公开(公告)号：EP3245130A1

公开(公告)日：2017-11-22

申请号：EP16705559.9

申请日：2016-01-11

申请人： Safran Helicopter Engines

发明人： MARIN, Jean Philippe, Jacques ,  GALLOT, Matthieu ,  ETCHEPARE, Philippe

IPC分类号： B64C27/04 ,  B64D35/08 ,  F02C3/10 ,  F02C6/02

CPC分类号： B64D31/06 ,  B64C27/04 ,  B64C27/06 ,  B64C27/12 ,  B64D27/10 ,  B64D35/08 ,  B64D41/00 ,  F02C3/04 ,  F02C3/10 ,  F02C6/02 ,  F05D2220/329 ,  F05D2220/50 ,  F05D2270/304 ,  F05D2270/705

摘要： The invention relates to a device for controlling an auxiliary engine (8) including a gas generator and a free turbine suitable for being connected mechanically to the rotor (12) of a helicopter in order to supply same with thrust power, characterised in that said control device includes a proportional-plus-integral controller (30) having proportional gain (Kp) and integral gain (Ki), which are functions of the speed of rotation of said gas generator, said controller (30) being configured to receive an error signal representing a speed error of said free turbine, and to generate a signal (Sc) for correcting the drive speed of said gas generator obtained by adding a signal which is proportional to said error signal according to said proportional gain (Kp), and an integrated signal (Si), resulting from adding a signal which is proportional to said error signal according to said integral gain (Ki) and a memory signal (Sm), provided by a feedback loop (31) of said integrated signal (Si), said memory signal (Sm) being dependent on a measurement that represents the speed of rotation of said free turbine.

公开(公告)号：EP2893169B1

公开(公告)日：2017-04-05

申请号：EP13767024.6

申请日：2013-08-27

申请人： Safran Helicopter Engines

发明人： HARRIET, Pierre ,  MARIN, Jean Philippe, Jacques

IPC分类号： F02C7/268 ,  F02C7/275

CPC分类号： F02C7/268 ,  F01D19/00 ,  F02C7/264 ,  F02C7/275 ,  F05D2260/85 ,  F05D2270/04 ,  F05D2270/304 ,  F05D2270/309

公开(公告)号：EP3123020A1

公开(公告)日：2017-02-01

申请号：EP15717551.4

申请日：2015-03-20

申请人： Safran Helicopter Engines

发明人： LESCHER, Fabien ,  MARIN, Jean Philippe, Jacques ,  ETCHEPARE, Philippe

IPC分类号： F02K3/12 ,  B64D31/12 ,  F02C3/10 ,  F02C9/46 ,  F02C9/56

CPC分类号： F02C9/56 ,  B64D31/06 ,  F02C3/10 ,  F02C9/46 ,  F02K3/12 ,  F05D2220/329 ,  F05D2270/091 ,  F05D2270/093 ,  F05D2270/095 ,  F05D2270/335 ,  Y02T50/671

摘要： The invention relates to a method for detecting a failure of a first turbine engine, referred to as faulty engine (4), of a twin-engine helicopter and for operating a second turbine engine, referred to as sound engine (5), each engine (4, 5) comprising protection end stops regulated by a regulating device which define a maximum power speed, characterized in that it comprises: a step (10) of detecting a fault index of said faulty engine (4); a step (11) of modifying said end stops for protecting said sound engine (5) to protection end stops corresponding to a maximum power single-engine speed, in the event of a fault index being detected; a step (12) of confirming a fault with said faulty engine (4); a step (13) of commanding an increase in the rate of supply of fuel to said sound engine (5) in the event of the fault being confirmed.

摘要翻译： 本发明涉及一种用于在一个第一涡轮轴发动机检测故障，由被称为上不起作用发动机（4），双发动机直升机的，并用于控制第二涡轮轴发动机，通过被称为健康发动机（5） 中，每个发动机（4，5）包括由调节装置限定的最大功率政权调节保护停止，DASS它包括：检测到所述非操作发动机（4）的故障的指示的步骤（10）; 修改所述健康发动机（5）转换成其对应于最大功率的单引擎制度，在发生故障的所检测的指示的情况下，保护停止的所述保护停止的步骤（11）; 的故障的步骤（12），确认所述失效发动机（4）; 控制，以增加在健康所述发动机（5）的燃料供给的流量，在一个确认失败的情况下的步骤（13）。

公开(公告)号：EP3123020B1

公开(公告)日：2019-01-30

申请号：EP15717551.4

申请日：2015-03-20

申请人： Safran Helicopter Engines

发明人： LESCHER, Fabien ,  MARIN, Jean Philippe, Jacques ,  ETCHEPARE, Philippe

IPC分类号： F02K3/12 ,  B64D31/12 ,  F02C3/10 ,  F02C9/46 ,  F02C9/56