Vapor-liquid separator design with vapor driven pump for separated liquid pumping for application in propellant transfe

Ward, W. D.

English

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NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 
WASIIINGTON. D C ?054b 
3 
TO : USI/Scientific & Technical Information Division 
Attention: Miss Winnie M, Morgan 
FROM: GP/Office of Assistant General 
Counsel for Patent Matters 
SUBJECT: Announcement of NASA-Owned 
U.S. Patents in STAR 
In accordance with the procedures contained in the Code GP 
to Code US1 memorandum on this subject, dated June 8, 1970, 
the attached NASA-owned U.S.  patent is being forwarded for 
abstracting and announcement in NASA STAR, 
The following information is provided: 
U,S. Patent No. 
Corporate Source 
Supplementary 
Corporate Source 
NASA Patent Case No.: 
Please note that this patent covers an invention made by an 
employee of a NASA contractor. Pursuant to Section 305(a) of 
the National Aeronautics and Space Act, the name of the 
Administrator of NASA appears on the first page of the patent; 
however, the name of the actual inventor (author) appears at 
the heading of Column No, 1 of the Specification, following the 
words 'I. e e with respect to an invention of, e 
Gayle Parker 
Enclosure: 
Copy of Patent 
https://ntrs.nasa.gov/search.jsp?R=19710013547 2020-03-17T02:51:43+00:00Z
JAMES 
ISTRATOR OF THE L AERON 
A N D  SPACE A ATION 
Filed Dec. 28, 1966 
VAPOR-LIQUID SEPARATOR 
,49 
I 
I 1  
LJ 
BY 
w 
.. 
atent ate 
Aero- 
an in- 
5 
pellant tanks of space vehicles by separating the vapor 
formed during the vaporization of a cryogenic fluid such 
as to vent the vapor overboard and return the liquid from 
the separating unit to the tank. 
These and other objects and advantages of the inven- 
tion will become apparent upon reference to the following 
specification, attendant claims and drawings: 
3,397,512 
~ A ~ ~ ~ - ~ ~ Q ~ ~  S E ~ ~ A ~ ~  
James E. National 
IlZtUtiCS respect to 
~ e ~ ~ Q ~  Ala. 
@5,518 
Briefly described, the invention comprises a separation 
chamber having inlet swirl nozzles at one end thereof 
through which the fluid being separated enters and ex- 
rating vapor from liquid of a hetero- pands within the separation chamber imparting a cen- 
geneous vapor-liquid fluid mixture ranging from 100% trifugal action to the incoming fluid and causing a portion 
liquid to gravity environment of the incoming fluid to vaporize. The end the separation 
wherein the separated vapor drives a pump that forces the chamber opposite the swirl nozzles merges into a liquid 
separated liquid to the desired location thus avoiding the 15 collector manifold and a vapor venting conduit, the lat- 
need for an to drive the pump. ter receiving the vapor occupying the central region of the 
The heterogeneous fluid is expanded and swirled in a sep swirl pattern and the liquid collector manifold collecting 
aration chamber and a vapor exhaust conduit receives the the vapor from the outer region of the swirl pattern. The 
vapor at central region of the swirl pattern while vapor emergiW from the separation chamber through the 
the liquid at the outer region of the swirl pattern is col- 20 vapor venting conduit is utilized to energize a pump that 
lected in a liquid collection manifold and pumped to the forces the liquid from the liquid collector manifold into the propellant tank. 
FIGURE 1 is an elevational view of a rocket having a desired location. 
stage thereof equipped with a vapor-liquid separator in- 
formance of work under a NASA contract and is subject FIGURE 2 is a cross-sectional view of the vapor-liquid 
to the provisions Of Section 305 Of the National Aero- separator indicated in FIGURE 1 with the top of the pro- 
nautics and Space Act of 1958, Public Law 85-568 (72 pellant tank of the rocket stage indicated in phantom line; 
Stat. 435; 42 U.S.C. 2457). FIGURE 3 is a cross-sectional view taken along line 
and more particularly to a device for separating vapor and Referring to FIGURE 1 therein is shown a rocket B 
liquid in a heterogeneous fluid mixture ranging from comprising a stage 11 equipped with a vapor-liquid sep- 
100% liquid to  100% vapor. arator 12 at  the top thereof. As shown in FIGURE 2, 
In the development and operation of space vehicles, the separator 12 comprises a separation chamber 13 being 
cryogenic fluids, such as liquid oxygen and liquid hydro- 35 circular in cross-section and closed at one end 14 with 
gen, are used as propellants, and these propellants while the opposite end 15 projecting into a liquid collection 
in propellant tanks of a rocket in space absorb heat, taus- manifold B7. A top 19 of a propellant tank of the stage 
ing the liquid to vaporize thereby increasing pressure in 11 is indicated in phantom line. 
the tank. Unless the vapor is vented from the propellant Joined to the closed end 14 of the separation chamber 
tanks the tank will eventually become over-pressurized. 40 13 is concentric relation thereto is a conical guide vane 21 
Under conditions of very low or zero gravity, such as having its converging end directed toward the liquid col- 
exists in space, the vapor formed in the Propellants Will lection manifold 17. Swirl nozzles 23 and 25 (FIGURE 3)  
not readily rise and separate from the liquid; therefore, are located near the closed end 14 of the separation cham- 
a heterogeneous fluid mixture of vapor and liquid forms, ber 13, entering the chamber tangentially to  the circular 
and it is required that a means be incorporated in the pro- 45 wall thereof. Near the other end of the separation cham- 
pellant tanks for separating the vapor from the liquid and ber 13 is the open end of a vapor venting conduit 27 that 
