FIELD: engines and pumps.
SUBSTANCE: heat-transfer system for a gas turbine engine with an air intake fairing comprises a circular jacket of a fan, a circular airing of an air intake arranged in front of the circular jacket of the fan, a heat exchanger having a source of heat passing through it and installed outside the circular jacket of the fan; and multiple heat tubes, every of which passes between the heat exchanger and the inner space of the air intake fairing. Each heat tube comprises a rear section passing in axial direction, a transition section passing in circular direction and having an arched shape. The transition section connects the rear section and the front section with each other arranged near the top of the air intake fairing. The front section passes inside the air intake fairing, at the same time front sections of each heat tube are arranged inside the air intake fairing along the circumference.
EFFECT: improved cost-effectiveness due to use of lubricant oil waste heat, lower weight.
9 cl, 11 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| AIRCRAFT DE-ICING SYSTEM AND AIRCRAFT WITH SUCH SYSTEM | 2011 |
|
RU2529927C1 |
| HEAT TRANSFER SYSTEM FOR TURBINE ENGINE USING HEAT PIPES | 2007 |
|
RU2436975C2 |
| HEAT TRANSFER SYSTEM | 2007 |
|
RU2447300C2 |
| SYSTEM FOR REMOVING ICE DEPOSITS FROM AIR INTAKE FAIRING FOR GAS-TURBINE ENGINE | 2007 |
|
RU2413081C2 |
| GAS PUMPING UNIT | 2017 |
|
RU2685802C1 |
| AIR ENGINE DESIGN | 2004 |
|
RU2355902C2 |
| SYSTEM TO ELIMINATE ICING OF TURBINE ENGINE NOSE FAIRING INLET FRONT EDGE | 2006 |
|
RU2380558C2 |
| TURBOFAN ENGINE WITH PRECOOLER | 2006 |
|
RU2376205C1 |
| NUCLEAR GAS TURBINE AIRCRAFT ENGINE | 2008 |
|
RU2379532C1 |
| COOLING SYSTEM AND METHOD OF HEAT REMOVAL FROM THERMAL SOURCES LOCATED INSIDE AIRCRAFT | 2004 |
|
RU2378596C2 |
