CN107849939A - 辐条安装布置 - Google Patents
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
一种燃气涡轮发动机的涡轮中间框架具有结构环组件,该结构环组件包括外环、具有从其径向外表面延伸的多个有螺纹突起的内环,和将内环与外环相互连接的对应数量的结构辐条。每个辐条均具有螺纹接合在内环上的有螺纹突起中的相关联的一个中的径向内部有螺纹端部。
Description
相关专利申请
本申请要求于2015年7月24日提交的美国专利临时申请第62/196,360号和第62/196,330号的优先权,其全部内容通过引用并入本文。
技术领域
本申请大体涉及燃气涡轮发动机,并且更具体地,涉及辐条安装布置。
背景技术
已知使用结构辐条将载荷从轴承壳体传递到燃气涡轮发动机的外结构环。比如,可以在涡轮中间框架模块中找到这种辐条。每个辐条通常从外环径向地延伸通过气体路径中的支柱到达支撑轴承壳体的内环。通常,使用安装衬垫和带有垫片间隔件的多个螺栓来将每个辐条的内端附接到内环并且调整内环相对于外环的位置。机加工的衬垫/间隔件的使用增加了最终堆叠累积,增多了发动机部件数量并且增加了总体组装的复杂性。
发明内容
在一方面,提供一种使用辐条的径向内端部上的螺纹将辐条的内端部附接到内结构环的简单方式,所述螺纹用于与和所述内结构环一体化的对应的有螺纹突起螺纹接合。
根据另一方面,提供一种适于接收并支撑轴承壳体的内结构环,所述内结构环在其径向外表面上具有周向间隔分开的有螺纹突起,以便与相应辐条的径向内端部处的匹配螺纹螺纹接合。
根据另一方面,提供一种结构环组件,所述结构环组件包括外环、具有从其径向外表面延伸的多个有螺纹突起的内环、将内环与外环相互连接的对应数量的结构辐条,每个辐条均具有能够螺纹接合在内环上的有螺纹突起中的相关联的一个中的径向内部有螺纹端部。
根据另一方面,提供一种燃气涡轮发动机的涡轮中间框架,其包括:外环、内环,和将所述内环与所述外环在结构上相互连接的多个周向地间隔分开的辐条,所述辐条具有径向内部有螺纹端部和径向外端部,所述径向内部有螺纹端部能够螺纹接合到所述内环,且所述径向外端部定位成沿径向向外方向相对所述外环的径向内表面施加力,由此使所述辐条在所述内环与所述外环之间保持处于压缩状态。
根据另一方面,提供一种燃气涡轮发动机,其包括第一涡轮区段、第二涡轮区段,和轴向地位于所述第一涡轮区段与所述第二涡轮区段之间的涡轮中间框架,所述涡轮中间框架包括:外结构环、构造为支撑轴承的内结构环、将所述外结构环与所述内结构环在结构上相互连接的多个载荷承载辐条,每个载荷承载辐条具有径向内部有螺纹端部和径向外端部,所述径向内部有螺纹端部与一体地形成在所述内结构环中的匹配螺纹能够螺纹接合,且所述径向外端部安装成抵靠所述外结构环的径向内表面支承接触,由此使所述载荷承载辐条在所述内结构环与所述外结构环之间保持处于压缩状态。
根据又一大体方面,提供一种将用于在燃气涡轮发动机中使用的涡轮中间框架轴向地组装在第一涡轮区段和第二涡轮区段之间的方法,所述方法包括:使各个辐条的相应径向内部有螺纹端部与设置在内结构环的周边周围的周向地间隔分开的位置处的对应有螺纹部位能够螺纹接合;使所述内结构环相对于外结构环居中,其中居中包括通过以下方式调节所述辐条从所述内结构环径向向外突伸的长度:使所述辐条围绕它们相应的纵向轴线旋转直到所述辐条的相应径向外端部邻接所述外结构环的径向内表面并在其上施加径向向外的力;以及然后将所述辐条的径向外端部紧固到所述外结构环,以将所述辐条在所述内结构环与所述外结构环之间固定在压缩状态中。
附图说明
现在参考附图,附图中:
图1是燃气涡轮发动机的示意性横截面视图;
图2是涡轮中间框架模块的等距视图;
图3是涡轮中间框架模块的另一等距视图,但其中省略了一体式支柱-叶片壳体以更好地示出在内结构环和外结构环之间延伸的结构辐条;
图4是放大的等距视图,其示出辐条的能够螺纹接合在从内结构环的径向外表面延伸的有螺纹突起中的内端;
图5是示出辐条的能够螺纹接合在内结构环上的有螺纹突起中的径向内端部的横截面视图。
图6是示出辐条中的一个与外结构环之间的螺栓连接的分解等距视图;和
图7是示出图6中所示的螺栓连接的防旋转特征的等距视图。
具体实施方式
图1示出优选地设置为用于在亚音速飞机中使用的类型的涡轮风扇式燃气涡轮发动机10,其大体包括串行流动连通的风扇12,通过该风扇12推动周围空气;用于对空气加压的多级压缩机14;燃烧器16,在该燃烧器16中压缩空气与燃料混合并被点燃以便生成热燃烧气体的环形流;以及用于从燃烧气体提取能量的涡轮区段18。
图2示出涡轮区段18的一部分。更具体地,图2示出涡轮中间框架模块20,其适于轴向地安装在第一涡轮区段和第二涡轮区段之间。涡轮中间框架模块20包括适于接收和支撑轴承壳体23(参见图5)的内结构环22,该轴承壳体23相应地适于支撑发动机10的主轴。如图5中所示,轴承壳体23可以借助于螺栓25可拆卸地安装于内环。现在同时参考图2和图3,能够看到的是,内结构环22由外结构环24借助于多个周向分布的辐条26(在所示实施例中为6个)在结构上支撑。除了将载荷从内环22传递到外环24之外,辐条26还被用于使内环22且因此使轴承壳体23相对于外环24居中。
每个辐条26可以径向地延伸通过“浮动地”安装在内结构环22和外结构环24之间的非结构一体式支柱-叶片壳体28(图2)的中空支柱27(图5),以便在两个轴向邻近的涡轮级之间导引燃烧气体。壳体28具有径向外气体路径壁28a和径向内气体路径壁28b(图5),其间限定涡轮区段18的气体路径的一部分。根据所示实施例,壳体28不起结构作用。即来自轴承壳体23的载荷不经由一体式支柱-叶片壳体28传递至外壳体24。而是载荷被传递通过辐条26,辐条26由一体式支柱-叶片壳体28的中空支柱27屏蔽免受热燃烧气体的影响。在这样的布置中,辐条能够被称为冷辐条。
如图3至图5中最佳地示出的,每个辐条26在其径向内端部处与一体地形成在内环22上的有螺纹突起30能够螺纹接合。根据所示示例,辐条的径向内端部处的外螺纹与内部有螺纹突起30的匹配螺纹接合,该内部有螺纹突起30从内环22的径向外表面径向向外突伸。应注意的是,有螺纹突起30能够从内环22的径向内周向表面延伸,并且因此不限于被设置在内环的径向外表面上。突起能够被设置在内环上的各种径向/周向位置处。而且,应理解的是,内螺纹能够被设置在辐条上并且外螺纹能够被设置在突起上。而且,内环22上的每个有螺纹部位也能够采用各种合适的构造来提供所需的螺纹长度。
辐条26上的螺纹可以与辐条的车削操作同时地被机加工。内环22可以被铸造、机加工或以其它方式合适地以在其径向外表面或内表面之一上具有周向地间隔分开的有螺纹突起的简单环的形式被制成。
上述布置提供了一种将辐条26可调节地附接到支撑轴承壳体23的内环22的简单且有效的方式。不需要额外的紧固件或附接零件。其提供紧凑的设计,从而允许改进的空气动力学气体路径(存在额外的径向空间可用于修改内部气体路径壁28a和外部气体路径壁28b)。辐条内端与内环22之间的螺纹连接减少了失准的积聚,并且相比于带有衬垫、螺栓和垫片间隔件的常规辐条安装布置简化了轴承壳体居中过程。
如图6和图7中最佳地示出的,每个辐条26可以在其径向外端部处螺栓连接到外结构环24。在每个组装点处,在外环24的径向外表面中限定用于接收垫圈32的座31。垫圈32可以具有扁平本体,并且该扁平本体带有限定在其中以便单个地接收相应的螺栓36或等效的有螺纹紧固件(在所示的示例中为4个)的周向地间隔分开的孔34。对应的细长安装槽38被限定在座31的底部中,以便接收螺栓36。每个槽38容许与在辐条26的径向外端部处限定在安装凸缘或头部42中的孔的环形阵列中的至少一个对应的有螺纹孔40对齐。因此,垫圈32定位在其相关联的座31中,使得限定在其中的孔34与辐条26的安装凸缘的对应孔40对齐或对准。在垫圈32中的孔34已经与辐条26的安装凸缘中的对应孔40适当地角度上对齐之后,螺栓36被拧紧以将辐条26牢固地连结到外结构环24的径向内周向表面。
如图6和图7中所示,垫圈32可在每个孔34处设置有一对防旋转突片42。根据所示实施例,每对防旋转突片42包括在垫圈32的内径上的第一突片42a和在垫圈32的外径上的面向相对方向的第二突片42b。如图7中所示,每对第一突片42a和第二突片42b均可弯折出垫圈32的平面与相关联的螺栓36的头部接合,以明确地锁定所述头部防止其旋转。在所示实施例中,每对防旋转突片42均可与相关联的螺栓36的六角头部的相对侧接合。这有效地防止螺栓36的松动。虽然已经示出可变形或可弯折的突片,但应理解的是,也能够使用任何合适类型的锁定突片。
参照图6,能够看出的是,垫圈的外围部分可变形成设置在垫圈座30的周边周围的一个位置处的防旋转凹口或卡抓部46。根据一个实施例,在所有螺栓36均已被拧紧并且用突片42锁定在恰当位置之后,垫圈32的外围部分能够被冲压至防旋转卡抓部46内。这防止垫圈32相对于外壳体24旋转运动,从而锁定辐条26以防止其围绕其纵向轴线旋转。
