公开(公告)号：US08596035B2

公开(公告)日：2013-12-03

申请号：US13171538

申请日：2011-06-29

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F02C7/057 ,  F02C9/00 ,  F02G3/00 ,  F23R3/26

CPC classification number: F01D17/146 ,  F04D27/0238 ,  F04D29/4213 ,  F04D29/462 ,  F05D2250/51

Abstract: Apparatus for reducing air mass flow through the compressor in a single shaft gas turbine engine having an extended operating range including part load conditions, to provide low emissions combustion. The apparatus includes one or more nozzles positioned for injecting compressed air into the inlet region of the compressor. The nozzles are oriented to direct the compressed air tangentially to, and in the same angular direction as, the direction of rotation to create a swirl in the inlet air flow to the compressor inducer. The apparatus also includes conduits in flow communication between the compressor diffuser and the nozzles, one or more valves operatively connected to control the flow of compressed air from the diffuser to the nozzles, and a controller operatively connected to the valves to cause compressed air flow to the nozzles during operation at part load conditions.

Abstract translation: 用于在单轴燃气涡轮发动机中减少空气质量流动的装置，其具有包括部分负载条件的延长的工作范围，以提供低排放燃烧。 该设备包括一个或多个喷嘴，定位成将压缩空气喷射到压缩机的入口区域中。 喷嘴被定向成将压缩空气切向地沿着旋转方向转动并且在与旋转方向相同的角度方向上，以在到压缩机诱导器的入口空气流中产生涡流。 该设备还包括在压缩机扩散器和喷嘴之间流动连通的管道，一个或多个阀，其可操作地连接以控制从扩散器到喷嘴的压缩空气流，以及可操作地连接到阀的控制器，以使压缩空气流入 喷嘴在部分负载条件下运行。

公开(公告)号：US08001792B1

公开(公告)日：2011-08-23

申请号：US12662284

申请日：2010-04-08

Applicant: Marek Dvorak ,  R. Jan Mowill

Inventor： Marek Dvorak ,  R. Jan Mowill

IPC: F01D25/14 ,  F01D25/26

CPC classification number: F01D9/045 ,  F01D5/187 ,  F01D9/042 ,  F01D25/246 ,  F02C7/20 ,  Y02T50/676 ,  Y10T29/49323

Abstract: Apparatus for channeling combustion gases to a turbine in a gas turbine engine. The engine has a compressor for providing compressed air, a combustor for combusting fuel with the compressed air to provide combustion gases, and a radial inflow turbine having an inlet configured to receive the combustion gases. The turbine is rotatable about an axis for expanding the combustion gases to produce work. The apparatus includes a subassembly of plurality of nozzle guide vanes fixed between a pair of spaced apart, ring-shaped sidewalls. A pair of spaced apart supports is configured to position the subassembly therebetween, concentric with the axis, and adjacent the turbine inlet. The apparatus further includes a plurality of bolt assemblies extending axially through the pair of supports, apertures in the sidewalls, and holes in the guide vanes. The sidewall apertures and guide vane holes each have an internal dimension in the radial direction sized and configured to accommodate thermal expansion and/or contraction sliding radial movement of the subassembly relative to the supports.

Abstract translation: 用于将燃烧气体引导到燃气涡轮发动机中的涡轮机的装置。 发动机具有用于提供压缩空气的压缩机，用于与压缩空气一起燃烧燃料以提供燃烧气体的燃烧器，以及具有被配置为接收燃烧气体的入口的径向流入涡轮机。 涡轮机可绕轴线旋转，用于膨胀燃烧气体以产生作业。 该装置包括固定在一对间隔开的环形侧壁之间的多个喷嘴导向叶片的子组件。 一对间隔开的支撑件构造成将子组件定位在它们之间，与轴线同心并且与涡轮机入口相邻。 该装置还包括多个螺栓组件，其轴向延伸穿过该对支撑件，侧壁中的孔和导向叶片中的孔。 侧壁孔和导向叶片孔各自具有在径向方向上的内部尺寸，其尺寸和构造适于容纳子组件相对于支撑件的热膨胀和/或收缩滑动径向移动。

