Advanced Materials for Ultrahigh Temperature Structural Applications Above 2000 deg C
Abstract
The primary incentive for developing ultrahigh temperature materials for liquid bi-propellant rocket engines lies in the minimization and/or elimination of fuel-film and regenerative cooling of combustion chambers. Cooling is currently required because the most commonly used material for rocket combustion chambers is niobium alloy coated with disilicide with upper limit of operation up to 1450 deg C which is only approximately 50 % of the propellant combustion temperature. Therefore, by developing an ultrahigh temperature material with temperature capabilities in the range of 2200 - 3000 deg C, the fuel-film and regenerative cooling can be significantly reduced and/or eliminated resulting in cleaner burning of rocket engine. Thus fuel utilization can be vastly improved, more payload can be sent to space, higher specific impulse (Isp) can be achieved and finally the cost of the rocket engine could be reduced.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 07, 1997
- Accession Number
- ADA397998
Entities
People
- Jeremy Yang
- K. Upadhya
- W. Hoffman
Organizations
- Air Force Research Laboratory