Method and apparatus for a rocket engine power cycle

Details Method and apparatus for a rocket engine power cycle Method and apparatus for a rocket engine power cycle

2007-05-15

2007-05-15

Casaregola, L. J. (Department: 3746)

Power plants

Reaction motor

Liquid oxidizer

C060S260000, C060S266000

Reexamination Certificate

active

10098955

ABSTRACT:
A system for cooling a portion of a rocket engine with an inert compound and transferring the thermal energy from the inert compound to the propellants. The energy absorbed by the coolant is used also to power the turbines which powers the pumps that pump the fuel, the oxidizer, and the coolant. Additionally, the coolant, which is an inert compound, is used to separate the oxidizer and the fuel before the oxidizer and the fuel enter the combustion chamber eliminating the need for a complex inert turbo pump seal package. The systems which pump or comprise the coolant physically separate the propellants before the propellants enter the rocket engine. The coolant remains substantially unconsumed in this cycle.

REFERENCES:
patent: 2900168 (1959-08-01), Nyborg
patent: 3049870 (1962-08-01), Chamberlain
patent: 3516254 (1970-06-01), Hammond
patent: 4583362 (1986-04-01), Wagner
patent: 5052176 (1991-10-01), Labatut et al.
patent: 5101622 (1992-04-01), Bond
patent: 5410874 (1995-05-01), Limerick
patent: 5444973 (1995-08-01), Limerick et al.
patent: 6052987 (2000-04-01), Dressler
patent: 6769242 (2004-08-01), Balepin

Affiliated with

Also associated with

Rating

Method and apparatus for a rocket engine power cycle does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Method and apparatus for a rocket engine power cycle, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Method and apparatus for a rocket engine power cycle will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-3797293