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1. 发明申请

US20090084109A1 Fuel nozzle of gas turbine combustor for DME and design method thereof 有权
标题翻译： DME燃气轮机燃油喷嘴及其设计方法
公开(公告)号：US20090084109A1
公开(公告)日：2009-04-02
申请号：US12215159
申请日：2008-06-25
申请人： Min Chul Lee , Dal Hong Ahn , Yong Jin Joo , Seok Bin Seo , Jae Hwa Chung , Won Shik Park , Hae Kyung Seo
发明人： Min Chul Lee , Dal Hong Ahn , Yong Jin Joo , Seok Bin Seo , Jae Hwa Chung , Won Shik Park , Hae Kyung Seo
IPC分类号： F02C7/22 , B05B1/14
CPC分类号： F23R3/286 , F23R3/12
摘要： Disclosed herein are a fuel nozzle of a gas turbine combustor for dimethyl ether (DME, CH3OCH3) and a design method thereof. The fuel nozzle includes a pilot fuel injection hole formed at the center of the nozzle and a plurality of fuel injection ports formed at equiangular positions around the pilot fuel injection hole to inject DME. Each of the fuel injection ports includes a pair of upper and lower DME injection orifices communicating with a fuel-air mixture injection swirler. The upper DME injection orifice becomes gradually wider, whereas the lower DME injection orifice becomes gradually narrower. Thus, DME can be optimally combusted in the gas turbine combustor, thereby achieving cost reduction of power plants, enhancement in reliability of the power plants, and diversification of usable fuel.
摘要翻译：本文公开了一种用于二甲醚（DME，CH 3 OCH 3）的燃气轮机燃烧器的燃料喷嘴及其设计方法。燃料喷嘴包括形成在喷嘴中心处的先导燃料喷射孔和形成在引燃燃料喷射孔附近的等角位置处的多个燃料喷射口以喷射DME。每个燃料喷射口包括与燃料 - 空气混合物喷射旋流器连通的一对上部和下部DME喷射孔。上部DME喷射孔逐渐变宽，而下部DME喷射孔逐渐变窄。因此，DME可以在燃气轮机燃烧器中最佳地燃烧，从而实现发电厂的成本降低，发电厂的可靠性提高，以及可用燃料的多样化。

2. 发明授权

US08132415B2 Fuel nozzle of gas turbine combustor for DME and design method thereof 有权
标题翻译： DME燃气轮机燃油喷嘴及其设计方法
公开(公告)号：US08132415B2
公开(公告)日：2012-03-13
申请号：US12215159
申请日：2008-06-25
申请人： Min Chul Lee , Dal Hong Ahn , Yong Jin Joo , Seok Bin Seo , Jae Hwa Chung , Won Shik Park , Hae Kyung Seo
发明人： Min Chul Lee , Dal Hong Ahn , Yong Jin Joo , Seok Bin Seo , Jae Hwa Chung , Won Shik Park , Hae Kyung Seo
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/286 , F23R3/12
摘要： Disclosed herein are a fuel nozzle of a gas turbine combustor for dimethyl ether (DME, CH3OCH3) and a design method thereof. The fuel nozzle includes a pilot fuel injection hole formed at the center of the nozzle and a plurality of fuel injection ports formed at equiangular positions around the pilot fuel injection hole to inject DME. Each of the fuel injection ports includes a pair of upper and lower DME injection orifices communicating with a fuel-air mixture injection swirler. The upper DME injection orifice becomes gradually wider, whereas the lower DME injection orifice becomes gradually narrower. Thus, DME can be optimally combusted in the gas turbine combustor, thereby achieving cost reduction of power plants, enhancement in reliability of the power plants, and diversification of usable fuel.
摘要翻译：本文公开了一种用于二甲醚（DME，CH 3 OCH 3）的燃气轮机燃烧器的燃料喷嘴及其设计方法。燃料喷嘴包括形成在喷嘴中心处的先导燃料喷射孔和形成在引燃燃料喷射孔附近的等角位置处的多个燃料喷射口以喷射DME。每个燃料喷射口包括与燃料 - 空气混合物喷射旋流器连通的一对上部和下部DME喷射孔。上部DME喷射孔逐渐变宽，而下部DME喷射孔逐渐变窄。因此，DME可以在燃气轮机燃烧器中最佳地燃烧，从而实现发电厂的成本降低，发电厂的可靠性提高，以及可用燃料的多样化。

