公开(公告)号：US06925809B2

公开(公告)日：2005-08-09

申请号：US10014415

申请日：2001-12-14

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F23R3/26 ,  F23R3/28 ,  F02C7/00 ,  F02C9/00 ,  F02C9/50

CPC classification number: F23R3/26 ,  F23R3/286 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

Abstract: Apparatus for premixing fuel and air to provide a fuel/air mixture includes a mixing tube configured for receiving fuel and air, a mixing tube axis, and a mixing tube exit for discharging a fuel/air mixture. The apparatus further includes a mixture valve associated with the mixing tube exit and including inner and outer valve members that define an exit flow area. The defined exit flow area includes at least two segmented, substantially opposed area portions with respect to angular position about the mixing tube axis for directing the mixture flow, and at least one of the inner and outer valve members is movable relative to the other of said valve members to selectively vary the defined exit flow area with respect to time. In a gas turbine gas generator or engine application, a separate controllable combustion air valve can be used with a fuel valve to provide controlled fuel/air ratios for the mixture.

Abstract translation: 用于将燃料和空气预混合以提供燃料/空气混合物的装置包括构造成用于接收燃料和空气的混合管，混合管轴线和用于排出燃料/空气混合物的混合管出口。 该装置还包括与混合管出口相关联并包括限定出口流动区域的内部和外部阀构件的混合阀。 限定的出口流动区域包括相对于围绕混合管轴线的角度位置的至少两个分段的基本上相对的区域部分，用于引导混合物流，并且内部和外部阀构件中的至少一个可相对于所述混合管轴线中的另一个移动 阀构件以相对于时间选择性地改变限定的出口流动面积。 在燃气轮机气体发生器或发动机应用中，单独的可控燃烧空气阀可与燃料阀一起使用以提供混合物的受控燃料/空气比。

公开(公告)号：US06220034B1

公开(公告)日：2001-04-24

申请号：US09033615

申请日：1998-03-03

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F23R330

CPC classification number: F02C9/50 ,  F05D2250/322 ,  F23R3/26 ,  F23R3/286 ,  F23R3/346 ,  F23R3/42 ,  F23R3/50 ,  F23R3/54

Abstract: A premixer for a combustor system has a venturi-type mixing tube with a flow axis, an inlet adjacent one axial mixing tube end, and a nozzle assembly at the opposite axial mixing tube end. The mixing tube inlet is flow connected to a source of compressed air and a source of fuel, and the mixing tube is connected to combustion chamber, an annular or can-type liner and an inlet, and the nozzle assembly extends into the combustion chamber and has at least one port for distributing the fuel/air mixture within a single stage combustion zone. In a preferred configuration, a pair of premixers are located at diametrically opposed positions on an annular combustion chamber, and the venturi axes are both radially disposed and axially inclined with respect to the combustion chamber axis. A single, centrally located, cylindrical air valve controls compressed air flow to both premixers through a manifold and distribution conduits.

Abstract translation: 用于燃烧器系统的预混合器具有文氏管式混合管，其具有流动轴线，邻近一个轴向混合管端的入口和在相对的轴向混合管端部处的喷嘴组件。 混合管入口流动连接到压缩空气源和燃料源，混合管连接到燃烧室，环形或罐型衬套和入口，喷嘴组件延伸到燃烧室中， 具有至少一个用于在单级燃烧区域内分配燃料/空气混合物的端口。 在优选的结构中，一对预混合器位于环形燃烧室上的直径相对的位置处，并且文丘里轴线相对于燃烧室轴线径向设置并且轴向倾斜。 单个中心位置的圆柱形空气阀通过歧管和分配管道控制通过两个预混合器的压缩空气流。

公开(公告)号：US5765363A

公开(公告)日：1998-06-16

申请号：US779350

申请日：1997-01-06

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

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

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

Abstract: An annular combustor system is disclosed in use with a radial turbine-type gas turbine gas generator, the system having an annular housing defining a single stage combustor, an external fuel/air premixer system having a mixing chamber and a fuel valve under the control of a controller, to provide a preselected lean fuel/air ratio mixture for introduction to the combustion zone of the annular housing. A separate compressed air valve under the control of the controller can optionally be included. Compressed air conduits are used to channel a portion of the total compressed air flow to the premixer and the remainder to the dilution zone of the combustor, and a fuel conduit is used to deliver all of the fuel to the premixer. Convection cooling of the annular housing is accomplished using 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, the venturi axis being aligned substantially tangentially to the annular housing axis to provide a swirling admission of the fully premixed fuel/air mixture to the combustion zone. The venturi can include a flow-smoothing member and be heated to provide augmented vaporization of liquid fuels. The compressed air valve can be integrated with the premixer housing.