在涡轮中间框架的组装期间,通过根据螺纹方向使辐条26围绕其相应的轴线沿顺时针方向或逆时针方向旋转来调节辐条26在有螺纹突起30中的螺纹接合,使得辐条26的径向外端部牢固地邻接外环24的径向内周向表面。每个辐条均如此旋转,以便调节从内环22径向向外突伸的辐条的部分的长度。辐条没有螺纹,直到所有辐条的径向外端部一致地邻接外环的内表面。调节辐条的长度,使得每个辐条相对外环的内表面施加指向径向向外方向的力。这些力应当遍及整个环是一致的。一旦所有辐条均已被适当地调节以共同使内环相对于外环居中,那么螺栓36就能够从外环的外侧与在辐条的径向外端部处在辐条的头部中限定的对应有螺纹孔螺纹接合。
本领域技术人员将认识到的是,辐条26在径向内环22和外环24之间以压缩状态被安装。即,如上文所述,在发动机组装期间,载荷承载辐条36被预加应力成压缩状态。因此,在辐条26的径向内端部和外端部处的螺纹上总是维持压缩作用。这有助于防止辐条的两端处的螺纹连接的松动。在发动机操作期间,当辐条26暴露于热时,辐条往往膨胀,由此进一步增加螺纹上的压力,并且因此防止松动。构建预加应力成压缩状态的辐条的优点有2方面:1)组装预应力的量得以最小化,从而促进组装,并且当在发动机操作期间辐条热膨胀时,它们将对抗内环和外环起作用,由此增加辐条中的压缩载荷。如果在张力中组装辐条,则在发动机操作期间预应力张力的水平将被热地减小,并且因此螺纹连接遭受松动。这能够导致轴承偏离中央的问题。如根据前述内容能够认识到的,这些问题可以通过在压缩状态中组装辐条来克服。发动机操作将仅增加压缩的量,由此进一步防止螺纹连接的松动。
以上描述仅意在是示例性的,并且本领域技术人员将认识到的是,可以在不背离所公开的本发明的范围的情况下对所描述的实施例做出改变。根据对本公开的审视,落入本发明的范围内的任何修改对于本领域技术人员而言都将是显而易见的,并且此类修改旨在落入所附权利要求内。
Claims (19)
1.一种燃气涡轮发动机的涡轮中间框架,其包括:外环、内环和将所述内环与所述外环在结构上相互连接的多个周向间隔分开的辐条,所述辐条具有径向内部有螺纹端部和径向外端部,所述径向内部有螺纹端部能够螺纹接合到所述内环,且所述径向外端部定位成沿径向向外方向相对所述外环的径向内表面施加力,由此保持所述辐条在所述内环与所述外环之间处于压缩状态。
2.根据权利要求1所述的涡轮中间框架,其特征在于,有螺纹紧固件延伸穿过所述外环与所述辐条的径向外端部螺纹接合。
3.根据权利要求2所述的涡轮中间框架,其特征在于,所述有螺纹紧固件包括螺栓,其能够与限定在所述辐条的径向外端部中的有螺纹孔螺纹接合。
4.根据权利要求1所述的涡轮中间框架,其特征在于,所述辐条中的每个在其径向外端部处具有与所述外环的径向内表面支承接触的凸缘,至少两个孔被限定在所述凸缘中,所述孔与限定为通过所述外环的槽对准以便接收紧固件。
5.根据权利要求1所述的涡轮中间框架,其特征在于,周向间隔分开的突起一体地形成在所述内环上,并且其中在所述突起中形成螺纹以便与所述辐条接合。
6.根据权利要求5所述的涡轮中间框架,其特征在于,所述突起从所述内环的径向外表面径向向外延伸。
7.根据权利要求1所述的涡轮中间框架,其特征在于,所述辐条与在所述内环上一体地形成的螺纹能够螺纹接合。
8.一种燃气涡轮发动机,其包括第一涡轮区段、第二涡轮区段和轴向地位于所述第一涡轮区段与所述第二涡轮区段之间的涡轮中间框架,所述涡轮中间框架包括:外结构环、构造为支撑轴承的内结构环、将所述外结构环与所述内结构环在结构上相互连接的多个载荷承载辐条,每个载荷承载辐条均具有径向内部有螺纹端部和径向外端部,所述径向内部有螺纹端部能够与一体地形成在所述内结构环中的匹配螺纹螺纹接合,所述径向外端部安装成相对所述外结构环的径向内表面支承接触,由此保持所述载荷承载辐条在所述内结构环与所述外结构环之间处于压缩状态。
9.根据权利要求8所述的燃气涡轮发动机,其特征在于,所述载荷承载辐条中的每个沿径向向外方向相对所述外结构环的径向内表面施加力。
10.根据权利要求8所述的燃气涡轮发动机,其特征在于,有螺纹紧固件延伸穿过所述外结构环与所述载荷承载辐条的径向外端部螺纹接合。
11.根据权利要求10所述的燃气涡轮发动机,其特征在于,所述有螺纹紧固件包括螺栓,其能够螺纹接合在限定在所述载荷承载辐条的径向外端部中的有螺纹孔中。
12.根据权利要求8所述的燃气涡轮发动机,其特征在于,所述载荷承载辐条中的每个在其径向外端部处具有与所述外结构环的径向内表面支承接触的凸缘,至少两个孔被限定在所述凸缘中,所述孔与限定为通过所述外结构环的对应槽对准以便接收紧固件。
13.根据权利要求8所述的燃气涡轮发动机,其特征在于,周向间隔分开的突起一体地形成在所述内结构环上,并且其中所述匹配螺纹形成在所述突起中。
14.根据权利要求13所述的燃气涡轮发动机,其特征在于,所述突起从所述内结构环的径向外表面径向向外延伸。
15.根据权利要求8所述的燃气涡轮发动机,其特征在于,所述匹配螺纹与所述内结构环一体化。
16.一种将用于在燃气涡轮发动机中使用的涡轮中间框架轴向地组装在第一涡轮区段和第二涡轮区段之间的方法,所述方法包括:使各个辐条的相应径向内部有螺纹端部与设置在内结构环的周边周围的周向地间隔分开的位置处的对应有螺纹部位能够螺纹接合;使所述内结构环相对于外结构环居中,其中居中包括通过以下方式调节所述辐条从所述内结构环径向向外突伸的长度:使所述辐条围绕它们的相应纵向轴线旋转直到所述辐条的相应径向外端部邻接所述外结构环的径向内表面并在其上施加径向向外的力;以及然后将所述辐条的径向外端部紧固于所述外结构环,以使所述辐条在所述内结构环与所述外结构环之间固定在压缩状态中。
17.根据权利要求16所述的方法,其特征在于,紧固包括将每个辐条螺栓连接到所述外结构环。
18.根据权利要求16所述的方法,其特征在于,调整所述长度包括从所述内结构环部分地退解所述辐条。
19.根据权利要求16所述的方法,其特征在于,能够螺纹接合包括使所述辐条在所述有螺纹部位中的每个处与一体地形成在所述内结构环上的有螺纹突起能够螺纹接合。
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US62/196330 | 2015-07-24 | ||
US62/196360 | 2015-07-24 | ||
PCT/CA2016/050818 WO2017015745A1 (en) | 2015-07-24 | 2016-07-12 | Spoke mounting arrangement |
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Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2971579B1 (en) * | 2013-03-11 | 2020-04-29 | United Technologies Corporation | Aft fairing sub-assembly for turbine exhaust case fairing |
US10605119B2 (en) * | 2017-09-25 | 2020-03-31 | United Technologies Corporation | Turbine frame assembly for gas turbine engines |
US10815830B2 (en) | 2017-12-21 | 2020-10-27 | Raytheon Technologies Corporation | Lightweight tierod |
RU2724074C1 (ru) * | 2019-06-21 | 2020-06-19 | Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Опора турбины турбомашины |
GB202018430D0 (en) * | 2020-11-24 | 2021-01-06 | Rolls Royce Plc | Support assembly for gas turbine engine |
US11739664B1 (en) * | 2022-03-17 | 2023-08-29 | Pratt & Whitney Canada Corp. | Service tube locking device |
US11578618B1 (en) * | 2022-04-01 | 2023-02-14 | Pratt & Whitney Canada Corp. | Service tube locking device |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100132376A1 (en) * | 2008-11-28 | 2010-06-03 | Pratt & Whitney Canada Corp. | Mid turbine frame for gas turbine engine |
CN103306818A (zh) * | 2012-03-05 | 2013-09-18 | 通用电气公司 | 燃气涡轮机架加强轨 |
