公开(公告)号：US20070260391A1

公开(公告)日：2007-11-08

申请号：US11730835

申请日：2007-04-04

Applicant: Francois-Xavier Gaulmin ,  Lionel Iraudo

Inventor： Francois-Xavier Gaulmin ,  Lionel Iraudo

IPC: G06F19/00

CPC classification number: F02C9/42 ,  F02C9/28 ,  F05D2220/90 ,  F05D2260/80 ,  F05D2270/023 ,  F05D2270/051 ,  F05D2270/304 ,  G07C3/00

Abstract: The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M1) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (M1 and M2) controlled respectively by first and second control means (MC1 and MC2). The device is remarkable in that it comprises check means (C) provided with main means (C1), the main means (C1) controlling the first and second control means (MC1 and MC2) so that the surveillance parameters of the first and second turbine engines (M1 and M2) respectively reach the real first and second final values (V1f and V2f) as determined in accordance with the method of the invention.

Abstract translation: 本发明涉及一种能够在旋翼航空器的至少第一涡轮发动机（M1）上执行健康检查的装置（D），旋翼航空器设有第一和第二涡轮发动机（M 1和 M 2）分别由第一和第二控制装置（MC 1和MC 2）控制。 该装置是显着的，它包括设有主装置（C 1）的检查装置（C），控制第一和第二控制装置（MC 1和MC 2）的主装置（C 1），使得 第一和第二涡轮发动机（M 1和M 2）分别达到根据本发明的方法确定的实际的第一和第二最终值（V 1 f和V 2 f）。

公开(公告)号：US20080125931A1

公开(公告)日：2008-05-29

申请号：US11808168

申请日：2007-06-07

Applicant: Francois-Xavier Gaulmin ,  Lionel Iraudo

Inventor： Francois-Xavier Gaulmin ,  Lionel Iraudo

IPC: G01M15/14

CPC classification number: F02C9/00 ,  F05D2260/80 ,  G01D1/18

Abstract: The present invention relates to a method and to an instrument for determining the limiting margin of a surveillance parameter of a turboshaft engine. During a preliminary stage, a secondary processor means (11) determines a preliminary comfort margin. Thereafter, during a main stage, it estimates a useful comfort margin from the preliminary comfort margin, and then an apparent difference between the current value and the limit value of the surveillance parameter, and finally the limiting margin by subtracting the useful comfort margin from the apparent difference.

Abstract translation: 本发明涉及一种用于确定涡轮轴发动机的监视参数的限制裕度的方法和仪器。 在初级阶段，次级处理器装置（11）确定初步舒适余量。 此后，在主阶段，它从初步舒适度估计有用的舒适程度，然后估计当前值和监视参数的极限值之间的明显差异，最后通过从 明显差异

公开(公告)号：US07769521B2

公开(公告)日：2010-08-03

申请号：US11730835

申请日：2007-04-04

Applicant: Francois-Xavier Gaulmin ,  Lionel Iraudo

Inventor： Francois-Xavier Gaulmin ,  Lionel Iraudo

IPC: G06F19/00 ,  G06G7/70

CPC classification number: F02C9/42 ,  F02C9/28 ,  F05D2220/90 ,  F05D2260/80 ,  F05D2270/023 ,  F05D2270/051 ,  F05D2270/304 ,  G07C3/00

Abstract: The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M1) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (M1 and M2) controlled respectively by first and second control means (MC1 and MC2). The device is remarkable in that it comprises check means (C) provided with main means (C1), the main means (C1) controlling the first and second control means (MC1 and MC2) so that the surveillance parameters of the first and second turbine engines (M1 and M2) respectively reach the real first and second final values (V1f and V2f) as determined in accordance with the method of the invention.

Abstract translation: 本发明涉及能够在旋翼航空器的至少第一涡轮发动机（M1）上执行健康检查的方法和装置（D），所述旋翼飞机设有第一和第二涡轮发动机（M1和M2） 分别由第一和第二控制装置（MC1和MC2）控制。 该装置是显着的，它包括设有主装置（C1）的检查装置（C），主装置（C1）控制第一和第二控制装置（MC1和MC2），使得第一和第二涡轮机的监视参数 发动机（M1和M2）分别达到根据本发明的方法确定的实际的第一和第二最终值（V1f和V2f）。

公开(公告)号：US20080173768A1

公开(公告)日：2008-07-24

申请号：US11790976

申请日：2007-04-30

Applicant: Daniel Chaniot ,  Francois-Xavier Gaulmin ,  Lionel Iraudo

Inventor： Daniel Chaniot ,  Francois-Xavier Gaulmin ,  Lionel Iraudo

IPC: B64D33/02

CPC classification number: B64C27/14 ,  B64D33/02

Abstract: The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body (20) of the engine (8) having a first end (21) opening out into the ambient atmosphere in front of the engine, and a second end (22) connected to the engine at the rearmost portion thereof.

