公开(公告)号：EP2861493A1

公开(公告)日：2015-04-22

申请号：EP13733392.8

申请日：2013-06-12

申请人： Turbomeca ,  Microturbo

发明人： DAURIAC, Pascal ,  BEDRINE, Olivier ,  MARCONI, Patrick ,  RIDEAU, Jean-François

IPC分类号： B64D35/08

CPC分类号： B64D35/08 ,  B64D41/00 ,  B64D2041/002 ,  F02C6/02 ,  F02C7/277 ,  F05D2220/329 ,  Y02T50/53

摘要： The aim of the invention is to optimize the entirety of the drive power available in a helicopter by using an auxiliary motor to supply power to the equipment and accessories of the helicopter that are connected to the engines. In an example of an optimized power transfer architecture for implementing the invention, the main engines (1, 1') and the APU group (8), as an auxiliary motor, comprise a gas generator (2; 81) connected, for the main engines (1, 1'), to the gearboxes (6) and accessory boxes (7) of mechanical, electric, and/or hydraulic power sockets, and connected, for the APU group (8), to at least one power conversion member (83, 84, 11). The power conversion member (83, 84, 11) of the APU group (8) is connected to the equipment and accessories via the gearbox (6) and/or via the accessory box (7) of the main engines (1, 1').

摘要翻译： 的方法和体系结构通过使用辅助发动机的将能量提供给设备和连接到所述发动机的直升机的配件，以优化在直升机上可用的整个系统上的牵引力。 主发动机和在APU单元，作为辅助发动机，包括连接到气体发生器，对于主发动机，减速齿轮箱和用于机械，电气和/或液压动力输出附件齿轮箱和连接到，对于 APU单元，至少一个电力转换构件。 APU装置的功率转换部件由所述减速齿轮箱和/或所述主发动机的附件齿轮箱连接到所述的设备和附件。

公开(公告)号：EP2591219A1

公开(公告)日：2013-05-15

申请号：EP11743295.5

申请日：2011-07-05

申请人： Turbomeca

发明人： BEDRINE, Olivier ,  MARCONI, Patrick ,  PUERTO, Alphonse

IPC分类号： F02C6/02

CPC分类号： F02C6/00 ,  F02C1/04 ,  F02C6/02 ,  F02C7/10 ,  F02C7/36 ,  Y02E20/14 ,  Y02T50/671

摘要： The invention aims to get around the problems of size, mass or reliability. To do this, energy is recovered in the exhaust nozzle, converted and recirculated using mechanical and/or electrical power recombining means. An example of an architecture of a turbomachine according to the invention includes a main turbine engine (1) and a heat exchanger (18) positioned in the exhaust nozzle (70) and coupled, via pipes (18a and 18b), to an independent system (16) that converts thermal energy into mechanical energy. This independent system (16) is connected to localized (Z1) mechanical recombination means (20) via a power shaft (15) to supply power to a power transmission shaft (80) according to aircraft requirements.

公开(公告)号：EP2558728A1

公开(公告)日：2013-02-20

申请号：EP11730371.9

申请日：2011-04-13

申请人： Turbomeca

发明人： BISCAY, Pierre ,  MARCONI, Patrick ,  VIGNAU, Hubert, Hippolyte

IPC分类号： F04D29/44 ,  F04D29/46

CPC分类号： F04D29/444 ,  F04D29/462 ,  F05D2250/52

摘要： The invention relates to a method for maintaining the efficiency and duty of a turbine engine compressor in order substantially to reduce the specific consumption Cs, while guaranteeing a high enough pumping margin with partial load. For this purpose, the invention proposes an optimised method for adapting the airflow to a variable demand for flow or mechanical or electric power in a centrifugal compressor of a turbine engine. The method includes diffusing the airflow (F) through a first annular blade ring (G1) having variable-pitch blades (24), radially bordered by a second annular blade ring (G2) having the same number of fixed-pitch blades (28) with an equivalent extension, guiding the radial extension diffusion by coupling the blades (24, 28) of the two blade rings. According to said method, each blade (24) of the first blade ring (G1) is spun off-axis.

公开(公告)号：EP3055531A1

公开(公告)日：2016-08-17

申请号：EP14787237.8

申请日：2014-10-03

申请人： Turbomeca

发明人： MARCONI, Patrick ,  THIRIET, Romain

IPC分类号： F02C6/20 ,  F02C9/44

CPC分类号： F02C9/42 ,  B64C27/04 ,  B64D27/10 ,  F01D15/08 ,  F01D15/12 ,  F02C3/04 ,  F02C6/206 ,  F02C7/262 ,  F02C9/44 ,  F05D2220/329 ,  F05D2240/35 ,  Y02T50/671

摘要： The invention relates to a method for optimising the specific consumption of a helicopter provided with two turboshafts (1, 2), each one comprising a gas generator (11, 21) provided with a combustion chamber (CC), each of said turboshafts (1, 2) being able to operate alone in the continuous flight mode, the other turboshaft (2, 1) being then in a so-called super-slow mode with zero power and with the combustion chamber lit, said super-slow mode being assisted by a mechanical rotation of the shaft (AE) of the gas generator in this mode, in such a way as to reduce the operating temperature and the fuel consumption of said gas generator.

