Abstract This paper presents a detailed account of the metallurgical principles involved in the development of precipitation-hardened alloys for gas turbines, together with typical data on heat-resistant alloys “K42B,” “Discaloy,” “Refractaloy 26,” and “Refractaloy 70.” Selection of base alloy and hardening agent, choice of heat-treatment for optimum properties, and the use of short-time tensile and creep rupture tests in evaluating the effects of composition and heat-treatment variables are discussed in Part I. The creep rupture properties of K42B, Discaloy, Refractaloy 26, and Refractaloy 70 are given in Part II in the form of design curves for each alloy at one or more temperatures in the range 1200 to 1600 F. The factors governing choice of alloy for rotor and blading service are discussed together with some considerations on forging, machining, welding, and heat-treating these gas-turbine components.