Abstract translation: 本发明涉及一种动力装置（18），其包括用于驱动旋转翼飞机（1）的转子（3）的齿轮箱（7）后面的至少一个涡轮轴发动机（8），空气入口主体（20） 所述发动机（8）具有在所述发动机前方开放到所述环境大气中的第一端（21），以及在其最后部连接到所述发动机的第二端（22）。

公开(公告)号：US08050842B2

公开(公告)日：2011-11-01

申请号：US12142819

申请日：2008-06-20

Applicant: Lionel Iraudo

Inventor： Lionel Iraudo

IPC: G06F19/00

CPC classification number: F01D21/003 ,  B64C27/04 ,  B64D43/00 ,  F02C9/00 ,  G07C5/0816 ,  Y02T50/671

Abstract: The present invention relates to a method and to an apparatus (9) for controlling and regulating a rotorcraft turbine engine (1). The apparatus is provided with an electronic control and regulation computer (3) that receives signals relating to monitored parameters of the turbine engine (1). The apparatus is remarkable in that it is provided with an alarm (4) controlled by the electronic computer (3) via an analog connection (8) to operate whenever an event occurs that might diminish the safety of the rotorcraft.

Abstract translation: 本发明涉及一种用于控制和调节旋翼航空器涡轮发动机（1）的方法和装置（9）。 该装置设置有电子控制和调节计算机（3），其接收与涡轮发动机（1）的监测参数有关的信号。 该装置是显着的，其具有经由模拟连接（8）由电子计算机（3）控制的报警器（4），以在事件发生时进行操作，这可能降低旋翼航空器的安全性。

公开(公告)号：US09346553B2

公开(公告)日：2016-05-24

申请号：US11764825

申请日：2007-06-19

Applicant: François-Xavier Gaulmin ,  Lionel Iraudo ,  Daniel Chaniot

Inventor： François-Xavier Gaulmin ,  Lionel Iraudo ,  Daniel Chaniot

IPC: F23N5/18 ,  G05B13/02 ,  B64D31/12 ,  F02C9/28 ,  F02C9/42

CPC classification number: B64D31/12 ,  F02C9/28 ,  F02C9/42

Abstract: The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M1, M2) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.

Abstract translation: 本发明涉及一种方法和相关联的燃料计量系统，用于通过确定变换成第一和第二功率余量的发动机（M1，M2）的第一和第二限制余量来平衡由两个飞机涡轮轴发动机输送的功率。 此后，比较第一和第二功率余量的值，以便确定所述第一和第二功率余量之间的主要差异。 最后，加速具有较大功率余量的发动机，以通过将主要差异最小化到尽可能大的程度来平衡第一和第二发动机的动力。

公开(公告)号：US07717369B2

公开(公告)日：2010-05-18

申请号：US11790976

申请日：2007-04-30

Applicant: Daniel Chaniot ,  François-Xavier Gaulmin ,  Lionel Iraudo

Inventor： Daniel Chaniot ,  François-Xavier Gaulmin ,  Lionel Iraudo

IPC: B64D35/08

CPC classification number: B64C27/14 ,  B64D33/02

Abstract: The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body (20) of the engine (8) having a first end (21) opening out into the ambient atmosphere in front of the engine, and a second end (22) connected to the engine at the rearmost portion thereof.

Abstract translation: 本发明涉及一种动力装置（18），其包括用于驱动旋转翼飞机（1）的转子（3）的齿轮箱（7）后面的至少一个涡轮轴发动机（8），空气入口主体（20） 所述发动机（8）具有在所述发动机前方开放到所述环境大气中的第一端（21），以及在其最后部连接到所述发动机的第二端（22）。

公开(公告)号：US08121773B2

公开(公告)日：2012-02-21

申请号：US11808168

申请日：2007-06-07

Applicant: François-Xavier Gaulmin ,  Lionel Iraudo

Inventor： François-Xavier Gaulmin ,  Lionel Iraudo

IPC: G01M15/00 ,  G01M15/02 ,  G06F19/00

CPC classification number: F02C9/00 ,  F05D2260/80 ,  G01D1/18

Abstract: The present invention relates to a method and to an instrument for determining the limiting margin of a surveillance parameter of a turboshaft engine. During a preliminary stage, a secondary processor means (11) determines a preliminary comfort margin. Thereafter, during a main stage, it estimates a useful comfort margin from the preliminary comfort margin, and then an apparent difference between the current value and the limit value of the surveillance parameter, and finally the limiting margin by subtracting the useful comfort margin from the apparent difference.

Abstract translation: 本发明涉及一种用于确定涡轮轴发动机的监视参数的限制裕度的方法和仪器。 在初级阶段，次级处理器装置（11）确定初步舒适余量。 此后，在主阶段，它从初步舒适度估计有用的舒适程度，然后估计当前值和监视参数的极限值之间的明显差异，最后通过从 明显差异