公开(公告)号：US07568336B2

公开(公告)日：2009-08-04

申请号：US12037499

申请日：2008-02-26

申请人： Michel Gilbert Roland Brault ,  Stephane Rousselin ,  Nicolas Jerome Jean Tantot ,  Roxane Carmelle Jeanne Yvonne Touret

发明人： Michel Gilbert Roland Brault ,  Stephane Rousselin ,  Nicolas Jerome Jean Tantot ,  Roxane Carmelle Jeanne Yvonne Touret

IPC分类号： F02K3/02

CPC分类号： F02C7/143 ,  F02K3/115 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2260/205 ,  F05D2260/211 ,  Y02T50/675

摘要： An aeroengine includes a primary air circuit; a high-pressure compressor fed by the primary air; and a secondary air circuit. The engine further includes at least one heat exchanger mounted in the primary air circuit upstream from the high-pressure compressor, the heat exchanger including a cold secondary circuit and a hot primary circuit, the hot primary circuit being fed with air from the primary air circuit and the cold secondary circuit being fed with air from the secondary air circuit. The cold circuit of the heat exchanger is fed by pipes that open out into the secondary air circuit.

摘要翻译： 航空发动机包括一次空气回路; 由一次空气供给的高压压缩机; 和二次空气回路。 发动机还包括安装在高压压缩机上游的一次空气循环中的至少一个热交换器，该热交换器包括一个冷二次回路和一个热一次回路，该热一次回路由一次空气回路供给空气 并且冷二次回路从二次空气回路供给空气。 热交换器的冷回路由通向二次风回路的管道供给。

公开(公告)号：US20080202094A1

公开(公告)日：2008-08-28

申请号：US12037499

申请日：2008-02-26

申请人： Michel Gilbert Roland BRAULT ,  Stephane Rousselin ,  Nicolas Jerome Jean Tantot ,  Roxane Carmelle Jeanne Yvonne Touret

发明人： Michel Gilbert Roland BRAULT ,  Stephane Rousselin ,  Nicolas Jerome Jean Tantot ,  Roxane Carmelle Jeanne Yvonne Touret

IPC分类号： F02C7/143 ,  F02K3/02 ,  F02C7/14

CPC分类号： F02C7/143 ,  F02K3/115 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2260/205 ,  F05D2260/211 ,  Y02T50/675

摘要： The invention relates to an aeroengine comprising: a primary air circuit; a high-pressure compressor fed by said primary air; and a secondary air circuit. The engine further comprising at least one heat exchanger mounted in the primary air circuit upstream from said high-pressure compressor, said heat exchanger comprising a cold secondary circuit and a hot primary circuit, said hot primary circuit being fed with air from said primary air circuit and said cold secondary circuit being fed with air from the secondary air circuit. The cold circuit of the heat exchanger is fed by pipes that open out into the secondary air circuit.

摘要翻译： 本发明涉及一种航空发动机，其包括：主空气回路; 由所述一次空气供给的高压压缩机; 和二次空气回路。 所述发动机还包括至少一个热交换器，所述至少一个热交换器安装在所述高压压缩机上游的所述一次空气回路中，所述热交换器包括冷二次回路和热一次回路，所述热一次回路供给来自所述一次空气回路的空气 并且所述冷二次回路从二次空气回路供给空气。 热交换器的冷回路由通向二次风回路的管道供给。

公开(公告)号：US20140180657A1

公开(公告)日：2014-06-26

申请号：US14239355

申请日：2012-08-14

申请人： Nicolas Jerome Jean Tantot

发明人： Nicolas Jerome Jean Tantot

IPC分类号： G06F17/50

CPC分类号： G06F17/5009

摘要： A method for determining performance levels of at least one turbine engine propeller in an incident air flow (V) including an axial component (Vz) and a tangential component (Vθ), the propeller being modelled by a defined generalized theoretical model (Mg), for plural blade angles (β) of the propeller, by a set of adimensional coefficients, including at least one generalized advance coefficient (Jg), a generalized power coefficient (CPg), and a generalized traction coefficient (CTg) defined by formulae:   { J g = v z u - v θ  C Tg  ( β ) = T  ( β ) ρ · ( u - v θ ) 2 · D 2 C Pg  ( β ) = P  ( β ) ρ · ( u - v θ ) 3 · D 2 wherein the generalized theoretical model (Mg) of the propeller is parameterized with input conditions of the turbine engine, including at least the axial component (Vz), the tangential component of the incident air flow (Vθ), the blade angle (β) and the drive speed (u) of the propeller; and at least the traction performance level (T) and power performance level (P) of the propeller are derived from the parameterized generalized theoretical model (Mg).

