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1. 发明申请

US20150121885A1 Gas Turbine Combustor 审中-公开
标题翻译：燃气轮机燃烧器
公开(公告)号：US20150121885A1
公开(公告)日：2015-05-07
申请号：US14531253
申请日：2014-11-03
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Osami YOKOTA , Masataka HIDAKA , Shohei NUMATA , Tetsuma TATSUMI
IPC分类号： F23R3/06 , F23R3/00
CPC分类号： F23R3/06 , F05D2260/202 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F23R3/002 , F23R3/005 , F23R3/54 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03045
摘要： There is provided a gas turbine combustor that achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural intensity.A gas turbine combustor structure includes a plurality of circularity recesses 20 formed on a side of an annular passage 11 on a partial area of a combustion liner 8 that requires cooling. The circularity recesses 20 each have a rectangular surface 25 forming a convex at a right angle with respect to a flowing direction of combustion air 2. The circularity recesses 20 is a rectangular triangle having an oblique surface 26 facing upstream of the flowing direction of the combustion air 2.
摘要翻译：提供了一种燃气轮机燃烧器，其通过在冷却特性和结构强度上的改进来实现提高的产品可靠性和减小的压力损失增加。燃气轮机燃烧器结构包括形成在需要冷却的燃烧衬套8的局部区域上的环形通道11的侧面上的多个圆形凹部20。圆形凹部20各自具有相对于燃烧用空气2的流动方向成直角的矩形的表面25.圆形凹部20是具有朝向燃烧流动方向的上游侧的倾斜面26的矩形三角形空气2。

2. 发明申请

US20160069566A1 GAS TURBINE COMBUSTOR 审中-公开
标题翻译：气体涡轮搅拌机
公开(公告)号：US20160069566A1
公开(公告)日：2016-03-10
申请号：US14845600
申请日：2015-09-04
申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.
发明人： Shohei NUMATA , Osami YOKOTA , Tetsuma TATSUMI
IPC分类号： F23R3/00 , F23R3/12
摘要： A gas turbine combustor includes a combustor liner, a flow sleeve in which the combustor liner is provided and an annular flow passage formed between the combustor liner and the flow sleeve, through which compressed air flows. The flow sleeve includes an internal-diameter changing portion diagonally connected to the flow sleeve and an internal-diameter reducing portion connected to the internal-diameter changing portion and extending along the flow direction of the compressed air. The combustor liner includes an annular protruding portion annularly formed on an outer wall of the combustor liner and protruding toward the flow sleeve. The annular protruding portion is located at a position on the outer wall of the combustion liner, the position facing a connection position between the flow sleeve and the internal-diameter changing portion or being at an upstream side of the position facing the connection position in the flow direction of the compressed air.
摘要翻译：燃气轮机燃烧器包括燃烧器衬套，其中设置燃烧器衬套的流动套筒和形成在燃烧器衬套和流动套筒之间的环形流动通道，压缩空气通过该套筒流动。流动套管包括与流动套筒对角连接的内径变更部分和连接到内径变化部分并沿着压缩空气的流动方向延伸的内径减小部分。燃烧器衬套包括环形突出部分，环形地形成在燃烧器衬套的外壁上并向着流动套筒突出。环形突出部分位于燃烧衬套的外壁上的位置，该位置面向流动套管和内径可变部分之间的连接位置，或位于面向连接位置的位置的上游侧压缩空气的流动方向。

3. 发明申请

US20150369486A1 Heat-Transfer Device and Gas Turbine Combustor with Same 审中-公开
标题翻译：传热装置和燃气轮机燃烧器
公开(公告)号：US20150369486A1
公开(公告)日：2015-12-24
申请号：US14742962
申请日：2015-06-18
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Osami YOKOTA , Shohei NUMATA , Tomomi KOGANEZAWA , Tetsuma TATSUMI
IPC分类号： F23R3/00 , F15D1/00
CPC分类号： F23R3/005 , F15D1/009 , F23R3/002 , F23R3/54 , F23R2900/03044 , F23R2900/03045
摘要： Disclosed is a heat-transfer device adapted to enhance uniformity of cooling characteristics to be given to a heat transfer object, and thereby to extend a life of the heat transfer object. The heat-transfer device for facilitating heat exchange between combustion air (heat transfer medium) flowing along an outer surface of a combustor liner (heat transfer object), and the combustor liner, the heat-transfer device including at least one longitudinal vortex generating device protruding toward a annular passage (flow passage) of the combustion air and formed to generate a longitudinal vortex E with a central axis in a flow direction of the combustion air, and stir the combustion air flowing in the annular passage; and at least one radiator fin provided in a region A on the outer surface of the combustor liner, the region A being where a flow of the vortex E, on a swirling plane thereof, that are generated by the vortex generating device is directed from a side of the combustor liner, toward a side of a flow sleeve, the fin exchanging heat with the combustion air stirred by the vortex generating device.
摘要翻译：公开了一种热传递装置，其适于提高给予传热物体的冷却特性的均匀性，从而延长传热物体的寿命。用于促进沿着燃烧器衬套（传热物体）的外表面流动的燃烧空气（传热介质）与燃烧器衬套之间的热交换的热传递装置，所述传热装置包括至少一个纵向涡流产生装置朝向燃烧空气的环形通道（流动通道）突出并形成以产生在燃烧空气的流动方向上具有中心轴线的纵向涡流E，并搅拌在环形通道中流动的燃烧空气; 以及设置在燃烧器衬套的外表面上的区域A中的至少一个散热器翅片，区域A是由涡流产生装置产生的涡流E在其旋转平面上的流动从一个燃烧器衬套的侧面朝向流动套筒的一侧，翅片与由涡流产生装置搅动的燃烧空气交换热量。

