FIELD: engines.
SUBSTANCE: invention relates to gas turbine engine (100) for helicopter (200). Helicopter comprises main reduction gear, screw (204) and rotation frequency reduction device (206) arranged completely in main gearbox (202) of helicopter and connected with said propeller. Gas turbine engine includes housing (102), gas generator (114) with shaft (115) of gas generator and free turbine (124) driven by gas flow generated by gas generator. Said free turbine has free turbine shaft (128).
EFFECT: in gas turbine engine, when gas turbine engine is attached to gear of helicopter, free turbine shaft passes axially in main gearbox of helicopter to be directly connected with rotation frequency reducing device.
12 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| COMPENSATION FOR REACTIVE MOMENT OF ROTOR | 2012 |
|
RU2514010C1 |
| TURBO-SHAFT DISCHARGE DEVICE | 2013 |
|
RU2535813C1 |
| AUXILIARY DEVICE FOR AN AIRCRAFT GAS TURBINE ENGINE WITH A FREE TURBINE | 2015 |
|
RU2683351C2 |
| POWER PLANT OF THE AIRCRAFT WITH A ROTATING TRANSFORMER FOR SUPPLYING ELECTRICITY TO THE BLADES | 2019 |
|
RU2762600C1 |
| TURBINE ENGINE WITH PARALLEL SHAFTS | 2010 |
|
RU2583186C2 |
| VTOL AIRCRAFT POWER PLANT | 2008 |
|
RU2361783C1 |
| GAS TURBINE ENGINE BUILT INSIDE REDUCTION GEAR HOUSING | 2016 |
|
RU2706855C2 |
| GAS TURBINE ENGINE FOR AIRCRAFT, EQUIPPED WITH AUTOMATICALLY ACTIVATED CENTRING ELEMENT | 2016 |
|
RU2704585C2 |
| DEVICE FOR TRANSFERRING OIL BETWEEN TWO COORDINATE SYSTEMS ROTATING RELATIVE TO EACH OTHER AND PROPELLER TURBOMACHINE FOR AIRCRAFT WITH SUCH DEVICE | 2014 |
|
RU2665194C2 |
| METHOD AND SYSTEM FOR RELIABLE STARTING TURBINE ENGINE | 2014 |
|
RU2666029C2 |
