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公开(公告)号：WO2013122713A3
公开(公告)日：2014-05-30
申请号：PCT/US2013022035
申请日：2013-01-18
Applicant: UNITED TECHNOLOGIES CORP , MTU AERO ENGINES AG
Inventor： TOPOL DAVID A , MORIN BRUCE L , KORTE DETLEF
CPC classification number: F02K3/02 , F02K3/06 , F05D2260/40311 , F05D2260/96 , F05D2270/02
Abstract: A gear reduction effects a reduction in the speed of a fan relative to a speed of a low pressure turbine and a 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 x rotational speed)/60 ≥ 5500 Hz. The rotational speed is an approach speed in revolutions per minute.
Abstract translation: 齿轮减速实现风扇速度相对于低压涡轮和低压压缩机部分的速度的降低。 低压涡轮机部分和低压压缩机部分中的至少一个在多排中的每一排中具有多个叶片。 叶片至少在某些时间以转速运行。 叶片的数量和旋转速度使得对于低压涡轮机部分和/或低压压缩机部分中的至少一个的至少一个叶片排适用以下公式：（叶片数量x旋转 速度）/ 60≥5500 Hz。 转速是每分钟转数的接近速度。
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公开(公告)号：WO2014186017A2
公开(公告)日：2014-11-20
申请号：PCT/US2014017056
申请日：2014-02-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MORIN BRUCE L , TOPOL DAVID A
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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公开(公告)号：WO2013122713A8
公开(公告)日：2014-06-19
申请号：PCT/US2013022035
申请日：2013-01-18
Applicant: UNITED TECHNOLOGIES CORP , MTU AERO ENGINES AG
Inventor： TOPOL DAVID A , MORIN BRUCE L , KORTE DETLEF
CPC classification number: F02K3/02 , F02K3/06 , F05D2260/40311 , F05D2260/96 , F05D2270/02
Abstract: A gear reduction effects a reduction in the speed of a fan relative to a speed of a low pressure turbine and a 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 x rotational speed)/60 ≥ 5500 Hz. The rotational speed is an approach speed in revolutions per minute.
Abstract translation: 齿轮减速会相对于低压涡轮机和低压压缩机部分的速度降低风扇的速度。 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机部分和/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x旋转 速度）/ 60≥5500 Hz。 旋转速度是每分钟转数的接近速度。
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公开(公告)号：WO2014189572A3
公开(公告)日：2015-01-08
申请号：PCT/US2014017016
申请日：2014-02-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TOPOL DAVID A , MORIN BRUCE L , PRASAD DILIP , OUELLETTE THOMAS J
CPC classification number: F01D25/24 , F01D1/02 , F01D5/021 , F02C7/045 , F05D2220/32 , F05D2250/283 , F05D2260/96
Abstract: A gas turbine engine has a propulsor including a fan and a liner positioned upstream of the fan. The liner has a backing plate, a cellular structure with cells extending from the backing plate, and a perforated sheet with a depth defined as a distance between the perforated sheet and the backing sheet. The depth is selected to achieve a desired ratio of the depth relative to a gap ?. A depth to gap ratio is substantially in a range of 0.035 to 0.08. A method is also disclosed.
Abstract translation: 燃气涡轮发动机具有包括风扇和位于风扇上游的衬垫的推进器。 衬垫具有背板，具有从背板延伸的单元的多孔结构以及被定义为多孔板和背衬板之间距离的深度的多孔板。 选择深度以实现相对于间隙δ的深度的期望比率。 深度与间隙比基本上在0.035至0.08的范围内。 还公开了一种方法。
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公开(公告)号：CA2863620C
公开(公告)日：2015-11-03
申请号：CA2863620
申请日：2013-01-18
Applicant: UNITED TECHNOLOGIES CORP , MTU AERO ENGINES AG
Inventor： TOPOL DAVID A , MORIN BRUCE L , KORTE DETLEF
Abstract: A gear reduction effects a reduction in the speed of a fan relative to a speed of a low pressure turbine and a 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 x rotational speed)/60 ? 5500 Hz. The rotational speed is an approach speed in revolutions per minute.
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Patent Agency Ranking
公开(公告)号：CA2879244C
公开(公告)日：2018-04-03
申请号：CA2879244
申请日：2015-01-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TOPOL DAVID A , MORIN BRUCE L
Abstract: A gas turbine engine comprises a fan and a turbine section having a first turbine rotor. The first turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from a fan drive turbine 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: (the number of blades x the rotational speed)/ (60 seconds/minute) >= 5500 Hz; and the rotational speed being in revolutions per minute. A compressor module and a method of designing a gas turbine engine are also disclosed.
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公开(公告)号：CA2882565C
公开(公告)日：2017-05-30
申请号：CA2882565
申请日：2013-09-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TOPOL DAVID A , POTTER GLEN E , THOMAS FLAVIEN L
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.
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公开(公告)号：CA2882565A1
公开(公告)日：2014-04-03
申请号：CA2882565
申请日：2013-09-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TOPOL DAVID A , POTTER GLEN E , THOMAS FLAVIEN L
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.
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公开(公告)号：CA2915233C
公开(公告)日：2018-12-04
申请号：CA2915233
申请日：2015-12-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TOPOL DAVID A , MORIN BRUCE L
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 fan drive turbine rotor has a number of blades in at least one of a plurality of rows. The turbine blades operate at least some of the time at a rotational speed. The number of turbine 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 fan drive turbine rotor: (number of blades × rotational speed)/60s >= 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.
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10.发明专利
公开(公告)号：BR102015001345A2
公开(公告)日：2016-10-25
申请号：BR102015001345
申请日：2015-01-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MORIN BRUCE L , TOPOL DAVID A
Abstract: “motor de turbina a gás, método para projetar um motor de turbina a gás, e, módulo de compressor” a motor de turbina a gás compreende um ventilador e uma seção de turbina, tendo um primeiro rotor de turbina. o primeiro rotor de turbina impulsiona um rotor de compressor. uma redução de engrenagem efetua uma redução na velocidade do ventilador em relação a uma velocidade de entrada de um rotor de turbina de impulsionamento de ventilador. o rotor de compressor tem um número de lâminas de compressor em pelo menos uma dentre uma pluralidade de linhas do rotor de compressor. as lâminas operam pelo menos alguma parte do tempo em uma velocidade de rotação. o número de lâminas de compressor em pelo menos uma linha e a velocidade de rotação são tais que a fórmula a seguir se faz verdadeira para pelo menos uma linha do rotor de compressor: (o número de lâminas × a velocidade de rotação)/(60 segundos/minuto) = 5500 hz; e a velocidade de rotação, sendo em rotações por minuto. um módulo de compressor e um método para projetar um motor de turbina a gás também são divulgados.
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