US20140013770A1 (en) * | 2012-07-13 | 2014-01-16 | United Technologies Corporation | Vane insertable tie rods with keyed connections |
Family Cites Families (186)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB910446A (en) | 1960-01-01 | 1962-11-14 | Rolls Royce | Improvements in or relating to nuts and bolts |
GB898164A (en) | 1960-01-26 | 1962-06-06 | Austin Motor Co Ltd | Improved means for clamping rotor assemblies |
US3261587A (en) | 1964-06-24 | 1966-07-19 | United Aircraft Corp | Bearing support |
US3403889A (en) | 1966-04-07 | 1968-10-01 | Gen Electric | Frame assembly having low thermal stresses |
US3451456A (en) | 1967-04-26 | 1969-06-24 | Standard Pressed Steel Co | Bolt with restrainer |
US3486544A (en) | 1968-06-21 | 1969-12-30 | Shur Lok Corp | High-speed nut and lockwasher |
US3543588A (en) | 1968-11-12 | 1970-12-01 | Gen Motors Corp | Accessory installation |
GB1361994A (en) | 1971-06-22 | 1974-07-30 | Girling Ltd | Disc brakes |
GB1411299A (en) | 1973-04-10 | 1975-10-22 | Rolls Royce | Anti-rotation washers for flanged or round headed screwed fastenings |
US4050494A (en) | 1976-06-18 | 1977-09-27 | The United States Of America As Represented By The Secretary Of The Army | Anti-rotation lock for fastener bolt |
US4183207A (en) | 1978-03-07 | 1980-01-15 | Avco Corporation | Oil-conducting strut for turbine engines |
US4214851A (en) | 1978-04-20 | 1980-07-29 | General Electric Company | Structural cooling air manifold for a gas turbine engine |
US4321007A (en) | 1979-12-21 | 1982-03-23 | United Technologies Corporation | Outer case cooling for a turbine intermediate case |
US4369016A (en) | 1979-12-21 | 1983-01-18 | United Technologies Corporation | Turbine intermediate case |
DE3233976C1 (de) | 1982-09-14 | 1983-08-25 | Daimler-Benz Ag, 7000 Stuttgart | Verdrehsicherung für Schrauben |
US4571936A (en) | 1985-07-10 | 1986-02-25 | The United States Of America As Represented By The Secretary Of The Air Force | Length adjustable strut link with low aerodynamic drag |
US4735536A (en) | 1986-09-26 | 1988-04-05 | Avibank Mfg., Inc. | Captive panel fastener assembly and method for installing the same |
GB2196083B (en) | 1986-10-02 | 1991-02-06 | Avibank Mfg Inc | Captive panel fastener assembly |
US4747738A (en) | 1986-10-03 | 1988-05-31 | Avilbank Mfg., Inc. | Captive panel fastener assembly |
US4815908A (en) | 1986-10-14 | 1989-03-28 | Avibank Mfg., Inc. | Captive panel fastener assembly |
US4948316A (en) | 1986-11-04 | 1990-08-14 | Avibank Mfg., Inc. | Quick action fastener assembly |
US4820117A (en) | 1987-07-09 | 1989-04-11 | United Technologies Corporation | Crossed I-beam structural strut |
US4793770A (en) | 1987-08-06 | 1988-12-27 | General Electric Company | Gas turbine engine frame assembly |
US4836708A (en) | 1988-07-05 | 1989-06-06 | Motorola, Inc. | Self-locking, anti-rotational retaining washer for a "D" shaped shaft |
FR2635751B1 (fr) | 1988-09-01 | 1991-01-04 | Snecma | Dispositif de fixation d'une biellette de suspension d'un turboreacteur |
US4987736A (en) | 1988-12-14 | 1991-01-29 | General Electric Company | Lightweight gas turbine engine frame with free-floating heat shield |
US4979872A (en) | 1989-06-22 | 1990-12-25 | United Technologies Corporation | Bearing compartment support |
US5076049A (en) | 1990-04-02 | 1991-12-31 | General Electric Company | Pretensioned frame |
US5080555A (en) * | 1990-11-16 | 1992-01-14 | General Motors Corporation | Turbine support for gas turbine engine |
US5160251A (en) | 1991-05-13 | 1992-11-03 | General Electric Company | Lightweight engine turbine bearing support assembly for withstanding radial and axial loads |
DE9111729U1 (zh) | 1991-09-19 | 1993-01-28 | Waldemar Link Gmbh & Co, 2000 Hamburg, De | |
US5236303A (en) | 1991-09-27 | 1993-08-17 | General Electric Company | Gas turbine engine structural frame with multi-clevis ring attachment of struts to outer casing |
