulage a cire perdue de pieces comportant au moins une cavite. |
Families Citing this family (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2852999B1 (fr) * | 2003-03-28 | 2007-03-23 | Snecma Moteurs | Aube allegee de turbomachine et son procede de fabrication |
US20050000674A1 (en) * | 2003-07-01 | 2005-01-06 | Beddard Thomas Bradley | Perimeter-cooled stage 1 bucket core stabilizing device and related method |
GB0418906D0 (en) * | 2004-08-25 | 2004-09-29 | Rolls Royce Plc | Internally cooled aerofoils |
US7481623B1 (en) * | 2006-08-11 | 2009-01-27 | Florida Turbine Technologies, Inc. | Compartment cooled turbine blade |
US8087447B2 (en) * | 2006-10-30 | 2012-01-03 | United Technologies Corporation | Method for checking wall thickness of hollow core airfoil |
US7487819B2 (en) * | 2006-12-11 | 2009-02-10 | General Electric Company | Disposable thin wall core die, methods of manufacture thereof and articles manufactured therefrom |
US7762774B2 (en) * | 2006-12-15 | 2010-07-27 | Siemens Energy, Inc. | Cooling arrangement for a tapered turbine blade |
US8277193B1 (en) * | 2007-01-19 | 2012-10-02 | Florida Turbine Technologies, Inc. | Thin walled turbine blade and process for making the blade |
US8506256B1 (en) * | 2007-01-19 | 2013-08-13 | Florida Turbine Technologies, Inc. | Thin walled turbine blade and process for making the blade |
US8066052B2 (en) * | 2007-06-07 | 2011-11-29 | United Technologies Corporation | Cooled wall thickness control |
FR2933884B1 (fr) * | 2008-07-16 | 2012-07-27 | Snecma | Procede de fabrication d'une piece d'aubage. |
GB0901129D0 (en) * | 2009-01-26 | 2009-03-11 | Rolls Royce Plc | Rotor blade |
US8013569B2 (en) * | 2009-03-06 | 2011-09-06 | Sustainable Structures LLC | Renewable energy vehicle charging station |
US8453327B2 (en) * | 2010-02-05 | 2013-06-04 | Siemens Energy, Inc. | Sprayed skin turbine component |
US11000899B2 (en) * | 2012-01-29 | 2021-05-11 | Raytheon Technologies Corporation | Hollow airfoil construction utilizing functionally graded materials |
US8408446B1 (en) | 2012-02-13 | 2013-04-02 | Honeywell International Inc. | Methods and tooling assemblies for the manufacture of metallurgically-consolidated turbine engine components |
US9033670B2 (en) | 2012-04-11 | 2015-05-19 | Honeywell International Inc. | Axially-split radial turbines and methods for the manufacture thereof |
US9115586B2 (en) | 2012-04-19 | 2015-08-25 | Honeywell International Inc. | Axially-split radial turbine |
EP2844839A1 (de) | 2012-04-23 | 2015-03-11 | General Electric Company | Turbinenschaufel mit lokaler wanddickensteuerung |
EP2706195A1 (de) * | 2012-09-05 | 2014-03-12 | Siemens Aktiengesellschaft | Kühleinsatz mit einer Trennwand zur Prallkühlung einer Leitschaufel |
US9476305B2 (en) | 2013-05-13 | 2016-10-25 | Honeywell International Inc. | Impingement-cooled turbine rotor |
CN105873694B (zh) * | 2013-08-23 | 2018-05-15 | 西门子能源公司 | 带有高分解度区域的涡轮机部件铸造芯 |
CN104015247B (zh) * | 2014-05-30 | 2016-07-06 | 西安交通大学 | 整体式空心涡轮叶片陶瓷铸型型芯烧结蠕变控制的方法 |
CN106794514A (zh) * | 2014-10-15 | 2017-05-31 | 西门子公司 | 用于形成可用于燃气涡轮发动机中的部件的利用陶瓷铸模的压铸系统 |
FR3030333B1 (fr) * | 2014-12-17 | 2017-01-20 | Snecma | Procede de fabrication d'une aube de turbomachine comportant un sommet pourvu d'une baignoire de type complexe |
US10052683B2 (en) * | 2015-12-21 | 2018-08-21 | General Electric Company | Center plenum support for a multiwall turbine airfoil casting |
US10286450B2 (en) * | 2016-04-27 | 2019-05-14 | General Electric Company | Method and assembly for forming components using a jacketed core |