公开(公告)号：US07628018B2

公开(公告)日：2009-12-08

申请号：US12073980

申请日：2008-03-12

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F02C1/00 ,  F02G3/00

CPC classification number: F02C3/145 ,  F01D5/043 ,  F01D9/026 ,  F02C3/05 ,  F02C3/08 ,  F02C3/103 ,  F04D17/162 ,  F05D2220/50 ,  Y02T50/673

Abstract: A compact, single shaft gas turbine gas generator uses a high pressure ratio dual-entry single stage centrifugal compressor, can combustors, and a radial inflow turbine with the compressor configured to achieve an overall pressure ratio of about 12:1 or greater and Mach Numbers less than or equal to about 1.4. The radial inflow turbine is configured to provide an expansion ratio of about 4:1 to about 5:1, to provide partially expanded combustion gases to a free-power turbine or an expansion nozzle, in a work-producing engine configuration. A ball bearing assembly in front of the compressor is used in conjunction with a thrust piston assembly to take up turbine thrust load, while a radial tilt pad bearing assembly is used in front of the turbine. A collector with scroll-shaped sector portions collects compressed air from an annular vaned diffuser, and respective crossover ducts channel the collected diffused compressed air from each sector portion to a plenum feeding can combustors. Bleed systems at each compressor inlet provide increased diffuser stability margins. Gas turbine engines configured with the above gas generator may provide 30% thermal efficiency or more in a rated power range of about 4 Mw or less.

Abstract translation: 紧凑型单轴燃气轮机气体发生器使用高压比双入口单级离心压缩机，可燃烧器和径向流入涡轮机，压缩机构造成实现大约12:1或更大的总体压力比和马赫数 小于或等于约1.4。 径向流入涡轮机被配置为在工作发动机构造中提供约4:1至约5:1的膨胀比，以将部分膨胀的燃烧气体提供给自由动力涡轮机或膨胀喷嘴。 在压缩机前面的滚珠轴承组件与推力活塞组件结合使用以承担涡轮机推力负载，而在涡轮机前方使用径向倾斜瓦块轴承组件。 具有涡旋形扇形部分的收集器从环形叶片扩散器收集压缩空气，并且相应的交叉导管将收集的扩散压缩空气从每个扇形部分引导到供气罐燃烧器的增压室。 每个压缩机入口处的排气系统提供增加的扩散器稳定裕度。 配置有上述气体发生器的燃气涡轮发动机可以在约4Mw或更小的额定功率范围内提供30％的热效率或更高。

公开(公告)号：US5572862A

公开(公告)日：1996-11-12

申请号：US348829

申请日：1994-11-29

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F02C3/05 ,  F02C3/10 ,  F02C9/50 ,  F23C99/00 ,  F23L1/00 ,  F23R3/26 ,  F23R3/28 ,  F23R3/30 ,  F23R3/42 ,  F23R3/50 ,  F23R3/52 ,  F23R3/54 ,  F02C7/22

CPC classification number: F23R3/42 ,  F02C9/50 ,  F23R3/26 ,  F23R3/286 ,  F23R3/50 ,  F23R3/54 ,  F05D2250/322

Abstract: An annular combustor system has an annular housing defining a single stage combustor, an external fuel/air premixer system to provide a preselected, nominally constant lean fuel/air ratio mixture for introduction to the combustion zone of the annular housing. Compressed air conduits channel a portion of the total compressed air flow to the premixer and the remainder to the dilution zone of the combustor. Convection cooling of the annular housing and the turbine shroud is accomplished using essentially the remainder portion of the compressed air without diluting the fuel air ratio in the combustion zone. The premixer includes a venturi, and a fuel nozzle for spraying fuel into the venturi inlet along the venturi axis to provide admission of the fully premixed fuel/air mixture. The venturi includes a perforated flow-smoothing and premixing initiating member surrounding both the venturi inlet and the fuel nozzle exit which is spaced from the venturi inlet to prevent impingement of the liquid fuel spray on the venturi walls and augment vaporization of liquid fuels.

