FIELD: engines and pumps.
SUBSTANCE: position control device of turning guide blades of compressor or turbine of gas turbine engine includes synchronising rings arranged outside the housing of compressor or turbine and connected to guide blades with adjustable rods and drive mechanism containing at least one blade position angle sensor. The latter is connected to one of shafts of blade drive through levers and additional rod, one end of which is hinged to one of levers of blade drive shaft, and the other end of additional rod - to levers of sensor; at that, levers of blade drive shaft, one of which is kinematically connected to sensor and the other one - to drive mechanism, are made separately on drive shaft with possibility of being moved in parallel planes.
EFFECT: ensuring fail-safe operation of device owing to accurate measurement of actual angles ϕHA of blade position of compressor or turbine of gas turbine engine at failure of drive mechanism of the above blades.
3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| CONTROL SYSTEM OF STAGES OF ROTATING BLADES OF STATOR OF COMPRESSOR OF GAS TURBINE ENGINE | 2009 |
|
RU2422644C1 |
| GAS-TURBINE ENGINE AXIAL-FLOW COMPRESSOR | 1998 |
|
RU2141062C1 |
| MECHANISM OF REGULATION OF PADDLES OF THE GUIDE DEVICE OF THE STATOR MULTISTAGE COMPRESSOR OF A GAS TURBINE ENGINE | 2017 |
|
RU2674227C1 |
| DEVICE TO CONTROL POSITION OF TURNING GUIDE VANES OF COMPRESSOR OR TURBINE OF GAS-TURBINE ENGINE | 1995 |
|
RU2098670C1 |
| GAS-TURBINE ENGINE AXIAL-FLOW COMPRESSOR | 1995 |
|
RU2111385C1 |
| AXIAL-FLOW COMPRESSOR FOR TURBOMACHINE | 2004 |
|
RU2267656C2 |
| SYSTEM OF ROTATING BLADES STAGES CONTROL OF HIGH PRESSURE COMPRESSOR STATOR | 2011 |
|
RU2474698C1 |
| STATOR OF GAS TURBINE ENGINE COMPRESSOR | 2001 |
|
RU2193699C2 |
| DEVICE FOR TURNING GUIDING BLADES OF COMPRESSOR AND ALSO NOZZLE BLADES OF TURBINE | 2005 |
|
RU2300669C1 |
| GAS-TURBINE ENGINE | 2013 |
|
RU2555933C2 |
