Circular manifold with tangential orifices at the inner circumference provides for the vapor constituent of a vaporized cryogenic propellant to enter a rocket combustion chamber before the liquid constituent. The vapor is separated from the liquid by centrifugal action and precedes it into the chamber through carefully positioned orifices

Baker, D. I.

English

NASA Technical Reports Server

February 1966
	 Brief 66-10052 
NASA TECH BRIEF H 
NASA Tech Briefs are issued to summarize specific innovations derived from the U. S. space 
program and to encourage their commercial application. Copies are available to the public from 
the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151. 
Combustion Chamber Inlet Manifold Separates Vapor from Liquid 
The problem: 
To have the vapor constituent of a pressurized cry-
ogenic propellant enter a rocket combustion chamber 
before the liquid constituent. 
The solution: 
A circular manifold with tangential orifices at the 
inner circumference from which the relatively lighter 
vapor, separated from the liquid as the result of 
centrifugal action, flows ahead of the liquid into the 
combustion chamber. As the propellant flows around 
the circular manifold, the much heavier liquid compo-
nent is centrifugally forced to the outer circumference 
of the manifold, while the lighter vapor is confined to 
an inner path. The manifold and the combustion cham-
ber orifices are so positioned that the separated vapor 
will precede the liquid into the chamber. 
Notes: 
1. With modifications, this device can be used in the 
food, petrochemical, and pharmaceutical industries 
to effect a separation between liquid and vapor, or 
between two immiscible liquids.
2. Implementation of this concept in a device for sep-
arating liquid from gaseous nitrogen is described in 
NASA Tech Brief B63-1025l, June 1964. As of date 
of publication of this Tech Brief neither a model 
nor a prototype has been constructed. Inquiries 
may also be directed to: 
Technology Utilization Officer 
Marshall Space Flight Center 
Huntsville, Alabama, 35812 
Reference: B66-10052 
Patent status: 
No patent action is contemplated by NASA. 
Source: Dwight I. Baker 
of North American Aviation, Inc., 
under contract to 
Marshall Space Flight Center 
(M-FS-53 I) 
Category 05 
This document was prepared under the sponsorship of the National 
Aeronautics and Space Administration. Neither the United States 
Government nor any person acting on behalf of the United States
Government assumes any liability resulting from the use of the 
information contained in this document, or warrants that such use 
will be free from privately owned rights.
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Combustion chamber inlet manifold separates vapor from liquid

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