Abstract translation: 环形燃烧器系统具有限定单级燃烧器的环形壳体，外部燃料/空气预混合器系统，以提供用于引入环形壳体的燃烧区域的预选的，名义上恒定的贫燃料/空气比混合物。 压缩空气管道将总压缩空气流的一部分通向预混合器，其余部分通向燃烧器的稀释区。 环形壳体和涡轮机护罩的对流冷却基本上是压缩空气的剩余部分，而不会在燃烧区域中稀释燃料空气比。 预混合器包括文氏管和用于沿文丘里轴将燃料喷入文氏管入口的燃料喷嘴，以提供完全预混燃料/空气混合物的进入。 文氏管包括围绕文丘里入口和燃料喷嘴出口的穿孔流动平滑和预混合起始构件，其与文丘里管入口间隔开，以防止液体燃料喷雾冲击文丘里壁并增加液体燃料的蒸发。

公开(公告)号：US5988589A

公开(公告)日：1999-11-23

申请号：US895456

申请日：1997-07-16

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F01D17/14 ,  F02C9/18 ,  F16K1/22 ,  F16K1/226 ,  F23L13/02 ,  F23R3/26 ,  F61K1/22

CPC classification number: F16K1/221 ,  F01D17/145 ,  F02C9/18 ,  F16K1/2268 ,  F23L13/02 ,  F23R3/26

Abstract: An air valve assembly for use with a premixer for a gas turbine engine module. The air valve assembly includes a valve disk and a support plate having a valve aperture in which the valve disk is disposed for rotation, the support plate having aligned first and second shaft apertures through opposing support plate ends that define an axis of rotation of the valve disk. The assembly also has a first shaft having one end section rotatably supported in the first aperture and having another end section connected to the valve disk; a second shaft having one end section rotatably supported in and extending through the second shaft aperture and with a bearing end terminating outside the support plate, and also having another end section connected to the valve disk. The assembly further includes an actuator shaft having an engagement end in axial abutting contact with the second shaft bearing end; and a coupling interconnecting the second shaft and the actuator shaft for transmitting precise rotary motion therebetween, the coupling having high torsional rigidity and low axial rigidity. The assembly still further has a coupling housing surrounding the coupling, the second shaft bearing end, and the actuator shaft engagement end, and having an actuator shaft aperture through which the actuator shaft extends, and a seal disposed between the actuator shaft engagement end and the housing for preventing air flow past the actuator shaft through the actuator shaft aperture.

Abstract translation: 一种用于燃气轮机发动机模块的预混合器的空气阀组件。 空气阀组件包括阀盘和具有阀孔的支撑板，其中阀盘设置在其中以便旋转，支撑板具有通过相对的支撑板端部对准的第一和第二轴孔，该支撑板端限定阀的旋转轴线 磁盘。 组件还具有第一轴，其具有可旋转地支撑在第一孔中的一个端部部分，并且具有连接到阀盘的另一端部; 第二轴具有可旋转地支撑在第二轴孔中并延伸穿过第二轴孔的一个端部部分，并且具有终止于支撑板外部的轴承端，并且还具有连接到阀盘的另一端部。 所述组件还包括致动器轴，所述致动器轴具有与所述第二轴承端端轴向抵接的接合端; 以及连接第二轴和致动器轴的联接器，用于在它们之间传递精确的旋转运动，联接器具有高扭转刚度和低轴向刚度。 组件还具有围绕联接器，第二轴承端和致动器轴接合端的联接壳体，并且具有致动器轴孔，致动器轴延伸穿过该致动器轴孔，以及设置在致动器轴接合端和 壳体，用于防止空气流过致动器轴通过致动器轴孔。

公开(公告)号：US5924276A

公开(公告)日：1999-07-20

申请号：US892397

申请日：1997-07-15

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F01D17/14 ,  F02C9/18 ,  F16K1/22 ,  F23L13/02 ,  F23R3/26 ,  F23R3/34

CPC classification number: F01D17/145 ,  F02C9/18 ,  F16K1/221 ,  F23L13/02 ,  F23R3/26 ,  F23R3/346

