EP1106927B1 - Verfahren zum Herstellen einer Brennkammer eines Gasturbinen-Triebwerks - Google Patents
Verfahren zum Herstellen einer Brennkammer eines Gasturbinen-Triebwerks Download PDFInfo
- Publication number
- EP1106927B1 EP1106927B1 EP00121120A EP00121120A EP1106927B1 EP 1106927 B1 EP1106927 B1 EP 1106927B1 EP 00121120 A EP00121120 A EP 00121120A EP 00121120 A EP00121120 A EP 00121120A EP 1106927 B1 EP1106927 B1 EP 1106927B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- gas turbine
- turbine engine
- manufacturing
- engine combustion
- 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.)
- Expired - Lifetime
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- 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
- Y10T29/49229—Prime mover or fluid pump making
- Y10T29/49231—I.C. [internal combustion] engine making
Definitions
- the invention relates to a method for producing a combustion chamber Gas turbine engine consisting of individual wall parts made by casting consists. For technical reasons, reference is made to the EP 0 753 704 A1.
- Gas turbine combustors are usually forged and / or rolled rings which are subsequently machined and be drilled appropriately. To achieve increased thermal resilience Thermal barrier coatings are sometimes applied to the rings.
- the dome of the combustion chamber is particularly highly thermally stressed manufactured in some embodiments as a casting and exists made of a heat-resistant nickel-based cast alloy.
- the rings and the Combustion chamber domes are usually welded together connected, but has this welded connection, due to the limited thermal load capacity of the required filler metal, not the thermal resilience of the cast material.
- a gas turbine is described in EP 0 753 704 A1 mentioned above, their combustion chamber and a transition piece adjoining them to the downstream turbine section as cylindrical castings are designed without a weld seam, and in turn by inert gas welding be connected to each other.
- the individual cast wall parts of a gas turbine combustion chamber can be joined together by laser welding.
- the casting material is a highly heat-resistant nickel-based casting alloy is due to the low energy input laser welding, a crack-free connection of wall parts made of nickel-based cast materials possible, but no thermally less resilient Filler metal is required.
- the crack-free weldability was, for example the high-temperature cast alloy C1023 has been verified.
- the individual wall parts of the combustion chamber can therefore preferably be made using the precision casting process are produced and after the necessary processing of the Joining edges joined by laser welding, i.e. be connected this laser welding also with the now very inexpensive Diode laser is possible. It is preferably the individual Wall parts around segments of the annular or circular Combustion chamber, i.e. one considers the combustion chamber in a direction to the combustion chamber longitudinal axis vertical cross section, so you can see the one Circle or circular ring of wall parts lined up, each segment represent this circle or annulus, and each in the direction the combustion chamber longitudinal axis, preferably over its entire length.
- several burners are arranged in an annular chamber, in each case on a combustion chamber manufactured according to the invention a wall part or segment can be assigned to a burner.
- the proposed method results in lower manufacturing costs as well as an increased thermomechanical load capacity of the combustion chamber and resulting in an increased with respect to the gas turbine engine specific power density, a reduced specific fuel consumption, as well as a reduced pollutant emission.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Laser Beam Processing (AREA)
Description
Claims (3)
- Verfahren zum Herstellen einer Brennkammer eines Gasturbinen-Triebwerkes, die aus einzelnen durch Gießen gefertigten Wandteilen besteht,
dadurch gekennzeichnet, daß die Wandteile durch Laserschweißen miteinander verbunden und somit zur Brennkammer zusammengesetzt werden. - Verfahren nach Anspruch 1,
dadurch gekennzeichnet, daß es sich bei den einzelnen Wandteilen um Segmente der ringförmigen oder kreisförmigen Brennkammer handelt. - Verfahren nach Anspruch 1 oder 2,
dadurch gekennzeichnet, daß es sich beim Gußmaterial der Wandteile um eine hochwarmfeste Nickelbasis-Gußlegierung handelt.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19959292 | 1999-12-09 | ||
