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公开(公告)号：US5615546A
公开(公告)日：1997-04-01
申请号：US323688
申请日：1994-10-17
CPC分类号： F23R3/002 , F05B2260/20 , F05B2260/201
摘要： In a gas turbine combustion chamber cooled by means of impingement and convection cooling or pure convection cooling, a compensating flow of the cooling air is guided between adjacent cooling ducts (2) in such a way that the flow velocity in the cooling duct (2) always exceeds a critical limiting value even downstream of a local damage location (6) so that the temperature is less than a critical limiting value. The compensating flow is led past the combustion chamber outer wall. Connecting openings (5) are arranged between adjacent cooling ducts (2) and are respectively offset on the opposite sides of the cooling duct (2).
摘要翻译： 在通过冲击和对流冷却或纯对流冷却冷却的燃气轮机燃烧室中，冷却空气的补偿流在相邻的冷却管道（2）之间被引导，使得冷却管道（2）中的流速 总是超过临界极限值，甚至在局部损伤位置（6）的下游，使得温度小于临界极限值。 补偿流通过燃烧室外壁。 连接开口（5）设置在相邻的冷却管道（2）之间，并分别偏置在冷却管道（2）的相对侧上。
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公开(公告)号：US5651253A
公开(公告)日：1997-07-29
申请号：US699731
申请日：1996-08-20
CPC分类号： F23R3/002 , F05B2260/20 , F05B2260/201
摘要： In a gas turbine combustion chamber cooled by means of impingement and convection cooling or pure convection cooling, a compensating flow of the cooling air is guided between adjacent cooling ducts (2) in such a way that the flow velocity in the cooling duct (2) always exceeds a critical limiting value even downstream of a local damage location (6) so that the temperature is less than a critical limiting value. The compensating flow is led past the combustion chamber outer wall. Connecting openings (5) are arranged between adjacent cooling ducts (2) and are respectively offset on the opposite sides of the cooling duct (2).
摘要翻译： 在通过冲击和对流冷却或纯对流冷却冷却的燃气轮机燃烧室中，冷却空气的补偿流在相邻的冷却管道（2）之间被引导，使得冷却管道（2）中的流速 总是超过临界极限值，甚至在局部损伤位置（6）的下游，使得温度小于临界极限值。 补偿流通过燃烧室外壁。 连接开口（5）设置在相邻的冷却管道（2）之间，并分别偏置在冷却管道（2）的相对侧上。
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公开(公告)号：US5490388A
公开(公告)日：1996-02-13
申请号：US310393
申请日：1994-09-22
摘要： In a gas turbine combustion chamber in which for cooling purposes use is made of combinations of convective heat transfer mechanisms whose basic principle is the elimination of heat by flow, the transition from the convective cooling channel (4) to the plenum upstream of the burners (5) is in the form of a small diffuser (6). The total pressure loss in the entire system is thereby reduced, thus leading to improved efficiency with minimum emissions.
摘要翻译： 在用于冷却目的的燃气轮机燃烧室中，使用的是对流传热机构的组合，其基本原理是通过流动消除热量，从对流冷却通道（4）到燃烧器上游的增压室 5）是小扩散器（6）的形式。 因此，整个系统中的总压力损失减小，从而以最小的排放物提高了效率。
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公开(公告)号：US5513982A
公开(公告)日：1996-05-07
申请号：US225319
申请日：1994-04-08
IPC分类号： F23R3/12 , B01F5/04 , B01F5/06 , F15D1/02 , F23D11/40 , F23R3/20 , F23R3/30 , F23R3/58 , F23D14/46
CPC分类号： F23D11/408 , B01F5/0451 , B01F5/061 , B01F5/0656 , F15D1/02 , F23R3/20 , B01F2005/0621 , B01F2005/0622
摘要： In a combustion chamber, a gaseous or liquid fuel is injected as a secondary flow into a gaseous, channelized main flow. The main flow is directed to pass over a plurality of vortex generators (9) arranged side by side over the width or circumference of the channel (20) through which the flow passes. The height (h) of the vortex generators is at least 50% of the height (H) of the channel through which the flow passes or of that part of the channel associated with the vortex generators. The secondary flow is introduced into the channel (20) in the immediate vicinity of the vortex generators (9). Longitudinal vortices without any recirculation region are produced in the channel through which the flow passes by means of the new static mixer. Extraordinarily short mixing distances, with a low pressure loss at the same time, are thus achieved in a combustion chamber according to the invention.