US5180282A (en) | 1991-09-27 | 1993-01-19 | General Electric Company | Gas turbine engine structural frame with multi-yoke attachment of struts to outer casing |
GB2267736B (en) * | 1992-06-09 | 1995-08-09 | Gen Electric | Segmented turbine flowpath assembly |
US5292227A (en) | 1992-12-10 | 1994-03-08 | General Electric Company | Turbine frame |
US5272869A (en) | 1992-12-10 | 1993-12-28 | General Electric Company | Turbine frame |
US5517817A (en) | 1993-10-28 | 1996-05-21 | General Electric Company | Variable area turbine nozzle for turbine engines |
US5438756A (en) | 1993-12-17 | 1995-08-08 | General Electric Company | Method for assembling a turbine frame assembly |
US5634767A (en) | 1996-03-29 | 1997-06-03 | General Electric Company | Turbine frame having spindle mounted liner |
GB2324833B (en) | 1997-02-22 | 2000-10-04 | Rolls Royce Plc | Gas turbine engine support structure |
US5746574A (en) | 1997-05-27 | 1998-05-05 | General Electric Company | Low profile fluid joint |
US6290442B1 (en) | 1997-09-18 | 2001-09-18 | Okabe Corporation, Inc. | Locking fastener assembly for threaded joint |
US6250840B1 (en) | 1998-09-11 | 2001-06-26 | Trw Inc. | Tie rod end |
FR2786230B1 (fr) | 1998-11-19 | 2001-02-09 | Cba | Dispositif pour le blocage anti-rotation d'un ecrou sur une tige filetee |
US6439841B1 (en) | 2000-04-29 | 2002-08-27 | General Electric Company | Turbine frame assembly |
US6358001B1 (en) | 2000-04-29 | 2002-03-19 | General Electric Company | Turbine frame assembly |
US6439616B1 (en) | 2001-03-29 | 2002-08-27 | General Electric Company | Anti-rotation retainer for a conduit |
US6547518B1 (en) | 2001-04-06 | 2003-04-15 | General Electric Company | Low hoop stress turbine frame support |
US6708482B2 (en) | 2001-11-29 | 2004-03-23 | General Electric Company | Aircraft engine with inter-turbine engine frame |
DE10303088B4 (de) | 2002-02-09 | 2015-08-20 | Alstom Technology Ltd. | Abgasgehäuse einer Wärmekraftmaschine |
US6619030B1 (en) | 2002-03-01 | 2003-09-16 | General Electric Company | Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors |
FR2836963A1 (fr) | 2002-03-08 | 2003-09-12 | Airbus France | Dispositif de fixation d'un element sur une structure d'aeronef |
US7063505B2 (en) | 2003-02-07 | 2006-06-20 | General Electric Company | Gas turbine engine frame having struts connected to rings with morse pins |
US6860716B2 (en) | 2003-05-29 | 2005-03-01 | General Electric Company | Turbomachine frame structure |
DE10352089A1 (de) | 2003-11-07 | 2005-06-09 | Alstom Technology Ltd | Verfahren zum Betreiben einer Turbomaschine, und Turbomaschine |
US7220119B1 (en) | 2004-02-28 | 2007-05-22 | Force Pro | Pre-stressed tie rod and method of manufacture |
US7195447B2 (en) | 2004-10-29 | 2007-03-27 | General Electric Company | Gas turbine engine and method of assembling same |
US7419121B2 (en) | 2004-12-09 | 2008-09-02 | Honeywell International Inc. | Integrated mount duct for use with airborne auxiliary power units and other turbomachines |
US7584621B2 (en) | 2005-08-05 | 2009-09-08 | Siemens Energy, Inc. | Radially expanding turbine engine exhaust cylinder interface |
EP1793091A1 (de) | 2005-12-01 | 2007-06-06 | Siemens Aktiengesellschaft | Dampfturbine mit Lagerstreben |
US7597537B2 (en) | 2005-12-16 | 2009-10-06 | General Electric Company | Thermal control of gas turbine engine rings for active clearance control |
US20070196196A1 (en) | 2006-02-23 | 2007-08-23 | Schorling Detlef T | High strength fastener system |
US7775049B2 (en) | 2006-04-04 | 2010-08-17 | United Technologies Corporation | Integrated strut design for mid-turbine frames with U-base |
US7610763B2 (en) | 2006-05-09 | 2009-11-03 | United Technologies Corporation | Tailorable design configuration topologies for aircraft engine mid-turbine frames |
US7594404B2 (en) | 2006-07-27 | 2009-09-29 | United Technologies Corporation | Embedded mount for mid-turbine frame |