DE19959292A DE19959292A1 (de) | 1999-12-09 | 1999-12-09 | Verfahren zum Herstellen einer Brennkammer eines Gasturbinen-Triebwerks |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1106927A1 EP1106927A1 (de) | 2001-06-13 |
EP1106927B1 true EP1106927B1 (de) | 2004-03-17 |
Family
ID=7931942
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00121120A Expired - Lifetime EP1106927B1 (de) | 1999-12-09 | 2000-09-28 | Verfahren zum Herstellen einer Brennkammer eines Gasturbinen-Triebwerks |
Country Status (3)
Country | Link |
---|---|
US (1) | US7243426B2 (de) |
EP (1) | EP1106927B1 (de) |
DE (2) | DE19959292A1 (de) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SE519781C2 (sv) * | 2001-08-29 | 2003-04-08 | Volvo Aero Corp | Förfarande för framställning av en stator-eller rotorkomponent |
DE102011076473A1 (de) * | 2011-05-25 | 2012-11-29 | Rolls-Royce Deutschland Ltd & Co Kg | Segmentbauteil aus Hochtemperaturgussmaterial für eine Ringbrennkammer, Ringbrennkammer für ein Flugzeugtriebwerk, Flugzeugtriebwerk und Verfahren zur Herstellung einer Ringbrennkammer |
EP2613080A1 (de) * | 2012-01-05 | 2013-07-10 | Siemens Aktiengesellschaft | Brennkammer einer Ringbrennkammer für eine Gasturbine |
DE102012204777B4 (de) * | 2012-03-26 | 2014-02-06 | MTU Aero Engines AG | Verfahren zur Herstellung eines Verkleidungselementes sowie Verkleidungselement |
WO2024049370A1 (en) * | 2022-08-29 | 2024-03-07 | Süleyman Demi̇rel Üni̇versi̇tesi̇ İdari̇ Ve Mali̇ İşler Dai̇re Başkanliği Genel Sekreterli̇k | A compact combustion chamber mold for a circulating fluidized bed boiler and a method of obtaining a combustion chamber with this mold |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4296606A (en) * | 1979-10-17 | 1981-10-27 | General Motors Corporation | Porous laminated material |
US4708750A (en) * | 1985-12-23 | 1987-11-24 | United Technologies Corporation | Thermal treatment of wrought, nickel base superalloys in conjunction with high energy hole drilling |
US4833295A (en) * | 1988-05-17 | 1989-05-23 | Ford Motor Company | Welding of parts separated by a gap using a laser welding beam |
US5018661A (en) * | 1988-11-25 | 1991-05-28 | Cyb Frederick F | Heat-resistant exhaust manifold and method of preparing same |
US5430346A (en) * | 1989-10-13 | 1995-07-04 | Ultra Performance International, Inc. | Spark plug with a ground electrode concentrically disposed to a central electrode and having precious metal on firing surfaces |
US5181379A (en) | 1990-11-15 | 1993-01-26 | General Electric Company | Gas turbine engine multi-hole film cooled combustor liner and method of manufacture |
JPH0727335A (ja) * | 1993-07-09 | 1995-01-27 | Hitachi Ltd | ガスタービン用燃焼室ライナーの製作方法 |
EP0758283B1 (de) | 1994-04-29 | 1998-01-28 | United Technologies Corporation | Herstellung von rohrwand-raketenbrennkammern mit hilfe von laser-auftragschweissen |
DK172987B1 (da) * | 1994-12-13 | 1999-11-01 | Man B & W Diesel As | Cylinderelement, nikkelbaseret pålægningslegering og anvendelse af legeringen |
JPH08278029A (ja) * | 1995-02-06 | 1996-10-22 | Toshiba Corp | 燃焼器用ライナー及びその製造方法 |
US5964091A (en) * | 1995-07-11 | 1999-10-12 | Hitachi, Ltd. | Gas turbine combustor and gas turbine |
JP2918829B2 (ja) * | 1995-11-30 | 1999-07-12 | 本田技研工業株式会社 | 燃料タンクの製造方法、レーザ溶接体及び燃料タンク |
FR2749787B1 (fr) * | 1996-06-12 | 1998-07-24 | Commissariat Energie Atomique | Procede d'assemblage a l'aide d'un joint epais de pieces en materiaux a base de sic par brasage refractaire et joint refractaire et epais ainsi obtenu |
WO1999006771A1 (en) * | 1997-07-31 | 1999-02-11 | Alliedsignal Inc. | Rib turbulators for combustor external cooling |
US6016785A (en) * | 1998-10-01 | 2000-01-25 | Caterpillar Inc. | Pre-combustion chamber assembly and method |
IT247723Y1 (it) * | 1999-03-19 | 2002-09-10 | Lowara Spa | Struttura di corpo per pompe centrifughe |
-
1999
- 1999-12-09 DE DE19959292A patent/DE19959292A1/de not_active Withdrawn
-
2000
- 2000-09-28 DE DE50005675T patent/DE50005675D1/de not_active Expired - Lifetime
- 2000-09-28 EP EP00121120A patent/EP1106927B1/de not_active Expired - Lifetime
- 2000-12-07 US US09/731,250 patent/US7243426B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
DE50005675D1 (de) | 2004-04-22 |
EP1106927A1 (de) | 2001-06-13 |
US7243426B2 (en) | 2007-07-17 |
US20010003226A1 (en) | 2001-06-14 |
DE19959292A1 (de) | 2001-06-13 |
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