• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    This invention relates to a method for the manufacture of a gas-turbine combustion chamber which consists of individual wall sections produced by casting. To make up the combustion chamber, the wall sections are joined by laser welding. Preferably, the individual wall sections are segments of the annular or circular combustion chamber, with the casting material of the wall sections being a high-temperature nickel-base casting alloy.
    公开号:US20010003226A1
    申请号:US09/731,250
    申请日:2000-12-07
    公开日:2001-06-14
    发明作者:Karl Schreiber；Heike Floege
    申请人:Rolls Royce Deutschland Ltd and Co KG；
    IPC主号:F23R3-002
    专利说明:
    [0001] This invention relates to a method for the manufacture of a combustion chamber of a gas-turbine engine, this combustion chamber consisting of individual wall sections made by a casting process. For background art, reference is made to EP 0 753 704 A1, by way of example. [0001]
    [0002] Gas-turbine combustion chambers are normally made of forged and/or rolled rings which are subsequently machined and suitably drilled. For increased thermal strength, thermal barrier coatings are partly applied to the rings. The dome of the combustion chamber, which is subject to extremely high thermal stress, is in some designs made as a casting in a highly temperature-resistant nickel-base casting alloy. The rings and the dome of the combustion chamber are usually joined by welding, however, the thermal strength of this weld joint is inferior to that of the casting, this circumstance being due to the limited thermal strength of the weld filler material. [0002]
    [0003] The manufacturing route, i.e. the forging and subsequent machining of the ring and, if applicable, the subsequent welding of the cast dome, incurs an enormous manufacturing effort. Furthermore, the forging materials available are inferior to the precision casting materials available in terms of their thermo-mechanical strength above 100° C., as a result of which a considerable share of the air compressed in the compressor of the gas-turbine engine is to be used for the cooling of components and is thus not available for combustion. This impairs the power density, the specific fuel consumption and the pollutant-emission characteristics of the gas-turbine engine. [0003]
    [0004] The above-mentioned EP 0 753 704 A1 teaches a gas turbine whose combustion chamber and a subsequent transition piece to the downstream turbine section are each made as cylindrical castings without weld, with the combustion chamber and the transition piece being joined together by inert-gas welding. Full castability, i.e. castability in one piece, as proposed in the referenced Specification, is, however, limited to small combustion chambers for gas-turbine engines in the lower thrust range. In the thrust range above 10,000 lbs. take-off thrust, the manufacture of a combustion chamber by casting is not economical due to constraints such as the size of the combustion chamber and the dimensional and quality requirements. [0004]
    [0005] In a broad aspect, the present invention provides a method enabling larger combustion chambers of gas-turbine engines to be completely manufactured of a casting material, i.e. from wall sections made by a casting process. It is a particular object of the present invention to provide remedy to the above problematics by providing wall sections which are joined together by laser welding to make up the combustion chamber. Further advantageous objects of the present invention are cited in the subclaims. [0005]
    [0006] According to the present invention, the individual cast wall sections of a gas-turbine combustion chamber are to be joined by laser welding. In particular if the casting material is a highly temperature-resistant nickel-base casting alloy, the low energy input of the laser welding process will enable a crack-free joint to be made between the wall sections in the nickel-base casting materials, with the weld filler metal with inferior thermal strength being dispensable. Weldability free from cracking was demonstrated on the high-strength casting alloy C1023, for example. [0006]
    [0007] Accordingly, the individual wall sections of the combustion chamber can preferably be made by the precision casting process and joined, i.e. combined, by laser welding after machining, if necessary, of the joining edges, with the laser weld being also producible with the now very cost-effective diode lasers. Preferably, the individual wall sections are segments of the annular or circular combustion chamber, i.e. when viewing the combustion chamber in a cross-section vertical to the longitudinal axis of the combustion chamber, the wall sections following each other form a circle or annulus, with the sections being segments of this circle or annulus and extending in the direction of the combustion chamber longitudinal axis, preferably throughout its length. Since an annular combustion chamber is known to comprise several burners, one wall section or segment, respectively, may be allocated to one burner in the combustion chamber manufactured to the method according to the present invention. [0007]
    [0008] The method proposed by this Specification provides for reduced manufacturing costs and increased thermo-mechanical strength of the combustion chamber and, as consequence thereof, for an increased specific power density, a reduced specific fuel consumption and a reduced pollutant emission of the gas-turbine engine. [0008]
    权利要求:
    Claims (4)
    [1" id="US-20010003226-A1-CLM-00001] 1. A method for manufacturing a combustion chamber of a gas-turbine engine which comprises a plurality of individual cast wall sections, comprising:
    joining the individual wall sections by laser welding to make up the combustion chamber.