Abstract translation: 公开了一种环形燃烧器系统，其与径向涡轮式燃气轮机气体发生器一起使用，该系统具有限定单级燃烧器的环形壳体，具有混合室和燃料阀的外部燃料/空气预混合器系统， 控制器，以提供用于引入环形壳体的燃烧区域的预选的贫燃料/空气比混合物。 可以选择在控制器的控制下单独的压缩空气阀。 压缩空气管道用于将总压缩空气流的一部分引导到预混合器，其余部分通向燃烧器的稀释区，并且使用燃料管道将所有燃料输送到预混合器。 环形壳体的对流冷却是使用压缩空气完成的，而不会在燃烧区域内稀释燃料空气比。 预混合器包括文氏管和用于沿文丘里轴将燃料喷入文丘里管入口的燃料喷嘴，文丘里轴基本上与环形壳体轴线相切地对齐，以提供完全预混燃料/空气混合物到燃烧的旋转进入 区。 文丘里管可以包括流动平滑部件，并被加热以提供液体燃料的增强蒸发。 压缩空气阀可以与预混合器壳体集成。

公开(公告)号：US5377483A

公开(公告)日：1995-01-03

申请号：US178848

申请日：1994-01-07

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F02C7/18 ,  F02C7/22 ,  F02C7/232 ,  F02C9/50 ,  F23R3/12 ,  F23R3/26 ,  F23R3/28 ,  F23R3/30 ,  F23R3/42 ,  F23R3/50 ,  F23R3/54

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

Abstract: An annular combustor system is disclosed in use with a radial turbine-type gas turbine engine module, the system having an annular housing defining a single stage combustor, an external fuel/air premixer system having a mixing chamber and a compressed air valve and a fuel valve both under the control of a controller, to provide a preselected lean fuel/air ratio mixture for introduction to the combustion zone of the annular housing. Compressed air conduits are used to channel a portion of the total compressed air flow to the premixer and the remainder to the dilution zone of the combustor, and a fuel conduit is used to deliver all of the fuel to the premixer. Convection cooling of the annular housing is accomplished using compressed air without diluting the fuel air ratio in the combustion zone. The premixer includes a venturi, a fuel nozzle for spraying fuel into the venturi inlet along the venturi axis, and a premixer housing integrating the compressed air valve, the venturi axis being aligned substantially tangentially to the annular housing axis to provide a swirling admission of the premixed fuel/air mixture to the combustion zone.

Abstract translation: 公开了一种使用径向涡轮式燃气涡轮发动机模块的环形燃烧器系统，该系统具有限定单级燃烧器的环形壳体，具有混合室和压缩空气阀以及燃料的外部燃料/空气预混合器系统 阀门都在控制器的控制下，以提供用于引入环形壳体的燃烧区域的预选的稀燃料/空气比混合物。 压缩空气管道用于将总压缩空气流的一部分引导到预混合器，其余部分通向燃烧器的稀释区，并且使用燃料管道将所有燃料输送到预混合器。 环形壳体的对流冷却是使用压缩空气完成的，而不会在燃烧区域内稀释燃料空气比。 预混合器包括文丘里管，用于沿着文丘里轴将燃料喷入文丘里管入口的燃料喷嘴，以及整合压缩空气阀的预混合器壳体，文丘里轴线基本上切向地与环形壳体轴线对齐，以提供涡旋入口 预混燃料/空气混合物到燃烧区。

公开(公告)号：US07162874B2

公开(公告)日：2007-01-16

申请号：US10902089

申请日：2004-07-30

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F02C9/52

CPC classification number: F02C9/52 ,  F02C9/18 ,  F02C9/28 ,  F05D2270/053 ,  F23N1/02 ,  F23N2041/20 ,  F23R3/26 ,  F23R3/286

Abstract: A gas turbine engine with a single stage combustor includes an external premixer to provide premixed fuel/compressed air to the combustor as well as compressed air for dilution; and an automatic controller to provide feedback control of the compressed air flow and fuel flow to the premixer in accordance with actual power versus power demand. The fuel/compressed air mixture is combusted in a combustor and the combustion gases and dilution air are expanded in a turbine. The engine further includes a bleed valve under control of the controller for diverting sufficient compressed dilution air past the turbine to induce increased fuel flow and compressed air flow to the premixer for delivery to, and combustion of, the combustor to compensate for the power deficit due to the bled air, to provide selected minimum premixer exit velocities during engine operation.

