TURBOJET ENGINE COMPRISING THERMOELECTRIC GENERATORS Russian patent published in 2017 - IPC F02C7/04 F02K3/02 F02C7/32 

FIELD: engine devices and pumps.

SUBSTANCE: turbojet with a front fan comprises at least one fluid circuit and an air/fluid heat exchanger, by means of which said fluid is cooled by air external relative to turbojet engine, and a flow divider. The flow divider is located downstream of the fan between the primary flow and the secondary flow. The flow divider has a substantially triangular cross-section and comprises a front annular edge line forming an attack rib, a portion of the outer wall extending towards the outlet from the attack rib which limits the inlet part of the path of the secondary flow radially from the inside, and a portion of the inner wall passing towards the outlet from the attack rib and limiting the inlet portion of the primary flow path radially from the inside. The outer and inner wall portions define a space, in which the heat exchanger is placed. On the portion of the outer wall there are guide vanes which extend radially between the section of the outer wall and the body surrounding the fan blades. The heat exchanger comprises a chamber through which cooled fluid passes and which is formed between two parallel walls along the inner surfaces the portion of the outer wall and the inner surface of the portion of the inner wall. The heat exchanger is connected to thermoelectric generator comprising a first and a second heat exchange surfaces. The first surface is in thermal contact with the secondary air stream and the second surface is in thermal contact with fluid which is cooled in the heat exchanger of one of the walls of the heat exchanger chamber. The first heat exchange surface forms a wall portion of the divider, which is downstream from the front edge of the air flow divider on the side of the secondary flow path of the outer surface of the outer wall portion of the divider.

EFFECT: use of thermoelectric reactors in aircraft engines.

3 cl, 4 dwg