FIELD: engines and pumps.
SUBSTANCE: enhanced dual-flow turbo jet engine with the fan driven via a reduction gear incorporates a braking device arranged beyond the fan impeller in the outer circuit. The said braking device consists of a braking disk and a caliper, the former being fitted on the fan plate periphery and the caliper with braking pad being arranged on the fan bearing case. The aforesaid device is designed to be continuously thrown in depending upon the turbo jet engine gas generator rotor rpm.
EFFECT: higher engine reliability ensured by ruling out the cranking by means of the fan rotor braking device and its reduction gear with the inoperative pump feeding oil in the reduction gear.
3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| ENHANCED DUAL-FLOW TURBO JET ENGINE | 2006 |
|
RU2330170C2 |
| SUPERHIGH BY-PASS RATIO TURBOJET ENGINE WITH DRIVE REDUCTION GEAR OF DOUBLE-ROW OPPOSITE ROTATION FAN | 2006 |
|
RU2316667C2 |
| BYPASS GAS TURBINE ENGINE WITH FAN DRIVEN BY SIMPLE COAXIAL INNER GEARING REDUCTION GEAR | 2007 |
|
RU2346176C1 |
| FRONT PART OF AIRCRAFT DOUBLE-FLOW GAS TURBINE ENGINE AND AIRCRAFT DOUBLE-FLOW GAS TURBINE ENGINE | 2015 |
|
RU2686248C2 |
| HELICOPTER | 2018 |
|
RU2710839C1 |
| SUPER-BYPASS GAS TURBINE ENGINE WITH BIROTARY BLOWER. | 2007 |
|
RU2347929C2 |
| GAS-TURBINE ENGINE ROTOR SUPPORT | 1991 |
|
RU2075658C1 |
| BYPASS GAS-TURBINE ENGINE | 2006 |
|
RU2349784C2 |
| ASSEMBLY FOR AIRCRAFT GAS-TURBINE ENGINE AND METHOD OF ITS MOUNTING | 2015 |
|
RU2673027C2 |
| PROPFAN GAS TURBINE ENGINE | 2019 |
|
RU2730562C1 |