3. 发明授权

US08291708B2 Combustor and multi combustor including the combustor, and combusting method 有权
标题翻译：包括燃烧器的燃烧器和多燃烧器，以及燃烧方法
公开(公告)号：US08291708B2
公开(公告)日：2012-10-23
申请号：US11928522
申请日：2007-10-30
申请人： Min-Chul Lee , Jae-Hwa Chung , Seok-Bin Seo , Yong-Jin Joo , Jong-Jin Kim , Dal-Hong Ahn
发明人： Min-Chul Lee , Jae-Hwa Chung , Seok-Bin Seo , Yong-Jin Joo , Jong-Jin Kim , Dal-Hong Ahn
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/14 , F23C7/004 , F23D14/58 , F23D14/60 , F23D17/002 , F23R3/286 , F23R3/36
摘要： A dual fuel nozzle of a gas turbine combustor with a variable jetting hole diameter is disclosed. The combustor includes a plurality of swirling wings disposed along an outer peripheral surface of a central shaft to have at least one main fuel jetting hole, an air duct positioned at the lower side of the swirling wings to supply air to the swirling wings, a pilot fuel injection hole and jetting hole formed to pass through a central portion of the central shaft to supply a pilot fuel, a switching plate disposed inside the swirling wings to vary the size of the main fuel jetting hole, a driving unit disposed to be connected to the switching plate to move a position of the switching plate, and a casing containing the swirling wings, the air duct, the switching plate and the driving unit. It is possible to enhance fuel flexibility in a multiple fuel system for applying two or more fuels to a gas turbine at the same time.
摘要翻译：公开了具有可变喷射孔直径的燃气轮机燃烧器的双燃料喷嘴。燃烧器包括沿着中心轴的外周表面设置的多个旋转翼，具有至少一个主燃料喷射孔，位于旋转翼的下侧的空气管，以向旋转翼供应空气;飞行员燃料喷射孔和喷射孔，其形成为穿过中心轴的中心部分以供应引燃燃料;转换板，设置在旋转翼内部，以改变主燃料喷射孔的尺寸;驱动单元，设置成连接到所述切换板移动所述切换板的位置，以及壳体，其容纳所述旋转翼，所述风道，所述切换板和所述驱动单元。可以提高多燃料系统中的燃料灵活性，以同时向燃气轮机施加两种或更多种燃料。

4. 发明申请

US20080098736A1 COMBUSTOR AND MULTI COMBUSTOR INCLUDING THE COMBUSTOR, AND COMBUSTING METHOD 有权
标题翻译： COMBUSTOR和多个燃烧器，包括燃烧器和燃烧方法
公开(公告)号：US20080098736A1
公开(公告)日：2008-05-01
申请号：US11928522
申请日：2007-10-30
申请人： Min-Chul LEE , Jae-Hwa Chung , Seok-Bin Seo , Yong-Jin Joo , Jong-Jin Kim , Dal-Hong Ahn
发明人： Min-Chul LEE , Jae-Hwa Chung , Seok-Bin Seo , Yong-Jin Joo , Jong-Jin Kim , Dal-Hong Ahn
IPC分类号： F02C9/26 , F23R3/04
CPC分类号： F23R3/14 , F23C7/004 , F23D14/58 , F23D14/60 , F23D17/002 , F23R3/286 , F23R3/36
摘要： A dual fuel nozzle of a gas turbine combustor with a variable jetting hole diameter is disclosed. The combustor includes a plurality of swirling wings disposed along an outer peripheral surface of a central shaft to have at least one main fuel jetting hole, an air duct positioned at the lower side of the swirling wings to supply air to the swirling wings, a pilot fuel injection hole and jetting hole formed to pass through a central portion of the central shaft to supply a pilot fuel, a switching plate disposed inside the swirling wings to vary the size of the main fuel jetting hole, a driving unit disposed to be connected to the switching plate to move a position of the switching plate, and a casing containing the swirling wings, the air duct, the switching plate and the driving unit. It is possible to enhance fuel flexibility in a multiple fuel system for applying two or more fuels to a gas turbine at the same time.
摘要翻译：公开了具有可变喷射孔直径的燃气轮机燃烧器的双燃料喷嘴。燃烧器包括沿着中心轴的外周表面设置的多个旋转翼，具有至少一个主燃料喷射孔，位于旋转翼的下侧的空气管，以向旋转翼供应空气;飞行员燃料喷射孔和喷射孔，其形成为穿过中心轴的中心部分以供应引燃燃料;转换板，设置在旋转翼内部，以改变主燃料喷射孔的尺寸;驱动单元，设置成连接到所述切换板移动所述切换板的位置，以及壳体，其容纳所述旋转翼，所述风道，所述切换板和所述驱动单元。可以提高多燃料系统中的燃料灵活性，以同时向燃气轮机施加两种或更多种燃料。

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