Turbine engine comprising a heat exchanger in the secondary path
An aircraft turbine engine having a primary air flow path with low-pressure and high-pressure compressors, a secondary air flow path which is located around the primary path and runs coaxially thereto, the turbine engine including vanes distributed about a main axis of the turbine engine. A pressurized air circuit draws air between the low-pressure compressor and the high-pressure compressor or in the high-pressure compressor and supplies at least one component located close to a main axis of the turbine engine. The pressurized air circuit includes a heat exchanger between the stream of pressurized air and the stream of air flowing in the secondary path, the heat exchanger being arranged in at least one of the straightening vanes, where a heat exchanger pipe is arranged, the pipe having a pressurized-air inlet and a pressurized-air outlet that are located at the same radial end of the vane.
1. An aircraft turbine engine including a main axis and comprising:
a primary air flow path in which a low-pressure compressor and a high-pressure compressor are arranged,
a secondary air flow path which is located around the primary air flow path and coaxial with the primary air flow path, including a straightener of an air stream flowing in the secondary air flow path, the straightener including a plurality of vanes distributed around the main axis of the turbine engine,
a pressurized air circuit extracting air from between the low-pressure compressor and the high-pressure compressor or from within the high-pressure compressor to produce a pressurized air stream supplying at least one component of the turbine engine, said at least one component being located radially within the turbine engine closer to the main axis of the turbine engine than the primary air flow path,
wherein the pressurized air circuit includes a heat exchanger between the pressurized air stream and the air stream flowing in the secondary air flow path, the pressurized air circuit being arranged in at least one of the plurality of vanes of the straightener,
wherein the heat exchanger includes a duct arranged in said at least one of the plurality of vanes, each of said at least one of the plurality of vanes including a pressurized air inlet and a pressurized air outlet which are located at a same radial end of said at least one of the plurality of vanes, and
wherein a lubrication circuit in which a lubrication fluid circulates, includes a section arranged in said at least one of the plurality of vanes,
wherein the section of the lubrication circuit cooperates with the said at least one of the plurality of vanes to carry out a cooling of the lubrication fluid, and
wherein for each of said at least one of the plurality of vanes, the duct includes a bend, the bend being radially outward of the section of the lubrication circuit with respect to the main axis.
2. The turbine engine according to claim 1 , wherein for each of said at least one of the plurality of vanes, the pressurized air inlet and the pressurized air outlet of the duct are located at the same radial end at a level of an inner radial end of said at least one of the plurality of vanes.
3. The turbine engine according to claim 1 , wherein an internal volume of each of said at least one of the plurality of vanes is isolated from the air stream flowing in the secondary air flow path.
4. The turbine engine according to claim 3 , wherein the duct of the heat exchanger and the section of the lubrication circuit are arranged in the respective internal volume of each of said at least one of the plurality of vanes.
5. The turbine engine according to claim 3 , wherein for each of said at least one of the plurality of vanes, said section includes a lubrication fluid inlet and a lubrication fluid outlet which are located at a level of the same radial end of said at least one of the plurality of vanes as the pressurized air inlet and the pressurized air outlet of the duct.
6. The turbine engine according to claim 5 , wherein for each of said at least one of the plurality of vanes, the lubrication fluid inlet is upstream of the pressurized air inlet with respect to the air stream flowing in the secondary air flow path, and the lubrication fluid outlet is downstream of the pressurized air outlet with respect to the air stream flowing in the secondary air flow path.
7. The turbine engine according to claim 1 , which includes an inter-path compartment located between the primary air flow path and the secondary air flow path, wherein:
the pressurized air circuit includes, in a direction of air flow therein:
at least one air extraction point which is borne by a radially inner wall of the inter-path compartment;
an upstream section extending through the inter-path compartment to the secondary air flow path;
said duct disposed in said at least one of the plurality of vanes; and
a downstream section extending through the inter-path compartment from the secondary air flow path to the primary air flow path and extending through a profiled arm traversing the primary air flow path; and
the pressurized air stream is distributed from the downstream section to said at least one component of the turbine engine.
8. The turbine engine according to claim 1 , wherein said at least one component of the turbine engine is a low-pressure shaft of the turbine engine.
9. The turbine engine according to claim 1 , wherein said at least one component is a lubrication oil pressurization enclosure.
10. The turbine engine according to claim 1 , wherein said at least one component is a reduction gear which is arranged between the low-pressure shaft and a fan of the turbine engine.
11. The turbine engine according to claim 1 , wherein the lubrication fluid is oil.