CPC B21D 53/04 (2013.01) [Y10T 29/4935 (2015.01)] | 7 Claims |
1. A method for manufacturing a structural surface heat exchanger of an adjusted or left final shape for an aircraft, the method comprising:
forming a first skin to obtain a first corrugated skin;
shaping the first corrugated skin, shaping a second smooth skin, and assembling the first corrugated skin and the second smooth skin so that the first corrugated skin and the second smooth skin define channels, each channel being delimited by the second smooth skin and a corrugation of the first corrugated skin, wherein the step of assembling the first corrugated skin and the second smooth skin includes welding or brazing the first corrugated skin to the second smooth skin, wherein the steps of shaping the first corrugated skin, shaping the second smooth skin, and assembling the first corrugated skin and the second smooth skin form the structural surface heat exchanger of an adjusted or left final shape, configured to permit a fluid to circulate in the channels and air to circulate in contact with the second smooth skin; and
forming cavities in the first skin simultaneously with the step of forming the first skin to obtain the first corrugated skin, or in the second smooth skin prior to the step of shaping the second smooth skin or assembling the first corrugated skin on the second smooth skin, to obtain fluid distributors and collectors when assembling the first corrugated skin and second smooth skin, wherein the step of forming cavities includes forming the cavities by operation of a press or by machining the first corrugated skin or the second smooth skin,
wherein the first skin has a thickness of 1 mm to 3 mm and the second smooth skin has a thickness of 0.6 mm to 2 mm.
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