CN1550655A - 更换涡轮喷气发动机风扇外壳上的可摩擦部分的方法 - Google Patents
更换涡轮喷气发动机风扇外壳上的可摩擦部分的方法 Download PDFInfo
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Abstract
本发明提供了一种既简单又低成本的替换在涡轮喷气发动机风扇外壳上的可摩擦部分的方法。此方法效果显著,因为一个内部加热带(100)以及扇形支持件(110)被置于紧靠着可摩擦部分(80)的位置,每一个扇形支持件包括一个可膨胀的软外壳(120),可摩擦部分(80)和内部加热带(100)被完全夹在风扇外壳(60)和软外壳(120)之间,扇形支持件(110)则通过多个条带(125)固定在位,多层条带(125)通过固定点(96)固定在风扇外壳上(60)。
Description
技术领域
本发明关于涡轮喷气发动机的维修,特别是关于一种替换涡轮喷气发动机风扇外壳上的被损坏的可摩擦部分的方法。
背景技术
涡轮喷气发动机风扇外壳上的可摩擦部分通常是通过实施下述方法被替换的:
1)取下空气入口锥体和风扇级(fan stage);
2)用机械手段消除被损坏的可摩擦部分;
3)修整表面以准备涂抹粘合剂;
4)紧靠着外壳通过将复合材料粘接在一起的“真空包”工艺,粘接新的可摩擦部分,此工艺在于通过在啮合外壳的密封垫圈之间延伸的柔软真空袋或真空包而覆盖可摩擦部分,可摩擦条带和通过泵吸结构填充的柔软薄膜之间的空隙,以及整个系统都与抽吸源相连,将热空气或者电动热皮带产生的热量传递出去,目的是给予粘合剂所需的热循环。
5)冷却、取下泵吸结构,取下包、垫圈,等等;和
6)用直接安装在装配好的风扇圆盘上的特殊工具加工新的可摩擦部分。
上述工艺对于小型外壳是合适的,但是对于大型喷气发动机的外壳,这样的外壳在现在有直径为3米的,就变得冗长和困难了。放置真空包和对位于柔软薄膜与外壳之间的垫圈提供防泄漏密封都变得非常困难,因为:
-垫圈相对于柔软薄膜和外壳之间的体积来说非常长;
-在外壳上的无数固定孔需要彻底地密封,因为这些孔的作用是通过螺钉将发动机的吸音盘固定在外壳上;
-放置真空包变得危险;和
-在所述包内得到真空需要采取无数的预防措施,以及用到那些昂贵又难于实施的特殊手段。
上述工艺还存在只用相对低的压力冲压紧靠着外壳的可摩擦部分的缺陷,所述压力是大气压和在真空包内得到的相对真空的差。
此工艺存在的另一种难题是控制涂抹粘合剂的温度,因为热损失是很大的,既通过外壳材料的传导又通过周围空气的对流,对于大型外壳这样的热损失变得非常大。
要解决的第一个问题是,提出一种既简单又低成本的替换方法,替换在涡轮喷气发动机风扇外壳上的可摩擦部分,风扇位于飞机的机翼下面,在此方法中外壳的尺寸不再是障碍。
要解决的第二个问题是控制粘合聚合物的整个循环。
发明内容
本发明提供了一种替换涡流喷气发动机风扇外壳上的可摩擦部分的方法,涡轮喷气发动机有一个旋转部件,这个旋转部件本身包含使风扇级固定在其前端的轴,风扇级本身包含一个支持多个叶片的毂,
涡轮喷气发动机还包含围绕风扇级的环形风扇外壳,所述风扇外壳包含内壁,紧靠着内壁粘接同样的环形可摩擦部分,可摩擦部分以及风扇外壳的粘接表面,和粘接表面相对的可摩擦部分的表面被称作它的“密封”表面,风扇外壳有多个固定点,风扇级先前已经被取下,
本方法包含以下步骤:
a)除去已磨损的可摩擦部分;
b)准备新的可摩擦部分;
c)施加粘合剂到可摩擦部分的粘接表面和风扇外壳的粘接表面,所述粘合表面先前被清理干净;
d)紧靠着风扇外壳的内壁施加可摩擦部分;
e)放置“内部”加热带(heating belt)在紧靠着可摩擦部分的密封表面的位置,内部加热带完全覆盖可摩擦部分;
f)放置扇形支持件(holding sector)在紧靠着内部加热带的位置,每一个扇形支持件包括一个可膨胀的软外壳,可摩擦部分和内部加热带被完全夹在风扇外壳和软外壳之间,扇形支持件本身通过多个由固定点固定在风扇外壳上的皮带固定;
g)连接软外壳和一定压力下的普通空气源,和连接内部加热带和可调节的电源,压缩软外壳,采用温度循环方式和适于所用的粘结剂和风扇外壳热传导的压力条件加热粘结剂;和
h)冷却并取下扇形支持件和内部加热带。
