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1.发明授权公开(公告)号：US08297037B2
公开(公告)日：2012-10-30
申请号：US12933870
申请日：2008-12-01
IPC分类号： F02C3/00
CPC分类号： F23R3/002 , F02C3/14 , F02C7/20 , F23R3/60 , F23R2900/00017 , Y10T29/49231
摘要： A gas turbine includes a combustor, a combustor casing formed in a cylindrical shape to house the combustor therein, and a combustor insertion hole, which is a hole formed on a side periphery of the combustor casing, where a size thereof in a direction orthogonal to a circumferential direction of the combustor casing is formed larger than that in the circumferential direction of the combustor casing, and when the combustor inserted into the hole, a member moved together with the combustor, and the hole are viewed from a moving direction of the combustor, the hole includes an entire external form of the combustor and the member moved together with the combustor.
摘要翻译： 燃气轮机包括：燃烧器，形成为筒状的燃烧器壳体，用于容纳燃烧器;以及燃烧器插入孔，该燃烧器插入孔形成在燃烧器壳体的侧周上， 燃烧器壳体的圆周方向形成为大于燃烧器壳体的圆周方向的周向，并且当燃烧器插入孔中时，与燃烧器一起移动的构件和孔从燃烧器的移动方向观察 ，该孔包括燃烧器的整个外部形式，并且该构件与燃烧器一起移动。
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2.发明申请公开(公告)号：US20110016865A1
公开(公告)日：2011-01-27
申请号：US12933870
申请日：2008-12-01
CPC分类号： F23R3/002 , F02C3/14 , F02C7/20 , F23R3/60 , F23R2900/00017 , Y10T29/49231
摘要： A gas turbine includes a combustor, a combustor casing formed in a cylindrical shape to house the combustor therein, and a combustor insertion hole, which is a hole formed on a side periphery of the combustor casing, where a size thereof in a direction orthogonal to a circumferential direction of the combustor casing is formed larger than that in the circumferential direction of the combustor casing, and when the combustor inserted into the hole, a member moved together with the combustor, and the hole are viewed from a moving direction of the combustor, the hole includes an entire external form of the combustor and the member moved together with the combustor.
摘要翻译： 燃气轮机包括：燃烧器，形成为筒状的燃烧器壳体，用于容纳燃烧器;以及燃烧器插入孔，该燃烧器插入孔形成在燃烧器壳体的侧周上， 燃烧器壳体的圆周方向形成为大于燃烧器壳体的圆周方向的周向，并且当燃烧器插入孔中时，与燃烧器一起移动的构件和从燃烧器的移动方向观察孔 ，该孔包括燃烧器的整个外部形式，并且该构件与燃烧器一起移动。
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3.发明授权Combustor-transition-piece guide jig and method of detaching and attaching combustor of gas turbine 有权燃烧器 - 过渡件导向夹具及燃气轮机分离与安装方法公开(公告)号：US08607451B2
公开(公告)日：2013-12-17
申请号：US12919051
申请日：2009-01-26
CPC分类号： F01D25/285 , F01D9/023 , F05D2230/64 , F05D2230/70 , F23R3/60 , F23R2900/00017
摘要： A combustor-transition-piece guide jig is constituted by two rails, a fixing member, and a holding member. The fixing member is provided at one ends of the rails and attached to a combustor attachment port. The rails are inserted from the combustor attachment port toward inside of the combustor casing and fixed to the combustor attachment port by the fixing member. The rails come into contact with a combustor-transition-piece guiding part provided on a combustor transition piece to guide a movement of the combustor transition piece in one direction.
摘要翻译： 燃烧器 - 过渡件引导夹具由两个轨道，固定构件和保持构件构成。 固定构件设置在轨道的一端并附接到燃烧器附接口。 轨道从燃烧器附件端口朝向燃烧器壳体的内部插入并通过固定构件固定到燃烧器附接口。 导轨与设置在燃烧器过渡件上的燃烧器 - 过渡件引导部分接触，以引导燃烧器过渡件在一个方向上的移动。
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4.发明申请COMBUSTOR-TRANSITION-PIECE GUIDE JIG AND METHOD OF DETACHING AND ATTACHING COMBUSTOR OF GAS TURBINE 有权燃气轮机转向指南和拆卸和连接气体涡轮机的方法公开(公告)号：US20110000080A1
公开(公告)日：2011-01-06
申请号：US12919051
申请日：2009-01-26
IPC分类号： B23P19/00
CPC分类号： F01D25/285 , F01D9/023 , F05D2230/64 , F05D2230/70 , F23R3/60 , F23R2900/00017
摘要： A combustor-transition-piece guide jig is constituted by two rails, a fixing member, and a holding member. The fixing member is provided at one ends of the rails and attached to a combustor attachment port. The rails are inserted from the combustor attachment port toward inside of the combustor casing and fixed to the combustor attachment port by the fixing member. The rails come into contact with a combustor-transition-piece guiding part provided on a combustor transition piece to guide a movement of the combustor transition piece in one direction.