Abstract translation: 具有单级燃烧器的燃气涡轮发动机包括外部预混合器，以向燃烧器提供预混燃料/压缩空气以及用于稀释的压缩空气; 以及自动控制器，以根据实际功率对功率需求提供对预混合器的压缩空气流和燃料流的反馈控制。 燃料/压缩空气混合物在燃烧器中燃烧，燃烧气体和稀释空气在涡轮机中膨胀。 发动机还包括在控制器的控制下的排放阀，用于将足够的压缩稀释空气转移通过涡轮机，以引起增加的燃料流量和压缩空气流到预混合器以传递到燃烧器和燃烧燃烧器，以补偿由于 在发动机运行期间提供选定的最小预混合器出口速度。

公开(公告)号：US5638674A

公开(公告)日：1997-06-17

申请号：US264844

申请日：1994-07-05

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

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

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

Abstract: An annular combustor system is disclosed in use with a radial turbine-type gas turbine gas generator, the system having an annular housing defining a single stage combustor, an external fuel/air premixer system having a mixing chamber and a fuel valve under the control of a controller, to provide a preselected lean fuel/air ratio mixture for introduction to the combustion zone of the annular housing. A separate compressed air valve under the control of the controller can optionally be included. Compressed air conduits are used to channel a portion of the total compressed air flow to the premixer and the remainder to the dilution zone of the combustor, and a fuel conduit is used to deliver all of the fuel to the premixer. Convection cooling of the annular housing is accomplished using 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, the venturi axis being aligned substantially tangentially to the annular housing axis to provide a swirling admission of the fully premixed fuel/air mixture to the combustion zone. The venturi can include a flow-smoothing member and be heated to provide augmented vaporization of liquid fuels. The compressed air valve can be integrated with the premixer housing.

Abstract translation: 公开了一种环形燃烧器系统，其与径向涡轮式燃气轮机气体发生器一起使用，该系统具有限定单级燃烧器的环形壳体，具有混合室和燃料阀的外部燃料/空气预混合器系统， 控制器，以提供用于引入环形壳体的燃烧区域的预选的贫燃料/空气比混合物。 可以选择在控制器的控制下单独的压缩空气阀。 压缩空气管道用于将总压缩空气流的一部分引导到预混合器，其余部分通向燃烧器的稀释区，并且使用燃料管道将所有燃料输送到预混合器。 环形壳体的对流冷却是使用压缩空气完成的，而不会在燃烧区域内稀释燃料空气比。 预混合器包括文氏管和用于沿文丘里轴将燃料喷入文丘里管入口的燃料喷嘴，文丘里轴基本上与环形壳体轴线相切地对齐，以提供完全预混燃料/空气混合物到燃烧的旋转进入 区。 文丘里管可以包括流动平滑部件，并被加热以提供液体燃料的增强蒸发。 压缩空气阀可以与预混合器壳体集成。

公开(公告)号：US4704861A

公开(公告)日：1987-11-10

申请号：US933357

申请日：1986-11-19

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F02C7/20 ,  F04D29/04 ,  F04D29/051 ,  F04D29/40 ,  F16D1/06 ,  F02C7/04

CPC classification number: F04D29/051 ,  F02C7/20 ,  F04D29/403 ,  F16D1/06

Abstract: A gas generator having a double entry low pressure centrifugal compressor, a single entry high pressure centrifugal compressor and a radial inflow turbine positioned coaxially and coupled for interdependent rotation by a single shaft assembly for the double entry compressor mounted to the generator frame using a plurality of rigid hollow cross-over ducts which also carry diffused compressed air to the high pressure compressor, where the single shaft assembly uses two shaft portions connected by an expansible coupling having a helical spline torque transmitting device to allow the double entry compressor rotor to "follow" compressor housing axial position changer and to maintain a close running clearance despite thermal expansion in the structure between the low pressure (LP) and high pressure (HP) compressor portions of the gas generator.

