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1. 发明申请

US20170176012A1 FUEL INJECTORS AND STAGED FUEL INJECTION SYSTEMS IN GAS TURBINES 审中-公开
公开(公告)号：US20170176012A1
公开(公告)日：2017-06-22
申请号：US14977979
申请日：2015-12-22
申请人： General Electric Company
发明人： Benjamin Paul Lacy
IPC分类号： F23R3/34 , F01D25/12 , F02C7/22 , F02C3/04 , F01D9/04
CPC分类号： F01D25/12 , F01D5/185 , F01D9/023 , F01D9/041 , F01D9/065 , F02C3/04 , F02C3/14 , F02C7/222 , F02C7/224 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/35 , F05D2260/202 , F05D2260/232 , F05D2260/601 , F23R3/20 , F23R3/34
摘要： A gas turbine that includes a row of circumferentially spaced stator blades in a turbine. Each of the stator blades may include an airfoil defined between a concave pressure side face and a laterally opposed convex suction side face. At least one of the stator blades within the row may include a fuel injector that includes: a transverse nozzle extending through the airfoil between an inlet formed through the pressure side face and an outlet formed through the suction side face of the airfoil; and a fuel channel formed through the airfoil of the stator blade, the fuel channel having an upstream end, at which an inlet port fluidly connects the fuel channel to a fuel supply, and a downstream end, at which an outlet port fluidly connects the fuel channel to the transverse nozzle.

2. 发明申请

US20150369060A1 TAPERED THERMAL BARRIER COATING ON CONVEX AND CONCAVE TRAILING EDGE SURFACES 审中-公开
标题翻译：锥形热障涂层和凹凸边缘表面
公开(公告)号：US20150369060A1
公开(公告)日：2015-12-24
申请号：US14767699
申请日：2013-12-30
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Jeffrey R Levine
IPC分类号： F01D5/28 , F01D9/02 , F01D25/12 , F01D5/18
CPC分类号： F01D5/288 , F01D5/185 , F01D5/187 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2230/312 , F05D2230/313 , F05D2230/90 , F05D2260/231 , F05D2300/21 , Y10T29/49343
摘要： A turbine engine component has an airfoil portion having a pressure side, a suction side, and a trailing edge. The trailing edge has a center discharge cooling circuit, which center discharge cooling circuit has an exit defined by a concave surface on the pressure side of the airfoil portion and a convex surface on the suction side of the airfoil portion. The airfoil portion has a thermal barrier coating on the pressure side and the suction side. The thermal barrier coating on the convex surface tapers to zero in thickness at a point spaced from the trailing edge so as to leave an uncoated portion on the convex surface.
摘要翻译：涡轮发动机部件具有具有压力侧，吸力侧和后缘的翼型部。后缘具有中心排出冷却回路，中心排出冷却回路具有由翼型部的压力侧的凹面界定的出口和翼型部的吸入侧的凸面。翼型部分在压力侧和吸力侧具有热障涂层。凸表面上的热障涂层在与后缘间隔开的位置处的厚度变薄到零，以便在凸面上留下未涂覆的部分。

3. 发明授权

US06988367B2 Gas turbine engine cooling system and method 有权
标题翻译：燃气轮机发动机冷却系统及方法
公开(公告)号：US06988367B2
公开(公告)日：2006-01-24
申请号：US10709199
申请日：2004-04-20
申请人： Robert S. Thompson Jr. , Gregg Williams
发明人： Robert S. Thompson Jr. , Gregg Williams
IPC分类号： F02C7/12
CPC分类号： F02C7/224 , F01D5/085 , F01D5/185 , F05D2260/205 , F23R3/38 , Y02T50/676
摘要： Fuel supplied to a rotary fluid trap is centrifugally accelerated within a first cavity adjacent a first side of a rotor, and is then directed though a plurality of first passages extending through the rotor between and proximate to the blades, and shaped so as to at least partially conform to the shape of the blades. Second passages extend within the blades from the first passages and terminate within associated cavities proximate to the tips of the blades. Relatively cooler fuel in the first passages is thermosiphon exchanged for relatively hotter fuel in the second passages so as to cool the blades. The heated fuel flows into a second cavity adjacent to a second side of the rotor and is discharged from the rotating frame of reference directly into the combustion chamber through a second rotary fluid trap. A separate fuel distribution circuit is used for starting and warm-up.
摘要翻译：提供给旋转流体捕集器的燃料在邻近转子的第一侧的第一空腔内离心加速，然后被引导通过在叶片之间和附近延伸穿过转子的多个第一通道，并至少成形为至少部分地符合叶片的形状。第二通道在叶片内从第一通道延伸并终止于靠近叶片尖端的相关空腔内。第一通道中相对较冷的燃料在第二通道中被热交换为相对较热的燃料，以便冷却叶片。加热的燃料流入与转子的第二侧相邻的第二腔体，并通过第二旋转流体阱直接从旋转参考框架排出到燃烧室中。单独的燃料分配电路用于启动和预热。

