With introduction of the turbulent kinetic energy equation for the Reynolds stress term, the characteristics of compressible turbulent boundary layers along the wall of a rocket thrust chamber are theoretically solved. This inclusion of the turbulent kinetic energy equation provides the character of chemically reactive flow with mass injection and can exhibit the past history of boundary layers. Results show the variation of eddy viscosity in flow direction including the laminarization tendency in the nozzle convergent section. The results appears to be in good agreement with available experimental data. The eddy viscosity decreases significantly in the reactive hydrogen-oxygen boundary layer when a small amount of hydrogen is injected from the wall.