可以理解为,通过应用扇形支持件和包在加热带上的软外壳,渐进地安装用于压缩可摩擦部分的工具是可能的,该工具用于粘接外壳和用于加热粘结剂以及要粘接的表面。表面在等同于周围温度下被粘接,不需要在此放置密封工具。依次安装同它们的软外壳固定的扇形支持件,一个接着一个。这种操作因而简单,不昂贵,并且容易实施,即使对于大型涡轮喷气发动机也解决了第一个问题。
有利地是,风扇外壳包括外壁,紧靠着和可摩擦部分并齐的外壁,放置至少一个“在外的”加热带,在外的加热带围绕风扇外壳延伸,因而包围可摩擦部分,所述在外的加热带与电源相连接并在热循环过程中被加热。
可以理解为,在外的加热带传送热量给粘合剂,以及沿外壳,例如通过外壳的外壁向内壁,传送给粘接的表面。这种加热于是对抗了任何相反方向的热损失,结果是提供了更好的对粘结剂温度和粘接在一起的表面的控制,于是解决了第二个问题。
这种方法使运转涡轮喷气发动机成为可能,当它被安装在飞机上,如在飞机的翅膀下面,并且无论外部温度条件如何。这种方法对于被拆卸后的发动机也是可清楚地应用的。
附图说明
依照详细的实施例和有关附图,可以更好地理解本发明,以及发明的优点显得更加清楚。
附图1表示双流涡轮喷气发动机基于图3中AA线的截面图。
附图2表示被粘接在一起的可摩擦部分同样基于图3中AA线的截面图。
附图3表示从图2中沿BB线方向看的,由四个扇形支持件以及它们的条带和螺钉形成的圆环。
具体实施方式
首先同时参照图1和图2。为清晰起见,涡轮喷气发动机10的前面称作14,涡轮喷气发动机10的后端称作16。涡轮喷气发动机10是双流型,并包含以轴22为轴线的旋转部件20,旋转部件20特别含有轴30和由其毂42固定在轴30前端的风扇级40,毂42支持多个叶片44,每一个叶片离毂42最远的部分称为尖端46。旋转部件20也包含固定在毂42的前端14的空气入口圆锥体50。
在它的前端14,涡轮喷气发动机10也包括围绕风扇级40并朝向前端14开口的圆形风扇外壳60。风扇外壳60是固定的,以轴22为圆心并且基本上为圆柱外形。风扇外壳60包含内壁70,紧靠着内壁粘接围绕叶片44的圆形可摩擦部分80,所述可摩擦部分同叶片44的尖端46共同作用只留下小的间隙。82和86分别指示可摩擦部分80的粘接表面和内壁70的粘接表面。84指示朝向叶片44的尖端46的可摩擦部分80的密封表面,密封表面84依次和可摩擦部分80的粘接表面82相对。
风扇外壳60还有外壁90,在外壁上一般安装凸出的圆形加强环92,此加强环92特别布置在和可摩擦部分80并齐的位置,于是在叶片44断裂时,连同叶片44一起局部地加强风扇40的外壳。在前端44,风扇外壳60也包括圆形前法兰94,围绕涡轮喷气发动机10的吊舱(没示出)固定在法兰上。风扇外壳60也包括一般由钻螺纹孔形成的凸缘组成的多个固定点96,这些固定点96在前法兰94以及外壁90上,起布置那些要固定在风扇外壳60上的元件的作用。
现在同时参考图2和图3说明修理风扇外壳60的可摩擦部分80的方法,涡轮喷气发动机可固定在飞机的机翼上,也可在支架(没示出)上水平布置。修理方法包括下列步骤:
1)取下前空气入口圆锥体50,此圆锥体50一般用螺钉安装在位于风扇级40后锥体42的前端14的圆形法兰(没示出)上。
2)取下风扇级40的后锥体,此锥体一般用螺钉安装在位于风扇40级的前端14的圆形法兰(没示出)上。
3)取下风扇叶片。
4)取下前后吸音板。
现在从风扇外壳60的前端14就可以达到可摩擦部分了。
5)去除已磨损的可摩擦部分80,或者采用手动空气压的或者电空气压的机械工具,或者直接采用安装在风扇级40上的手动砂轮。
6)准备新的可摩擦部分80的条带。
7)砂磨和清理可摩擦部分80和风扇外壳60的粘接表面86,向风扇外壳60的粘接表面86涂抹粘结剂。应当注意的是涂抹粘结剂应当在这种砂磨和清理之后不超过两三个小时内进行,因为要粘接的表面必须认真清理并且没有被氧化。
8)紧靠着风扇外壳60的内壁70的位置放置可摩擦部分80,彼此抵靠放置粘接表面82和86。在这个步骤中,使用过量的粘结剂,以及通过短锤敲打内壁70和用刮刀去除超出可摩擦部分80的粘结剂,任何气泡都被消除。在这一步中,很便利的是,通过使用粘结剂条带在紧靠着内壁70的位置固定可摩擦部分80。
