• 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:
    A hollow liner (14) for fitting in the interior of a aerofoil vane (10) is crimped prior to fitting within the vane (10). Following fitting, the liner (14) is expanded so as to fit snugly within the vane (10). The technique permits the insertion of liners (14) into vanes (10) that are so configured as to preclude the insertion of conventional liners.
    公开号:US20010009108A1
    申请号:US09/759,529
    申请日:2001-01-16
    公开日:2001-07-26
    发明作者:Alec Dodd
    申请人:Rolls Royce PLC；
    IPC主号:F01D5-189
    专利说明:
    [0001] The present invention relates to the manufacture of an artefact comprising a liner which is intended to reside in spaced relationship within a hollow structure. [0001]
    [0002] More particularly, the invention relates to the manufacture of a liner which is required to reside in said spaced relationship within a hollow structure, the interior of which is so shaped as to preclude inserting the liner therein, when the liner has its operational shape. [0002]
    [0003] The invention has particular efficacy, where the liner is multi-perforated, and is intended to fit within the hollow interior of a guide vane which has opposing ends of radically differing profiles, and is utilised in a gas turbine engine. The liner is fitted for the purpose of enabling an impingement cooling airflow onto the interior surface of the guide vane during operation thereof in an associated said gas turbine engine. [0003]
    [0004] According to the present invention, a method of manufacturing and fitting a hollow liner within a hollow structure which has respective open ends of differing proportions, comprising the steps of producing said hollow liner and crimping a portion thereof so as to enable said liner to be fitted into said hollow structure, then fitting said liner into said hollow structure and subsequently stretching said liner so as to substantially obviate said crimping and form said liner to its desired final shape within said hollow structure. [0004]
    [0005] The invention will now be described, by way of example, and with reference to the accompanying drawings, in which: [0005]
    [0006] FIG. 1 is a pictorial representation of a gas turbine engine guide vane, which includes a perforated impingement cooling liner in accordance with the present invention. [0006]
    [0007] FIG. 2 is a developed view of the liner of FIG. 1, prior to perforation, and: [0007]
    [0008] FIG. 3 is a view on FIG. 2 in the direction of arrow [0008] 3.
    [0009] FIGS. [0009] 4 to 6 depict alternative crimp forms.
    [0010] FIG. 7 depicts an alternative mode of manufacturing an impingement cooling liner in accordance with the present invention. [0010]
    [0011] FIG. 8 depicts an impingement cooling liner crimped in accordance with the present invention. [0011]
    [0012] Referring to FIG. 1, a hollow guide vane [0012] 10 has a number of ribs 12 formed on its inner wall surface, which extend the full length of the vane 10, though only one rib 12 is thus shown. The ribs 12 locate a perforated liner 14 in spaced relationship with the inner wall surface of the vane 10.
    [0013] The guide vane [0013] 10 is formed in the configuration of an aerofoil. However, in view of the greater understanding of aerodynamic flows which today's designers possess, accompanied by the ever increasing demand to achieve higher engine efficiency, the overall shape of guide vanes has changed dramatically, resulting in profiles, the proportions of which change radically from one end of the vane to the other end thereof, as in guide vane 10. As is seen in FIG. 1, the relative chordal dimensions A at the end extremities of vane 10 are approximately 2:1. However, the relative width dimensions are approximately 1:2. It would thus be impossible to insert a liner 14 of corresponding shape in either end of vane 10.
    [0014] Referring now to FIG. 2, liner [0014] 14 is first produced as a developed shape of the finished article, which shape, in the present example, defines an actual or near trapezoid 16. The trapezoid 16 is then crimped a sufficient number of times, on both sides of datum line 20, (though crimps 22 are only shown on one side thereof), so as to draw each end portion thereof towards datum line 20, and thus shortens it.
