High Temperature Air System for High Speed Propulsion Experiments
Abstract
Funds are requested for the development of an extremely high temperature, air delivery and control system. This equipment will be used in support of multiple (funded and proposed) projects with the Oce of Naval Research that target solid fuel ramjets, scramjets with rotating detonations, advanced hydrocarbon fuel applications in super- and hypersonic systems, and other Department of Defense technologies. Specically, we propose the procurement of a valve system that is capable of actuating a ow of non-vitiated air at temperatures up to 1450 F and pressures up to 750 psia with ow rates up to 10 lbm/s. This system will be used to deliver supersonic free-stream ight conditions (matching total temperature and total pressure) to direct-connect test articles for high-delity characterization of combustion processes in solid fueled ramjets and other high-speed propulsion devices. The system is comprised of three main components: two pneumatically actuated high pressure-temperature valves (run and divert) and a Haynes Grayloc hub/clamp set to integrate the valves into the existing high temperature air system at Purdue. The requested equipment will complement the extensive, high-pressure propulsion research infrastructure at the Purdue University Zucrow Laboratories, enhancing eective control and increasing the testing productivity of these important, device-relevant experiments.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jul 20, 2020
- Source ID
- N000142012706
Entities
People
- Carson D. Slabaugh
Organizations
- Office of Naval Research
- United States Navy
- University of Virginia