CN101321940B - 燃气涡轮发动机的辅助部件安装 - Google Patents
燃气涡轮发动机的辅助部件安装 Download PDFInfo
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Abstract
一种用于辅助部件的安装系统,其包括两个侧托架(42,44)和将辅助部件(32)刚性地附连到发动机外壳(22)的一个顶部托架(46)。每个侧托架(42,44)限定安装节段(50,52)、一可变形构件(SO)和安装节段之间的两个保持构件(62,64)。可变形构件(60)在风机叶片脱落事件中塑性地变形,从而缓冲辅助部件(32)经受的大部分高冲击载荷。在风机叶片脱落事件之后,保持构件(62,64)维持辅助部件(32)和发动机外壳(22)之间的附连。
Description
技术领域
本发明涉及一种安装系统,更具体地是涉及一种用于燃气涡轮发动机的辅助部件的能量缓冲安装系统。
背景技术
燃气涡轮航空发动机采用涡轮风机将周围空气吸入发动机中,发动机压缩空气并使其燃烧。涡轮风机被发动机外壳遮蔽。一般,各种辅助部件,诸如发动机油箱、变速箱、阀门、调节发动机工作的控制系统以及其它部件是安装到发动机外壳上的。可用各种安装系统将辅助部件安装到发动机外壳上。
传统安装系统一般包括多个刚性托架构件,这些构件通过一串剪切销附连到辅助部件和发动机外壳之间。这种传统的安装系统也可以具有隔离器,隔离器在额定负载和工作条件下将发动机振动载荷衰减传输到辅助部件上。
传统的安装系统可能会遇到在额定发动机工作条件下不会遇到的高强度冲击负载。例如,高冲击载荷可能是由风机叶片脱落事件引起的。当风机叶片由于受到外来物体的撞击脱离发动机的转子主体时,会发生风机叶片脱落事件。风机叶片脱落事件造成发动机转子主体不平衡,这又可能会引起向外偏斜及转子主体轴的不平衡。传统的安装系统尽管有效,但是,它们是用相对笨重且体积大的硬件制造的,以提供对抗额定发动机工作条件以及高冲击载荷的高强度和耐用性,来阻止辅助部件从发动机外壳分离。
因此,需要提供一种用于燃气涡轮发动机的辅助部件的安装系统,要求该系统重量轻、生产相对便宜并能有效、可靠地缓冲风机叶片脱落事件中的冲击载荷。
发明内容
根据本发明的安装系统提供了一种用于发动机辅助部件的刚性安装,此外,还提供高冲击载荷事件中的能量缓冲。
三点安装系统包括将辅助部件安装到发动机外壳上的两个侧托架和一个顶部托架。侧托架的位置靠近辅助部件的重心。顶部托架轴向偏移到辅助部件的末端。
每个侧托架包括第一安装节段、第二安装节段、可变形构件和两个保持构件。可变形构件被层压在两个保持构件之间。通过可变形构件限定一连串开口。保持构件至少部分为非平面,并面对可变形构件。
在风机叶片脱落事件中,可变形构件分裂以缓冲辅助部件经受的相当大的一部分高冲击载荷。随后的任何载荷是由保持构件的非平面部分缓冲的,该事件之后保持构件还将辅助部件保持在发动机外壳上。
本发明的能量缓冲安装系统提供了一种用于燃气涡轮发动机的辅助部件的安装系统,该系统体量轻、生产相对便宜并能有效、可靠地缓冲风机叶片脱落事件中的冲击载荷。
附图说明
从下文对优选实施例的详细描述中,本领域技术人员会明白本发明的各个特征和优点。详细描述参考使用的附图可以简要地描述如下:
图1是燃气涡轮发动机组件的透视图,图中辅助部件安装在发动机的外部壳体上;
图2是一部分燃气涡轮发动机组件的俯视图,图中辅助部件是用根据本发明的安装系统安装到发动机外壳上的;
图3是图2中图示的组件的侧视图;
图4是顶部托架关于辅助部件和发动机外壳的位置的透视图;
图5是一部分燃气涡轮发动机的仰视图,图中辅助部件是用根据本发明的安装系统安装到发动机外壳上的;
图6是根据本发明的侧托架的透视图;
图7是本发明的侧托架经受高冲击载荷事件之后的透视图。
具体实施方式
参考图1,燃气涡轮发动机10一般包括风机部分12、压缩部分14、内燃部分16和涡轮部分18。压缩部分和涡轮部分每个都包含一级或多于一级压缩机和涡轮机(未示出),压缩机和涡轮机绕发动机纵轴20旋转。燃气涡轮发动机10的各部件被基本为圆柱形的发动机外壳22包围。发动机外壳22作为燃气涡轮发动机10的主要结构支撑。发动机外壳22通常由单独的外壳部分构成,如外壳部分24和26,它们由螺结法兰(诸如发动机箱法兰30)连接在一起。
