Report presenting an investigation in a 16-inch-diameter simulated afterburner using gaseous hydrogen fuel. Results regarding combustion efficiency, afterburner pressure losses, spontaneous ignition, and a heat-balance check are provided.

Memorandum presenting an investigation of a number of short turbojet combustor configurations for hydrogen fuel in a quarter-annulus duct. The best combustor liner consisted of an annular primary zone and a secondary zone composed of T-shaped channels sloping from the primary zone to the combustor wall.

A report about the mechanical properties of dilute uranium alloys which might be crucial to developing high strength alloys for possible use as fuel.

From Summary: "An investigation was conducted in a 16-inch-diameter simulated afterburner using gaseous hydrogen fuel. No flameholder was used with a multipoint fuel injector. The burner length was varied from 9.5 to 38 inches. The afterburner-inlet conditions were: temperature of 1200 degrees or 1500 degrees F, pressure of 14 to 44 inches mercury absolute, and velocity of 300 to The measured combination efficiency ranged from 85 to 98 percent over an equivalence-ratio range of 0.2 to 1.0. The cold-flow pressure-drop coefficient was 1.0 for the system. Spontaneous ignition was always possible at temperatures above 1200 degrees F but was not possible at temperatures above 1200 degrees F but was not possible below 1100 degrees F for all pressures and velocities tested."

Satisfactory combustion efficiencies and outlet radial-temperature distributions at low total-pressure loss were obtained in an experimental, quarter-annulus combustor with hydrogen fuel at total pressures as low as 5.7 inches of mercury absolute. The combustor was 25 percent shorter than previous models for liquid hydrocarbon fuels. Similar performance was obtained from this combustor design operated with hydrogen in a full-scale engine.