WO2002022291A1 - 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
- WO2002022291A1 WO2002022291A1 PCT/EP2001/010600 EP0110600W WO0222291A1 WO 2002022291 A1 WO2002022291 A1 WO 2002022291A1 EP 0110600 W EP0110600 W EP 0110600W WO 0222291 A1 WO0222291 A1 WO 0222291A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- blade
- cores
- outer walls
- cavity
- central web
- Prior art date
Links
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 producing a blade with two outer walls and at least one cavity arranged between the outer walls for a turbine, with an outer shape and a plurality of cores for forming the outer walls and the at least one cavity.
- the invention further relates to a method for producing a blade with two outer walls and at least one cavity arranged between the outer walls for a turbine, wherein an outer shape and a plurality of cores are provided for forming the outer walls and the at least one cavity.
- Another object of the invention is a blade for a turbine, in particular a gas turbine, with two outer walls and at least one cavity arranged between the outer walls.
- Blades in particular blades for gas turbines, have to be cooled from the inside due to the high operating temperatures.
- the blades have one or more cavities. In the previously known blades, these cavities extend from one outer wall of the blade to the other outer wall. A portion of a core is provided to form each cavity. The individual sections are interconnected.
- the core is experienced in a suitable receptacle of an outer shape for producing the blade in a cast. The length of the core can take on comparatively large values. ⁇ C ⁇ J NJ ro
- DJ ⁇ ds ⁇ H ⁇ OJ ⁇ P- r + 00 ⁇ - 1 P- CL tr ⁇ r + 3 CL DJ 3 d hj 3 ⁇ 3 ⁇ hj 3 ⁇ rt 00 d H ⁇ ⁇ L CL tr tr d; CL 0 CL
- Outer walls are therefore formed independently of one another, at least in some areas.
- the method according to the invention provides for the sections of each core serving to form the channels to be supported in such a way that a minimum wall thickness is ensured.
- projections are advantageously used, which are supported on the inside of the outer shape.
- Wall thickness of the outer walls significant outside of the cores can be significantly improved. All tolerances are shifted to the area of the center bar. This does not have any disadvantages for the cooling effect since the central web is not directly exposed to the hot fluid flowing through the turbine.
- the central web is also cooled by the channels on both sides.
- the central web also provides the required strength for the blade with small wall thicknesses of the outer walls.
- the cores are provided with projections for support on the outer shape. They are then advantageously supported against one another during the casting and pressed against the inside of the outer mold.
- the support can take place by means of rigid, in particular wedge-shaped, or elastic spacers.
- a cavity on an entry edge and / or an exit edge of the blade is free of the central web.
- the reason for this is that an increased cooling effect is required in the area of the leading edge.
- the cooling effect would be impaired in the junction area of the central web. This also applies analogously to the trailing edge.
- the wall thickness of the central web is greater than the wall thickness of the outer walls. The required strength of the blade is then ensured by the central web and, if necessary, the ribs. The wall thickness of the outer walls can be reduced accordingly.
- the invention based on a
- FIG. 1 shows a schematic longitudinal section through a gas turbine
- Figure 2 shows a cross section through a blade of the
- Figure 3 shows a cross section through the device provided according to the invention for producing the
- Figure 4 is a schematic side view of the storage of the cores in the device according to the invention.
- Figure 5 is a view similar to Figure 4 in a further embodiment.
- FIG. 6 shows a top view of FIG. 5, co co f ro h- 1 P 1 ⁇ o c ⁇ o C ⁇ o C ⁇ tr S! ⁇ £ m> tr S 00 w tc d CO> i x)>tr> ⁇ P 1 DJ: CL " ⁇ tr ⁇ P- O • n ir> QQ ⁇
- the central web 28 together with the ribs 19, 20, 21 provides the strength of the rotor blade 14 required for operation.
- the outer walls 17, 18 can therefore be made thin.
- FIG. 3 shows a cross section through a device 29 according to the invention for producing a blade 13, 14.
- An outer shape 30 is provided with two shaped parts 31, 32, which can be moved apart and moved towards one another in the direction of the arrow 33.
- Two separate cores 34, 35 are inserted between the two molded parts 31, 32.
- the first core 34 has three sections 3 ⁇ a, 37a, 38a.
- the sections 3 ⁇ a, 37a serve to form the channels 26a, 27a.
- the section 38a forms the cavity 24 in the region of the leading edge 22.
- the second core 35 is formed essentially similarly with sections 36b, 37b, 38b.
- sections 36b, 37b are provided for forming the channels 26b, 27b.
- the cavity 25 in the region of the exit edge 23 is formed by the section 38b.
- the individual sections 36ab, 37ab, 38ab of the cores 34, 35 are connected to one another.
- the sections 36ab, 37ab for forming the channels 26a, 26b, 27a, 27b have projections 39 for support on an inner side 40 of the outer mold 30.
- the projections 39 taper and are conical. They provide the minimum distance between the inside 40 of the outer shape and a respectively assigned outside 46a, 47a, 46b, 47b of the sections 36a, 36b, 37a, 37b. This distance corresponds essentially to the wall thickness d of the outer walls 17, 18.
- the wall thickness D of the central web 28 is determined by the distance between the sections 36a, 37a and the sections 36b, 37b.