摘要翻译： 一种用于确定包括轴向分量（Vz）和切向分量（V'）的入射气流（V）中的至少一个涡轮发动机推进器的性能水平的方法，所述螺旋桨由定义的广义理论模型（Mg）建模， 对于螺旋桨的多个叶片角度（＆amp; bgr），通过一组三维系数，包括至少一个通用推进系数（Jg），广义功率系数（CPg）和由公式定义的广义牵引系数（CTg） ：{J g = vzu - v＆thetas; （＆bgr）= T（＆bgr。）＆rgr; ·（u - v＆thetas;）2·D 2 C Pg（＆bgr）= P（＆bgr;）＆rgr; ·（u-v＆thetas）3·D 2其中螺旋桨的广义理论模型（Mg）参数化为涡轮发动机的输入条件，包括至少轴向分量（Vz），入射空气的切向分量 螺旋桨的叶片角度（＆amp; bgr）和驱动速度（u）; 并且从参数化的广义理论模型（Mg）导出至少推进器的牵引性能水平（T）和功率性能水平（P）。

公开(公告)号：US10102312B2

公开(公告)日：2018-10-16

申请号：US14239355

申请日：2012-08-14

申请人： Nicolas Jerome Jean Tantot

发明人： Nicolas Jerome Jean Tantot

IPC分类号： G06F7/60 ,  G06F17/50

摘要： A method for determining performance levels of at least one turbine engine propeller in an incident air flow (V) including an axial component (Vz) and a tangential component (VΘ), the propeller being modelled by a defined generalized theoretical model (Mg), for plural blade angles (ß) of the propeller, by a set of adimensional coefficients, including at least one generalized advance coefficient (Jg), a generalized power coefficient (CPg), and a generalized traction coefficient (CTg) defined by formulae:   { J g = v z u - v θ ⁢ C Tg ⁡ ( β ) = T ⁡ ( β ) ρ · ( u - v θ ) 2 · D 2 C Pg ⁡ ( β ) = P ⁡ ( β ) ρ · ( u - v θ ) 3 · D 2 wherein the generalized theoretical model (Mg) of the propeller is parameterized with input conditions of the turbine engine, including at least the axial component (Vz), the tangential component of the incident air flow (VΘ), the blade angle (ß) and the drive speed (u) of the propeller; and at least the traction performance level (T) and power performance level (P) of the propeller are derived from the parameterized generalized theoretical model (Mg).

公开(公告)号：US20140003916A1

公开(公告)日：2014-01-02

申请号：US14004713

申请日：2012-03-14

申请人： Sebastien Dron ,  Nicolas Jerome Jean Tantot

发明人： Sebastien Dron ,  Nicolas Jerome Jean Tantot

IPC分类号： F01D9/02

CPC分类号： F01D9/02 ,  B64D2027/005 ,  F02K1/09 ,  F02K1/763 ,  F02K3/025 ,  F02K3/072 ,  F02K3/075 ,  F05D2300/505 ,  Y02T50/66

摘要： A turbomachine for an aircraft including at least one turbine driving rotation of a fan, and a jet nozzle coaxially extending a turbine and creating, with an outlet cone that terminates the turbine, a passage of annular cross section for combustion gases that pass through the turbine. The jet nozzle can be mounted so that it can move between two extreme positions for which under action of a controller, an annular cross section of the passage for the gases is respectively at its minimum or maximum, making it possible to vary the cross section according to phases of operation of the aircraft and distribute thrust between the fan and the jet nozzle.

摘要翻译： 一种用于飞行器的涡轮机，包括至少一个涡轮机驱动风扇的旋转，以及喷射喷嘴，其同轴地延伸涡轮机并且产生具有终止涡轮机的出口锥体，用于通过涡轮机的燃烧气体的环形横截面通道 。 喷嘴可以安装成使得其可以在控制器的作用下的两个极限位置之间移动，气体通道的环形截面分别处于其最小或最大值，使得可以根据 到飞机的运行阶段并在风扇和喷嘴之间分配推力。

公开(公告)号：US09556744B2

公开(公告)日：2017-01-31

申请号：US14004713

申请日：2012-03-14

申请人： Sebastien Dron ,  Nicolas Jerome Jean Tantot

发明人： Sebastien Dron ,  Nicolas Jerome Jean Tantot

IPC分类号： F02K1/09 ,  F01D9/02 ,  F02K1/76 ,  F02K3/02 ,  F02K3/072 ,  F02K3/075 ,  B64D27/00

CPC分类号： F01D9/02 ,  B64D2027/005 ,  F02K1/09 ,  F02K1/763 ,  F02K3/025 ,  F02K3/072 ,  F02K3/075 ,  F05D2300/505 ,  Y02T50/66

摘要： A turbomachine for an aircraft including at least one turbine driving rotation of a fan, and a jet nozzle coaxially extending a turbine and creating, with an outlet cone that terminates the turbine, a passage of annular cross section for combustion gases that pass through the turbine. The jet nozzle can be mounted so that it can move between two extreme positions for which under action of a controller, an annular cross section of the passage for the gases is respectively at its minimum or maximum, making it possible to vary the cross section according to phases of operation of the aircraft and distribute thrust between the fan and the jet nozzle.

摘要翻译： 一种用于飞行器的涡轮机，包括至少一个涡轮机驱动风扇的旋转，以及喷射喷嘴，其同轴地延伸涡轮机并且产生具有终止涡轮机的出口锥体，用于通过涡轮机的燃烧气体的环形横截面通道 。 喷嘴可以安装成使得其可以在控制器的作用下的两个极限位置之间移动，气体通道的环形截面分别处于其最小或最大值，使得可以根据 到飞机的运行阶段并在风扇和喷嘴之间分配推力。