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公开(公告)号：US20200284270A1
公开(公告)日：2020-09-10
申请号：US16849204
申请日：2020-04-15
发明人： Bruce L. Morin , Detlef Korte
IPC分类号： F04D29/66 , F02C3/107 , F02K3/04 , G06F30/17 , F01D15/12 , F04D29/32 , F01D5/14 , F02C3/04 , F02K3/06 , F01D5/06 , F01D25/24 , F02C7/36 , F04D25/04 , F04D29/053
摘要： A method of designing a gas turbine engine comprises the steps of including a fan section with a fan. A turbine section is included having a first turbine and a high pressure turbine. A gear reduction is included between the fan and the first turbine, the gear reduction being configured to receive an input from the first turbine and to turn the fan at a lower speed than the first turbine in operation. The first turbine is designed to include a number of turbine blades in each of a plurality of rows of the first turbine, the first turbine blades operating at least some of the time at a rotational speed, and the number of blades and the rotational speed being such that the following formula holds true for at least one of the blade rows of the first turbine: (number of blades×speed)/60≥5500.
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公开(公告)号：US20200174032A1
公开(公告)日：2020-06-04
申请号：US16667334
申请日：2019-10-29
发明人： David A. Topol , Bruce L. Morin , Detlef Korte
IPC分类号： G01P3/48 , F02C3/04 , F02C7/36 , F01D5/02 , F01D5/12 , F02K3/06 , F02C7/32 , F02C3/10 , F02C7/24
摘要： A gas turbine engine has a fan section including a fan, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, and a gear reduction. The low pressure compressor and the low pressure turbine have a number of blades in each of at least one of a plurality of blade rows. The blades are rotatable at least some of the time at a rotational speed in operation. The number of 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: 5500≤(number of blades×rotational speed)/60≤10000, the rotational speed being in revolutions per minute.
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公开(公告)号：US10422280B2
公开(公告)日：2019-09-24
申请号：US15452614
申请日：2017-03-07
摘要： A flutter damper is disclosed, which includes a chamber configured to fluidly communicate with a gas flow, the chamber being filled with an open celled foam bulk damper, and wherein the chamber is configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes.
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公开(公告)号：US20190024581A1
公开(公告)日：2019-01-24
申请号：US16143662
申请日：2018-09-27
摘要： 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：US20180258788A1
公开(公告)日：2018-09-13
申请号：US15452627
申请日：2017-03-07
发明人： Bruce L. Morin , Daniel L. Gysling , Mani Sadeghi
CPC分类号： F01D25/06 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , F02C7/045 , F02K1/827 , F02K3/06 , F05D2220/323 , F05D2240/14 , F05D2260/96 , F05D2260/963 , G10K11/172 , Y02T50/672
摘要： Disclosed is flutter damper including a first cavity having a radially inner side in fluid communication with a flow path, and a second cavity having a radially inner side in fluid communication with a radially outer side of the first cavity, and the flutter damper having an impedance characteristic at one or more target frequencies defined as ftarget=fS,ND+Ω·ND wherein fS,ND is a resonance frequency corresponding to a structural mode of a rotating component, ND is a nodal diameter count of the structural mode, and Ω is a rotational speed of the rotating component, and wherein the flutter damper has the following impedance characteristic at the one or more targeted frequencies R≥2ρc −3ρc≤X≤−0.6ρc wherein R is the real part of the impedance characteristic, X is the imaginary part of the impedance characteristic, ρ is air density, and c is speed of sound.
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公开(公告)号：US09879611B2
公开(公告)日：2018-01-30
申请号：US14754298
申请日：2015-06-29
发明人： Bruce L. Morin , David A. Topol , Mark Boyer , Brian Desfosses , W. Marshall Quin , John Holchin , Jonathan D. Little , Bryan Roseberry
IPC分类号： F04D27/02 , F02C6/08 , F02C9/18 , F01D17/10 , F04D29/66 , F16K47/04 , F16K3/02 , F02C3/13 , F04D29/52
CPC分类号： F02C9/18 , F01D17/105 , F02C3/13 , F02C6/08 , F04D27/0215 , F04D27/023 , F04D29/522 , F04D29/665 , F05D2260/36 , F05D2260/963 , F16K3/02 , F16K47/04
摘要： Bleed valve assemblies in a gas turbine engine are disclosed herein. A bleed valve assembly in a low pressure compressor may include a bleed valve and a resonator chamber. A manifold may allow passage of air from a bleed duct into the resonator chamber. The resonator chamber may alter resonation properties of the bleed duct in order to prevent damage to components in the low pressure compressor.
