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1.发明申请GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES 审中-公开具有高速低压涡轮部分和轴承支持特性的气体涡轮发动机公开(公告)号：US20130192265A1
公开(公告)日：2013-08-01
申请号：US13446194
申请日：2012-04-13
CPC分类号： F02K3/06 , F01D25/162 , F02C3/067 , F02C7/06 , F02C7/36 , F02K3/072 , F02K3/075 , F05D2260/40311
摘要： A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted on the low pressure turbine with an intermediate bearing.
摘要翻译： 燃气涡轮发动机包括非常高速的低压涡轮机，使得由低压涡轮机的出口面积所规定的量乘以低压涡轮机转速的平方，与用于高压涡轮机的相同参数相比是在 在约0.5和约1.5之间。 高压涡轮机安装在具有中间轴承的低压涡轮机上。
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公开(公告)号：US20130192263A1
公开(公告)日：2013-08-01
申请号：US13410776
申请日：2012-03-02
IPC分类号： F02C3/06
CPC分类号： F02K3/072
摘要： A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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3.发明申请公开(公告)号：US20130195621A1
公开(公告)日：2013-08-01
申请号：US13558605
申请日：2012-07-26
申请人： Frederick M. Schwarz , Daniel Bernard Kupratis , Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
发明人： Frederick M. Schwarz , Daniel Bernard Kupratis , Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
IPC分类号： F04D29/00
CPC分类号： F02C7/36 , F01D5/06 , F01D25/162 , F02C3/06 , F02C3/107 , F02C7/06 , F02K3/06 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/35 , F05D2240/60 , F05D2260/40311
摘要： A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.
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4.发明授权公开(公告)号：US09611859B2
公开(公告)日：2017-04-04
申请号：US13446510
申请日：2012-04-13
IPC分类号： F02K3/06 , F04D29/056 , F02C7/06 , F02C7/20
CPC分类号： F04D29/056 , F02C7/06 , F02C7/20 , F02K3/06
摘要： A gas turbine engine includes a very high speed fan drive turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted by bearings positioned at an outer periphery of a shaft driven by the high pressure turbine.
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5.发明授权Gas turbine engine with high speed low pressure turbine section and bearing support features 有权具有高速低压涡轮机部分和轴承支持特征的燃气轮机公开(公告)号：US09540948B2
公开(公告)日：2017-01-10
申请号：US13558605
申请日：2012-07-26
申请人： Frederick M. Schwarz , Daniel Bernard Kupratis , Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
发明人： Frederick M. Schwarz , Daniel Bernard Kupratis , Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
CPC分类号： F02C7/36 , F01D5/06 , F01D25/162 , F02C3/06 , F02C3/107 , F02C7/06 , F02K3/06 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/35 , F05D2240/60 , F05D2260/40311
摘要： A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.
摘要翻译： 燃气涡轮发动机包括非常高速的低压涡轮机，使得由低压涡轮机的出口面积所规定的数量乘以低压涡轮转速的平方，与高压涡轮机的相同参数相比是在 在约0.5和约1.5之间。 高压涡轮机由位于第一轴连接到承载与第二涡轮机部分相关联的涡轮转子的轮毂的位置处的轴承支撑。
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公开(公告)号：US20130192196A1
公开(公告)日：2013-08-01
申请号：US13363154
申请日：2012-01-31
IPC分类号： F02K3/02
摘要： A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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7.发明申请GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES 有权具有高速低压涡轮部分和轴承支持特性的气体涡轮发动机公开(公告)号：US20130195648A1
公开(公告)日：2013-08-01
申请号：US13446510
申请日：2012-04-13
IPC分类号： F04D29/04
CPC分类号： F04D29/056 , F02C7/06 , F02C7/20 , F02K3/06
摘要： A gas turbine engine includes a very high speed fan drive turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted by bearings positioned at an outer periphery of a shaft driven by the high pressure turbine.
摘要翻译： 燃气涡轮发动机包括非常高速的风扇驱动涡轮机，使得由与低压涡轮机的相同参数相比较的低压涡轮机的出口面积乘以低压涡轮机转速的平方所定义的数量为 在约0.5和约1.5之间。 高压汽轮机由位于由高压汽轮机驱动的轴的外周处的轴承安装。
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8.发明申请GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES 审中-公开具有高速低压涡轮部分和轴承支持特性的气体涡轮发动机公开(公告)号：US20130192191A1
公开(公告)日：2013-08-01
申请号：US13455235
申请日：2012-04-25
申请人： Frederick M. Schwarz , Daniel Bernard Kupratis , Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
发明人： Frederick M. Schwarz , Daniel Bernard Kupratis , Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
IPC分类号： F02G3/00
CPC分类号： F02C7/36 , F01D5/06 , F01D25/162 , F02C3/06 , F02C3/107 , F02C7/06 , F02K3/06 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/35 , F05D2240/60 , F05D2260/40311
摘要： A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.
摘要翻译： 燃气涡轮发动机包括非常高速的低压涡轮机，使得由低压涡轮机的出口面积所规定的数量乘以低压涡轮转速的平方，与高压涡轮机的相同参数相比是在 在约0.5和约1.5之间。 高压涡轮机由位于第一轴连接到承载与第二涡轮机部分相关联的涡轮转子的轮毂的位置处的轴承支撑。
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公开(公告)号：US20130219908A1
公开(公告)日：2013-08-29
申请号：US13483406
申请日：2012-05-30
IPC分类号： F02C3/10
CPC分类号： F01D25/162 , F02C3/107 , F02K3/072 , F05D2260/40311
摘要： A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.
摘要翻译： 涡轮发动机包括风扇，具有低压压缩机部分和高压压缩机部分的压缩机部分，与压缩机部分流体连通的燃烧器和与燃烧器流体连通的涡轮部分。 涡轮部分包括低压涡轮部分和高压涡轮部分。 低压压缩机部分，低压涡轮部分和风扇沿第一方向旋转，而高压压缩机部分和高压涡轮部分沿与第一方向相反的第二方向旋转。
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公开(公告)号：US20130219907A1
公开(公告)日：2013-08-29
申请号：US13408109
申请日：2012-02-29
IPC分类号： F02C3/10
CPC分类号： F01D25/162 , F02C3/107 , F02K3/072 , F05D2260/40311
摘要： A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.
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