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公开(公告)号：US20240287942A1
公开(公告)日：2024-08-29
申请号：US18386816
申请日：2023-11-03
摘要： A powerplant is provided that includes a first gas turbine engine, a second gas turbine engine, a second engine bypass flowpath and a flow control system. The first gas turbine engine includes a first core flowpath fluidly coupled with a first inlet and a first exhaust. The first core flowpath extends sequentially through a first compressor section, a first combustor section and a first turbine section. The second gas turbine engine a second core flowpath fluidly coupled with a second inlet and a second exhaust. The second core flowpath extends sequentially through a second compressor section, a second combustor section and a second turbine section. The flow control system fluidly couples the first inlet and the first exhaust to the second core flowpath during a first mode. The flow control system fluidly couples the first inlet and the first exhaust to the second engine bypass flowpath during a second mode.
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公开(公告)号：US09279388B2
公开(公告)日：2016-03-08
申请号：US13287073
申请日：2011-11-01
申请人： Daniel B. Kupratis
发明人： Daniel B. Kupratis
摘要： A gas turbine engine and a method of operating the gas turbine engine according to an exemplary aspect of the present disclosure includes modulating a variable high pressure turbine inlet guide vane of a high pressure spool to performance match a first stage fan section of a low pressure spool and an intermediate stage fan section of an intermediate spool to maintain a generally constant engine inlet flow while varying engine thrust.
摘要翻译： 根据本公开的示例性方面的燃气涡轮发动机和操作燃气涡轮发动机的方法包括调制高压阀芯的可变高压涡轮机入口引导叶片以使其与低压阀芯的第一级风扇部分匹配 以及中间阀芯的中间级风扇部分，以在改变发动机推力的同时保持发动机入口流体的大致恒定。
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公开(公告)号：US09188083B2
公开(公告)日：2015-11-17
申请号：US13283649
申请日：2011-10-28
申请人： Daniel B. Kupratis
发明人： Daniel B. Kupratis
摘要： A propulsion system and a method of operating the propulsion system according to an exemplary aspect of the present disclosure includes powering an auxiliary fan with a gas turbine engine, the auxiliary fan along an auxiliary axis and the gas turbine engine along an engine axis, the auxiliary axis parallel to the engine axis.
摘要翻译： 根据本公开的示例性方面的推进系统和操作推进系统的方法包括：利用燃气涡轮发动机，沿着辅助轴线的辅助风扇和沿着发动机轴线的燃气涡轮发动机来驱动辅助风扇，辅助风扇 轴平行于发动机轴。
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公开(公告)号：US08516789B2
公开(公告)日：2013-08-27
申请号：US13190595
申请日：2011-07-26
申请人： Daniel B. Kupratis
发明人： Daniel B. Kupratis
IPC分类号： F02K3/065
摘要： A gas turbine engine includes a low spool along an engine axis with a forward fan section and a low pressure turbine section. A high spool along the engine axis with a high pressure turbine section and an aft core driven fan section (CDFS), the aft core driven fan section (CDFS) axially aft of the high pressure turbine section along the engine axis.
摘要翻译： 燃气涡轮发动机包括具有前风扇部分和低压涡轮部分的沿着发动机轴线的低线轴。 沿着发动机轴线的具有高压涡轮部分和后部核心驱动风扇部分（CDFS）的高阀芯，沿着发动机轴线的高压涡轮机部分的后部后轴驱动风扇部分（CDFS）。
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公开(公告)号：US20130145769A1
公开(公告)日：2013-06-13
申请号：US13316058
申请日：2011-12-09
CPC分类号： F02C7/36 , F02C3/145 , F02C7/32 , F02K3/105 , F05D2220/76 , F05D2260/4023 , F05D2260/96
摘要： A gas turbine engine has a variable overall pressure rate (“OPR”). The engine includes a high pressure compressor having at least a primary stage having a set of primary rotors and a secondary stage having a set of secondary rotors. A clutch is provided to selectively engage the secondary rotors with the primary rotors. Engagement of the clutch may be controlled based on the vehicle travel mode, such as disengaging during a takeoff mode to reduce turbine entry temperature and engaging during a loiter mode to increase OPR.