Abstract: A low emissions combustor system for a gas turbine includes a combustion chamber liner defining a combustion space for combusting a homogeneous fuel and compressed air mixture received through an inlet to produce combustion gases for delivery to the turbine through a liner exit. The liner has both principal dilution ports and secondary dilution ports adjacent and upstream of the liner exit, and a premixer assembly operatively connected to the liner for providing the fuel/air mixture. The premixer assembly includes an air valve for controlling the fuel/air ratio of the mixture. The combustor system also includes a compressed air supply plenum upstream of, and in flow communication with, the air valve. A shroud partly surrounds the liner and provides a cooling channel between the plenum and the principal dilution ports. The combustor system still further includes a bypass channel between the plenum and the secondary dilution ports, and a bypass valve operatively positioned to control flow from the plenum through the bypass channel. Alternatively, a single valve may be employed for regulating the flow of compressed air into the compressed air supply chamber and the bypass channel in lieu of an air valve and bypass valve, which combines their functions. Also, the liner can include an annular ridge extending into the combustion space for increasing residence time of the fuel/air mixture and combustion gases in the combustion space.

Abstract translation: 用于燃气轮机的低排放燃烧器系统包括限定用于燃烧通过入口接收的均质燃料和压缩空气混合物的燃烧空间的燃烧室衬套，以产生用于通过衬管出口输送到涡轮机的燃烧气体。 衬套具有邻近衬套出口的上游的主要稀释口和二次稀释口，以及可操作地连接到衬套上用于提供燃料/空气混合物的预混合器组件。 预混合器组件包括用于控制混合物的燃料/空气比的空气阀。 燃烧器系统还包括在空气阀上游并与气阀连通的压缩空气供应室。 护罩部分地围绕衬垫并且在气室和主稀释口之间提供冷却通道。 燃烧器系统还包括在气室和辅助稀释口之间的旁通通道，以及可操作地定位以控制来自气室通过旁通通道的流动的旁通阀。 或者，可以使用单个阀来调节压缩空气供应室和旁路通道中的压缩空气的流量，以代替空气阀和旁通阀，其组合其功能。 此外，衬套可以包括延伸到燃烧空间中的环形脊，以增加燃料/空气混合物和燃烧气体在燃烧空间中的停留时间。

公开(公告)号：US5628182A

公开(公告)日：1997-05-13

申请号：US450948

申请日：1995-05-23

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F02C9/50 ,  F23R3/26 ,  F23R3/28 ,  F23R3/42 ,  F23R3/50 ,  F23R3/54 ,  F02C3/14

CPC classification number: F02C9/50 ,  F23R3/26 ,  F23R3/286 ,  F23R3/42 ,  F23R3/50 ,  F23R3/54 ,  F05D2250/322

Abstract: A generally annular combustor system has a chamber with an annular chamber portion and a plurality of can-like chamber portions protruding from the annular chamber portion. An external fuel/air premixer is associated with each can chamber portion to provide a mixture with a desired (generally lean) fuel/air ratio tangentially through the can sidewall. A first portion of the total compressed air flows to the premixers, a second portion enters the combustion chamber through ports which, for can chamber volumes sufficient for complete combustion, can be located in the can chamber portion proximate the connection between the can portion and the annular portion. The premixer associated with each can chamber portion preferably includes a venturi and a fuel nozzle for spraying liquid fuel or gas into the venturi inlet to provide a fully premixed fuel/air mixture. An auxiliary fuel nozzle can be positioned in the annular portion for selectively supplying fuel for reheat of the combustion gases, using the dilution air, to maintain combustor outlet temperature. The annular chamber portion advantageously can be nested between the compressor and turbine components of large axial flow-type gas turbines in retrofit applications.

