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1.发明授权Tangential annular combustor with premixed fuel and air for use on gas turbine engines 有权具有预混燃料和空气的切向环形燃烧器用于燃气涡轮发动机公开(公告)号：US09052114B1
公开(公告)日：2015-06-09
申请号：US12771338
申请日：2010-04-30
CPC分类号： F23R3/286 , F23R3/04 , F23R3/346 , F23R3/58 , F23R2900/00015 , Y02T50/675
摘要： A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes an annular combustor with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air. The fuel and air inlets are placed at various longitudinal locations circumferentially, and can take on different configurations where all nozzles inject a fuel-air mixture or some may inject only air. The combustion device provides an optimal mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions reducing the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, allows increased fuel flexibility, decreases the required size of the first stage nozzle guide vane (NGV), and improves vibration reduction.
摘要翻译： 燃气涡轮发动机中用于产生推进或旋转轴用于发电的燃烧装置包括具有燃料和空气入口通道和喷嘴系统的环形燃烧器，其导致预混燃料和空气的分段燃烧。 燃料和空气入口沿周向放置在各种纵向位置，并且可以具有不同的构造，其中所有喷嘴喷射燃料 - 空气混合物，或者一些喷射器只能注入空气。 燃烧装置提供燃料和空气的最佳混合，产生燃烧环境，减少污染物排放，减少对昂贵的污染控制装置的需要，增强点燃和火焰稳定性，减少导引问题，允许增加燃料灵活性，减少所需尺寸 第一级喷嘴引导叶片（NGV），并改善振动。
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2.发明授权Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines 有权具有用于燃气涡轮发动机的预混合切向燃料 - 空气喷嘴的罐形环形燃烧器公开(公告)号：US09181812B1
公开(公告)日：2015-11-10
申请号：US12772398
申请日：2010-05-03
CPC分类号： F23R3/34 , F01D9/02 , F01D9/023 , F02C3/34 , F05D2220/32 , F23C6/045 , F23R3/286 , F23R3/46 , F23R2900/00014
摘要： A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes a can-annular combustor with a system of fuel and air inlet passages and nozzles that results in an optimal combustion environment of premixed fuel and air. The fuel-air inlets are placed at various longitudinal locations and circumferentially distributed, and direct the flow tangentially or nearly tangent to the can liner. The combustion device provides effective mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions, reduces the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, and improves vibration reduction.
摘要翻译： 用于燃气涡轮发动机以产生推进或旋转轴用于发电的燃烧装置包括具有燃料和空气入口通道和喷嘴系统的罐环式燃烧器，其导致预混燃料和空气的最佳燃烧环境。 燃料空气入口被放置在各种纵向位置并且周向分布，并且使流动与罐衬里切向或几乎相切。 燃烧装置提供燃料和空气的有效混合，产生燃烧环境，减少污染物排放，减少对昂贵的污染控制装置的需要，增强点燃和火焰稳定性，减少驾驶问题，并改善振动减少。
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3.发明授权Can-annular combustor with staged and tangential fuel-air nozzles for use on gas turbine engines 有权罐式环形燃烧器，具有用于燃气涡轮发动机的分段和切向燃料 - 空气喷嘴公开(公告)号：US08739511B1
公开(公告)日：2014-06-03
申请号：US12772353
申请日：2010-05-03
IPC分类号： F02C3/00
摘要： A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes a can-annular combustor with a system of fuel and air inlet passages and nozzles that results in an optimal combustion environment of fuel and air. Fuel, air and/or fuel-air inlets are placed at various longitudinal locations and circumferentially distributed, and direct the flow tangentially or nearly tangent to the can liner. The combustion device provides an optimal mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions, reduces the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, and improves vibration reduction.
摘要翻译： 燃气涡轮发动机中用于产生推进或旋转轴用于发电的燃烧装置包括具有燃料和空气入口通道和喷嘴系统的罐环式燃烧器，其导致燃料和空气的最佳燃烧环境。 燃料，空气和/或燃料空气入口被放置在各种纵向位置并且周向分布，并且引导流动与罐衬里切向或几乎相切。 燃烧装置提供燃料和空气的最佳混合，创造一种减少污染物排放的燃烧环境，减少对昂贵污染控制装置的需求，增强点火和火焰稳定性，减少驾驶问题，并改善振动减少。
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4.发明授权公开(公告)号：US09091446B1
公开(公告)日：2015-07-28
申请号：US12771269
申请日：2010-04-30
CPC分类号： F23R3/58 , F23R3/04 , F23R3/286 , F23R3/34 , F23R3/346 , Y02E20/342 , Y02E20/344 , Y02T50/675
摘要： A combustion device used in gas turbine engines that produces propulsion or rotates a shaft for power generation includes an annular combustor with a system of fuel and air inlet passages and nozzles that results in a flameless combustor, such that there is not an anchored flame as in typical gas turbine combustors. The fuel and air inlets are placed at various longitudinal locations and circumferentially spaced, and take on several different configurations where some nozzles inject only air and others inject a rich fuel-air mixture. The combustion device provides an optimal mixing of fuel and air as well as creates an environment for combustion that reduces pollutant emissions reducing the need for costly pollution control devices, and enhances ignition and flame stability, reduces piloting issues and improves vibration reduction.
