Electroformed nickel-chromium alloy
Aircraft turbomachine comprising at least one heat exchanger ( 40 ) and a gearbox ( 10 ) in a V-shaped overall configuration and comprising two lateral arms ( 20 ) joined together by a central joining piece, the heat exchanger being mounted between the arms of the gearbox.
1. An aircraft turbine engine, comprising at least one heat exchanger and a gearbox for driving equipment, which is generally V-shaped and which has two lateral arms which are interconnected by a middle joining portion, said arms enclosing lines of gears which are located in non-parallel planes and which are joined to one another by at least one gear which is located in said joining portion, wherein the heat exchanger is mounted between the arms of the gearbox.
2. The turbine engine according to claim 1 , wherein the heat exchanger is an air/oil exchanger.
3. The turbine engine according to claim 1 , wherein the heat exchanger comprises a fluid output for cooling equipment which is supported by the gearbox.
4. The turbine engine according to claim 1 , wherein the gearbox is located in a lower portion of the turbine engine.
5. The turbine engine according to claim 1 , wherein the exchanger comprises means for fixing to the two arms of the gearbox.
6. The turbine engine according to claim 5 , wherein the fixing means comprise damping means.
7. The turbine engine according to claim 1 , wherein the gearbox is fixed to a body of the turbine engine which is surrounded by an annular wall which is formed by two substantially semi-cylindrical cowls, each cowl being connected by connecting rods to a rail/sliding rail system which is supported by the exchanger.
8. The turbine engine according to claim 7 , wherein the rail/sliding rail system comprises a rail which is rigidly connected to the exchanger and a sliding rail which is movable in translation with respect to the rail, the sliding rail being connected by a first connecting rod to a second connecting rod, one end of which is articulated on the body, and the opposite end of which is articulated on a cowl.
9. The turbine engine according to claim 8 , wherein the first connecting rods substantially form a V shape, and one of the ends thereof is fixed to substantially the same point on the sliding rail.
10. The turbine engine according to claim 8 , wherein the two connecting rods substantially form a V shape and one of the ends thereof is fixed to substantially the same point on the body of the turbine engine, each second connecting rod being connected to one of the first connecting rods at a point which is remote from the longitudinal ends thereof.
11. The turbine engine according to claim 1 , wherein the at least one heat exchanger comprises a first heat exchanger of the surface type and a second heat exchanger of the volume or brick type, the first heat exchanger being mounted between the arms of the gearbox, and the second heat exchanger being rigidly connected to the first exchanger and mounted under the first heat exchanger.
12. The turbine engine according to claim 11 , wherein said second exchanger comprises a scoop having a movable flap.