| 摘要 |
The invention relates to a thermoelectric and thermal insulation device, to an aircraft engine nacelle incorporating same and to a method of manufacture thereof. This device (1) can be used in a wall of such a nacelle defined by internal and external faces and is able to have an annular section delimited by a hot face (6a) facing toward the internal face and by a cold face (6b) facing toward the external face, the device comprising: a thermally insulating and flexible structure (2a, 2b, 2c) between the hot and cold faces and able to extend circumferentially, and a thermoelectric module incorporated into the structure and including: • alternating p and n semiconductor units (3), and • electrical connection means (4a, 4b) which electrically connect said p and n units together in pairs. According to the invention, the device comprises a plurality of thermally conducting heat dissipating means (7a, 7b) coupled to said blocks and connecting said electrical connection means, which are able to be deformed so as to extend circumferentially, at the hot face and at the cold face. |