    [0015] The number of crimps [0015] 22, and their proportions, as shown in FIG. 2 and FIG. 3 are merely illustrative. Their actual proportions and numbers will be dictated by the proportions of the vane 10 in which the liner 14 is to be fitted. Thus, in the present example, FIG. 2 depicts six crimps 22 extending from edge 18 to edge 24. The pitch of the crimps 22, multiplied by the number thereof, equals the dimension B (FIG. 3), which is repeated on the opposing side of datum line 20.
    [0016] After crimping, the trapezoid [0016] 16 is folded about datum line 20, to bring edges 26 and 28 together, and the resulting liner 14 inserted into the vane 10, via its wider, shorter end. Thereafter, a forming tool (not shown) is inserted in liner 14, and a force applied thereon in a direction chordally of the liner 14 and vane 10, so as to expand liner 14 by straightening the crimps 22.
    [0017] An alternative mode of reforming line [0017] 14 may be utilised, and consists of filling it with an elastomeric material, which is then pressurised and thus causes liner 14 to expand.
    [0018] The crimps [0018] 22 shown in FIG. 2 are of inverted V shape and stand proud of one side only of trapezoid 16. however, as depicted in FIG. 4, crimps 22 could be formed so as to alternately protrude from both sides thereof.
    [0019] FIG. 5 depicts another alternative, wherein the crimps [0019] 22 are corrugated in serpentine manner, and protrude from one side only. However, the serpentine corrugations could, if so desired, protrude alternately from both sides, as shown in FIG. 6.
    [0020] A further method of manufacturing liner [0020] 14, is by deforming a frusto-conical tube 30 (FIG. 7) of circular cross section into the finished desired shape, and then, as shown in FIG. 8, crimping the side walls thereof over at least a major portion of its length. The crimps 34 are tapered, being their widest at that end of the tube 30 which defines the longest chordal dimension. A sufficient number of crimps, of appropriate proportions, are formed so as to draw the long ends of the liner together, to allow insertion of the tube 30 into the smaller end of the vane 10 (FIG. 1). Stretching of the liner tube 30 can be effected as described hereinbefore, with respect to FIGS. 1 to 3.
    权利要求:
    Claims (8)
    [1" id="US-20010009108-A1-CLM-00001] 1. A method of manufacturing and fitting a hollow liner within a hollow structure which has respective open ends of differing proportions, comprising the steps of producing said hollow liner and crimping a portion thereof so as to enable said liner to be fitted into said hollow structure, fitting said liner into said hollow structure, and subsequently stretching said liner so as to substantially obviate said crimping and form said liner to its desired final shape within said hollow structure.
    [2" id="US-20010009108-A1-CLM-00002] 2. A method of manufacturing and fitting a hollow liner as claimed in
    claim 1 including the steps of producing the liner as a developed plane form, crimping the plane form to shorten it, folding the plane form to join opposing ends thereof, and then inserting the resulting liner in the hollow structure and stretching it to substantially obviate said crimps and form said liner into its final desired shape within said hollow structure.
    [3" id="US-20010009108-A1-CLM-00003] 3. A method of manufacturing and fitting a hollow liner within a hollow structure as claimed in
    claim 1 including the steps of forming a frusto-conical tube of circular cross section, each end of which has a peripheral length equal to the peripheral length of a respective end of said hollow structure, deforming said tube to the final desired shape of said liner, crimping the end thereof having the greater peripheral length, so as to effectively shorten it, inserting it in that end of the hollow structure having the smaller periphery, then stretching said liner to substantially obviate said crimps and form said liner into its final desired shape within said hollow structure.
    [4" id="US-20010009108-A1-CLM-00004] 4. A method of manufacturing and fitting a hollow liner into a hollow structure as claimed in
    claim 1 , wherein said crimps define a series of ridges.
    [5" id="US-20010009108-A1-CLM-00005] 5. A method of manufacturing and fitting a hollow liner into a hollow structure as claimed in
    claim 1 , wherein said crimps define a series of sinusoidal corrugations.
    [6" id="US-20010009108-A1-CLM-00006] 6. A method of manufacturing and fitting a hollow liner into a hollow structure as claimed in
    claim 1 wherein said crimps are formed on only one side of the material from which said liner is manufactured.