辅助部件32由安装系统40沿辅助部件轴A安装到发动机外壳22,辅助部件轴A通常横向于发动机纵轴20。辅助部件32可包括需安装到发动机外壳22的本领域已知的任何部件,包括但不局限于油箱、变速箱、阀门以及用于调节燃气涡轮发动机10工作的电子控制系统,辅助部件32可以任何方位安装。
参考图2,三点安装系统40包括侧托架42,44和顶部托架46。应当理解在本发明的考虑范围之内,可使用更少的托架或附加的托架安装辅助部件32。每个侧托架42,44位于辅助部件32的每一侧,相对于燃气涡轮发动机纵轴20是前后关系。侧托架42,44优选位于辅助部件重心的每一侧。应当理解侧托架42,44的位置可以根据辅助部件32的尺寸和形状而变化。一般,侧托架42,44尽可能位于最靠近辅助部件32重量的平均位置处,只要不影响设计功能。在发动机额定工作期间,通过将侧托架42,44设置在靠近辅助部件重量的平均位置的地方,侧托架42,44可将辅助部件32刚性附连到发动机外壳22上,从而大体上减少此处的振动。
参考图3,顶部托架46的轴向方向位于沿辅助部件32的轴A方向的侧托架42,44的前方。顶部托架46的位置相对于燃气涡轮发动机10的发动机纵轴20是大致平行的,燃气涡轮发动机靠近辅助部件32的顶端节段51。应当理解,在本发明前提下也可使用其它方位和托架的组合。
参考图4,顶部托架46包括一组臂57,59和颈部部分61。这组臂55,57每个都附连到单独的发动机箱法兰30。顶部托架46的这组臂55,57通过多个紧固件F啮合辅助部件32,以在辅助部件32和发动机外壳22之间提供相对灵活的支架。也就是说,侧托架42,44是辅助部件32的主要支撑件,而顶部托架46一般使其间的辅助部件稳定。
托架部件(包括侧托架42,44和顶部托架46)优选由薄片金属材料构成。托架优选完全由AMS5599,Inconel 625(镍合金)制成。这种材料很适用于本发明,原因是其硬度相当,同时具有高的塑性和良好的疲劳特性。应当理解其它材料及材料组合也可以用来构建本发明安装系统的托架。
参考图5,此处辅助部件32安装到发动机外壳22,使得辅助部件轴A(延伸进入页面方向)横向于发动机外壳22的发动机纵轴20。应当理解对于辅助部件可使用各种安装配置,且安装配置可取决于设计的特定参数。侧托架42,44沿发动机外壳22的发动机纵轴20方向大致是对齐的,并位于辅助部件轴A的每一侧。
每个侧托架42,44限定第一安装节段50和第二安装节段52。第一和第二安装节段50,52是平面构件,两者大致相互平行。第一安装节段50附连到辅助部件32,第二安装节段52附连到发动机外壳22。安装节段50,52优选分别通过在安装节段50,52上形成的多个孔被固定到辅助部件32和发动机外壳22上(也如图6所示)。
侧托架42,44是由三层制成的,但应当理解可以使用任意多的层来形成安装节段50,52。这些层优选用铆钉R(图6)铆接在一起以维持安装节段50,52的结构完整性;然而,也可以使用其它的附连方法(包括焊接)以使托架42,44的各层夹紧。安装节段50,52可包括重量减轻的开口53以更进一步减轻侧托架42,44的部重量。侧托架42,44的构造优选不要求焊接,铜焊或类似操作。侧托架42,44是由三片金属薄片组装的。如本文以上描述的侧托架42,44和各个节段的分离只是出于说明目的。
每个侧托架42,44都包括夹在第一和第二保持构件62,64之间的一个可变形构件60。可变形构件60限定一平面节段74,该节段横向延伸到安装节段50,52。可变形构件60夹在第一保持构件62和第二保持构件64之间。保持构件62和64包括安装节段50,52之间的至少部分非平面节段72。非平面节段72侧面与平面安装节段50,52之间的可变形构件60的平面节段74分开。也就是说保持构件62,64将可变形构件60夹在其间以提供层压的侧托架42,44设计。
