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1. 发明申请

WO0131180A3 GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机
公开(公告)号：WO0131180A3
公开(公告)日：2002-01-10
申请号：PCT/US0026251
申请日：2000-10-11
申请人： ALM DEV INC
发明人： RAKHMAILOV ANATOLY
IPC分类号： F02C3/34 , F02C6/00
CPC分类号： F02C6/006 , F02C3/34
摘要： A gas turbine engine comprising a compressor, a power turbine, a counter-rotating compressor turbine for powering the compressor and a heat exchanger interconnected among them, uses a mixer to mix waste fluid heater by the heat exchanger with combustion air and feed the mixture to a combustor.
摘要翻译：一种燃气涡轮发动机，包括压缩机，动力涡轮机，用于为压缩机供电的反向旋转压缩机涡轮机和彼此相互连接的热交换器，使用混合器将热交换器的废液加热器与燃烧空气混合并将混合物供给一个燃烧器。

2. 发明申请

WO0020738A9 GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机
公开(公告)号：WO0020738A9
公开(公告)日：2001-07-05
申请号：PCT/US9920887
申请日：1999-09-24
申请人： ALM DEV INC
发明人： RAKHMAILOV ANATOLY
IPC分类号： F02C9/28 , F01D15/10 , F02C3/067 , F02C3/10 , F02C6/00 , F02C7/08 , F02C9/00 , F04B49/00 , F04D15/00 , H02K11/00 , H02P9/04
CPC分类号： F02C7/08 , F01D15/10 , F02C3/10
摘要： A gas turbine engine has a turbine (12) mounted downstream of a compressor (16) and a compressor turbine (18) mounted downstream of the turbine (12) for driving the compressor (16). The compressor turbine (18) has a rotor disk that is mechanically coupled to the compressor (16) and rotates in a direction opposite to the direction of rotation of the turbine rotor disk (10). A heat exchanger (22) has a first circuit (24) connected to the compressor turbine (18) and a second circuit (25) connected between the compressor (16) and the turbine (12). An electric load (26) for taking off a fraction of power produced by the compressor turbine (18) includes an electric generator (28) that is mechanically coupled to the compressor turbine (18). An electric load controller (32) changes the fraction of power produced by the compressor (18) turbine based on readings from the temperature sensor located in the engine.
摘要翻译：燃气涡轮发动机具有安装在压缩机（16）下游的涡轮机（12）和安装在涡轮机（12）下游的用于驱动压缩机（16）的压缩机涡轮机（18）。压缩机涡轮（18）具有机械地联接到压缩机（16）并沿与涡轮转子盘（10）的旋转方向相反的方向旋转的转子盘。热交换器（22）具有连接到压缩机涡轮机（18）的第一回路（24）和连接在压缩机（16）和涡轮机（12）之间的第二回路（25）。用于取出由压缩机涡轮机（18）产生的功率的一部分的电负载（26）包括机械地联接到压缩机涡轮机（18）的发电机（28）。电力负载控制器（32）基于来自位于发动机中的温度传感器的读数改变由压缩机（18）涡轮机产生的功率的分数。