Abstract translation: 一种具有双入口低压离心压缩机，单入口高压离心压缩机和径向流入涡轮机的气体发生器，其同轴并联接，用于通过单个轴组件进行相互转动，用于使用多个 刚性中空交叉管道，其还将高压压缩机承载扩散的压缩空气，其中单轴组件使用两个轴部分，该两个轴部分通过具有螺旋花键扭矩传递装置的可膨胀联接器连接，以允许双入口压缩机转子“跟随” 压缩机壳体轴向位置更换器，并且尽管在气体发生器的低压（LP）和高压（HP）压缩机部分之间的结构中的热膨胀而保持紧密的运行间隙。

公开(公告)号：US20090232676A1

公开(公告)日：2009-09-17

申请号：US12073980

申请日：2008-03-12

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F04D25/04 ,  F02C7/00 ,  F04D17/10

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：US5481866A

公开(公告)日：1996-01-09

申请号：US261256

申请日：1994-06-14

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F02C7/18 ,  F02C7/22 ,  F02C7/232 ,  F02C9/50 ,  F23R3/12 ,  F23R3/26 ,  F23R3/28 ,  F23R3/30 ,  F23R3/42 ,  F23R3/50 ,  F23R3/54

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

Abstract: An annular combustor system is disclosed in use with a radial turbine-type gas turbine engine module, the system having an annular housing defining a single stage combustor, an external fuel/air premixer system having a mixing chamber and a compressed air valve and a fuel valve both under the control of a controller, to provide a preselected lean fuel/air ratio mixture for introduction to the combustion zone of the annular housing. Compressed air conduits are used to channel a portion of the total compressed air flow to the premixer and the remainder to the dilution zone of the combustor, and a fuel conduit is used to deliver all of the fuel to the premixer. Convection cooling of the annular housing is accomplished using compressed air without diluting the fuel air ratio in the combustion zone. The premixer includes a venturi, a fuel nozzle for spraying fuel into the venturi inlet along the venturi axis, and a premixer housing integrating the compressed air valve, the venturi axis being aligned substantially tangentially to the annular housing axis to provide a swirling admission of the premixed fuel/air mixture to the combustion zone.

公开(公告)号：US5477671A

公开(公告)日：1995-12-26

申请号：US253567

申请日：1994-06-03

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F02C7/18 ,  F02C7/22 ,  F02C7/232 ,  F02C9/50 ,  F23R3/12 ,  F23R3/26 ,  F23R3/28 ,  F23R3/30 ,  F23R3/42 ,  F23R3/50 ,  F23R3/54

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

Abstract: An annular combustor system is disclosed in use with a radial turbine-type gas turbine engine module, the system having an annular housing defining a single stage combustor, an external fuel/air premixer system having a mixing chamber and a compressed air valve and a fuel valve both under the control of a controller, to provide a preselected lean fuel/air ratio mixture for introduction to the combustion zone of the annular housing. Compressed air conduits are used to channel a portion of the total compressed air flow to the premixer and the remainder to the dilution zone of the combustor, and a fuel conduit is used to deliver all of the fuel to the premixer. Convection cooling of the annular housing is accomplished using compressed air without diluting the fuel air ratio in the combustion zone. The premixer includes a venturi, a fuel nozzle for spraying fuel into the venturi inlet along the venturi axis, and a premixer housing integrating the compressed air valve, the venturi axis being aligned substantially tangentially to the annular housing axis to provide a swirling admission of the premixed fuel/air mixture to the combustion zone.

Abstract translation: 公开了一种使用径向涡轮式燃气涡轮发动机模块的环形燃烧器系统，该系统具有限定单级燃烧器的环形壳体，具有混合室和压缩空气阀以及燃料的外部燃料/空气预混合器系统 阀门都在控制器的控制下，以提供用于引入环形壳体的燃烧区域的预选的稀燃料/空气比混合物。 压缩空气管道用于将总压缩空气流的一部分引导到预混合器，其余部分通向燃烧器的稀释区，并且使用燃料管道将所有燃料输送到预混合器。 环形壳体的对流冷却是使用压缩空气完成的，而不会在燃烧区域内稀释燃料空气比。 预混合器包括文丘里管，用于沿着文丘里轴将燃料喷入文丘里管入口的燃料喷嘴，以及整合压缩空气阀的预混合器壳体，文丘里轴线基本上切向地与环形壳体轴线对齐，以提供涡旋入口 预混燃料/空气混合物到燃烧区。