US20180161866A1 (en) | 2016-12-13 | 2018-06-14 | General Electric Company | Multi-piece integrated core-shell structure for making cast component |
US11813669B2 (en) | 2016-12-13 | 2023-11-14 | General Electric Company | Method for making an integrated core-shell structure |
US11002138B2 (en) * | 2017-12-13 | 2021-05-11 | Solar Turbines Incorporated | Turbine blade cooling system with lower turning vane bank |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB628522A (en) * | 1946-07-26 | 1949-08-30 | Philippe Robert | Device for ensuring the fixity of a core in a mould |
EP0585183A1 (de) * | 1992-08-10 | 1994-03-02 | Howmet Corporation | Präzisionsgiessen unter Verwendung von Kern mit integrierter Wanddickenkontrollvorrichtung |
WO1999059748A1 (de) | 1998-05-14 | 1999-11-25 | Siemens Aktiengesellschaft | Verfahren und vorrichtung zur herstellung eines metallischen hohlkörpers |
EP1027943A1 (de) * | 1999-02-11 | 2000-08-16 | ABB Alstom Power (Schweiz) AG | Hohlgegossenes Bauteil und Verfahren zu dessen Herstellung |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5813835A (en) * | 1991-08-19 | 1998-09-29 | The United States Of America As Represented By The Secretary Of The Air Force | Air-cooled turbine blade |
-
2000
- 2000-09-14 EP EP00120035A patent/EP1188500B1/de not_active Expired - Lifetime
- 2000-09-14 DE DE50013334T patent/DE50013334D1/de not_active Expired - Lifetime
-
2001
- 2001-09-13 JP JP2002526531A patent/JP4350372B2/ja not_active Expired - Fee Related
- 2001-09-13 WO PCT/EP2001/010600 patent/WO2002022291A1/de active Application Filing
- 2001-09-13 US US10/239,792 patent/US6805535B2/en not_active Expired - Lifetime
- 2001-09-13 CN CNB018027393A patent/CN1213823C/zh not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB628522A (en) * | 1946-07-26 | 1949-08-30 | Philippe Robert | Device for ensuring the fixity of a core in a mould |
EP0585183A1 (de) * | 1992-08-10 | 1994-03-02 | Howmet Corporation | Präzisionsgiessen unter Verwendung von Kern mit integrierter Wanddickenkontrollvorrichtung |
WO1999059748A1 (de) | 1998-05-14 | 1999-11-25 | Siemens Aktiengesellschaft | Verfahren und vorrichtung zur herstellung eines metallischen hohlkörpers |
EP1027943A1 (de) * | 1999-02-11 | 2000-08-16 | ABB Alstom Power (Schweiz) AG | Hohlgegossenes Bauteil und Verfahren zu dessen Herstellung |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2874186A1 (fr) * | 2004-08-12 | 2006-02-17 | Snecma Moteurs Sa | Procede de fabrication par moulage a cire perdue de pieces comportant au moins une cavite. |
US7275585B1 (en) | 2004-08-12 | 2007-10-02 | Snecma | Process for the manufacture by lost wax moulding of parts that include at least one cavity |
GB2417922B (en) * | 2004-08-12 | 2009-11-18 | Snecma | A process for the manufacture by lost wax moulding of parts that include at least one cavity |
Also Published As
Publication number | Publication date |
---|---|
CN1392809A (zh) | 2003-01-22 |
US6805535B2 (en) | 2004-10-19 |
JP2004508201A (ja) | 2004-03-18 |
DE50013334D1 (de) | 2006-09-28 |
WO2002022291A1 (de) | 2002-03-21 |
EP1188500B1 (de) | 2006-08-16 |
JP4350372B2 (ja) | 2009-10-21 |
CN1213823C (zh) | 2005-08-10 |
US20030047298A1 (en) | 2003-03-13 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1188500A1 (de) | Vorrichtung und Verfahren zur Herstellung einer Schaufel für eine Turbine sowie entsprechend hergestellte Schaufel | |
DE3211139C1 (de) | Axialturbinenschaufel,insbesondere Axialturbinenlaufschaufel fuer Gasturbinentriebwerke | |