9)紧靠着可摩擦部分80的密封表面84的位置,放置“内部”加热带100,内部加热带100完全覆盖可摩擦部分80。内部加热带100优选的组成是薄而柔软的、同被覆盖的可摩擦部分80一样形状的条带,所述条带带有通常分布在其表面上的电热阻元件,内部加热带100覆盖整个可摩擦部分80的周边,这样能保证被均匀加热。
为了更好地控制粘接温度,内部加热带100包括至少一个用于调节目的的内部温度计102。
10)紧靠着内部加热带100的位置,放置刚性的扇形支持件110和软外壳120,叠加由可摩擦部分80、内部加热带100和被完全夹在风扇外壳60和扇形支持件110之间的软外壳120相继组成,这里术语“完全”用来指在整个可摩擦部分80的表面上。扇形支持件110本身通过多个条带125固定在位,条带125由螺钉126在固定点96固定在风扇外壳60上。在实践中,操作人员先放置最上面的组件,然后是侧面的组件,于是在装配中,侧面的组件能紧靠着已经放进去的组件被挤压。条带125的形状变化广泛,并在风扇外壳60的固定点96处同所述外壳匹配。这种布置很适用于大型外壳,因为每一个扇形支持件110都能被放置进去并单独固定在外壳上。这些扇形支持件优选为三个,目的是减少放置步骤。当外壳为大直径时,扇形支持件可以更多,如更小和更轻以使更容易操作。一旦所有的扇形支持件110装配完,它们就在各自的端部116间形成清晰可见的圆周,这足够允许安装以及取下扇形件了。
更准确地说,每一个扇形支持件110通常为圆弧的形式,标记112,113,114和116分别用来指示凸面、与凸面112相对的凹面、侧面、和端部。每一个扇形支持件110具有紧靠着内部加热带100和可摩擦部分80压缩软外壳120的凸面112。扇形支持件110还包括沿侧面114延伸的颊板118,这些颊板118从凸面112凸出,并从侧面方向固定紧靠着凸面112布置的受限制的软外壳120。
还可更精确地说,条带125通过一系列支架、螺钉、和销125a被固定在扇形支持件110上,条带125本身由螺钉126、厚垫片126a和螺母126b固定在软外壳120上,外壳60被夹紧在厚垫片126a和螺母126b之间的固定点96。在扇形支持件110的后端16处的螺钉126被径向固定在邻接件126c上,邻接件126c压缩可摩擦部分80的后端16,粘接表面86在内壁70形成印痕,内壁70限制可摩擦部分80向前端14或者后端16的运动。膨胀的软外壳120在扇形支持件110上施加直接向前的力,这种力趋向于迫使扇形件朝向前端14。为了防止扇形支持件110被压迫,这种力相继被销125a、条带125、容纳在邻接件126c中的螺钉126、和在外壳60中形成印痕的位于粘接表面86中的可摩擦部分80吸收。
11)在与可摩擦部分80并齐的外壁90上放置至少一个“外部”加热带140,外部加热带140均围绕风扇外壳60布置,于是围绕可摩擦部分80。还在外部加热带140和外壳60的外壁90之间放置至少一个温度计。外部加热带140能通过粘接条带紧靠着外壳60固定。当圆形加强环92出现在与可摩擦部分80并齐的位置时,多个加热带140被放置在圆形环92的旁边和环之间,目的是确保整个可摩擦部分80被完全覆盖。
12)将软外壳和调节压力下的普通空气源130连接,这种空气压力源130是普通的,是为了确保所有的软外壳处于同样的压力下膨胀。内部加热带100和外部加热带140还同电源132连接。最后,连接内部和外部温度计102和142用于测量和调节温度。
13)对软外壳120施加压力和执行适合于所用的粘结剂的热循环。在这个例子中,所用的粘结剂是以商标RTV147A/147B出售的粘结剂,软外壳120在1bar的压强下膨胀,粘结剂和粘接表面82和86升温到105C和130C之间的温度范围保持两个小时。
14)冷却,给软外壳放气,断开连接并取下扇形支持件110、软外壳120、加热带100,140和温度计102,142。
15)用固定在轴30上的砂轮加工可摩擦部分80的密封表面84,随着固定在轴30上的砂轮的旋转能使密封表面84达到精确的圆度并以轴线22为圆心。
由软外壳施加在可摩擦部分上用于粘接的压力被以下吸收:
-同软外壳支持件连接的条带125;和
-将条带固定在外壳上的螺钉126。
