Integration of a surface heat exchanger to the wall of an aerodynamic flowpath by a structure of reinforcement rods
Setting in place of one or several coolers in the wall of a secondary flow of a bypass turbomachine. The wall extends from an intermediate casing toward a leading edge of a separator nose between a primary flow and the secondary flow. The wall includes a series of support arms attached to an intermediate casing, distributed over the perimeter of the wall and directed upstream. A series of surface air-oil heat exchangers forming wall segments are arranged end-to-end on the support arms, so as to form an annular wall. A shroud having a leading edge is arranged and fixed in the area of the upstream edges of the heat exchangers, so as to complete the wall. The support arms include hydraulic connectors connected to one another on each arm, adapted to cooperate with corresponding connectors in the area of the heat exchangers and in the area of the intermediate casing.
1. An annular inner wall for a bypass turbojet engine with
a nose for separating a primary flow and a secondary flow and
an intermediate casing for supporting a rotor; said inner wall being intended to be
disposed between a leading edge of the nose and the intermediate casing and comprising:
at least one surface air-oil heat exchanger forming an annular segment of the wall; and
at least one support arm fixed to the intermediate casing and extending from the intermediate casing toward the leading edge; said support arm comprising:
an attachment flange for attaching each support arm to the intermediate casing; and
an elongated portion extending from the attachment flange and being configured to support the heat exchanger.
2. The wall according to claim 1 , further comprising:
a plurality of heat exchangers forming a series of annular segments of the wall portion.
3. The wall according to claim 2 , further comprising:
a support arm disposed in the vicinity of each junction of two heat exchangers.
4. The wall according to claim 2 , wherein the heat exchangers are configured end-to-end, so as to form the annular segment.
5. The wall according to claim 2 , wherein the heat exchangers are configured so as to form at least one annular segment of the wall portion without a heat exchanger.
6. The wall according to claim 1 , wherein the heat exchanger extends from the intermediate casing toward the leading edge.
7. The wall according to claim 1 , further comprising:
a shroud forming the leading edge of the nose, the shroud being adapted to be fixed to the heat exchanger.
8. The wall according to claim 7 , wherein the shroud is a one-piece shroud.
9. The wall according to claim 7 , further comprising:
a means for attaching the shroud to the heat exchanger and the support arm.
10. The wall according to claim 9 , wherein the means for attaching is a screwing means.
11. The wall according to claim 3 , wherein the support arms are configured to be arranged along the inner side of the annular surface of the wall portion.
12. The wall according to claim 1 , wherein the support arm comprises:
a reinforcement means for connecting the flange to the elongated portion.
13. The wall according to claim 12 , wherein the reinforcement means comprises:
a perforated rib having a trellis-type of structure.
14. The wall according to claim 1 , further comprising:
a first hydraulic connector configured to ensure a hydraulic connection with the heat exchanger; and
a second hydraulic connector adapted to ensure a hydraulic connection with the intermediate casing; and
a duct connecting the first hydraulic connector and second hydraulic connector.
15. The wall according to claim 14 , wherein the second hydraulic connector is configured on the support arm, so as to directly engage a corresponding connector of the intermediate casing during attachment of the support arm to the intermediate casing.
16. The wall according to claim 14 , wherein the first hydraulic connector is configured on the support arm, so as to directly engage a corresponding connector of the adjacent heat exchanger by an approach motion of the heat exchanger toward the support arm followed by a translational movement in a direction corresponding to the upstream direction of the fluid flow of the turbojet engine.
17. A turbojet engine, comprising:
an intermediate casing
a nose for separating a primary flow and a secondary flow of the engine;
an internal wall portion of the secondary flow path of the engine, coupled to the intermediate casing, the internal wall portion comprising:
at least one surface air-oil heat exchanger forming an annular segment of said wall; and
at least one support arm carrying the heat exchanger, said support arm being fixed to the intermediate casing and extending from the intermediate casing toward the leading edge; said support arm comprising:
an attachment flange for attaching each support arm to the intermediate casing; and
an elongated portion extending from the attachment flange and being configured to support the heat exchanger.
18. A method of cooling oil of a lubrication and cooling circuit of a bypass axial turbomachine having a nacelle, a rotor, and an axial compressor, comprising:
coupling a support member to the nacelle;
coupling an intermediate casing to the support member;
coupling an internal casing to the intermediate casing;
providing an internal wall having a leading edge nose portion and a support arm for separating the flow into a primary flow and a secondary flow, said support arm comprising an attachment flange for attaching each support arm to the intermediate casing, and an elongated portion extending from the attachment flange and being configured to support the heat exchanger;
coupling the internal wall to the intermediate casing;
coupling at least one surface air-oil heat exchanger to the support arm, such that the heat exchanger is disposed in the secondary flow; and
circulating the oil of the lubrication and cooling circuit through the heat exchanger.