Rocket engine nozzle having a notched diverging portion

Details Rocket engine nozzle having a notched diverging portion Rocket engine nozzle having a notched diverging portion

1994-05-25

1995-09-19

Thorpe, Timothy S.

Power plants

Internal combustion engine with treatment or handling of...

Material from exhaust structure fed to engine intake

23926517, F02K 100

Patent

active

054507200

ABSTRACT:
In a rocket engine nozzle comprising: a converging portion that receives the gases produced in a combustion chamber; a throat of small section; and a diverging portion connected to the nozzle throat; the diverging portion includes a set of downstream notches running longitudinally from its downstream end and uniformly distributed around the entire periphery of the diverging portion, the total width of all of the notches within any section representing about 1% to 6% of the periphery of the diverging portion. The notches serve to avoid having a jet separation line that is irregular and unstable, and they facilitate matching the diverging portion to ambient conditions that vary in flight.

REFERENCES:
patent: 2395114 (1946-02-01), Goddard
patent: 2875577 (1959-03-01), Odenkirchen
patent: 3304722 (1967-02-01), Culpepper
patent: 3354645 (1967-11-01), Hsia
patent: 3925982 (1975-12-01), Mueller
patent: 4707981 (1987-11-01), Wagner
Liepmann et al., Elements of Gas Dynamics, New York, Wiley & Sons, Inc., 1967. pp. 124-132.

Affiliated with

Also associated with

Rating

Rocket engine nozzle having a notched diverging portion does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Rocket engine nozzle having a notched diverging portion, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Rocket engine nozzle having a notched diverging portion will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-1821681