当软外壳120被置于一定压力下时,它们出现端部与端部接触,于是紧靠着可摩擦部分80形成连续的的圆周,此可摩擦部分80被粘接。已经进行的测量表面,位于两个相邻软外壳之间的接触线相齐的位置处,由软外壳120施加在可摩擦部分80上的压力降低不超过10%,这是可以接受的。应当注意到,当软外壳受压时,颊板118使软外壳120被限定在扇形支持件110和可摩擦部分之间。
内部加热带100足够用于加热粘结剂,然而,经由外壳60到外壳60周围的空气的热损失(当室外工作时一例如,在飞机机翼下)使得调整粘接温度成为问题。这就是为什么发明人优选下面方案的原因,即根据外壳60的构造和圆形加强环92的有无和位置,围绕外壳60放置一个或者多个以外部加热带140的形式的第二个热源。于是,同时检测内部加热带100和外部加热带140的温度,使有效控制粘接剂的温度成为可能,粘接剂在内部加热带100和外部加热带140之间的空隙中。
例如,为了在正如一种以商标RTV147A出售的粘结剂要求的85C时进行粘接,用内部温度计102测量的内部加热带100的温度调节在120C,而用外部温度计142测量的外部加热带140的温度调节在90C,对每一个外壳模型有必要通过实验决定这两个温度。应当注意到,为聚合所需要的大部分热量是通过内部加热带100传递的,外部加热带140只是起次要的作用。
Claims (7)
1.一种替换涡流喷气发动机风扇外壳上的可摩擦部分的方法,涡轮喷气发动机(10)有旋转部件(20),这个旋转部件(20)本身包含使风扇级(40)固定在其前端的轴(30),风扇级本身包含支持多个叶片(44)的毂(42),
涡轮喷气发动机(10)还包含围绕风扇级(40)的环形风扇外壳(60),所述风扇外壳(60)包含内壁(70),紧靠着内壁粘接同样的环形可摩擦部分(80),可摩擦部分(80)的以及风扇外壳(60)的粘接表面(82,86),与其粘接表面(82)相对的、被称作它的“密封”表面(84)的可摩擦部分的表面,风扇外壳(60)有多个固定点(96),风扇级(40)先前已经被取下,
该方法的特征在于包含下列步骤:
a)除去已磨损的可摩擦部分(80);
b)准备新的可摩擦部分(80);
c)施加粘合剂到可摩擦部分的粘接表面(82,86)和风扇外壳(60)的粘接表面,所述粘合表面(82,86)先前已被清理干净;
d)紧靠着风扇外壳(60)的内壁(70),施加可摩擦部分(80);
e)在紧靠着可摩擦部分(80)的密封表面(84)的位置,放置“内部”加热带(100),内部加热带(100)完全覆盖可摩擦部分(80);
f)在紧靠着内部加热带(100)的位置放置扇形支持件(110),每一个扇形支持件包括一个可膨胀的软外壳(120),可摩擦部分(80)和内部加热带(100)被完全夹在风扇外壳(60)和软外壳(120)之间,扇形支持件(110)本身通过由多个固定点(96)固定在风扇外壳(60)上的条带(125)固定;
g)连接软外壳和一压力下的普通空气源(130),和连接内部加热带(100)和可调节的电源(140),压缩软外壳(120),采用温度循环方式和适于所用的粘结剂和风扇外壳(60)热传导的压力条件加热粘结剂;和
h)冷却并取下扇形支持件和内部加热带(100)。
2.如权利要求1所述的方法,其特征在于,扇形支持件的数量不少于三个。
3.如权利要求1或2所述的方法,其特征在于,粘结剂的温度通过至少一个放置在内部加热带(100)内的内部温度计(102)检测,内部温度计(102)和测量和调节温度的工具(134)连接。
4.如权利要求1至3中任何一项所述的方法,风扇外壳(60)包括外壁(90),其特征在于,在紧靠着与可摩擦部分(80)并齐的外壁(90)处,放置至少一个“外部”加热带(140),外部加热带(140)围绕风扇外壳(60)延伸,于是也围绕可摩擦部分(80),所述外部加热带(140)和电源(132)连接并在热循环过程中被加热。
5.如权利要求4所述的方法,其特征在于,在热循环过程中,粘结剂的温度也用紧靠着外部加热带(140)布置的至少一个外部温度计(142)控制,外部温度计(142)和温度测量工具(134)连接。
6.如权利要求1至5中任何一项所述的方法,其特征在于,可摩擦部分(80)的密封表面(84)随后被加工。
7.如权利要求1至6中任何一项所述的方法,其特征在于,使用固定在轴(30)上的砂轮加工可摩擦部分。