4. 发明授权

US06672075B1 Liquid cooling system for gas turbines 失效
标题翻译：燃气轮机液体冷却系统
公开(公告)号：US06672075B1
公开(公告)日：2004-01-06
申请号：US10197434
申请日：2002-07-18
申请人： Constantin Sandu , Dan Brasoveanu
发明人： Constantin Sandu , Dan Brasoveanu
IPC分类号： F02C716
CPC分类号： F02C7/16 , F01D5/088 , F01D5/185 , F05D2260/232 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： Cooling systems with liquid for gas turbine engines use the relative motion of the engine stator with respect to the rotor for actuating the coolant pump. The cooling system is completely encapsulated within the engine rotor. The cooling system includes a tank containing the cooling liquid, a coolant pump coupled to the tank to extract the cooling liquid from the tank, a system of ducts and channels extending in the rotor shaft, and rotor disks and rotor blades, where the heat exchanger is positioned either in the compressor drum, or in the end of compressor section.
摘要翻译：具有用于燃气涡轮发动机的液体的冷却系统使用发动机定子相对于转子的相对运动来致动冷却剂泵。冷却系统完全封装在发动机转子内。冷却系统包括容纳冷却液体的罐，连接到罐的冷却剂泵以从罐中提取冷却液体，在转子轴中延伸的管道和通道系统以及转子盘和转子叶片，其中热交换器被定位在压缩机鼓中或压缩机部分的末端。

5. 发明授权

US06565312B1 Fluid-cooled turbine blades 有权
标题翻译：流体冷却涡轮叶片
公开(公告)号：US06565312B1
公开(公告)日：2003-05-20
申请号：US10029451
申请日：2001-12-19
申请人： Mark D. Horn , James Lobitz , David R. Matthews , Luis A. Rosales , Kenneth M. Sprouse , Allan Von Arx
发明人： Mark D. Horn , James Lobitz , David R. Matthews , Luis A. Rosales , Kenneth M. Sprouse , Allan Von Arx
IPC分类号： F01D518
CPC分类号： F01D5/147 , F01D5/18 , F01D5/185
摘要： A cooled turbine blade (either a rotor blade or a stationary vane) comprises a blade structural member whose primary function is to withstand the various loads exerted on the blade and maintain structural integrity of the blade, and a heat-transfer sheath that surrounds the outer surface of the structural member. A plurality of coolant passages are formed between the structural member and the heat-transfer sheath. Thus, when coolant is passed through the coolant passages, the heat transferred to the sheath from the hot gases passing through the turbine is in turn transferred to the coolant, which is then removed from the blade, thereby cooling the blade.
摘要翻译：冷却的涡轮叶片（转子叶片或固定叶片）包括叶片结构构件，其主要功能是承受施加在叶片上的各种载荷并保持叶片的结构完整性，以及围绕外部的传热护套结构件的表面。在结构构件和传热护套之间形成多个冷却剂通道。因此，当冷却剂通过冷却剂通道时，从通过涡轮机的热气体传递到护套的热又转移到冷却剂中，然后将冷却剂从叶片中取出，从而冷却叶片。

6. 发明申请

US20010052230A1 Fuel preheating in a gas turbine 有权
标题翻译：燃气轮机中的燃料预热
公开(公告)号：US20010052230A1
公开(公告)日：2001-12-20
申请号：US09817673
申请日：2001-03-26
发明人： Klaus Werner
IPC分类号： F02C007/22
CPC分类号： F01D5/185 , F02C7/16 , F02C7/224 , F05D2260/20 , F05D2260/232
摘要： A gas turbine and a method for operating a gas turbine includes a combustion chamber, a turbine having rows of blades, an air compressor, a combustion-air line for feeding compressed air into the combustion chamber, a fuel supply unit, at least one fuel line, at least one cooling-air line. Some of the blades have an interior defining cavities whereby first cavities direct at least a portion of fuel to the combustion chamber through the first cavities at least in a section of the blades, thereby preheating the fuel before being introduced into the combustion chamber. The system defined by the first cavities and the section of the blades is closed relative to an interior of the gas turbine. Second cavities fluidically connect to the air compressor and receive at least a portion of the cooling air for cooling the blades.
摘要翻译：燃气轮机和操作燃气轮机的方法包括燃烧室，具有一排叶片的涡轮机，空气压缩机，用于将压缩空气供入燃烧室的燃烧空气管线，燃料供给单元，至少一种燃料至少有一条冷气线。一些叶片具有限定空腔的内部，由此第一空腔至少在叶片的一部分中通过第一空腔将至少一部分燃料引导到燃烧室，从而在引入燃烧室之前预热燃料。由第一腔体和叶片的截面限定的系统相对于燃气轮机的内部封闭。第二腔流体地连接到空气压缩机并且接收至少一部分冷却空气以冷却叶片。