3. 发明申请

WO0020740A3 GAS TURBINE ENGINE 审中-公开
标题翻译：燃气涡轮发动机
公开(公告)号：WO0020740A3
公开(公告)日：2000-07-06
申请号：PCT/US9920886
申请日：1999-09-24
申请人： ALM DEV INC
发明人： RAKHMAILOV ANATOLY
IPC分类号： F01D5/08 , F01D5/18 , F01D9/02 , F01D9/04 , F01D9/06 , F02C3/067 , F02C3/10 , F02C3/36 , F02C7/18 , F04D27/02
CPC分类号： F02C3/365 , F01D5/081 , F01D5/187 , F01D9/023 , F01D9/04 , F01D9/065 , F02C7/18 , F04D27/0215
摘要： A gas turbine engine includes a compressor driven by a compression turbine, a combustor (116) receiving a part (A) of the compressed air, a compression turbine rotor disc (118), and a power turbine rotor disc (114). A minor part of the compressor air is fed to the combuster (116) through ports (123). The fuel is provided through port (117) and the exhaust gases (D) flow through the power turbine and then through the compression turbine. A major part (B) of the compressor air is bled from the compressor and directly bypassed successively through a zone (122 and 124), to a zone (128) of the power turbine rotor disc (114). The air (B) is fed for driving the power turbine rotor disc (114) into passages (126) of the power turbine blades (115), thereby cooling them, and is consequently ejected and mixed into the main exhaust gas stream (D).
摘要翻译：燃气涡轮发动机包括由压缩涡轮驱动的压缩机，接收压缩空气的一部分（A）的燃烧器（116），压缩涡轮转子盘（118）和动力涡轮转子盘（114）。压缩空气的一小部分通过端口（123）供给到燃烧器（116）。燃料通过口（117）提供，排气（D）流过动力涡轮机，然后流过压缩涡轮机。压缩机空气的主要部分（B）从压缩机排出并直接旁路通过区域（122和124）到动力涡轮机转子盘（114）的区域（128）。供给空气（B）以驱动动力涡轮机转子盘（114）进入动力涡轮机叶片（115）的通道（126），由此冷却它们，并且因此喷射并混合到主排气流（D）。

4. 发明申请

WO0022287A2 GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机
公开(公告)号：WO0022287A2
公开(公告)日：2000-04-20
申请号：PCT/US9920884
申请日：1999-09-24
申请人： ALM DEV INC
发明人： RAKHMAILOV ANATOLY
IPC分类号： F23R3/12 , F01D5/08 , F01D9/02 , F01D9/04 , F01D9/06 , F02C7/08 , F02C9/16 , F04D27/02 , F23R3/54 , F02C
CPC分类号： F01D9/065 , F01D5/081 , F01D9/023 , F01D9/04 , F02C7/08 , F04D27/0215 , F23R3/54 , Y02T50/676
摘要： A gas turbine engine includes a compressor (12), a combustor (16) receiving with a part (A) of the compressed air, and a turbine rotor disk (14). A part (B) of the compressed air is bled from the compressor (12) and directly bypassed through a passage (30) to a zone (32) of the turbine rotor disc (14). Vanes (34) located inthe passage (30) impart a spin to the air (B), which is fed for driving the turbine rotor disc (14) into passages (36) of the turbine blades (15), thereby cooling them, and is consequently ejected into an annular zone (38) and then into an entry zone (19) of the combustor (16). Fuel is fed at ports (18) into this spinning heated air flow (C). The heated fluid (C) is then mixed with the incomming compressed air (A) for combustion. The exhaust gases are eventually directed through the turbine.
摘要翻译：燃气涡轮发动机包括压缩机（12），接收压缩空气的一部分（A）的燃烧器（16）和涡轮转子盘（14）。压缩空气的一部分（B）从压缩机（12）排出，并直接通过通道（30）旁通到涡轮转子盘（14）的区域（32）。位于通道（30）内的叶片（34）向空气（B）施加旋转，空气（B）被供给以将涡轮转子盘（14）驱动到涡轮叶片（15）的通道（36）中，从而冷却它们，因此被喷射到环形区域（38）中，然后被喷射到燃烧器（16）的进入区域（19）中。燃料在端口（18）进料到这个旋转的加热空气流（C）中。然后将加热的流体（C）与进入的压缩空气（A）混合以进行燃烧。废气最终被引导通过涡轮机。