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US4460185A (en) * | 1982-08-23 | 1984-07-17 | General Electric Company | Seal including a non-metallic abradable material |
FI840433A (fi) * | 1983-02-03 | 1984-08-04 | Coopetanche S.A. | Foerfarande foer att beklaeda en tunnel invaendigt, beklaedningsinstallation med anvaendande av detta foerfarande samt tunnlar foersedda med en beklaednad enligt detta foerfarande. |
DE3316535A1 (de) * | 1983-05-06 | 1984-11-08 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Turboverdichter mit einlaufbelag |
US4712979A (en) * | 1985-11-13 | 1987-12-15 | The United States Of America As Represented By The Secretary Of The Air Force | Self-retained platform cooling plate for turbine vane |
US5307623A (en) * | 1991-05-28 | 1994-05-03 | General Electric Company | Apparatus and method for the diassembly of an ultra high bypass engine |
US5451351A (en) * | 1991-09-13 | 1995-09-19 | Composite Components, Inc. | Method for rehabilitating a pipe with a liner having an electrically conductive layer |
FR2710968B1 (fr) * | 1993-10-06 | 1995-11-03 | Snecma | Chambre de combustion à double paroi. |
FR2712037B1 (fr) * | 1993-11-03 | 1995-12-08 | Snecma | Turbomachine à compresseur dont le rotor a un étage amont amovible. |
US5655701A (en) * | 1995-07-10 | 1997-08-12 | United Technologies Corporation | Method for repairing an abradable seal |
US5735045A (en) * | 1996-01-29 | 1998-04-07 | Gasi Engine Services Corporation | Method for refurbishing a jet engine |
-
2003
- 2003-04-22 FR FR0304906A patent/FR2854198B1/fr not_active Expired - Fee Related
-
2004
- 2004-04-07 MA MA27618A patent/MA26367A1/fr unknown
- 2004-04-13 CA CA2463180A patent/CA2463180C/fr not_active Expired - Lifetime
- 2004-04-15 RS YUP-309/04A patent/RS51027B/sr unknown
- 2004-04-16 SG SG200402105A patent/SG110091A1/en unknown