7. 发明授权

US5954478A Evaporatively cooled rotor for a gas turbine engine 失效
标题翻译：用于燃气涡轮发动机的蒸发冷却转子
公开(公告)号：US5954478A
公开(公告)日：1999-09-21
申请号：US7689
申请日：1998-01-15
申请人： David B. Stickler , Jack L. Kerrebrock
发明人： David B. Stickler , Jack L. Kerrebrock
IPC分类号： F01D5/08 , F01D5/18 , B63H1/14
CPC分类号： F01D5/181 , F01D5/088 , F01D5/185 , Y02T50/676
摘要： An evaporatively cooled rotor for a gas turbine engine. Each rotor defines an internal cavity which includes a vaporization section that corresponds generally to the blade section of the rotor and a condensing section that corresponds generally to the hub section of the rotor. A radial array of circumferentially disposed capture shelves is provided in the vaporization section for capturing cooling fluid contained within the internal cavity and flowing radially outward under the centrifugal field generated during rotation of the rotor. A barrier disposed along the inner surface of the rotor wall in the condensing section slows or temporarily stops the flow of cooling fluid prior to reaching the vaporization section and a perforated baffle attached to the capture shelves prevents cooling fluid from splashing out of the shelves.
摘要翻译：用于燃气涡轮发动机的蒸发冷却转子。每个转子限定内部空腔，其包括大致对应于转子的叶片部分的蒸发部分和大致对应于转子的毂部分的冷凝部分。在蒸发部分中设置有周向设置的捕获搁架的径向阵列，用于捕获内部空腔内的冷却流体，并且在转子旋转期间产生的离心场下径向向外流动。沿着冷凝部分的转子壁的内表面设置的阻挡件在到达蒸发部分之前减慢或暂时停止冷却流体的流动，并且附接到捕获架的穿孔挡板防止冷却流体从搁架中溅出。

8. 发明授权

US5341636A Gas turbine engine operating method 失效
标题翻译：燃气轮机发动机运行方式
公开(公告)号：US5341636A
公开(公告)日：1994-08-30
申请号：US3098
申请日：1993-01-11
申请人： Marius A. Paul
发明人： Marius A. Paul
IPC分类号： F01D5/18 , F02C6/00 , F02C7/12 , F02C9/16 , F02K3/075 , F23R3/34 , F23R3/38 , F02C7/16
CPC分类号： F01D5/18 , F01D5/185 , F01D5/189 , F02C3/08 , F02C3/30 , F02C6/003 , F02C7/12 , F02C7/16 , F02C7/224 , F02C9/16 , F02K3/075 , F02K3/10 , F02K3/11 , F23R3/34 , F23R3/38 , F05D2260/201 , F05D2260/232 , Y02E20/14 , Y02T50/671 , Y02T50/676
摘要： A gas turbine engine that can operate at a very high efficiency over a wide range of load conditions. In one important feature of the invention, combustion gases are discharged along two paths, one with constant energy and the other with energy that varies in accordance with the engine load. The constant energy discharge drives a turbine that, in turn, operates a compressor for the engine at a constant, high efficiency. Alternatively, the compressor is driven at a speed that varies inversely with the engine load such that the engine operates at a high efficiency for all loads. In another, independent feature of the invention, the combustion occurs at a stoichiometric ration of fuel and air, with the turbine blades being protected from the vastly increased combustion gas temperatures by an internal array of passageways through which cooling liquid, e.g., liquid fuel, and air are channeled. The fuel and air mix together to from a rich, turbulent pre-mix for ejection directly into the surrounding combustion chamber. This configuration can also be utilized to inject steam into the combustion chamber, to provide a Rankine cycle, with internal cogeneration. In yet another independent aspect of the invention, the compressor that supplied compressed air to the combustion chamber includes two counter-rotating radial impellers, with the second impeller further functioning as a diffuser for the first impeller.
摘要翻译：一种燃气涡轮发动机，可在宽范围的负载条件下以非常高的效率运行。在本发明的一个重要特征中，燃烧气体沿着两个路径排出，一个具有恒定的能量，另一个具有根据发动机负载而变化的能量。恒定能量放电驱动涡轮机，涡轮机又以恒定的高效率操作发动机的压缩机。或者，压缩机以与发动机负载成反比的速度驱动，使得发动机以高效率对所有负载进行操作。在另一个本发明的独立特征中，燃烧以燃料和空气的化学计量比进行发生，通过内部的通道阵列来保护涡轮机叶片免受大大增加的燃烧气体温度的影响，冷却液体例如液体燃料，空气被引导。燃料和空气混合在一起，由丰富的湍流预混合物直接喷射到周围的燃烧室中。这种结构也可用于将蒸气喷入燃烧室，以提供具有内部热电联产的兰金循环。在本发明的另一独立方面，向燃烧室供应压缩空气的压缩机包括两个反向旋转的径向叶轮，第二叶轮还用作第一叶轮的扩散器。

