GAS TURBINE ENGINE (VERSIONS) Russian patent published in 2014 - IPC F02K1/72 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises inner stage engine, blower and integrated mechanism. Blower is driven to form external airflow to allow bypass ratio about or over 6. Integrated mechanism interacts with airflow in external stage. It comprises blower variable-nozzle throat and thrust reverser and can be fitted at multiple different positions to allow control over external flow. Thrust reverser comprises locking flap arranged to displace between retracted position and in-position and link coupled with said flap for sliding therewith. In compliance with another version, inner stage engine comprises low-pressure turbine to allow the pressure difference of about or over 5. In compliance with one more version, said link has its one end engaged with the support while locking flap is equipped with T-like-cross-section cut-out to allow said link to slide therein.

EFFECT: higher stability and accuracy of control, simplified design of thrust reverser.

25 cl, 7 dwg