| 摘要 |
<p>#CMT# #/CMT# The hub (36) has an annular internal ring (38) defining a flow space in a main gas flow in a turbojet. Each of N number of discharge valves (48) of the ring includes a door (50) moved in rotation around a fulcrum pin (51) between a closing position and an opening position of an air passage opening formed in the ring. A control unit includes N number of actuators formed by electrical motors (54). The actuators are mechanically independent from/to each other and respectively connected to the doors of the valves to control individual movement of the doors. #CMT# : #/CMT# An independent claim is also included for a method for controlling N-number of discharge valves of a casing hub. #CMT#USE : #/CMT# Hub for a casing i.e. intermediate casing of a turbojet e.g. twin-spool turbojet and ducted-fan turbine engine, of an aircraft (all claimed). #CMT#ADVANTAGE : #/CMT# The discharge valve is connected with the actuator for authorizing mechanical independence of the discharge valve relative to other valves, thus facilitating assembling and disassembling of the valves during maintenance actions, and hence allowing repairing or replacing of a faulty valve in an easier and inexpensive manner. The actuator can be used as a power moderator, so that additional power moderators are avoided, thus reducing manufacturing costs and mass of the hub while improving synchronization of the discharge valves by avoiding hysteresis problem, and hence assuring a simple and reliable configuration for the hub. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a schematic partial perspective view of a twin-spool airplane turbojet including discharge valves equipping a hub with an intermediate casing for the turbojet. 36 : Hub 38 : Annular internal ring 48 : Discharge valves 50 : Door 51 : Fulcrum pin 54 : Electrical motors.</p> |