US7748209B1 (en) | 2006-12-08 | 2010-07-06 | Florida Turbine Technologies, Inc. | Small single use gas turbine engine with oil-less bearing arrangement |
EP1936210A1 (en) | 2006-12-19 | 2008-06-25 | BAE Systems PLC | Locking Expanding Diameter Fasteners |
US8001791B2 (en) | 2007-11-13 | 2011-08-23 | United Technologies Corporation | Turbine engine frame having an actuated equilibrating case |
US8215901B2 (en) | 2007-12-03 | 2012-07-10 | United Technologies Corporation | Gas turbine engines and related systems involving offset turbine frame struts |
JP5118496B2 (ja) | 2008-01-10 | 2013-01-16 | 三菱重工業株式会社 | ガスタービンの排気部の構造およびガスタービン |
JP4969500B2 (ja) | 2008-03-28 | 2012-07-04 | 三菱重工業株式会社 | ガスタービン |
DE102008019156A1 (de) | 2008-04-17 | 2009-10-22 | Mtu Aero Engines Gmbh | Strebe für ein Turbinenzwischengehäuse, Turbinenzwischengehäuse und Verfahren zur Herstellung eines Turbinenzwischengehäuses |
US8113768B2 (en) | 2008-07-23 | 2012-02-14 | United Technologies Corporation | Actuated variable geometry mid-turbine frame design |
US8099962B2 (en) | 2008-11-28 | 2012-01-24 | Pratt & Whitney Canada Corp. | Mid turbine frame system and radial locator for radially centering a bearing for gas turbine engine |
US8347635B2 (en) * | 2008-11-28 | 2013-01-08 | Pratt & Whitey Canada Corp. | Locking apparatus for a radial locator for gas turbine engine mid turbine frame |
US8245518B2 (en) | 2008-11-28 | 2012-08-21 | Pratt & Whitney Canada Corp. | Mid turbine frame system for gas turbine engine |
US20100132371A1 (en) | 2008-11-28 | 2010-06-03 | Pratt & Whitney Canada Corp. | Mid turbine frame system for gas turbine engine |
US8061969B2 (en) | 2008-11-28 | 2011-11-22 | Pratt & Whitney Canada Corp. | Mid turbine frame system for gas turbine engine |
US8347500B2 (en) | 2008-11-28 | 2013-01-08 | Pratt & Whitney Canada Corp. | Method of assembly and disassembly of a gas turbine mid turbine frame |
US8371812B2 (en) | 2008-11-29 | 2013-02-12 | General Electric Company | Turbine frame assembly and method for a gas turbine engine |
US20100275572A1 (en) | 2009-04-30 | 2010-11-04 | Pratt & Whitney Canada Corp. | Oil line insulation system for mid turbine frame |
US20100303610A1 (en) | 2009-05-29 | 2010-12-02 | United Technologies Corporation | Cooled gas turbine stator assembly |
US8511969B2 (en) | 2009-10-01 | 2013-08-20 | Pratt & Whitney Canada Corp. | Interturbine vane with multiple air chambers |
US8316523B2 (en) | 2009-10-01 | 2012-11-27 | Pratt & Whitney Canada Corp. | Method for centering engine structures |
US8500392B2 (en) | 2009-10-01 | 2013-08-06 | Pratt & Whitney Canada Corp. | Sealing for vane segments |
US8371127B2 (en) | 2009-10-01 | 2013-02-12 | Pratt & Whitney Canada Corp. | Cooling air system for mid turbine frame |
US8882384B2 (en) | 2010-04-16 | 2014-11-11 | Moeller Manufacturing Co., Inc. | Compact, highly-reusable, locking device |
FR2959539B1 (fr) | 2010-04-30 | 2012-07-13 | Snr Roulements Sa | Assemblage instrumente et rondelle frein associee |
US8979477B2 (en) | 2011-03-09 | 2015-03-17 | General Electric Company | System for cooling and purging exhaust section of gas turbine engine |
US9896966B2 (en) | 2011-08-29 | 2018-02-20 | United Technologies Corporation | Tie rod for a gas turbine engine |
JP5222384B2 (ja) | 2011-09-09 | 2013-06-26 | 三菱重工業株式会社 | ガスタービン |
US9097141B2 (en) | 2011-09-15 | 2015-08-04 | Pratt & Whitney Canada Corp. | Axial bolting arrangement for mid turbine frame |
US9279341B2 (en) | 2011-09-22 | 2016-03-08 | Pratt & Whitney Canada Corp. | Air system architecture for a mid-turbine frame module |
US9458721B2 (en) | 2011-09-28 | 2016-10-04 | United Technologies Corporation | Gas turbine engine tie rod retainer |
US9200536B2 (en) * | 2011-10-17 | 2015-12-01 | United Technologies Corporation | Mid turbine frame (MTF) for a gas turbine engine |
US9410596B2 (en) | 2011-11-04 | 2016-08-09 | Honeywell International Inc. | Mounting systems for structural members, fastening assemblies thereof, and vibration isolation systems including the same |