5. 发明申请

WO0020738A2 GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机
公开(公告)号：WO0020738A2
公开(公告)日：2000-04-13
申请号：PCT/US9920887
申请日：1999-09-24
申请人： ALM DEV INC
发明人： RAKHMAILOV ANATOLY
IPC分类号： F02C9/28 , F01D15/10 , F02C3/067 , F02C3/10 , F02C6/00 , F02C7/08 , F02C9/00 , F04B49/00 , F04D15/00 , H02K11/00 , H02P9/04
CPC分类号： F02C7/08 , F01D15/10 , F02C3/10
摘要： A gas turbine engine has a turbine (12) mounted downstream of a compressor (16) and a compressor turbine (18) mounted downstream of the turbine (12) for driving the compressor (16). The compressor turbine (18) has a rotor disk that is mechanically coupled to the compressor (16) and rotates in a direction opposite to the direction of rotation of the turbine rotor disk (10). A heat exchanger (22) has a first circuit (24) connected to the compressor turbine (18) and a second circuit (25) connected between the compressor (16) and the turbine (12). An electric load (26) for taking off a fraction of power produced by the compressor turbine (18) includes an electric generator (28) that is mechanically coupled to the compressor turbine (18). An electric load controller (32) changes the fraction of power produced by the compressor (18) turbine based on readings from the temperature sensor located in the engine.
摘要翻译：燃气涡轮发动机具有安装在压缩机（16）下游的涡轮机（12）和安装在涡轮机（12）下游的用于驱动压缩机（16）的压缩机涡轮机（18）。压缩机涡轮（18）具有机械地联接到压缩机（16）并沿与涡轮转子盘（10）的旋转方向相反的方向旋转的转子盘。热交换器（22）具有连接到压缩机涡轮机（18）的第一回路（24）和连接在压缩机（16）和涡轮机（12）之间的第二回路（25）。用于取出由压缩机涡轮机（18）产生的功率的一部分的电负载（26）包括机械地联接到压缩机涡轮机（18）的发电机（28）。电力负载控制器（32）基于来自位于发动机中的温度传感器的读数改变由压缩机（18）涡轮机产生的功率的分数。

6. 发明申请

WO0053907A8 METHOD OF OPERATION OF A GAS TURBINE ENGINE POWER PLANT AND A GAS TURBINE ENGINE POWER PLANT 审中-公开
标题翻译：气体涡轮发动机发电厂和燃气轮机发电厂的运行方法
公开(公告)号：WO0053907A8
公开(公告)日：2001-02-08
申请号：PCT/US0003711
申请日：2000-03-10
申请人： ALM DEV INC
发明人： RAKHMAILOV ANATOLY
IPC分类号： F01D15/10 , F02C3/067 , F02C3/10 , F02C3/20 , F02C3/28 , F02C3/34 , F02C6/18 , F02C7/08 , F02C9/00 , F02C9/28
CPC分类号： F02C3/067 , F02C3/10 , F02C3/28 , F02C3/34 , F02C6/18 , F02C7/08 , F02C9/28
摘要： A gas turbine engine that has a turbine (1) mounted downstream of a combustor (5), a compressor turbine (2) mounted downstream of turbine (1) for producing power for driving a compressor (3), a heat exchanger (6) having a first circuit (6 ) connected to compressor turbine (2) and a second circuit (6 ) connected between compressor (2) and turbine (1) and a fluid discharge device (7) between compressor (3) and combustor (5). The gas turbine engine has a reactor (8) that has a heating device (9), inlets (F, W) connected to sources of fuel and water and an outlet connected to combustor (5). Heating device (9) is connected to the outlet of compressor turbine (2). The engine also has a system for keeping the temperature at the outlet of compressor turbine (2) constant.
摘要翻译：一种燃气涡轮发动机，其具有安装在燃烧器（5）下游的涡轮机（1），安装在涡轮机（1）下游的用于产生用于驱动压缩机（3）的动力的压缩机涡轮机（2），热交换器（6）具有连接到压缩机涡轮机（2）的第一回路（6）和连接在压缩机（2）和涡轮机（1）之间的第二回路（6）和压缩机（3）之间的流体排放装置）和燃烧器（5）。燃气涡轮发动机具有具有加热装置（9）的反应器（8），连接到燃料和水源的入口（F，W）和连接到燃烧器（5）的出口。加热装置（9）连接到压缩机涡轮机（2）的出口。发动机还具有用于保持压缩机涡轮机（2）出口处的温度恒定的系统。

