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公开(公告)号：US20170321611A1
公开(公告)日：2017-11-09
申请号：US15437069
申请日：2017-02-20
Applicant: United Technologies Corporation
Inventor： David A. Topol , Bruce L. Morin
CPC classification number: F02C7/36 , F01D5/02 , F01D5/12 , F05D2220/36 , F05D2260/40311 , F05D2260/96 , Y02T50/673 , Y10T29/49236 , Y10T29/4932
Abstract: A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor, and having a gear reduction ratio of greater than 2.5:1. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor: (number of blades×rotational speed)/60 sec≧5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine also disclosed.
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公开(公告)号：US20170122218A1
公开(公告)日：2017-05-04
申请号：US15404490
申请日：2017-01-12
Applicant: United Technologies Corporation , MTU Aero Engines AG
Inventor： David A. Topol , Bruce L. Morin , Detlef Korte
CPC classification number: G01P3/48 , F01D5/02 , F01D5/12 , F02C3/04 , F02C3/10 , F02C7/24 , F02C7/32 , F02C7/36 , F02K3/06 , F05D2200/13 , F05D2200/14 , F05D2220/32 , F05D2220/36 , F05D2260/40311 , F05D2260/96 , Y02T50/673 , Y10T29/49236 , Y10T29/4932
Abstract: A gas turbine engine has a fan, a turbine section having a first turbine including a first turbine, a compressor, and a gear reduction positioned between the fan and the first turbine. Each of the compressor and the first turbine includes a number of blades in each of a plurality of blade rows, the number of blades rotatable at least some of the time at a rotational speed in operation, and the number of blades and the rotational speed being such that the following formula holds true for the plurality of the blade rows of the first turbine, but does not hold true for any of the blade rows of the compressor rotor: (number of blades×rotational speed)/60≧5500, and the rotational speed being an approach speed in revolutions per minute.
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13.发明授权Pylon matched fan exit guide vane for noise reduction in a geared turbofan engine 有权在齿轮涡扇发动机中，用于降噪的塔式风扇出风导叶公开(公告)号：US09540938B2
公开(公告)日：2017-01-10
申请号：US13721498
申请日：2012-12-20
Applicant: United Technologies Corporation
Inventor： David A. Topol , Glen E. Potter , Flavien L. Thomas
CPC classification number: F01D9/041 , F01D5/142 , F01D5/145 , F02C7/045 , F04D29/544 , F04D29/666 , F05D2250/31 , F05D2260/4031 , F05D2260/96 , F05D2260/961 , Y02T50/673 , Y10T29/49245
Abstract: A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades. The fan exit guide vane includes a plurality of exit guide vanes positioned downstream of the fan rotor with at least two of the plurality of exit guide vanes including different aft geometries for guiding airflow through the passage to reduce pressure distortions at the fan blades.
Abstract translation: 燃气涡轮发动机的公开的风扇部分包括具有多个风扇叶片的风扇转子和限定风扇转子后部的通道的管道。 风扇出口导叶设置在风扇叶片下游的管道内。 风扇出口导叶包括位于风扇转子下游的多个出口导向叶片，其中至少两个出口导向叶片包括不同的后部几何形状，用于引导气流通过通道以减小风扇叶片处的压力变形。
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14.发明申请PYLON MATCHES FAN EXIT GUIDE VANE FOR NOISE REDUCTION IN A GEARED TURBOFAN ENGINE 审中-公开PYLON匹配风扇离开导向器用于减速涡轮发动机的噪声公开(公告)号：US20160363137A1
公开(公告)日：2016-12-15
申请号：US15246752
申请日：2016-08-25
Applicant: United Technologies Corporation
Inventor： David A. Topol , Glen E. Potter , Flavien L. Thomas
CPC classification number: F04D29/563 , F01D5/142 , F01D5/145 , F01D5/147 , F01D9/041 , F01D17/162 , F02C7/045 , F04D29/544 , F04D29/666 , F04D29/667 , F05D2240/122 , F05D2250/31 , F05D2250/90 , F05D2260/4031 , F05D2260/96 , F05D2260/961 , Y02T50/673 , Y10T29/49245
Abstract: A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades. The fan exit guide vane includes a plurality of exit guide vanes positioned downstream of the fan rotor with at least two of the plurality of exit guide vanes including different aft geometries for guiding airflow through the passage to reduce pressure distortions at the fan blades.