摘要翻译： 用于优化配备有两个涡轮轴发动机（1,2）的直升机的比消耗量的方法，每个涡轮轴发动机（1,2）包括设置有燃烧室（CC）的气体发生器（11,21），这些涡轮轴发动机（1,2）中的每一个是 能够以连续的飞行速度自己操作，因此另一个涡轮轴发动机（2,1）处于以零功率被称为超怠速的速度，并且在燃烧室（CC）被点燃时，该超级 通过气体发生器的轴（AE）辅助的速度以该速度旋转机械驱动，以便降低该气体发生器的操作温度和燃料消耗。

公开(公告)号：EP3047117A1

公开(公告)日：2016-07-27

申请号：EP14784280.1

申请日：2014-09-12

申请人： Snecma ,  Turbomeca ,  HERAKLES

发明人： THIRIET, Romain ,  MARCONI, Patrick ,  SERGHINE, Camel ,  CARATGE, Antoine Marie Georges ,  DANGUY, François ,  FABBRI, Laurent ,  YVART, Pierre ,  SOULIE, Laurent ,  BARRAT, Philippe

IPC分类号： F01D19/00 ,  F02C7/272 ,  F02C7/277

CPC分类号： F02C7/277 ,  B64D27/10 ,  F01D19/00 ,  F02C6/206 ,  F02C7/272 ,  F05D2260/85 ,  Y02T50/672

摘要： System (20) for the emergency starting of aircraft turbomachines, comprising at least one solid-fuel gas generator (22), an electrically operated ignition device (24), a computer (28) connected to the ignition device, and at least two independent starters (18) each one intended to start a turbomachine, each starter comprising a turbine (38) for driving a shaft (34) intended to be coupled to a shaft (54) of the corresponding turbomachine, the gas outlet of the generator being connected to the inlet (44) of the turbine of each starter by one and the same distribution valve (26) connected to the computer (28).

摘要翻译： 本发明涉及一种用于飞行器的涡轮发动机的紧急启动系统（20），其特征在于其包括至少一个固体推进剂气体发生器（22），电控点火装置（24），计算机（28） 连接到点火装置的至少一个起动马达（18），以及至少一个起动马达（18），其包括用于驱动用于联接到涡轮发动机的轴（54）的轴（34）的涡轮机（38），来自 发电机连接到起动电动机的涡轮机的入口（44）。

公开(公告)号：EP2591219B1

公开(公告)日：2016-05-11

申请号：EP11743295.5

申请日：2011-07-05

申请人： Turbomeca

发明人： BEDRINE, Olivier ,  MARCONI, Patrick ,  PUERTO, Alphonse

IPC分类号： F02C6/02

CPC分类号： F02C6/00 ,  F02C1/04 ,  F02C6/02 ,  F02C7/10 ,  F02C7/36 ,  Y02E20/14 ,  Y02T50/671

公开(公告)号：EP2635782A2

公开(公告)日：2013-09-11

申请号：EP11824269.2

申请日：2011-10-28

申请人： Turbomeca

发明人： MARCONI, Patrick ,  THIRIET, Romain

IPC分类号： F02C6/20 ,  F02C9/44

CPC分类号： F02C5/00 ,  F02C6/206 ,  F02C7/268 ,  F02C9/44 ,  Y02T50/671

摘要： The invention seeks to reduce the specific fuel consumption Cs of a twin engine helicopter without compromising on the safety conditions regarding the minimum amount of power to be supplied for any kind of mission. To achieve this, the invention plans to make available special means capable of guaranteeing reliable in-flight restarts. One example of an architecture according to the invention involves two turbine engines (1, 2) each equipped with a gas generator (11, 21) and a with a free turbine (12, 22). Each gas generator (11, 21) is equipped with active drive means (E1, E2) capable of keeping the gas generator (1, 21) rotating with the combustion chamber inactive, and an emergency assistance device (U1, U2) comprising near-instantaneous firing means and mechanical means for accelerating the gas generator (11, 21). The control system (4) controls the drive means (E1, E2) and the emergency assistance devices (U1, U2) for the gas generators (11, 21) according to the conditions and phases of flight of the helicopter following a mission profile logged beforehand in a memory (6) of this system (4).