The　turbulent　fluid　flow　and　heat　transfer　in　a　regenerative-cooling　channel　of　the　liquid　propellant　rocket　engine　were　numerically　investigated　by　solving　three-dimensional　elliptical　Navier-Stokes　equations.　The　coolant　is　hydrogen,　whose　thermal　properties　such　as　thermal　conductivity,　density　and　dynamic　viscidity　are　varied　with　both　temperature　and　pressure.　The　specific　heat　of　hydrogen　and　thermal　properties　of　solid　metal　are　varied　with　temperature　only.　The　standard　k-ε　turbulent　model　and　gas-solid　coupled　technique　was　adopted.　The　results　show　that　both　the　highest　temperature　of　hydrogen　and　the　maximal　wall　heat　fluxes　at　the　hot-gas　side　occur　at　the　throat　region,　and　the　maximal　cross-sectional　temperature　gradients　of　the　solid　region　occur　close　to　the　hot-gas　side.　In　addition,　the　secondary　flow　is　generated　near　the　throat　region　perpendicular　to　the　main　flow,　the　highest　heat　flux　and　convective　heat　transfer　coefficient　of　gas-solid　coupled　interface　also　occur　at　throat　region.