Abstract translation: 大体上环形的燃烧器系统具有一个具有环形室部分的腔室和从环形室部分突出的多个罐形腔室部分。 外部燃料/空气预混合器与每个罐室部分相关联，以通过罐壁侧向切向提供具有期望（通常为贫的）燃料/空气比的混合物。 总压缩空气的第一部分流入预混合器，第二部分通过端口进入燃烧室，通过这些端口，对于可容纳完全燃烧的罐体积，可以将罐室部分中的罐体部分和 环形部分。 与每个罐室部分相关联的预混合器优选地包括文丘里管和用于将液体燃料或气体喷射到文丘里管入口中以提供完全预混燃料/空气混合物的燃料喷嘴。 辅助燃料喷嘴可以定位在环形部分中，用于选择性地供应用于再燃烧燃烧气体的燃料，使用稀释空气来维持燃烧器出口温度。 环形室部分有利地可以嵌套在改进应用中的大型轴流式燃气轮机的压缩机和涡轮机部件之间。

公开(公告)号：US5613357A

公开(公告)日：1997-03-25

申请号：US654936

申请日：1996-05-29

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F02C9/50 ,  F23R3/26 ,  F23R3/28 ,  F23R3/42 ,  F23R3/50 ,  F23R3/54

CPC classification number: F23R3/42 ,  F02C9/50 ,  F23R3/26 ,  F23R3/286 ,  F23R3/50 ,  F23R3/54 ,  F05D2250/322

Abstract: A generally annular combustor system has a combustion chamber with an annular chamber portion and a plurality of can-like chamber portions protruding tangentially from the annular chamber portion, the portions collectively defining a single stage combustor. An external fuel/air premixer is associated with each can chamber portion to provide a preselected, nominally constant, lean fuel/air ratio mixture. A portion of the total compressed air flows to the premixers and the remaining portion is ducted to convection cooling passageways and finally admitted as dilution air proximate the exit of the annular chamber portion. When the fuel/power setting is changed, the combustion air flow is automatically set by varying the position of air valves associated with each premixer to achieve the desired combustible mass flow. In one embodiment, the air valve controls the dilution air flow rate from the plenum region and thus, indirectly, the combustion air flow rate. In an alternative embodiment, the air valve controls the combustion air to the premixers directly. Each premixer includes a venturi and a fuel nozzle for spraying liquid fuel or gas into the venturi inlet along the venturi axis to provide the fully premixed fuel/air mixture. The annular chamber portion advantageously can be nested between the compressor and turbine components of large axial-type flow gas turbines.

Abstract translation: 大致环形的燃烧器系统具有燃烧室，其具有环形室部分和从环形室部分切向突出的多个罐状室部分，这些部分共同限定单级燃烧器。 外部燃料/空气预混合器与每个罐室部分相关联以提供预选的，名义上恒定的贫燃料/空气比混合物。 总压缩空气的一部分流入预混合器，其余部分被导管到对流冷却通道，最后被允许作为邻近环形室部分出口处的稀释空气。 当燃料/动力设定改变时，通过改变与每个预混合器相关联的空气阀的位置来自动设定燃烧空气流，以实现所需的可燃物质流。 在一个实施例中，空气阀控制来自增压室区域的稀释空气流量，从而控制燃烧空气流速。 在替代实施例中，空气阀直接控制到预混合器的燃烧空气。 每个预混合器包括文丘里管和燃料喷嘴，用于沿着文丘里轴线将液体燃料或气体喷入文丘里管入口以提供完全预混合的燃料/空气混合物。 环形室部分有利地可以嵌套在大型轴流式流动燃气涡轮机的压缩机和涡轮机部件之间。

公开(公告)号：US4641495A

公开(公告)日：1987-02-10

申请号：US698586

申请日：1985-02-05

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F02C3/10

CPC classification number: F02C3/103 ,  F05D2220/50

Abstract: A compact, highly efficient single spool gas turbine gas generator uses a double-entry centrifugal first stage compressor, a single-entry centrifugal second stage compressor, and a radial inflow turbine to achieve an overall pressure ratio of greater than 15:1. The first stage pressure ratio is more than twice the second stage pressure ratio, and the first stage entrance Mach numbers are greater than about 1.4. The specific speed of each the compressors ranges from 0.65 to 0.85, and of the turbine from 0.50 to 0.75.

Abstract translation: 一种紧凑，高效的单线轴燃气轮机气体发生器采用双入口离心式第一级压缩机，单级离心式第二级压缩机和径向流入式涡轮机，以实现大于15：1的总体压力比。 第一级压力比是第二级压力比的两倍以上，第一级入口马赫数大于约1.4。 每个压缩机的具体速度范围为0.65至0.85，涡轮的比例为0.50至0.75。