摘要翻译： 燃烧器 - 过渡件引导夹具由两个轨道，固定构件和保持构件构成。 固定构件设置在轨道的一端并附接到燃烧器附接口。 轨道从燃烧器附件端口朝向燃烧器壳体的内部插入并通过固定构件固定到燃烧器附接口。 导轨与设置在燃烧器过渡件上的燃烧器 - 过渡件引导部分接触，以引导燃烧器过渡件在一个方向上的移动。
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5.发明申请COMBUSTOR CONNECTION STRUCTURE, COMBUSTOR TRANSITION PIECE, DESIGNING METHOD OF COMBUSTOR TRANSITION PIECE, AND GAS TURBINE 有权COMBUSTOR连接结构，COMBUSTOR过渡片，COMBUSTOR TRANSITION PIECE和燃气轮机的设计方法公开(公告)号：US20110265491A1
公开(公告)日：2011-11-03
申请号：US12674352
申请日：2009-04-23
申请人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
发明人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
CPC分类号： F01D9/023 , F05D2250/50 , F23R3/46 , F23R3/60 , F23R2900/00017 , F23R2900/00018 , Y02E20/16 , Y10T29/49229 , Y10T29/49348
摘要： Provided is a combustor connection structure in which a cross-sectional area (Dout) of a transition piece outlet (222) is set within a range of 0.79≦Dout/Din≦0.9, relative to a cross-sectional area (Din) of a transition piece inlet (221) of a combustor (2), and in a first stage turbine nozzle (321) of a turbine (3) connected to the transition piece outlet (222), a size (Hin) in a radial direction of an upstream opening is matched with a size (a) in a radial direction of the transition piece outlet (222). In a combustor transition piece (22) that is included in the combustor (2) having a center line (S) arranged with an angle to an axial center (R) of a rotor (4) of a gas turbine and that guides combustion gas to the turbine (3), a cross-sectional area is monotonously reduced from the transition piece inlet (221) in which the combustion gas flows to the transition piece outlet (222) from which the combustion gas flows out.
摘要翻译： 提供了一种燃烧器连接结构，其中过渡件出口（222）的横截面面积（Dout）设定在0.79
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公开(公告)号：US08448451B2
公开(公告)日：2013-05-28
申请号：US12674352
申请日：2009-04-23
申请人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
发明人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
CPC分类号： F01D9/023 , F05D2250/50 , F23R3/46 , F23R3/60 , F23R2900/00017 , F23R2900/00018 , Y02E20/16 , Y10T29/49229 , Y10T29/49348
摘要： Provided is a combustor connection structure in which a cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79≦Dout/Din≦0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in a radial direction between upstream ends of the inner shroud and the outer shroud has a same dimension as a size (a) in a radial direction of the transition piece outlet. In a combustor transition piece that is included in the combustor having a center line (S) arranged with an angle to an axial center (R) of a rotor of a gas turbine and that guides combustion gas to the turbine, a cross-sectional area is monotonously reduced from the transition piece inlet in which the combustion gas flows to the transition piece outlet from which the combustion gas flows out.
摘要翻译： 提供了一种燃烧器连接结构，其中过渡件出口的横截面积（Dout）相对于过渡件入口的横截面面积（Din）设定在0.79 @ Dout / Din @ 0.9的范围内 并且在连接到过渡件出口的涡轮机的第一级涡轮喷嘴中，在内护罩和外护罩的上游端之间的径向方向上的尺寸（Hin）具有与尺寸相同的尺寸（a ）在过渡件出口的径向方向上。 在包括在具有与燃气轮机的转子的轴向中心（R）成一角度的中心线（S））并且将燃烧气体引导到涡轮机的燃烧器中的燃烧器过渡件中，横截面积 从燃烧气体流过到燃烧气体流出的过渡件出口的过渡件入口单调地减少。
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