可变形构件60的平面节段74限定大致横向于安装节段50,52的一串开口70。开口70的尺寸和数量是由特定于应用的参数确定的,包括用来制造可变形构件60的剪切强度和载荷强度以及可变形构件60可能会经受的冲击载荷的量值/大小。应当理解可变形构件60可以采用更为易碎的材料来代替优选用来制造可变形构件60的镍合金薄片金属材料,设计成有单独的开口,或者没有开口。在一个例子中,钛代替用作制成可变形构件60的材料。可变形构件60设计成在预定载荷下达到极限张力,该预定载荷在特殊的高冲击载荷,诸如在风机叶片脱落事件过程中会遇到。
第一保持构件62和第二保持构件64被设置在可变形构件60的每一侧以将可变形构件60夹在其间。保持构件62,64每个都具有与可变形构件60的平面节段74相邻的非平面节段72。非平面节段72优选被预制成具有弓形弯曲部分。
在发动机的额定工作期间,侧托架42,44和顶部托架46足够坚硬以刚性地支撑辅助部件32。保持构件62,64和侧托架42,44的可变形构件60提供必需的刚性以相对于发动机外壳22支撑辅助部件32。
参考图7,图示的侧托架42,44遭受了风机叶片脱落事件。也就是,开口70提供预先定义的故障区域。由于风机叶片脱落事件造成发动机转子产生相对严重的不平衡,以致于可变形构件60可撕裂、剪切、紧扣、熔化或以其它方式沿开口70方向上承受拉力而变形。可变形构件60的塑性变形缓冲大部分高冲击载荷。冲击载荷的平衡由保持构件62,64缓冲,保持构件62,64的非平面节段72延伸(由箭头B示意性说明)并凹陷或相对彼此凸起以提供进一步的载荷缓冲路径。也就是说,可变形构件60故障和保持构件62,64的非平面节段72的延伸的组合通过基本延长高冲击载荷事件的时间段来缓冲高冲击载荷。在风机叶片脱落事件之后,保持构件62,64还将辅助部件32保持到发动机外壳22上,使得辅助部件32不会完全脱离。这样,可牺牲支架系统40,但同时维持辅助部件32的完整性。
前述说明应该被解释为是说明性的,而不是限定性的。本领域技术人员会认识到某些修改也落在本发明的范围之内。为此,应该根据所附权利要求来确定本发明的真实范围和内容。
Claims (18)
1.一种将辅助部件安装到燃气涡轮发动机外壳的安装托架,包括:
第一安装节段;
第二安装节段;
可变形构件,其处于所述第一安装节段和所述第二安装节段之间,所述可变形构件包括预先定义的故障区域;和
保持构件,其处于所述第一安装节段和所述第二安装节段之间,
其中,响应高冲击载荷事件,所述可变形构件塑性变形以吸收冲击载荷,所述保持构件的非平面节段延伸以提供进一步的载荷缓冲路径。
2.根据权利要求1所述的安装托架,其中所述可变形构件限定了一开口。
3.根据权利要求1所述的安装托架,其中所述可变形构件限定了一系列开口。
4.根据权利要求1所述的安装托架,其中所述第一安装节段和所述第二安装节段包括所述可变形构件的一个节段,所述可变形构件的这个节段被层压到所述保持构件的第一和第二节段。
5.根据权利要求4所述的安装托架,包括一安装在所述第一安装节段和与所述第一安装节段相对的所述第二安装节段之间的第二保持构件,以将所述可变形构件夹在这两者之间。
6.根据权利要求1所述的安装托架,其中所述保持构件在所述第一和第二安装节段之间限定了一非平面节段。
7.根据权利要求6所述的安装托架,其中所述非平面节段是一弯曲节段,该弯曲节段的内弧面向所述可变形构件。
8.一种燃气涡轮发动机组件,包括:
发动机外壳部分;
安装到所述发动机外壳部分的多个托架,所述多个托架中的每一个都具有可变形构件,所述可变形构件夹在第一保持构件和与所述第一保持构件分开的第二保持构件之间,所述可变形构件包括预先定义的故障区域,其中,响应高冲击载荷事件,所述可变形构件塑性变形以吸收冲击载荷,所述第一保持构件和第二保持构件的非平面节段延伸以提供进一步的载荷缓冲路径;和
安装到所述多个托架的辅助部件。
9.根据权利要求8所述的组件,其中所述可变形构件在第一和第二安装节段之间限定了一平面节段,所述第一安装节段安装到所述发动机外壳部分,所述第二安装节段安装到所述辅助部件。
10.根据权利要求9所述的组件,其中所述保持构件包括一邻近于所述平面节段的非平面节段。
11.根据权利要求8所述的组件,其中所述可变形构件限定了至少一个开口。
12.根据权利要求8所述的组件,其中所述多个托架包括被定位成邻近于所述辅助部件的重心的第一托架和第二托架。