摘要翻译： 在燃烧室中，将气态或液态燃料作为二次流注入气态，通道化的主流中。 主要流动是通过在通道（20）的宽度或圆周上并排布置的多个涡流发生器（9），流体通过该涡流发生器。 涡流发生器的高度（h）至少为流经的通道的高度（H）或与涡流发生器相关的通道的那部分的高度（H）的50％。 二次流在涡流发生器（9）附近被引入通道（20）中。 在通过新的静态混合器流动的通道中产生没有任何再循环区域的纵向涡流。 因此，在根据本发明的燃烧室中实现了非常短的混合距离，同时具有低的压力损失。
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公开(公告)号：US5426943A
公开(公告)日：1995-06-27
申请号：US340454
申请日：1994-11-14
CPC分类号： F23R3/54 , F23R3/02 , F05B2240/32 , F05B2260/222 , F05B2260/2241
摘要： In a gas turbine combustion chamber (1)--having environment-friendly burners (5) which consist of at least two hollow partial conical bodies which are positioned one upon the other in the flow direction and whose longitudinal axes of symmetry extend radially offset relative to one another, by which means tangential opposed-flow air inlet slots are produced for a combustion air flow, at least one nozzle for spraying in the fuel being placed in the hollow conical space formed by the cone-shaped partial conical bodies, and having a cooling duct (4), which is bounded by the combustion chamber inner wall (2) and the combustion chamber outer wall (3), along which the cooling air flows and in which longitudinal and transverse ribs (8) can be arranged--the cooling duct (4) has a continuously decreasing height and/or increasing surface roughness in the flow direction of the cooling air. The total mass flow coming from the compressor (7) is used for pure convective cooling of the combustion chamber inner wall (2) and takes part in the combustion.
摘要翻译： 在燃气轮机燃烧室（1）中，具有环境友好的燃烧器（5），其由至少两个中空部分圆锥体组成，所述至少两个中空部分圆锥体在流动方向上一个一个地定位，并且其纵向对称轴线相对于 通过这种方式，为燃烧空气流产生切向相对流动的空气入口狭槽，至少一个用于喷射在燃料中的喷嘴被放置在由锥形部分圆锥体形成的空心锥形空间中，并具有 冷却管道（4），其由燃烧室内壁（2）和燃烧室外壁（3）限定，冷却空气流过冷却管道，其中可布置纵向和横向肋（8） - 冷却 管道（4）在冷却空气的流动方向上具有连续降低的高度和/或增加的表面粗糙度。 来自压缩机（7）的总质量流量用于燃烧室内壁（2）的纯对流冷却并参与燃烧。
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公开(公告)号：US5465577A
公开(公告)日：1995-11-14
申请号：US339292
申请日：1994-11-10
摘要： In a gas turbine combustion chamber, which consists of an inlet zone (1) with injection, an ignition delay zone (2), a reaction zone (3), a burn-out zone (4) and a transition zone (5) to the turbine, the reaction zone (3) has a cross-section which increases in such a way that the gas dynamics of the combustion process can take place at constant pressure or constant Mach number. By this means, the total pressure loss and the combustion chamber length necessary for the combustion are reduced and this is reflected in an improvement to the efficiency and the output.