Abstract translation: 燃气涡轮发动机的公开的风扇部分包括具有多个风扇叶片的风扇转子和限定风扇转子后部的通道的管道。 风扇出口导叶设置在风扇叶片下游的管道内。 风扇出口导叶包括位于风扇转子下游的多个出口导向叶片，其中至少两个出口导向叶片包括不同的后部几何形状，用于引导气流通过通道以减小风扇叶片处的压力变形。
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公开(公告)号：US20160040598A1
公开(公告)日：2016-02-11
申请号：US14774273
申请日：2014-02-19
Applicant: United Technologies Corporation
Inventor： Bruce L. Morin , David A. Topol
CPC classification number: F02C7/24 , F02C3/04 , F02C3/107 , F02C7/36 , F02K3/06 , F05D2260/40311 , F05D2260/96
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan, a compressor section having a low pressure compressor and a high pressure compressor, a combustor section, and a turbine section having a low pressure turbine, the low pressure turbine for driving the low pressure compressor and the fan; a gear reduction effecting a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor; and at least one stage of the compressor section having a ratio of vanes to blades that is greater than or equal to 1.8. The corrected tip speed of the blades is greater than or equal to 480 ft/sec at an approach speed.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机包括风扇，具有低压压缩机和高压压缩机的压缩机部分，燃烧器部分和具有低压涡轮机的涡轮部分， 用于驱动低压压缩机和风扇的低压涡轮机; 齿轮减速相对于低压涡轮机和低压压缩机的速度降低风扇的速度; 并且所述压缩机部分的至少一个级具有大于或等于1.8的叶片与叶片的比率。 在接近速度下，叶片的修正的叶尖速度大于或等于480英尺/秒。
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Patent Agency Ranking
公开(公告)号：US08714913B2
公开(公告)日：2014-05-06
申请号：US14016436
申请日：2013-09-03
Applicant: United Technologies Corporation
Inventor： David A. Topol , Bruce L. Morin
IPC: F01D1/02
CPC classification number: F02C3/10 , F01D5/02 , F01D5/12 , F02C7/24 , F02C7/36 , F05D2260/96 , Y02T50/673 , Y10T29/49236 , Y10T29/4932
Abstract: A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60 s≧5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine and a compressor module are also disclosed.
Abstract translation: 燃气涡轮发动机具有风扇和具有风扇驱动涡轮机转子的涡轮机。 风扇驱动涡轮转子驱动压缩机转子。 齿轮减速实现了风扇相对于来自驱动压缩机转子的风扇驱动涡轮转子的输入速度的降低。 压缩机转子在压缩机转子的多排中的至少一排中具有多个压缩机叶片。 叶片在旋转速度下至少运行一些时间。 至少一行中的压缩机叶片的数量和转速使得至少一排压缩机转子涡轮机的以下公式成立：（叶片数×转速）/60s≥5500Hz， 转速为每分钟转。 还公开了一种设计燃气涡轮发动机和压缩机组件的方法。
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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：US11168614B2
公开(公告)日：2021-11-09
申请号：US16833782
申请日：2020-03-30
Applicant: United Technologies Corporation
Inventor： Bruce L. Morin , David A. Topol , Detlef Korte
IPC: F02C7/24 , F02K3/06 , F01D5/02 , F01D5/12 , F01D9/04 , F01D15/12 , F01D17/10 , F01D5/16 , F01D25/04 , F02C3/107 , F02C7/36
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a compressor section driven by the turbine section, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.
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公开(公告)号：US20200291859A1
公开(公告)日：2020-09-17
申请号：US16740611
申请日：2020-01-13
Applicant: United Technologies Corporation
Inventor： Bruce L. Morin , David A. Topol , Detlef Korte
IPC: F02C7/24 , F02K3/06 , F01D5/02 , F01D5/12 , F01D9/04 , F01D15/12 , F01D17/10 , F01D5/16 , F01D25/04 , F02C3/107 , F02C7/36
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.
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公开(公告)号：US10337407B2
公开(公告)日：2019-07-02
申请号：US14774273
申请日：2014-02-19
Applicant: United Technologies Corporation
Inventor： Bruce L. Morin , David A. Topol
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan, a compressor section having a low pressure compressor and a high pressure compressor, a combustor section, and a turbine section having a low pressure turbine, the low pressure turbine for driving the low pressure compressor and the fan; a gear reduction effecting a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor; and at least one stage of the compressor section having a ratio of vanes to blades that is greater than or equal to 1.8. The corrected tip speed of the blades is greater than or equal to 480 ft/sec at an approach speed.
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