EP0974414B1 (de) | Giessform und Giessverfahren zur Herstellung eines Motorblocks | |
DE2932940C3 (de) | Luftgekühlte Hohlschaufel für Gasturbinen | |
EP1098725B1 (de) | Verfahren und vorrichtung zur herstellung eines metallischen hohlkörpers | |
DE60223115T2 (de) | Kühlfluidführung bei einem Gasturbinenschaufelblatt | |
EP1247602B1 (de) | Verfahren zur Herstellung einer Turbinenschaufel | |
EP1267040A2 (de) | Gasturbinenschaufelblatt | |
EP1113145A1 (de) | Schaufel für Gasturbinen mit Drosselquerschnitt an Hinterkante | |
EP1245785B1 (de) | Verfahren zur Herstellung einer Turbinenschaufel | |
DE60033768T2 (de) | Kern zur Einstellung der Wanddicke einer Turbinenschaufel und Verfahren | |
EP1668236A1 (de) | Brennkammer mit kühleinrichtung und verfahren zur herstellung der brennkammer | |
DE10033271A1 (de) | Wassermantelkern | |
EP3023586A1 (de) | Hohlschaufelkörper, Einsteckrippe und Hohlschaufel | |
DE10129975B4 (de) | Giessform für den Kern einer Gasturbinenschaufel oder dergleichen | |
WO2010028913A1 (de) | Turbinenschaufel mit einer modularen, gestuften hinterkante | |
EP2421666A1 (de) | Giessvorrichtung zum herstellen einer turbinenlaufschaufel einer gasturbine und turbinenlaufschaufel | |
EP1216770A2 (de) | Werkzeug und Verfahren zum Giessen eines Formteils für die Herstellung einer Turbinenschaufel | |
EP1857244A1 (de) | Gekühlter Formeinsatz für Spritzwerkzeuge | |
EP1138878A2 (de) | Plattenförmiger, auskragender Bauteilabschnitt einer Gasturbine | |
DE2453090B2 (de) | Verfahren und Form zum Herstellen einer gegossenen Turbinenhohlschaufel | |
EP1245792A1 (de) | Gekühlter Mantelring für eine Turbine und Verfahren zur Herstellung eines Mantelrings | |
EP1046784B1 (de) | Kühlbares Bauteil | |
EP1518619A1 (de) | Turbinenschaufel für ein Flugzeugtriebwerk und Giessform zu deren Herstellung | |
DE102004028426B4 (de) | Einsatzkern und Verfahren zur Herstellung eines Zylinders für einen Verbrennungsmotor mit dem Einsatzkern |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): DE FR GB IT Kind code of ref document: A1 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
17P | Request for examination filed |
Effective date: 20020506 |
|
AKX | Designation fees paid |
Free format text: DE FR GB IT |
|
17Q | First examination report despatched |
Effective date: 20040223 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE FR GB IT |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REF | Corresponds to: |
Ref document number: 50013334 Country of ref document: DE Date of ref document: 20060928 Kind code of ref document: P |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20061026 |
|
ET | Fr: translation filed | ||
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20070518 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 17 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 18 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20180926 Year of fee payment: 19 Ref country code: FR Payment date: 20180924 Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20180911 Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20181119 Year of fee payment: 19 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 50013334 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20200401 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190914 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20190914 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190914 Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190930 |