摘要翻译： 用于产生推进或旋转轴用于发电的燃气涡轮发动机中的燃烧装置包括具有燃料和空气入口通道和喷嘴系统的环形燃烧器，其导致无焰燃烧器，使得不存在锚定的火焰，如 典型的燃气轮机燃烧器。 燃料和空气入口被放置在各种纵向位置并且周向间隔开，并且具有几种不同的构造，其中一些喷嘴仅喷射空气，而其它喷嘴注入富燃料 - 空气混合物。 燃烧装置提供燃料和空气的最佳混合，并且产生燃烧环境，其减少污染物排放，减少对昂贵的污染控制装置的需要，并且增强点燃和火焰稳定性，减少驾驶问题并改善减振。
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5.发明授权公开(公告)号：US08904799B2
公开(公告)日：2014-12-09
申请号：US12786882
申请日：2010-05-25
摘要： A combustion device used in gas turbine engines includes an annular combustor that contains the combustion process of air and fuel and then guides the hot gas products to a first stage turbine subsection of a gas turbine engine. The annular combustor has an inner/outer shell having corrugated surfaces that extend radially outward and inward across an entire hot gas stream inside the annular combustor. The corrugations twist about the engine centerline in a longitudinal direction of travel of the engine. The resulting flow path accelerates and turns the hot gas stream to conditions suitable for introduction into the first stage turbine blades, which eliminate the need for first stage turbine vanes. The annular combustor is configured with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air.
摘要翻译： 在燃气涡轮发动机中使用的燃烧装置包括环形燃烧器，其包含空气和燃料的燃烧过程，然后将热气体产物引导到燃气涡轮发动机的第一级涡轮机部分。 环形燃烧器具有内/外壳，其具有波纹表面，其在环形燃烧器内部的整个热气流径向向外和向内延伸。 波纹在发动机的纵向方向上绕发动机中心线扭转。 所产生的流动路径加速并将热气流转化成适合于引入第一级涡轮叶片的条件，这消除了对第一级涡轮叶片的需要。 环形燃烧器配置有导致预混合燃料和空气的分段燃烧的燃料和空气入口通道和喷嘴的系统。
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6.发明申请TANGENTIAL COMBUSTOR WITH VANELESS TURBINE FOR USE ON GAS TURBINE ENGINES 有权带涡轮发动机用的无风轮的TANGENTIAL COMBUSTOR公开(公告)号：US20110209482A1
公开(公告)日：2011-09-01
申请号：US12786882
申请日：2010-05-25
摘要： A combustion device used in gas turbine engines includes an annular combustor that contains the combustion process of air and fuel and then guides the hot gas products to a first stage turbine subsection of a gas turbine engine. The annular combustor has an inner/outer shell having corrugated surfaces that extend radially outward and inward across an entire hot gas stream inside the annular combustor. The corrugations twist about the engine centerline in a longitudinal direction of travel of the engine. The resulting flow path accelerates and turns the hot gas stream to conditions suitable for introduction into the first stage turbine blades, which eliminate the need for first stage turbine vanes. The annular combustor is configured with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air.
摘要翻译： 在燃气涡轮发动机中使用的燃烧装置包括环形燃烧器，其包含空气和燃料的燃烧过程，然后将热气体产物引导到燃气涡轮发动机的第一级涡轮机部分。 环形燃烧器具有内/外壳，其具有波纹表面，其在环形燃烧器内部的整个热气流径向向外和向内延伸。 波纹在发动机的纵向方向上绕发动机中心线扭转。 所产生的流动路径加速并将热气流转化成适合于引入第一级涡轮叶片的条件，这消除了对第一级涡轮叶片的需要。 环形燃烧器配置有导致预混合燃料和空气的分段燃烧的燃料和空气入口通道和喷嘴的系统。
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