    [2" id="US-20010003226-A1-CLM-00002] 2. The method of
    claim 1 ,
    wherein the individual cast wall sections are annular/circular segments of the combustion chamber.
    [3" id="US-20010003226-A1-CLM-00003] 3. The method of
    claim 1 ,
    wherein the cast wall sections are made from a high-temperature nickel-base casting alloy.
    [4" id="US-20010003226-A1-CLM-00004] 4. The method of
    claim 2 ,
    wherein the cast wall sections are made from a high-temperature nickel-base casting alloy.
    类似技术:
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    同族专利:
    公开号 | 公开日
    DE19959292A1|2001-06-13|
    EP1106927A1|2001-06-13|
    DE50005675D1|2004-04-22|
    EP1106927B1|2004-03-17|
    US7243426B2|2007-07-17|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5430346A|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|
    US5975407A|1996-06-12|1999-11-02|Commissariat A L'energie Atomique|Method using a thick joint for joining parts in SiC-based materials by refractory brazing and refractory thick joint thus obtained|US20040158984A1|2001-08-29|2004-08-19|Volvo Aero Corporation|Method for manufacturing a stator or rotor component|
    US20140373548A1|2012-01-05|2014-12-25|Siemens Aktiengesellschaft|Combustion chamber of a combustor for a gas turbine|US4296606A|1979-10-17|1981-10-27|General Motors Corporation|Porous laminated material|
    US4708750A|1985-12-23|1987-11-24|United Technologies Corporation|Thermal treatment of wrought, nickel base superalloys in conjunction with high energy hole drilling|
    US4833295A|1988-05-17|1989-05-23|Ford Motor Company|Welding of parts separated by a gap using a laser welding beam|
    US5018661A|1988-11-25|1991-05-28|Cyb Frederick F|Heat-resistant exhaust manifold and method of preparing same|
    US5181379A|1990-11-15|1993-01-26|General Electric Company|Gas turbine engine multi-hole film cooled combustor liner and method of manufacture|
    JPH0727335A|1993-07-09|1995-01-27|Hitachi Ltd|Production of combustion chamber liner for gas turbine|
    WO1995029785A1|1994-04-29|1995-11-09|United Technologies Corporation|Fabrication of tubular wall thrust chambers for rocket engines using laser powder injection|
    DK172987B1|1994-12-13|1999-11-01|Man B & W Diesel As|Cylinder element, nickel-based alloy and application of the alloy|
    JPH08278029A|1995-02-06|1996-10-22|Toshiba Corp|Liner for combustor and manufacture thereof|
    US5964091A|1995-07-11|1999-10-12|Hitachi, Ltd.|Gas turbine combustor and gas turbine|
    JP2918829B2|1995-11-30|1999-07-12|本田技研工業株式会社|Fuel tank manufacturing method, laser welded body, and fuel tank|
    WO1999006771A1|1997-07-31|1999-02-11|Alliedsignal Inc.|Rib turbulators for combustor external cooling|
    US6016785A|1998-10-01|2000-01-25|Caterpillar Inc.|Pre-combustion chamber assembly and method|
    IT247723Y1|1999-03-19|2002-09-10|Lowara Spa|BODY STRUCTURE FOR CENTRIFUGAL PUMPS|DE102011076473A1|2011-05-25|2012-11-29|Rolls-Royce Deutschland Ltd & Co Kg|High temperature casting material segment component for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine, and method of manufacturing an annular combustion chamber|
    DE102012204777B4|2012-03-26|2014-02-06|MTU Aero Engines AG|Method for producing a cladding element and cladding element|
    法律状态:
    2001-02-08| AS| Assignment|Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, GERMANY Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SCHREIBER, KARL;FLOEGE, HEIKE;REEL/FRAME:011514/0143 Effective date: 20010111 |
    2011-01-18| FPAY| Fee payment|Year of fee payment: 4 |
    2015-02-27| REMI| Maintenance fee reminder mailed|
    2015-07-17| LAPS| Lapse for failure to pay maintenance fees|
    2015-08-17| STCH| Information on status: patent discontinuation|Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
    2015-09-08| FP| Lapsed due to failure to pay maintenance fee|Effective date: 20150717 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE19959292.6||1999-12-09||
    DE19959292A|DE19959292A1|1999-12-09|1999-12-09|Method of manufacturing a combustion chamber of a gas turbine engine|
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