There is provided a high temperature component with a thermal barrier coating, which can be used as a high temperature component for a gas turbine, an aircraft gas turbine engine, or the like. A top coat (3) is formed of a ceramic on a bond coat (2), the bond coat (2) being formed on a heat resistant alloy substrate (1) composed mainly of at least one element of nickel and cobalt, wherein the bond coat (2) contains at least one of nickel and cobalt, chromium and aluminum , and further contains at least one selected from a group consisting of tantalum, cesium, tungsten, silicon, platinum, manganese and boron in a range of 0 to 20 wt%. The high temperature component according to the present invention has very high durability of a thermal-insulating ceramic layer, and is less susceptible to spalling damage.