9. 发明授权

US4638628A Process for directing a combustion gas stream onto rotatable blades of a gas turbine 失效
标题翻译：将燃烧气体流引导到燃气轮机的可旋转叶片上的过程
公开(公告)号：US4638628A
公开(公告)日：1987-01-27
申请号：US716373
申请日：1985-03-26
申请人： Ivan G. Rice
发明人： Ivan G. Rice
IPC分类号： F01D5/18 , F01K23/10 , F02C6/00 , F02C6/18 , F02C7/16 , F02C7/00
CPC分类号： F02C7/16 , F01D5/185 , F01D5/187 , F01K23/103 , F02C6/003 , F02C6/18 , F05D2240/302 , F05D2250/25 , F05D2260/202 , F05D2260/2322 , Y02E20/16 , Y02T50/673 , Y02T50/676
摘要： A process for producing work comprises passing a combustion gas stream through a gas nozzle which directs the stream onto the rotatable blades of an expansion turbine. A fluid having a sonic velocity greater than the combustion gas is directed against and across the air-foil shaped vanes which form the nozzle at sonic velocity allowing the gas stream to accelerate to beyond Mach 1 without excessive loss of pressure. The fluid such as steam can be used to cool the vanes prior to entering the gas stream.
摘要翻译：一种用于生产工作的方法包括使燃烧气流通过气体喷嘴，该气体喷嘴将流引导到膨胀涡轮机的可旋转叶片上。具有大于燃烧气体的声速的流体被引导并穿过形成喷嘴的气翼形叶片，声音速度允许气流加速到超过马赫数1而没有过大的压力损失。诸如蒸汽的流体可以在进入气流之前用于冷却叶片。

10. 发明授权

US4384452A Steam-cooled blading with steam thermal barrier for reheat gas turbine combined with steam turbine 失效
标题翻译：蒸汽冷却叶片采用蒸汽热障，用于再热式燃气轮机与蒸汽轮机相结合
公开(公告)号：US4384452A
公开(公告)日：1983-05-24
申请号：US274660
申请日：1981-06-17
申请人： Ivan G. Rice
发明人： Ivan G. Rice
IPC分类号： F01D5/18 , F01K23/10 , F02C6/00 , F02C6/18 , F02C7/16
CPC分类号： F02C6/18 , F01D5/185 , F01D5/187 , F01K23/103 , F02C6/003 , F02C7/16 , F05D2240/302 , F05D2260/202 , F05D2260/2322 , Y02E20/16 , Y02T50/673 , Y02T50/676
摘要： Steam-cooling with a steam thermal barrier for reheat gas turbine vanes and blades offers advantages over cooling with air or water at the higher temperatures characteristic of existing high temperature gas turbines, in particular when coupled with a reheat steam cycle. Consequently, in such a combined cycle higher cycle efficiency is obtainable for gas turbine initial firing temperatures of about 2500.degree. F. (1371.degree. C.) and 2050.degree. F. (1121.degree. C.) reheat temperatures where over-all combined cycle degradation resulting from steam cooling is below about 1%. A proposed combined reheat gas turbine and steam turbine cycle includes a gas turbine having steam-cooled components operating at a cycle pressure ratio of about 38 without intercooling and included steam superheating in the reheat combustor.
摘要翻译：使用蒸汽热障的蒸汽冷却用于再热燃气涡轮机叶片和叶片提供了优于在现有高温燃气轮机特征的较高温度下空气或水的冷却，特别是当与再热蒸汽循环相结合时。因此，在这种联合循环中，可以获得约2500°F（1371℃）和2050°F（1121℃）的燃气轮机初始燃烧温度的更高的循环效率，其中全部组合循环降解由蒸汽冷却导致的温度低于约1％。所提出的组合式再热燃气轮机和蒸汽轮机循环包括具有蒸汽冷却部件的燃气轮机，其循环压力比为约38，而没有中间冷却，并且在再热燃烧器中包括蒸汽过热。

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