4. 发明申请

US20150113998A1 Gas Turbine Combustor and Gas Turbine Combustor Control Method 审中-公开
标题翻译：燃气轮机燃烧器和燃气轮机燃烧器控制方法
公开(公告)号：US20150113998A1
公开(公告)日：2015-04-30
申请号：US14522006
申请日：2014-10-23
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Tetsuma TATSUMI , Shohei NUMATA , Osami YOKOTA
IPC分类号： F02C9/34 , F23N1/00 , F23R3/16 , F23R3/46 , F23R3/00
CPC分类号： F02C9/34 , F05D2270/082 , F05D2270/112 , F05D2270/301 , F05D2270/44 , F23N1/00 , F23N5/18 , F23N2025/06 , F23N2035/12 , F23N2037/02 , F23N2041/20 , F23R3/002 , F23R3/16 , F23R3/286 , F23R3/46 , F23R2900/03043
摘要： The burners include a central burner and a plurality of outer burners disposed around the central burner. Each of the outer burners is equipped with a fuel supply system that includes a fuel flow regulating valve. The outer circumference of the combustor liner is provided with a cylindrical flow sleeve. At least one flow velocity measurement unit is disposed in a circular flow path formed between the combustor liner and the flow sleeve to measure the flow velocity of air flowing downward. The gas turbine combustor also includes a control device that adjusts the fuel flow rate of the fuel, which is to be supplied to the outer burners, in accordance with the flow velocity of the air in the circular flow path, which is measured by the flow velocity measurement units.
摘要翻译：燃烧器包括中央燃烧器和围绕中央燃烧器设置的多个外燃烧器。每个外燃烧器配备有包括燃料流量调节阀的燃料供应系统。燃烧器衬套的外周设有圆柱形流动套管。至少一个流速测量单元设置在形成在燃烧器衬套和流动套筒之间的圆形流动路径中，以测量向下流动的空气的流速。燃气轮机燃烧器还包括控制装置，该控制装置根据由流动测量的圆形流动路径中的空气的流速来调节要供给到外部燃烧器的燃料的燃料流量速度测量单位。

5. 发明申请

US20150101336A1 Cooling Structure for Gas Turbine Combustor Liner 有权
标题翻译：燃气轮机燃烧器衬套的冷却结构
公开(公告)号：US20150101336A1
公开(公告)日：2015-04-16
申请号：US14511260
申请日：2014-10-10
申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.
发明人： Shohei NUMATA , Osami YOKOTA , Tetsuma TATSUMI , Akinori HAYASHI
IPC分类号： F23R3/44
CPC分类号： F23R3/44 , F23R3/005 , F23R3/16 , F23R3/54 , F23R2900/03045
摘要： A gas turbine combustor is provided in which product reliability and heat transfer promotion are compatible while suppressing an increase in pressure loss.In a gas turbine combustor comprising a combustor liner, an outer tube provided around an outer periphery of the combustor liner, and an annular flow passage in which a cooling medium (cooling air) flows and which is formed between an outer surface of the combustor liner and an inner surface of the outer tube, the outer tube includes an inner diameter reduced portion and a taper portion smoothly connecting the inner diameter reduced portion and an inner peripheral portion on an upstream side, and is provided at an inner surface of the taper portion with longitudinal vortex generating means generating a vortex that has a central rotation axis in a flowing direction of the cooling medium (cooling air).
摘要翻译：提供了一种燃气轮机燃烧器，其中在抑制压力损失增加的同时，产品可靠性和传热促进相容。在包括燃烧器衬套的燃气轮机燃烧器中，设置在燃烧器衬套的外周周围的外管和冷却介质（冷却空气）流过的环形流动通道，其形成在燃烧器衬套的外表面之间外管的内表面，外管包括内径减小部分和平滑地连接内径减小部分和上游侧的内周部分的锥形部分，并且设置在锥形部分的内表面纵向涡流产生装置产生在冷却介质（冷却空气）的流动方向上具有中心旋转轴线的涡流。

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