7. 发明申请

WO2005001260A3 BLADE COOLING IN A GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机叶片冷却
公开(公告)号：WO2005001260A3
公开(公告)日：2005-04-21
申请号：PCT/US0323275
申请日：2003-08-20
申请人： ALM DEV INC , KOLOTILENKO MIKHAIL
发明人： KOLOTILENKO MIKHAIL
IPC分类号： F01D5/08 , F02C7/12
CPC分类号： F02C7/125 , F01D5/082 , F02C7/12 , F05D2260/202
摘要： A gas turbine engine rotor has a body and blades, which are attached to the rotor by a root portion, for receiving a hot fluid flow and a compressed fluid from a compressor. Each blade has a base portion, an external airfoil surface, a blade flow portion of the airfoil, and a passage system communicating with the compressor and with the blade flow portion to create a thermal insulating boundary between the heated fluid and the external airfoil surface. The blade has a substantially planar platform member, extending substantially transversally to the body of the blade and having an upstream portion protruding in the direction toward the combustion zone. The platform member has at least a pair of openings on either side of the airfoil, the openings being positioned in series along the blade flow portion. One opening of the pair defines an inclined passage in the platform member, and the other opening is separated by a partition from the first opening. The blade has a guide portion, which extends beyond the platform member toward the root portion, and the platform member and the guide portion define nozzles on either side of the airfoil surface to increase velocity of the compressed fluid flow.
摘要翻译：燃气涡轮发动机转子具有主体和叶片，其通过根部附接到转子，用于从压缩机接收热流体流和压缩流体。每个叶片具有底座部分，外部翼型件表面，翼型件的叶片流动部分以及与压缩机和叶片流动部分连通以在加热流体和外部翼型件表面之间形成隔热边界的通道系统。叶片具有基本平坦的平台构件，其基本上横向地延伸到叶片的主体并且具有沿朝向燃烧区域的方向突出的上游部分。平台构件在翼型件的任一侧具有至少一对开口，开口沿叶片流动部分串联设置。该对中的一个开口限定了平台构件中的倾斜通道，另一个开口由第一开口的隔板分开。叶片具有引导部分，其延伸超过平台构件朝向根部部分，并且平台构件和引导部分在翼面表面的任一侧上限定喷嘴以增加压缩流体流动的速度。

8. 发明申请

WO0020739A9 GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机
公开(公告)号：WO0020739A9
公开(公告)日：2001-07-05
申请号：PCT/US9920885
申请日：1999-09-24
申请人： ALM DEV INC
发明人： RAKHMAILOV ANATOLY
IPC分类号： F02C6/00 , F02C3/10 , F02C3/34 , F02C7/18
CPC分类号： F02C6/006
摘要： A gas turbine engine comprises a turbine (10), a compressor turbine (14) mounted downstream the turbine (10) for rotation in a direction opposite to the rotation direction of the turbine (10) that is mounted downstream the compressor (12). Exhaust fluid from the compressor turbine (14) is cooled in a heat exchanger (24) with a compressed fluid downstream the compressor (12) and is then cooled with air in separate heat exchanger (26) before being admitted to the compressor (12). A part (25.1) of the compressed fluid heated in the heat exchanger (24) is fed to cool the turbine blades, and the rest (25.2) of the fluid is fed to a heated fluid source for the turbine. To control the gas turbine engine, a part of fluid is boosted by a booster compressor (30) and is discharged from the engine. The booster compressor (30) is driven by an expanding turbine (32) that is rotated under the effect of combustion air that is expanded in the expanding turbine (32) and flows through the expanding turbine (32) under the action of reduced pressure in the heated fluid source.
摘要翻译：燃气涡轮发动机包括涡轮机（10），安装在涡轮机（10）下游的压缩机涡轮机（14），用于沿安装在压缩机（12）下游的涡轮机（10）的旋转方向相反的方向旋转。来自压缩机涡轮机（14）的排出流体在热交换器（24）内被压缩流体在压缩机（12）的下游冷却，然后在分离的热交换器（26）内被空气冷却，然后进入压缩机（12）。供给在热交换器（24）中加热的压缩流体的一部分（25.1）以冷却涡轮机叶片，并将流体的其余部分（25.2）进料到涡轮机的加热流体源。为了控制燃气涡轮发动机，一部分流体由增压压缩机30升压，并从发动机排出。增压压缩机30由膨胀式涡轮机32驱动，涡轮机32在膨胀涡轮机32内膨胀的燃烧空气的作用下旋转，并在减压作用下流过膨胀涡轮机32。加热的流体源。

