FIELD: engines and pumps.
SUBSTANCE: invention relates to development of power plants with oil cooling in closed circulation system, which is specific for aircraft gas turbine engines. Efficiency of ejector system is achieved by using double nozzle connected to output of turbine, through which jet of exhaust gases is passing, and branch pipe of trapezoidal shape air-oil radiator.
EFFECT: creation of autonomous ejector oil cooling system, which is structurally independent from conditions of location in aircraft cabin, and maximum use of surface of engine circuit nozzle to increase effect of ejection.
1 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| EJECTOR-TYPE OIL COOLING SYSTEM FOR AUXILIARY AIRCRAFT ENGINE | 1997 |
|
RU2131380C1 |
| CHEVRON EXHAUST NOZZLE | 1998 |
|
RU2213240C2 |
| AIRCRAFT WITH GAS TURBINE ENGINE PROVIDED WITH TURBULENCE EJECTION PROPULSORS | 2013 |
|
RU2567914C2 |
| AIRCRAFT WITH GYROSCOPIC STABILIZATION | 2020 |
|
RU2796279C2 |
| METHOD OF ATMOSPHERIC AIR EJECTION TO INCREASE THRUST OF CRUISE PROPULSION SYSTEM OF CARRIER ROCKET AND LAYOUT OF PIN NOZZLE UNIT FOR IMPLEMENTATION THEREOF | 2019 |
|
RU2744528C2 |
| LOW-NOTICE UNMANNED VERTICAL TAKE-OFF AND LANDING AIRCRAFT | 2018 |
|
RU2693427C1 |
| SYSTEM FOR SUPPRESSION OF INFRARED RADIATION | 2006 |
|
RU2413085C2 |
| METHOD OF AND DEVICE FOR OPERATION OF RAMJET ENGINE | 2003 |
|
RU2264554C2 |
| UNBOOSTED TURBOJET ENGINE | 2017 |
|
RU2663440C1 |
| AERIAL FIRE VALVE | 2022 |
|
RU2794471C1 |