摘要翻译： 燃气涡轮发动机具有可变的总压力（“OPR”）。 发动机包括具有至少一个初级级的高压压缩机，该初级级具有一组初级转子和具有一组次级转子的次级级。 提供离合器以选择性地将副转子与主转子接合。 可以基于车辆行驶模式来控制离合器的接合，例如在起飞模式期间分离以降低涡轮进入温度并且在升降机模式期间接合以增加OPR。
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公开(公告)号：US08176725B2
公开(公告)日：2012-05-15
申请号：US12556359
申请日：2009-09-09
申请人： Jams W. Norris , Alan Epstein , Gary D. Roberge , Mark W. Costa , Andrew P. Berryann , Daniel B. Kupratis
发明人： Jams W. Norris , Alan Epstein , Gary D. Roberge , Mark W. Costa , Andrew P. Berryann , Daniel B. Kupratis
IPC分类号： F02K3/02
CPC分类号： F02C3/107 , F02C3/145 , F02C7/32 , F02C7/36 , F02K3/105 , F05D2220/76 , Y02T50/671
摘要： A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and a forward-flow low pressure turbine disposed aft of the low pressure compressor. The high spool comprises a forward-flow high pressure turbine disposed aft of the low pressure turbine, a combustor disposed aft of the high pressure turbine, and a forward-flow high pressure compressor disposed aft of the combustor.
摘要翻译： 燃气涡轮发动机包括风扇驱动齿轮系统，连接到风扇驱动齿轮系统的低阀芯和位于低阀芯的后面的高阀芯。 低阀芯包括设置在风扇驱动齿轮系统后面的向后流动的低压压缩机，以及设置在低压压缩机后面的前进低压涡轮机。 高阀芯包括设置在低压涡轮机后方的前流高压涡轮机，设置在高压涡轮机后方的燃烧器和设置在燃烧器后部的前进高压压缩机。
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公开(公告)号：US08161728B2
公开(公告)日：2012-04-24
申请号：US11770024
申请日：2007-06-28
申请人： Daniel B. Kupratis
发明人： Daniel B. Kupratis
IPC分类号： F02C3/04
CPC分类号： F02K3/077
摘要： A representative gas turbine includes: a high pressure spool; a high pressure compressor; a high pressure turbine mechanically coupled to the high pressure spool; a lower pressure spool; a lower pressure turbine mechanically coupled to the lower pressure spool; a fan having a first set of fan blades and a second set of fan blades, the second set of fan blades being located downstream of the first set of fan blades and being operative to rotate at a rotational speed corresponding to a rotational speed of the lower pressure spool; and a gear assembly mechanically coupled to the lower pressure spool and engaging the first set of fan blades such that rotation of the lower pressure spool rotates the first set of fan blades at a lower rotational speed than the rotational speed of the second set of fan blades.
摘要翻译： 代表性的燃气轮机包括：高压阀芯; 高压压缩机; 机械地联接到高压阀芯的高压涡轮机; 低压阀芯; 机械地联接到所述低压阀芯的低压涡轮机; 具有第一组风扇叶片和第二组风扇叶片的风扇，第二组风扇叶片位于第一组风扇叶片的下游，并且可操作以以与下部风扇叶片的转速对应的转速旋转 压力阀芯; 以及齿轮组件，其机械地联接到所述下压力卷轴并且接合所述第一组风扇叶片，使得所述下压力卷轴的旋转以比所述第二组风扇叶片的旋转速度更低的旋转速度旋转所述第一组风扇叶片 。
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公开(公告)号：US20090000271A1
公开(公告)日：2009-01-01
申请号：US11770032
申请日：2007-06-28
申请人： Daniel B. Kupratis
发明人： Daniel B. Kupratis
IPC分类号： F02K3/04
摘要： Gas turbines with multiple gas flow paths are provided. In this regard, a representative gas turbine includes: a spool; a compressor; a turbine mechanically coupled to the spool; the compressor having a first set of blades and a second set of blades, the second set of blades being located downstream of the first set of blades, the first set of blades and the second set of blades being driven by the spool; and means for enabling the first set of blades to rotate at a lower rotational speed than the second set of blades.
