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公开(公告)号：US20160090909A1
公开(公告)日：2016-03-31
申请号：US14964727
申请日：2015-12-10
Applicant: United Technologies Corporation
Inventor： Jonthan Gilson , Burce L. Morin , Ramons A. Reba , David A. Topol , Wesley K. Lord
CPC classification number: F02C3/107 , F01D9/041 , F01D25/162 , F02K3/06 , F04D29/542 , F04D29/544 , F04D29/664 , F04D29/667 , F05D2220/36 , F05D2250/191 , F05D2250/38 , F05D2260/40311 , F05D2260/96 , F05D2260/961 , F05D2300/603
Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.
Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的风扇部分包括具有风扇叶片的风扇转子和位于风扇转子下游的多个风扇出口导向叶片。 风扇转子被构造成通过齿轮减速被驱动。 定义了多个风扇出口导向叶片与多个风扇叶片的比例。 风扇出口导向叶片具有优化的扫掠和优化的倾斜。
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公开(公告)号：US20130276424A1
公开(公告)日：2013-10-24
申请号：US13630276
申请日：2012-09-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David A. Topol , Burce L. Morin
IPC: F02C3/107
CPC classification number: F02C3/107 , F02K3/06 , F05D2260/961 , F05D2270/333
Abstract: A gas turbine engine has a fan, a compressor section having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a low pressure portion. The low pressure turbine portion drives the low pressure compressor portion and the fan. A gear reduction effects a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor portion. At least one of the low pressure turbine portion and low pressure compressor portion has a number of blades in each of a plurality of rows. The blades operate at least some of the time at a rotational speed. The number of blades and the rotational speed are such that the following formula holds true for at least one of the blade rows of the at least one of the low pressure turbine portion and/or the low pressure compressor sections: (number of blades×rotational speed)/60≧5500. The rotational speed is an approach speed in revolutions per minute.
Abstract translation: 燃气涡轮发动机具有风扇，具有低压部分和高压部分的压缩机部分，燃烧器部分和具有低压部分的涡轮机。 低压涡轮部分驱动低压压缩机部分和风扇。 齿轮减速实现风扇相对于低压涡轮机和低压压缩机部分的转速的降低。 低压涡轮机部分和低压压缩机部分中的至少一个在多行中的每一行中具有多个叶片。 叶片在旋转速度下至少运行一些时间。 叶片的数量和转速使得对于低压涡轮部分和/或低压压缩机部分中的至少一个的至少一个叶片排，以下公式成立：（叶片数×旋转数 速度）/ 60> = 5500。 旋转速度是每分钟转数的接近速度。
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公开(公告)号：US10107191B2
公开(公告)日：2018-10-23
申请号：US14964727
申请日：2015-12-10
Applicant: United Technologies Corporation
Inventor： Jonthan Gilson , Burce L. Morin , Ramons A. Reba , David A. Topol , Wesley K. Lord
Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.
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公开(公告)号：US08632301B2
公开(公告)日：2014-01-21
申请号：US13630276
申请日：2012-09-28
Applicant: United Technologies Corporation
Inventor： David A. Topol , Burce L. Morin
IPC: F01D1/02
CPC classification number: F02C3/107 , F02K3/06 , F05D2260/961 , F05D2270/333
Abstract: A gas turbine engine has a fan, a compressor section having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a low pressure portion. The low pressure turbine portion drives the low pressure compressor portion and the fan. A gear reduction effects a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor portion. At least one of the low pressure turbine portion and low pressure compressor portion has a number of blades in each of a plurality of rows. The blades operate at least some of the time at a rotational speed. The number of blades and the rotational speed are such that the following formula holds true for at least one of the blade rows of the at least one of the low pressure turbine portion and/or the low pressure compressor sections: (number of blades×rotational speed)/60≧5500. The rotational speed is an approach speed in revolutions per minute.
Abstract translation: 燃气涡轮发动机具有风扇，具有低压部分和高压部分的压缩机部分，燃烧器部分和具有低压部分的涡轮机。 低压涡轮部分驱动低压压缩机部分和风扇。 齿轮减速实现风扇相对于低压涡轮机和低压压缩机部分的转速的降低。 低压涡轮机部分和低压压缩机部分中的至少一个在多行中的每一行中具有多个叶片。 叶片在旋转速度下至少运行一些时间。 叶片的数量和转速使得对于低压涡轮部分和/或低压压缩机部分中的至少一个的至少一个叶片排，以下公式成立：（叶片数×旋转数 速度）/ 60> = 5500。 旋转速度是每分钟转数的接近速度。
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