US8992173B2 (en) | 2011-11-04 | 2015-03-31 | United Technologies Corporation | Tie-rod nut including a nut flange with a plurality of mounting apertures |
US9145908B2 (en) | 2011-12-16 | 2015-09-29 | Ev Ip Lp | Blind fastener |
US8827255B2 (en) | 2012-01-20 | 2014-09-09 | Raymond Woods | Clamp assembly |
US8944749B2 (en) | 2012-01-24 | 2015-02-03 | Pratt & Whitney Canada Corp. | Oil purge system for a mid turbine frame |
US9316117B2 (en) | 2012-01-30 | 2016-04-19 | United Technologies Corporation | Internally cooled spoke |
US9447694B2 (en) | 2012-01-30 | 2016-09-20 | United Technologies Corporation | Internal manifold for turning mid-turbine frame flow distribution |
US8794009B2 (en) | 2012-01-31 | 2014-08-05 | United Technologies Corporation | Gas turbine engine buffer system |
US20130192256A1 (en) | 2012-01-31 | 2013-08-01 | Gabriel L. Suciu | Geared turbofan engine with counter-rotating shafts |
US10724431B2 (en) | 2012-01-31 | 2020-07-28 | Raytheon Technologies Corporation | Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine |
US9140137B2 (en) | 2012-01-31 | 2015-09-22 | United Technologies Corporation | Gas turbine engine mid turbine frame bearing support |
US20130195624A1 (en) | 2012-01-31 | 2013-08-01 | Frederick M. Schwarz | Geared turbofan engine with counter-rotating shafts |
US8366382B1 (en) | 2012-01-31 | 2013-02-05 | United Technologies Corporation | Mid-turbine frame buffer system |
JP5962887B2 (ja) * | 2012-02-02 | 2016-08-03 | 株式会社Ihi | 翼の連結部構造及びこれを用いたジェットエンジン |
NO336731B1 (no) | 2012-02-07 | 2015-10-26 | Tomra Systems Asa | Komprimeringsanordning |
US9194252B2 (en) | 2012-02-23 | 2015-11-24 | United Technologies Corporation | Turbine frame fairing for a gas turbine engine |
US9157325B2 (en) | 2012-02-27 | 2015-10-13 | United Technologies Corporation | Buffer cooling system providing gas turbine engine architecture cooling |
US9347374B2 (en) | 2012-02-27 | 2016-05-24 | United Technologies Corporation | Gas turbine engine buffer cooling system |
KR101216286B1 (ko) | 2012-04-25 | 2012-12-28 | 반기수 | 철도레일의 이음매 체결장치 |
US8863531B2 (en) | 2012-07-02 | 2014-10-21 | United Technologies Corporation | Cooling apparatus for a mid-turbine frame |
US20140003920A1 (en) | 2012-07-02 | 2014-01-02 | United Technologies Corporation | Flow metering anti-rotation outer diameter (od) hex nut |
US9303528B2 (en) | 2012-07-06 | 2016-04-05 | United Technologies Corporation | Mid-turbine frame thermal radiation shield |
US9217371B2 (en) | 2012-07-13 | 2015-12-22 | United Technologies Corporation | Mid-turbine frame with tensioned spokes |
US9222413B2 (en) | 2012-07-13 | 2015-12-29 | United Technologies Corporation | Mid-turbine frame with threaded spokes |
US9151316B2 (en) | 2012-07-25 | 2015-10-06 | Alan R. Smith | Fastener with unidirectional latch |
US8888427B2 (en) | 2012-07-26 | 2014-11-18 | Cnh Industrial America Llc | System for preventing rotation of fasteners |
US9011060B2 (en) | 2012-07-31 | 2015-04-21 | United Technologies Corporation | No flange damage wedge lock washers |
US9482115B2 (en) | 2012-08-23 | 2016-11-01 | United Technologies Corporation | Turbine engine support assembly including self anti-rotating bushing |
US9945411B2 (en) | 2012-08-31 | 2018-04-17 | United Technologies Corporation | Self-anti-rotating dual lock washer |
WO2014051672A1 (en) | 2012-09-28 | 2014-04-03 | United Technologies Corporation | Split-zone flow metering t-tube |
EP2900973B1 (en) | 2012-09-28 | 2018-12-12 | United Technologies Corporation | Mid-turbine frame with fairing attachment |
US9328629B2 (en) | 2012-09-28 | 2016-05-03 | United Technologies Corporation | Outer case with gusseted boss |
US9091171B2 (en) | 2012-10-30 | 2015-07-28 | Siemens Aktiengesellschaft | Temperature control within a cavity of a turbine engine |
US20140255174A1 (en) | 2012-12-21 | 2014-09-11 | United Technologies Corporation | Manufacture of full ring strut vane pack |