    [7" id="US-20010009108-A1-CLM-00007] 7. A method of manufacturing and fitting a hollow liner into a hollow structure as claimed in
    claim 1 wherein said crimps are formed on both sides of the material from which said liner is manufactured.
    [8" id="US-20010009108-A1-CLM-00008] 8. A method of manufacturing and fitting a hollow liner into a hollow structure as claimed in
    claim 1 , wherein said hollow structure is a gas turbine engine guide.
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    同族专利:
    公开号 | 公开日
    EP1120177B1|2007-06-13|
    DE60128842T2|2007-10-18|
    US6467167B2|2002-10-22|
    GB0001679D0|2000-03-15|
    EP1120177A2|2001-08-01|
    EP1120177A3|2003-07-23|
    DE60128842D1|2007-07-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20100215880A1|2009-02-25|2010-08-26|Avery Dennison Corporation|Method for making multi-layer print media by extrusion coating|US1930285A|1929-05-27|1933-10-10|Roy H Robinson|Built up metal tube, frame and skeletonized metal member of high strength weight, and method of forming same|
    US2366164A|1943-02-17|1945-01-02|Engineering & Res Corp|Brazing|
    US2440127A|1944-07-31|1948-04-20|Curtiss Wright Corp|Art of producing propeller blades|
    GB1605194A|1974-10-17|1983-04-07|Rolls Royce|Rotor blade for gas turbine engines|
    US4153386A|1974-12-11|1979-05-08|United Technologies Corporation|Air cooled turbine vanes|
    JPH0320332B2|1984-12-17|1991-03-19|Ashimori Ind Co Ltd||
    US5000426A|1989-08-15|1991-03-19|Edna Corporation|Exothermic cutting torch|
    US5240376A|1991-07-31|1993-08-31|Mcdonnell Douglas Corporation|SPF/DB hollow core fan blade|
    GB9121107D0|1991-10-04|1991-11-20|British Aerospace|Improvements relating to diffusion bonded/superplastically formed cellular structures|
    US5941895A|1996-09-04|1999-08-24|Hemodynamics, Inc.|Cardiovascular stent and retrieval apparatus|
    US5810053A|1996-09-17|1998-09-22|Mandich; Ivan C.|Pipe liner, a coiled liner product and methods for forming, installing and coiling the liner|
    US5516260A|1994-10-07|1996-05-14|General Electric Company|Bonded turbine airfuel with floating wall cooling insert|
    US5941446A|1997-07-10|1999-08-24|Mcdonnell Douglas Corporation|SPF/DB airfoil-shaped structure and method of fabrication thereof|GB2365932B|2000-08-18|2004-05-05|Rolls Royce Plc|Vane assembly|
    GB0425137D0|2004-11-13|2004-12-15|Rolls Royce Plc|Blade|
    US8152468B2|2009-03-13|2012-04-10|United Technologies Corporation|Divoted airfoil baffle having aimed cooling holes|
    US20170130589A1|2015-11-05|2017-05-11|General Electric Company|Article, component, and method of cooling a component|
    US11085374B2|2019-12-03|2021-08-10|General Electric Company|Impingement insert with spring element for hot gas path component|
    法律状态:
    2001-01-16| AS| Assignment|Owner name: ROLLS-ROYCE PLC, ENGLAND Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:DODD, ALEC. G;REEL/FRAME:011463/0357 Effective date: 20001213 |
    2002-10-03| STCF| Information on status: patent grant|Free format text: PATENTED CASE |
    2006-03-15| FPAY| Fee payment|Year of fee payment: 4 |
    2010-04-15| FPAY| Fee payment|Year of fee payment: 8 |
    2014-04-22| FPAY| Fee payment|Year of fee payment: 12 |
    优先权:
    申请号 | 申请日 | 专利标题
    GB0001679.0||2000-01-26||
    GB0001679||2000-01-26||
    GBGB0001679.0A|GB0001679D0|2000-01-26|2000-01-26|Method of producing a lining artefact|
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