- 2004-04-19 ZA ZA200402966A patent/ZA200402966B/xx unknown
- 2004-04-20 AT AT04291033T patent/ATE526488T1/de not_active IP Right Cessation
- 2004-04-20 EP EP04291033A patent/EP1471212B1/fr not_active Expired - Lifetime
- 2004-04-20 ES ES04291033T patent/ES2373656T3/es not_active Expired - Lifetime
- 2004-04-21 NO NO20041617A patent/NO20041617L/no not_active Application Discontinuation
- 2004-04-21 IL IL161548A patent/IL161548A/en not_active IP Right Cessation
- 2004-04-21 US US10/709,211 patent/US7278208B2/en active Active
- 2004-04-22 TN TNP2004000074A patent/TNSN04074A1/fr unknown
- 2004-04-22 CN CNB2004100353349A patent/CN100374706C/zh not_active Expired - Lifetime
- 2004-04-24 EG EG2004040186A patent/EG24714A/xx active
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107214469A (zh) * | 2016-03-22 | 2017-09-29 | 通用电气公司 | 用于在翼修理的燃气涡轮机原位可充胀囊 |
CN109312629A (zh) * | 2016-06-15 | 2019-02-05 | 通用电气公司 | 风扇组件、对应的涡轮风扇发动机和控制隙距的方法 |
CN109312629B (zh) * | 2016-06-15 | 2021-10-01 | 通用电气公司 | 风扇组件、对应的涡轮风扇发动机和控制隙距的方法 |
Also Published As
Publication number | Publication date |
---|---|
IL161548A (en) | 2008-11-26 |
EG24714A (en) | 2010-06-06 |
YU30904A (sh) | 2006-03-03 |
EP1471212A1 (fr) | 2004-10-27 |
NO20041617L (no) | 2004-10-25 |
FR2854198A1 (fr) | 2004-10-29 |
TNSN04074A1 (fr) | 2006-06-01 |
ES2373656T3 (es) | 2012-02-07 |
CN100374706C (zh) | 2008-03-12 |
MA26367A1 (fr) | 2004-11-01 |
EP1471212B1 (fr) | 2011-09-28 |
FR2854198B1 (fr) | 2005-06-24 |
US7278208B2 (en) | 2007-10-09 |
IL161548A0 (en) | 2004-09-27 |
ZA200402966B (en) | 2004-10-28 |
CA2463180C (fr) | 2011-06-14 |
CA2463180A1 (fr) | 2004-10-22 |
SG110091A1 (en) | 2005-04-28 |
ATE526488T1 (de) | 2011-10-15 |
RS51027B (sr) | 2010-10-31 |
US20040231155A1 (en) | 2004-11-25 |
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