摘要:
The invention relates to a turbine engine such as a turbojet engine or a turboprop engine of an aircraft, comprising at least one oil circuit (8) and means (16) for cooling the oil of said circuit (8), the cooling means (16) comprising a refrigerant circuit (17) provided with a first heat exchanger (18) capable of exchanging heat between the refrigerant and the air and forming a condenser, a second heat exchanger (19) capable of exchanging heat between the refrigerant and the oil of the oil circuit and forming an evaporator, an expander (20), a compressor (21) and first control means (31) capable of controlling the pressure of the refrigerant entering the first exchanger (18).
摘要:
The invention relates to a turbine engine which comprises at least one stator bladed sector (10) and a fluid distribution circuit (22), the stator bladed sector comprising at least one blade (12), a fluid intake (25a), a fluid outlet (25b) and a channel (24a) providing fluid connection between the fluid intake and the fluid outlet, extending at least partially into the blade (12), the blade and the channel being suitable for allowing a heat exchange between a hot fluid passing through the channel and a stream of cold air passing through the bladed sector, the fluid distribution circuit (22) having a supply pipe (22a) and a recovery pipe (22b), the fluid intake (25a) being in fluid connection with a bypass tapping (23a) of the supply pipe (22a), while the fluid outlet (25b) is in fluid connection with a bypass tapping (23b) of the recovery pipe (22b).
摘要:
Panel (10) for heat exchange and noise reduction for a turbomachine, in particular of an aircraft, the panel comprising: an external surface (22) intended to be swept by an airflow and from which fins (26) extend along a first and a second main predetermined direction; cavities (20) forming Helmholtz resonators, linked to the first ends of channels (30) for the passage of air, the second ends of which communicate with said airflow, such that said channels form necks, referred to as Helmholtz resonators, extending substantially along the first direction; and at least one oil flow chamber (16) extending between said external surface and said at least one cavity, and intended to discharge the thermal energy carried by the oil, characterized in that said channels are formed, at least in part, inside said fins.
摘要:
The invention relates to a system (10) for supplying a turbomachine with fluid, the supply system (10) comprising a low-pressure pumping unit (101) intended to increase the pressure of the fluid flowing toward a downstream circuit (50, 60). According to the invention, the downstream circuit (50, 60) divides at an inlet node (E), situated between the low-pressure pumping unit (101) and the high-pressure volumetric pump (102), into a circuit (60) supplying an injection system (62) and a variable geometries supply circuit (50). The circuit (60) supplying the injection system comprises a high-pressure volumetric pump (102). The variable geometries supply circuit (50) is configured to convey the fluid toward variable geometry devices (54) from the inlet node (E) to an outlet node (S) connecting the variable geometries supply circuit (50) to the upstream circuit (100) between two pumps (101a, 111a) of the low-pressure pumping unit.