摘要翻译： 提供具有多个气体流路的燃气轮机。 在这方面，代表性的燃气轮机包括：阀芯; 压缩机 机械地联接到卷轴的涡轮机; 所述压缩机具有第一组叶片和第二组叶片，所述第二组叶片位于所述第一组叶片的下游，所述第一组叶片和所述第二组叶片由所述卷轴驱动; 以及用于使所述第一组叶片以比所述第二组叶片更低的转速旋转的装置。
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公开(公告)号：US20130104524A1
公开(公告)日：2013-05-02
申请号：US13287446
申请日：2011-11-02
申请人： Daniel B. Kupratis
发明人： Daniel B. Kupratis
CPC分类号： F02K3/04 , F02C3/107 , F02K3/06 , F02K3/077 , Y02T50/671
摘要： A gas turbine engine comprises an outer engine case, a combustor, a high pressure spool and a low pressure spool. The combustor is disposed within the outer engine case. The high pressure spool is configured for rotation coaxially with the combustor. The low pressure spool is configured for rotation coaxially with the high pressure spool. The low pressure spool is configured to rotate at speeds faster than that of the high pressure spool during operation of the gas turbine engine. In one embodiment, the low pressure spool includes a gear system configured to rotate a low pressure compressor faster than a low pressure turbine. In another embodiment, the high pressure spool rotates outward of the combustor within the outer engine case. In another embodiment, the high pressure spool includes a drum having radially inward projecting blades and vanes and radially outward projecting fan blades.
摘要翻译： 燃气涡轮发动机包括外发动机壳体，燃烧器，高压阀芯和低压阀芯。 燃烧器设置在外部发动机壳体内。 高压阀芯构造成与燃烧器同轴旋转。 低压阀芯构造成与高压阀芯同轴旋转。 低压阀芯构造成在燃气涡轮发动机的运行期间以比高压阀芯更快的速度旋转。 在一个实施例中，低压阀芯包括被配置为比低压涡轮机更快地旋转低压压缩机的齿轮系统。 在另一个实施例中，高压阀芯在外部发动机壳体内向外旋转燃烧器。 在另一个实施例中，高压线轴包括具有径向向内突出的叶片和叶片以及径向向外突出的风扇叶片的滚筒。
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10.发明申请GAS TURBINE ENGINE WITH INTERCOOLING TURBINE SECTION AND INTERCOOLING TURBINE SECTION BYPASS 有权具有介质涡轮部分和干扰涡轮机部分旁路的气体涡轮发动机公开(公告)号：US20130098055A1
公开(公告)日：2013-04-25
申请号：US13325034
申请日：2011-12-13
申请人： Daniel B. Kupratis
发明人： Daniel B. Kupratis
IPC分类号： F02C3/10
CPC分类号： F02C7/143 , Y02T50/675
摘要： A gas turbine engine includes an intercooling turbine section to at least partially drive one of a low spool and a high spool. An intercooling turbine section bypass to selectively bypass at least a portion of a core flow through an intercooling turbine section bypass path around the intercooling turbine section.
摘要翻译： 燃气涡轮发动机包括中间冷却涡轮机部分，以至少部分地驱动低滑阀和高滑阀中的一个。 中间冷却涡轮机部分旁路以选择性地绕过中心冷却涡轮机部分周围的中间冷却涡轮部分旁路的核心流的至少一部分。
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