WO2014105572A1 (en) | 2012-12-29 | 2014-07-03 | United Technologies Corporation | Combination flow divider and bearing support |
US9982564B2 (en) | 2012-12-29 | 2018-05-29 | United Technologies Corporation | Turbine frame assembly and method of designing turbine frame assembly |
WO2014105616A1 (en) | 2012-12-29 | 2014-07-03 | United Technologies Corporation | Turbine exhaust case architecture |
US9903224B2 (en) | 2012-12-29 | 2018-02-27 | United Technologies Corporation | Scupper channelling in gas turbine modules |
JP6232446B2 (ja) | 2012-12-31 | 2017-11-15 | ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation | タービン排気ケースのマルチピース型フレーム |
US10982565B2 (en) | 2013-01-21 | 2021-04-20 | Raytheon Technologies Corporation | Turbine case adjustment using Adjustable tie rods |
US9316153B2 (en) | 2013-01-22 | 2016-04-19 | Siemens Energy, Inc. | Purge and cooling air for an exhaust section of a gas turbine assembly |
JP5862806B2 (ja) | 2013-01-28 | 2016-02-16 | 三菱電機株式会社 | ボルト回り止め及びボルト回り止めの組み付け方法 |
US9617870B2 (en) | 2013-02-05 | 2017-04-11 | United Technologies Corporation | Bracket for mounting a stator guide vane arrangement to a strut in a turbine engine |
US9890659B2 (en) | 2013-02-11 | 2018-02-13 | United Technologies Corporation | Mid-turbine frame vane assembly support with retention unit |
WO2014137574A1 (en) | 2013-03-05 | 2014-09-12 | United Technologies Corporation | Mid-turbine frame rod and turbine case flange |
EP2971579B1 (en) * | 2013-03-11 | 2020-04-29 | United Technologies Corporation | Aft fairing sub-assembly for turbine exhaust case fairing |
US8920109B2 (en) | 2013-03-12 | 2014-12-30 | Siemens Aktiengesellschaft | Vane carrier thermal management arrangement and method for clearance control |
EP2971612B1 (en) | 2013-03-13 | 2018-01-31 | United Technologies Corporation | Engine mid-turbine frame transfer tube for low pressure turbine case cooling |
US9279339B2 (en) | 2013-03-13 | 2016-03-08 | Siemens Aktiengesellschaft | Turbine engine temperature control system with heating element for a gas turbine engine |
TWI580603B (zh) | 2013-07-05 | 2017-05-01 | Sr Suntour Inc | 自行車用鏈輪 |
US9835038B2 (en) | 2013-08-07 | 2017-12-05 | Pratt & Whitney Canada Corp. | Integrated strut and vane arrangements |
FR3014973B1 (fr) | 2013-12-12 | 2016-01-22 | Airbus Operations Sas | Assemblage comprenant un axe d'articulation supporte par une chape et immobilise en translation par un dispositif de blocage integrant un double systeme d'anti-rotation |
US9845705B2 (en) | 2014-01-07 | 2017-12-19 | United Technologies Corporation | Systems and methods for centering bearing compartments |
US9739301B2 (en) | 2014-01-07 | 2017-08-22 | United Technologies Corporation | Systems and methods for centering bearing compartments |
US9803501B2 (en) | 2014-02-14 | 2017-10-31 | United Technologies Corporation | Engine mid-turbine frame distributive coolant flow |
WO2015156882A2 (en) | 2014-02-26 | 2015-10-15 | United Technologies Corporation | Tie rod connection for mid-turbine frame |
JP6392371B2 (ja) | 2014-04-11 | 2018-09-19 | ゼネラル・エレクトリック・カンパニイ | タービン中央フレームフェアリングアセンブリ |
CN203778897U (zh) | 2014-04-17 | 2014-08-20 | 福建省建瓯精工齿轮(机械)有限公司 | 齿轮内齿插齿工装夹具 |
KR101558493B1 (ko) | 2014-04-30 | 2015-10-07 | 한양이엔지 주식회사 | 플랜지 체결 공구 |
US9920869B2 (en) | 2014-05-22 | 2018-03-20 | United Technologies Corporation | Cooling systems for gas turbine engine components |
US9976431B2 (en) | 2014-07-22 | 2018-05-22 | United Technologies Corporation | Mid-turbine frame and gas turbine engine including same |
US20160186614A1 (en) | 2014-08-27 | 2016-06-30 | United Technologies Corporation | Turbine exhaust case assembly |
US9702267B2 (en) | 2014-10-15 | 2017-07-11 | Pratt & Whitney Canada Corp. | Engine structure assembly procedure |
KR101624054B1 (ko) | 2014-11-21 | 2016-05-24 | 두산중공업 주식회사 | 복수 개의 타이로드를 구비한 가스터빈 및 그의 조립방법 |