摘要翻译： 在燃气轮机燃烧室中，其由具有喷射的入口区域（1），点火延迟区域（2），反应区域（3），燃尽区域（4）和过渡区域（5）构成， 涡轮机，反应区域（3）的横截面增加，使得燃烧过程的气体动力学可以在恒定压力或恒定马赫数下进行。 通过这种方式，减少燃烧所需的总压力损失和燃烧室长度，这反映在对效率和输出的改善。
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公开(公告)号：US5388412A
公开(公告)日：1995-02-14
申请号：US151797
申请日：1993-11-15
CPC分类号： F23R3/002 , F23R3/54 , F05B2260/201 , F23R2900/03044
摘要： In a gas turbine combustion chamber (1) cooled by means of impingement cooling, the height of the cooling duct (5) formed by the perforated plate (3) and the impingement surface (4) increases continuously in the transverse flow direction to correspond with the supply of cooling air. Tubes (7) are arranged in the cooling duct (5) on the holes (6) of the perforated plate (3) in such a way that the impingement air meets the impingement surface (4) at right angles, the height of the tubes (7) increasing in the transverse flow direction in such a way that the distance between the tubes (7) and the impingement surface (4) is constant over the complete length of the cooling duct (5). By this means, the heat transfer coefficient remains constant along the impingement cooling section and uniform removal of heat is made possible. The cooling effect can be specifically controlled by a suitable choice of the diameter of the holes (6) and the height of the tubes (7).
摘要翻译： 在通过冲击冷却冷却的燃气轮机燃烧室（1）中，由多孔板（3）和冲击表面（4）形成的冷却管道（5）的高度在横向流动方向上连续增加，以对应于 供应冷却空气。 管（7）以多孔板（3）的孔（6）的方式布置在冷却管道（5）中，使得冲击空气以直角与冲击表面（4）相交，管的高度 （7）在横向流动方向上增加，使得管（7）和冲击表面（4）之间的距离在冷却管道（5）的整个长度上是恒定的。 通过这种方式，传热系数沿着冲击冷却部分保持恒定，并且可以均匀地除去热量。 可以通过孔（6）的直径和管（7）的高度的适当选择来具体控制冷却效果。
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公开(公告)号：US5735126A
公开(公告)日：1998-04-07
申请号：US625190
申请日：1996-04-01
CPC分类号： F23R3/16 , F23R3/04 , F23R3/26 , F05B2250/00 , F05B2260/222 , F23R2900/03041
摘要： In a combustion chamber (100) which is designed as an annular combustion chamber and a mixing essentially comprises a primary zone (1), a mixing section (2) arranged downstream and an adjoining secondary stage (3), vortex generators (200) are fixed inside the mixing section (2), which vortex generators (200) serve to form vortices. Both the mixing section (2) and the vortex generators (200) are provided with passage openings through which mixing air (8) flows into the interior of the mixing section (2) and mixes there with the main flow (4). The quantity of the intermixed mixing air (8) is variable; it can have a supercritical or subcritical blow-out rate relative to the main flow (4), and in this connection at least film cooling of the duct walls (5, 6) and of the vortex generators (200) takes place even at subcritical blow-out rate. If a supercritical blow-out rate is taken as a basis, the mixing air (8) penetrates the marginal zones of the vortices induced by the vortex generators (200), which leads to rapid mixing of this mixing air (8) with the main flow (4).