9. 发明申请

WO0053908A8 GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机
公开(公告)号：WO0053908A8
公开(公告)日：2001-02-08
申请号：PCT/US0003713
申请日：2000-03-10
申请人： ALM DEV INC
发明人： RAKHMAILOV ANATOLY , KALIN MARTIN , YAISHNIKOV VALENTIN , KOLOTILENKO MIKHAIL , RAKHMAILOV OLEG , DROZD IGOR
IPC分类号： F01D15/02 , F02C1/06 , F02C3/067 , F02C3/10 , F02C6/00 , F02C6/20 , F02C7/08 , F28D21/00
CPC分类号： F28D21/0003
摘要： In a gas turbine engine in which bearings (18, 30) of the turbine (12) and the compressor turbine (22) and the exhaust duct (32) of the compressor turbine (22) are attached to the external annular wall (46) of the heat exchanger (44). The external annular wall (46) of the heat exchanger (44) has a heat insulation layer (48) on the inside surface. The engine has a cooling device (94) for cooling the external annular wall (46) of the heat exchanger (44) on the side opposite to the heat insulating layer (48).
摘要翻译：在涡轮机（12）和压缩机涡轮机（22）的轴承（18,30）和压缩机涡轮机（22）的排气管道（32）附接到外部环形壁（46）上的燃气涡轮发动机中，的热交换器（44）。热交换器（44）的外部环形壁（46）在内表面上具有绝热层（48）。发动机具有用于冷却热交换器（44）的与绝热层（48）相对的一侧的外部环形壁（46）的冷却装置（94）。

10. 发明申请

WO0020739A2 GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机
公开(公告)号：WO0020739A2
公开(公告)日：2000-04-13
申请号：PCT/US9920885
申请日：1999-09-24
申请人： ALM DEV INC
发明人： RAKHMAILOV ANATOLY
IPC分类号： F02C6/00 , F02C3/10 , F02C3/34 , F02C7/18
CPC分类号： F02C6/006
摘要： A gas turbine engine comprises a turbine (10), a compressor turbine (14) mounted downstream the turbine (10) for rotation in a direction opposite to the rotation direction of the turbine (10) that is mounted downstream the compressor (12). Exhaust fluid from the compressor turbine (14) is cooled in a heat exchanger (24) with a compressed fluid downstream the compressor (12) and is then cooled with air in separate heat exchanger (26) before being admitted to the compressor (12). A part (25.1) of the compressed fluid heated in the heat exchanger (24) is fed to cool the turbine blades, and the rest (25.2) of the fluid is fed to a heated fluid source for the turbine. To control the gas turbine engine, a part of fluid is boosted by a booster compressor (30) and is discharged from the engine. The booster compressor (30) is driven by an expanding turbine (32) that is rotated under the effect of combustion air that is expanded in the expanding turbine (32) and flows through the expanding turbine (32) under the action of reduced pressure in the heated fluid source.
摘要翻译：燃气涡轮发动机包括涡轮机（10），安装在涡轮机（10）下游的压缩机涡轮机（14），用于沿安装在压缩机（12）下游的涡轮机（10）的旋转方向相反的方向旋转。来自压缩机涡轮机（14）的排出流体在热交换器（24）内被压缩流体在压缩机（12）的下游冷却，然后在分离的热交换器（26）内被空气冷却，然后进入压缩机（12）。供给在热交换器（24）中加热的压缩流体的一部分（25.1）以冷却涡轮机叶片，并将流体的其余部分（25.2）输送到用于涡轮机的加热流体源。为了控制燃气涡轮发动机，一部分流体由增压压缩机30升压，并从发动机排出。增压压缩机30由膨胀式涡轮机32驱动，涡轮机32在膨胀涡轮机32内膨胀的燃烧空气的作用下转动，并在减压作用下流过膨胀涡轮机32。加热的流体源。

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