Study of fuel systems for LH2-fueled subsonic transport aircraft. Volume 1. Final report, September 1976--December 1977

Technical Report · Sat Jul 01 04:00:00 EDT 1978

OSTI ID:6274027

Brewer, G D; Morris, R E; Davis, G W; Versaw, E F; Cunnington, Jr, G R

Several engine concepts examined to determine a preferred design which most effectively exploits the characteristics of hydrogen fuel in aircraft tanks received major emphasis. Many candidate designs of tank structure and cryogenic insulation systems were evaluated. Designs of all major elements of the aircraft fuel system including pumps, lines, valves, regulators, and heat exchangers received attention. Selected designs of boost pumps to be mounted in the LH2 tanks, and of a high pressure pump to be mounted on the engine were defined. A final design of LH2-fueled transport aircraft was established which incorporates a preferred design of fuel system. That aircraft was then compared with a conventionally fueled counterpart designed to equivalent technology standards.

• Research Organization: Lockheed-California Co., Burbank (USA)
• OSTI ID: 6274027
• Report Number(s): N-78-31085
• Country of Publication: United States
• Language: English

Related Subjects

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION
320201* -- Energy Conservation
Consumption
& Utilization-- Transportation-- Air & Aerospace
AIRCRAFT
CONTAINERS
CONTROL EQUIPMENT
DESIGN
EQUIPMENT
FLOW REGULATORS
FUEL SYSTEMS
FUELS
HEAT EXCHANGERS
HYDROGEN FUELS
PUMPS
SYNTHETIC FUELS
TANKS
VALVES