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公开(公告)号：US09733266B2
公开(公告)日：2017-08-15
申请号：US15270027
申请日：2016-09-20
发明人： David A. Topol , Bruce L. Morin , Detlef Korte
CPC分类号： 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
摘要： A gas turbine engine has a fan, a turbine section having a first turbine including a first turbine rotor, a compressor rotor, and a gear reduction configured to effect a reduction in a speed of the fan relative to an input speed from the first turbine rotor. Each of the compressor rotor and the first turbine rotor includes a number of blades in each of a plurality of blade rows, the number of blades configured to operate at least some of the time at a rotational speed, and the number of blades and the rotational speed being such that the following formula holds true for at least a majority of the blade rows of the first turbine rotor, 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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公开(公告)号：US20170191415A1
公开(公告)日：2017-07-06
申请号：US15270027
申请日：2016-09-20
发明人： David A. Topol , Bruce L. Morin , Detlef Korte
CPC分类号： 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
摘要： A gas turbine engine has a fan, a turbine section having a first turbine including a first turbine rotor, a compressor rotor, and a gear reduction configured to effect a reduction in a speed of the fan relative to an input speed from the first turbine rotor. Each of the compressor rotor and the first turbine rotor includes a number of blades in each of a plurality of blade rows, the number of blades configured to operate at least some of the time at a rotational speed, and the number of blades and the rotational speed being such that the following formula holds true for at least a majority of the blade rows of the first turbine rotor, 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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公开(公告)号：US20160362983A1
公开(公告)日：2016-12-15
申请号：US15245383
申请日：2016-08-24
发明人： Bruce L. Morin , Detlef Korte
CPC分类号： F04D29/663 , F01D5/06 , F01D5/14 , F01D15/12 , F01D25/24 , F02C3/04 , F02C3/107 , F02C7/36 , F02K3/04 , F02K3/06 , F04D25/045 , F04D29/053 , F04D29/321 , F04D29/325 , F05D2220/323 , F05D2230/50 , F05D2260/40311 , F05D2260/96 , F05D2270/304 , F05D2270/333 , G06F17/5086
摘要： A method of designing a gas turbine engine comprises the steps of including a fan section with a fan. A turbine section is included having a first turbine and a second turbine. A gear reduction is included between the fan and the first turbine, the gear reduction being configured to receive an input from the first turbine and to turn the fan at a lower speed than the first turbine in operation. The first turbine is designed to include a number of turbine blades in each of a plurality of rows of the first turbine, the first turbine blades operating at least some of the time at a rotational speed, and the number of blades and the rotational speed being such that the following formula holds true for at least one of the blade rows of the first turbine: (number of blades×speed)/60≧5500.
摘要翻译： 一种设计燃气涡轮发动机的方法包括以下步骤：包括具有风扇的风扇部分。 包括具有第一涡轮机和第二涡轮机的涡轮机部分。 在风扇和第一涡轮机之间包括齿轮减速装置，齿轮减速装置构造成在第一涡轮机中接收来自第一涡轮机的输入并在比第一涡轮机低的速度下转动风扇。 第一涡轮机被设计成在第一涡轮机的多行中的每一个中包括多个涡轮机叶片，第一涡轮叶片以旋转速度至少部分时间运转，并且叶片的数量和转速为 使得下述公式对于第一涡轮机的至少一个叶片排是适用的：（叶片数×速度）/60≥5500。
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公开(公告)号：US20160177774A1
公开(公告)日：2016-06-23
申请号：US14606087
申请日：2015-01-27
发明人： Bruce L. Morin , David A. Topol , Detlef Korte
CPC分类号： F01D17/105 , F01D5/02 , F01D5/12 , F01D5/16 , F01D9/041 , F01D15/12 , F01D25/04 , F02C3/107 , F02C7/24 , F02C7/36 , F02K3/06 , F05D2200/36 , F05D2210/31 , F05D2220/32 , F05D2220/327 , F05D2240/301 , F05D2240/307 , F05D2260/40311 , F05D2260/96 , Y02T50/673
摘要： 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.
摘要翻译： 根据本公开的示例性方面的燃气涡轮发动机包括涡轮机部分，其包括风扇驱动涡轮机，由风扇驱动涡轮机驱动的齿轮架构，以及由风扇驱动涡轮经由齿轮传动驱动的风扇 建筑。 涡轮部分的至少一个级包括可旋转刀片阵列和一组叶片。 叶片数与叶片数之比大于或等于约1.55。 叶片的机械末端旋转马赫数被配置为在接近速度下大于或等于约0.5。
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