US10392969B2 (en) | 2014-12-02 | 2019-08-27 | United Technologies Corporation | Moment accommodating fastener assembly |
US9982567B2 (en) | 2014-12-16 | 2018-05-29 | United Technologies Corporation | Gas turbine engine mid-turbine frame tie rod arrangement |
US20160201516A1 (en) | 2015-01-09 | 2016-07-14 | United Technologies Corporation | Gas turbine engine mid-turbine frame tie rod arrangement |
US20160201512A1 (en) | 2015-01-09 | 2016-07-14 | United Technologies Corporation | Gas turbine engine mid-turbine frame tie rod arrangement |
US10371010B2 (en) | 2015-01-16 | 2019-08-06 | United Technologies Corporation | Tie rod for a mid-turbine frame |
US10309308B2 (en) | 2015-01-16 | 2019-06-04 | United Technologies Corporation | Cooling passages for a mid-turbine frame |
US9790860B2 (en) | 2015-01-16 | 2017-10-17 | United Technologies Corporation | Cooling passages for a mid-turbine frame |
US9915171B2 (en) | 2015-01-16 | 2018-03-13 | United Technologies Corporation | Cooling passages for a mid-turbine frame |
US9920651B2 (en) | 2015-01-16 | 2018-03-20 | United Technologies Corporation | Cooling passages for a mid-turbine frame |
US9856750B2 (en) | 2015-01-16 | 2018-01-02 | United Technologies Corporation | Cooling passages for a mid-turbine frame |
US9995171B2 (en) | 2015-01-16 | 2018-06-12 | United Technologies Corporation | Cooling passages for a mid-turbine frame |
US10392974B2 (en) | 2015-02-03 | 2019-08-27 | United Technologies Corporation | Mid-turbine frame assembly |
US10087785B2 (en) | 2015-02-09 | 2018-10-02 | United Technologies Corporation | Mid-turbine frame assembly for a gas turbine engine |
US9803502B2 (en) | 2015-02-09 | 2017-10-31 | United Technologies Corporation | Cooling passages for a mid-turbine frame |
US9951624B2 (en) | 2015-02-09 | 2018-04-24 | United Technologies Corporation | Clinch nut bolt hole geometry |
US9920641B2 (en) | 2015-02-23 | 2018-03-20 | United Technologies Corporation | Gas turbine engine mid-turbine frame configuration |
US9476443B2 (en) | 2015-02-25 | 2016-10-25 | Gallagher Group Limited | Nut and washer assembly |
US9869204B2 (en) | 2015-03-06 | 2018-01-16 | United Technologies Corporation | Integrated inner case heat shield |
US9879604B2 (en) | 2015-03-11 | 2018-01-30 | United Technologies Corporation | Cooling passages for a mid-turbine frame |
US9915170B2 (en) | 2015-03-20 | 2018-03-13 | United Technologies Corporation | Cooling passages for a mid-turbine frame |
US9732628B2 (en) | 2015-03-20 | 2017-08-15 | United Technologies Corporation | Cooling passages for a mid-turbine frame |
US9822666B2 (en) | 2015-04-06 | 2017-11-21 | United Technologies Corporation | Quad-tab U-washer |
US9822667B2 (en) | 2015-04-06 | 2017-11-21 | United Technologies Corporation | Tri-tab lock washer |
US10443440B2 (en) | 2015-04-09 | 2019-10-15 | United Technologies Corporation | Heat shield, systems and methods |
US9885254B2 (en) | 2015-04-24 | 2018-02-06 | United Technologies Corporation | Mid turbine frame including a sealed torque box |
US10975721B2 (en) | 2016-01-12 | 2021-04-13 | Pratt & Whitney Canada Corp. | Cooled containment case using internal plenum |
CN105805143A (zh) | 2016-04-05 | 2016-07-27 | 刘凤翼 | 一种无纹防松脱自紧螺栓 |
-
2016
- 2016-07-11 US US15/206,579 patent/US10443449B2/en active Active
- 2016-07-12 WO PCT/CA2016/050818 patent/WO2017015745A1/en active Application Filing
- 2016-07-12 CA CA2935994A patent/CA2935994C/en active Active
- 2016-07-12 CN CN201680043510.4A patent/CN107849939B/zh active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100132376A1 (en) * | 2008-11-28 | 2010-06-03 | Pratt & Whitney Canada Corp. | Mid turbine frame for gas turbine engine |
CN103306818A (zh) * | 2012-03-05 | 2013-09-18 | 通用电气公司 | 燃气涡轮机架加强轨 |
US20140013770A1 (en) * | 2012-07-13 | 2014-01-16 | United Technologies Corporation | Vane insertable tie rods with keyed connections |
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