- outer sides 46a, 47a, 46b, 47b of the sections 36a, 37a, 36b, 37b and the outer sides 48a, 48b of the sections 38a, 38b have to be processed with high precision.
- the further surfaces of the cores 34, 35 can have comparatively high tolerances since they are not important for determining the wall thickness d of the outer walls 17, 18.
- FIGS. 4 and 5 show the mounting of the cores 34, 35 in the device 29.
- Each of the cores 34, 35 has protrusions 41, 42 at both ends for fastening in a receptacle 43 of the device 29 according to the invention shown in dashed lines.
- the two cores 34, 35 are supported on one another via spacers 44, 45.
- the projections 39 are thereby pressed against the inside 40 of the outer mold 30.
- FIG. 4 shows the use of rigid spacers 44 and FIG. 5 shows the use of elastic, in particular spring-formed spacers 45.
- the minimum wall thickness d of the outer walls 17, 18 is thus ensured in that the cores 34, 35 are supported on the inner side 40 with the projections 39. Due to the tapering of the projections 39, there is only a punctiform opening in the outer walls 17, 18 of the finished blade 13, 14. The spacers 44, 45 prevent the cores 34, 35 from moving towards one another. It is thus ensured that the desired wall thickness d of the outer walls 17, 18 is reliably maintained. The tolerances of the wall thickness d that have occurred so far can be significantly reduced. The wall thickness d can therefore be reduced constructively from the outset compared to the known blades 13, 14 and devices 29.
- Another advantage is that the wall thicknesses d of the outer walls 17, 18 no longer depend on one another. A Displacement or deformation of the core 34 does not lead to a change in the wall thickness d of the outer wall 18. A displacement or deformation of the core 35 does not lead to a change in the wall thickness d of the outer wall 17 either.
- FIG. 6 schematically shows a plan view of FIG. 5.
- the 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 supported against one another via the elastic spacers 45 and are pressed against the inside 40. If several spacers 45 are used distributed over the entire length of the cores 34, 35, displacements and deformations during the casting can be significantly reduced.
- the desired cores 34, 35 are first preformed in a suitable shape (not shown) and then fired. They are then inserted into the outer mold 30 provided. The projections 39 of the sections 36a, 36b, 37a, 37b of the two cores 34, 35 are brought into contact with the inside 40 of the outer mold 30. For 'this purpose, either rigid or elastic spacers 44, 45 inserted between the two cores 34, 35th Then the two cores 34, 35 are fixed in the receptacles 43.
- a suitable material for example wax
- This protective layer like the cores 34, 35, can consist of a ceramic material.
- the wax tool with the protective layer is fired again. Then the pourable material is in the space between the protective layer and the cores 34, 35 introduced for the blade 13, 14. After this material has solidified, the protective layer and the cores 34, 35 are removed in a suitable manner, for example rinsed out with an acid or alkali.
- the manufacturing and assembly tolerances in the manufacture and fixation of the cores 34, 35, the wax tool and the protective layer present in the known methods and devices can be significantly reduced.
- the wall thickness of the outer walls 17, 18 of the blade 13, 14 can therefore be significantly reduced. This results in an improved cooling effect.
- the required strength of the blade 13, 14 is ensured by the central web 28.
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
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
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 |
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 |
Applications Claiming Priority (2)
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 |
EP00120035.1 | 2000-09-14 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2002022291A1 true WO2002022291A1 (de) | 2002-03-21 |
Family
ID=8169834
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
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 |
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) |
Families Citing this family (31)
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 |
FR2874186B1 (fr) * | 2004-08-12 | 2008-01-25 | Snecma Moteurs Sa | Procede de fabrication par moulage a cire perdue de pieces comportant au moins une cavite. |
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 |
JP5997831B2 (ja) | 2012-04-23 | 2016-09-28 | ゼネラル・エレクトリック・カンパニイ | 局所的な壁厚さ制御を伴うタービン翼 |
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 |
JP6355839B2 (ja) * | 2014-10-15 | 2018-07-11 | シーメンス アクチエンゲゼルシヤフトSiemens Aktiengesellschaft | ガスタービンエンジンで使用可能な構成部品を形成するためのセラミック鋳型を有するダイカストシステム |
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 |
US11813669B2 (en) | 2016-12-13 | 2023-11-14 | General Electric Company | Method for making an integrated core-shell structure |
US20180161866A1 (en) | 2016-12-13 | 2018-06-14 | General Electric Company | Multi-piece integrated core-shell structure for making cast component |
US10815791B2 (en) * | 2017-12-13 | 2020-10-27 | Solar Turbines Incorporated | Turbine blade cooling system with upper 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)
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---|---|---|---|---|
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 US US10/239,792 patent/US6805535B2/en not_active Expired - Lifetime
- 2001-09-13 WO PCT/EP2001/010600 patent/WO2002022291A1/de active Application Filing
- 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 |
Also Published As
Publication number | Publication date |
---|---|
US20030047298A1 (en) | 2003-03-13 |
DE50013334D1 (de) | 2006-09-28 |
CN1213823C (zh) | 2005-08-10 |
JP2004508201A (ja) | 2004-03-18 |
JP4350372B2 (ja) | 2009-10-21 |
US6805535B2 (en) | 2004-10-19 |
EP1188500A1 (de) | 2002-03-20 |
CN1392809A (zh) | 2003-01-22 |
EP1188500B1 (de) | 2006-08-16 |
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