Multi-stage semiconductor thermoelectric power generation and cooling integrated system for hypersonic flight vehicle

Multi-stage semiconductor thermoelectric power generation and cooling integrated system for hypersonic flight vehicle

  • CN 106,533,263 A
  • Filed: 12/29/2016
  • Published: 03/22/2017
  • Est. Priority Date: 12/29/2016
  • Status: Active Application
First Claim
Patent Images

1. hypersonic aircraft multilevel semiconductor thermo-electric generation and cooling integration system, it is characterised in that logical including low temperatureRoad (1), multilevel semiconductor temperature difference electricity generation device, multiple thermally conductive insulating layer (4), and high temperature channel (6);

  • Include multiple N-type semiconductor thermoelectric materials (2), multiple P-type semiconductor thermoelectricity per Level One semiconductor temperature difference electricity generation device blockMaterial (3) and multiple flow deflectors (5), N-type semiconductor thermoelectric material (2) and P-type semiconductor thermoelectric material (3) are intervally arranged, andAnd be sequentially connected in series by flow deflector (5);

    The multilevel semiconductor temperature difference electricity generation device is in parallel;

    The thermally conductive insulating layer (4) being brought into close contact with flow deflector (5), institute are provided with per Level One semiconductor temperature difference electricity generation device both sidesThere is the parallel distribution of thermally conductive insulating layer (4);

    Low temperature path (1) and high temperature channel (6) are respectively positioned at the outside of outermost two-stage semiconductor thermo-electric generation apparatus, andLow temperature path (1) is connected with high temperature channel (6).

View all claims
    ×
    ×

    Thank you for your feedback

    ×
    ×