FIELD: engines and pumps.
SUBSTANCE: anti-ice system 2 on aircraft gas turbine engine inlet cone 4 comprises air diffuser 18 arranged in engine inlet cone to feed hot air therein. Said system comprises also circuit 20 to remove supercharged air from constricted cavity of turbine engine. Said circuit communicates with diffuser to supply hot air therein. Aircraft turbine engine incorporates above described anti-ice system. Proposed method of de-icing features the use of above described system.
EFFECT: perfected operating performances.
13 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| AIRCRAFT DE-ICING SYSTEM AND AIRCRAFT WITH SUCH SYSTEM | 2011 |
|
RU2529927C1 |
| IMPROVED DESIGN OF THE INPUT DEVICE | 2018 |
|
RU2727820C2 |
| GAS-TURBINE POWER UNIT | 1995 |
|
RU2098649C1 |
| SYSTEM TO ELIMINATE ICING OF TURBINE ENGINE NOSE FAIRING INLET FRONT EDGE | 2006 |
|
RU2380558C2 |
| SYSTEM OF OIL SEPARATION FROM THE AIR/OIL MIXTURE FOR SEALING GAS TURBINE ENGINE SEALS | 2017 |
|
RU2745767C2 |
| GAS-TURBINE POWER-GENERATING PLANT | 2005 |
|
RU2293219C2 |
| SMALL-SIZE GAS TURBINE PLANT | 2024 |
|
RU2819326C1 |
| FRONT PART OF DIVIDER CONTAINING PLATE, MAKING SURFACE TO GUIDE CIRCUIT AND ACTING AS ANTI-ICING CHANNEL | 2014 |
|
RU2575676C2 |
| DEVICE FOR COMBATING CRYSTAL ICING OF TURBOFAN ENGINES (TDCE) | 2023 |
|
RU2814576C1 |
| GAS-TURBINE ENGINE | 0 |
|
SU1739065A1 |