摘要翻译： 在被设计为环形燃烧室的燃烧室（100）中，混合基本上包括主区（1），布置在下游的混合段（2）和毗邻的次级（3），涡流发生器（200） 固定在混合部分（2）内，该涡旋发生器（200）用于形成涡流。 混合部分（2）和涡流发生器（200）均设有通道开口，混合空气（8）通过该通道开口流入混合部分（2）的内部并与主流体（4）混合在一起。 混合混合空气（8）的量是可变的; 它可以具有相对于主流（4）的超临界或亚临界吹出速率，并且在这一点上，至少管道壁（5,6）和涡流发生器（200）的膜冷却甚至在次临界 吹出率。 如果以超临界吹出速率为基础，则混合空气（8）穿透由涡流发生器（200）引起的涡流的边缘区域，这导致该混合空气（8）与主体 流（4）。
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公开(公告)号：US5603212A
公开(公告)日：1997-02-18
申请号：US510658
申请日：1995-08-03
摘要： In a combustion chamber (14) of a gas-turbine group which is arranged downstream of a first turbine (11) and upstream of a second turbine (12) and has a burnerless combustion space, extending between the outflow plane of the first turbine (11) and the oncoming-flow plane of the second turbine (12), and a fuel injector (2) which comprises a fuel-nozzle holder (8), extending transversely to the main flow (1) approximately up to the center axis, and a fuel nozzle (9) arranged in the direction of flow in the center axis and connected to the fuel-nozzle holder (8), the combustion chamber (14) working with premixing combustion, and the inlet temperature of the exhaust gas of the first turbine (11) into the combustion chamber (14) being above the self-ignition temperature of the fuel (13), the fuel injector (2) has means for simultaneously evening out the velocity profile and for lowering the temperature of the flow in the wake region. These means are feed passages (5), arranged inside the fuel injector, and openings (6) for an additional mass air flow (3). Thus the formation of a region of recirculating flow, which leads to an undesirable flame effect before the actual combustion zone, is prevented.
摘要翻译： 在燃气轮机组的燃烧室（14）中，其布置在第一涡轮机（11）的下游并且在第二涡轮机（12）的上游并具有无燃烧器燃烧空间，在第一涡轮机的流出面（ 11）和第二涡轮机（12）的迎面平面以及燃料喷射器（2），其包括大致直到中心轴线横向于主流（1）延伸的燃料喷嘴保持器（8） 以及燃料喷嘴（9），其沿着中心轴线的流动方向配置并连接到燃料喷嘴保持器（8），燃烧室（14）进行预混合燃烧，并且排气的入口温度 燃料喷射器（2）具有高于燃料（13）的自燃温度的燃烧室（14）内的第一涡轮机（11），燃料喷射器（2）具有用于同时熄灭速度分布并降低流体的温度的装置 唤醒区域。 这些装置是布置在燃料喷射器内部的进料通道（5）和用于附加质量空气流（3）的开口（6）。 因此，防止了在实际燃烧区域之前导致不期望的火焰效应的循环流动区域的形成。
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公开(公告)号：US5941060A
公开(公告)日：1999-08-24
申请号：US938454
申请日：1997-09-29
CPC分类号： F02C6/003 , F01D9/042 , F05D2260/201
摘要： In a gas turbine having sequential combustion and two combustion chambers and in each case associated turbines, a secondary guide row (6a-c) formed in an annular transition duct (1) is arranged on the downstream side of the first turbine before entry into the second combustion chamber. A number of blades of this secondary guide row effect an irrotational flow with regard to the mixing elements, which are located in the second combustion chamber and in the flow plane of the blades, which in each case are combined to form an assembly. Due to the irrotational incident flow in the second combustion chamber, the mixing elements produce a uniform separate swirl flow which optimizes the subsequent combustion, designed for self-ignition, with regard to efficiency and pollutant emissions.
摘要翻译： 在具有顺序燃烧和两个燃烧室并且在每种情况下相关联的涡轮机的燃气轮机中，形成在环形过渡管道（1）中的次级引导排（6a-c）布置在第一涡轮机的下游侧，然后进入 第二燃烧室。 该辅助引导排的多个叶片相对于位于第二燃烧室中和在每个情况下组合以形成组件的叶片的流动平面中的混合元件影响不旋转流动。 由于第二燃烧室中的非旋转入射流动，混合元件产生均匀的单独旋流，其优化随后的燃烧，设计用于自燃，关于效率和污染物排放。
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