Heat induced high pressure lox pump rocket engine cycle

Details Heat induced high pressure lox pump rocket engine cycle Heat induced high pressure lox pump rocket engine cycle

1994-03-14

1996-09-03

Thorpe, Timothy S.

Power plants

Reaction motor

Liquid oxidizer

160 39461, F02K 900

Patent

active

055512305

ABSTRACT:
A liquid hydrogen-liquid oxygen (LH.sub.2 -LOX) rocket engine system wherein a conventional oxidizer turbo pump is replaced with a jet pump--a jet oxidizer pump. Beneficial features of the jet oxidizer pump system, over a conventional oxidizer turbo pump system, include: 1) it does not require a complicated seal system, 2) it has no moving parts, and 3) it is lighter. All these features improve the operational reliability of the rocket engine while decreasing its manufacturing cost.

REFERENCES:
patent: 2612752 (1952-10-01), Goddard
patent: 2704438 (1955-03-01), Sheets
patent: 3300981 (1967-01-01), Webb
patent: 3379011 (1968-04-01), Von Chain et al.
patent: 3672165 (1972-06-01), Baum
patent: 4771599 (1988-09-01), Brown et al.

Affiliated with

Also associated with

Rating

Heat induced high pressure lox pump rocket engine 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 Heat induced high pressure lox pump rocket engine cycle, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Heat induced high pressure lox pump rocket engine cycle will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-1944032