13.根据权利要求12所述的组件,进一步包括安装到所述辅助部件和所述发动机外壳部分的顶部托架。
14.一种将辅助部件安装到发动机外壳部分的方法,包括以下步骤;
1)用具有可变形构件和保持构件的托架将辅助部件附连到发动机外壳部分,其中所述可变形构件包括预先定义的故障区域;
2)响应高冲击载荷事件,所述可变形构件塑性变形以吸收冲击载荷,所述保持构件的非平面节段延伸以提供进一步的载荷缓冲路径;和
3)在所述步骤2)之后,所述保持构件将所述辅助部件保持到所述发动机外壳部分。
15.根据权利要求14所述的方法,其中所述步骤2)包括:
超过所述可变形构件的抗拉强度。
16.根据权利要求14所述的方法,其中所述步骤2)包括:
超过所述可变形构件的抗弯强度。
17.根据权利要求14所述的方法,其中所述步骤3)包括:
至少部分地使所述保持构件朝着所述可变形构件变平。
18.根据权利要求14所述的方法,其中所述步骤3)包括:
至少部分地使所述保持构件朝远离所述可变形构件的方向凸起。
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US11/291,348 US8104736B2 (en) | 2005-12-01 | 2005-12-01 | Gas turbine engine auxiliary component mount |
US11/291,348 | 2005-12-01 | ||
PCT/US2006/037381 WO2007064388A1 (en) | 2005-12-01 | 2006-09-25 | Gas turbine engine auxiliary component mount |
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CN101321940A CN101321940A (zh) | 2008-12-10 |
CN101321940B true CN101321940B (zh) | 2014-05-07 |
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CN200680044913.7A Active CN101321940B (zh) | 2005-12-01 | 2006-09-25 | 燃气涡轮发动机的辅助部件安装 |
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US (2) | US8104736B2 (zh) |
CN (1) | CN101321940B (zh) |
DE (1) | DE112006003297B4 (zh) |
GB (1) | GB2444692B (zh) |
WO (1) | WO2007064388A1 (zh) |
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Also Published As
Publication number | Publication date |
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US20120110821A1 (en) | 2012-05-10 |
US8104736B2 (en) | 2012-01-31 |
GB0807001D0 (en) | 2008-05-21 |
GB2444692B (en) | 2010-09-29 |
CN101321940A (zh) | 2008-12-10 |
WO2007064388A1 (en) | 2007-06-07 |
GB2444692A (en) | 2008-06-11 |
DE112006003297T5 (de) | 2008-10-23 |
US20070125087A1 (en) | 2007-06-07 |
DE112006003297B4 (de) | 2023-02-09 |
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