venting the vapor overboard while returning the liquid is positioned concentrically with the chamber and extends 
to the tanks. Moreover, the mixture of vapor to liquid through the wall of the liquid collection manifold before 
within the propellant tanks will be changing constantly turning upwardly through the top 19 of the propellant tank 
making it necessary to effect separation of the vapor from 50 and ultimately to the outside of the rocket 10. 
the liquid at all mixtures ranging from 100% liquid to Intersecting the vapor exhaust conduit 24 are the blades 
100% vapor. of a turbine 31 that turns in a slot 33 provided in the con- 
Separating devices of several types have been developed duit 27 and in an enclosure 35 that merges with the c m -  
for a variety of purposes such as separating liquid droplets duit 27. The turbine 331 is connected to a verically dis- 
from a gas stream, as in steam power plants, separating 55 posed shaft 37 that extends into a housing 39 for an 
particles from a gas and separating relatively heavy liquid impeller pump 41 which is connected to the shaft 37. The 
from relatively light liquid of a heterogeneous mixture. housing 39 communicates with a conduit 43 that returns 
These previous separations, however, have the disadvan- liquid from the liquid collection mani€old into the tank. 
tage of not being capable of operating when the fluid being The shaft 37 turns in bearings 45 supported by brackets 
processed is 100% liquid Or near 100% liquid at  the inlets 60 47, which may be secured to a mounting bracket 49. 
because no vapor is available for energizing the separator opration of the separator, a cryogenic propellant, 
location. within the propellant tank of perhaps 20 p.s.i. and would Accordingly, it is a general object of the present inven- enter the swirl nozzles 23 and 25 of the separation tion to provide an improved separating device. 
A specific object of the invention is to provide 65 chamber 13. Due to the relatively low pressure in the 
vapor in a 
power 
The invention described herein was made in the Per- 25 dicated in phantom line; 
This invention relates generally to separating devices 30 2-2 of FIGURE 2. 
pump for pumping the separated liquid to the desired such as hydrogen, would typically be under pressure 
a centrifugal separator vapor from liquid under near zero 
or zero gravity conditions which separator will effect sep- 
aration of a heterogeneous fluid lnixture rag ing  from 
100% liquid to 100% vapor. 
Another object of the invention is to provide a device 
for preventing excessive pressure from developing in pro- 
separation chamber the fluid enters the separation 
chamber rapidly and subsequently expands Producing a 
degree of vaporization of the fluid regardless of its vapor- 
70 liquid mixture at entry. The swirl nozzles and the conical 
guide vane 21 impart a centrifugal action to the fluid 
within the separation chamber 13 causing the vapor to 
3,397,512 
4 
concentrate in the center the swirl pattern and the 
heavier liquid to concentrate in the outer region of the 
swirl pattern. 
27, the open end of which is in the center of the separa- 5 
tion chamber and the liquid is collected in the liquid 
collection manifold 17. As the vapor moves out of the 
separation chamber through the exhaust conduit 27 it 
impinges on the turbine 31 turning the turbine which in 
turn drives the impeller pump 4% through the shaft 37. 10 
The action of the pump 4P forces the liquid out of the 
liquid collection manifold and back into the tank through 
the conduit 43. The liquid that is returned to the tank will 
have been subcooled due to the expansion and vaporiza- 
tion occurring in the separator. 
Since the separator always produces sufficient vapor 
to energize the turbine 31 even though the incoming fluid 
may be 100% liquid, no external power source for start- 
ing or otherwise driving the pump 41 is required. 
Obviously, many modifications and variations of the 20 
present invention are possible in the light of the above 
teachings. It is therefore, to be understood that within the 
scope of the appended claims the invention may be 
practiced other than as specifically described. 
(e) a vapor conduit for conducting vapor out of said 
(f) a portion of said vapor conduit extending through 
The vapor is collected into the vapor exhaust conduit said manifold and into said open end of said 
chamber; 
(8) said portion having an open end concentrically 
disposed within said chamber; 
(h) the cross sectional diameter of said chamber wall 
exceeding the cross sectional diameter of said con- 
duit portion; 
(i) pump means for pumping liquid from said mani- 
fold to a desired location; 
(j) said pump means including a drive means and an 
impeller with a housing enclosing said impeller; 
(k) said drive means including means intersecting said 
vapor conduit whereby vapor will impinge on said 
intersecting means and energize said drive means; 
(1) a liquid conducting conduit extending between said 
manifold and said impeller housing. 
2. The invention as defined in claim 1 wherein said 
means for imparting a whirling motion includes a conical 
guide vane adjacent said inlet nozzle. 
3. The invention as defined in claim P wherein said 
means intersecting said vapor conduit comprises a turbine, 
25 a drive shaft extending between said turbine and said 
impe11er. 
separation chamber; 
15 
What is claimed is: 
I. A zero gravity vapor-liquid separator comprising: 
(a) a separation chamber having a closed end and an efeerences Cited 
open end and a wall of circular cross section be- UNITED STATES PATENTS 
tween said ends; 3o 630,024 8/1899 Baker _ _ _ _ _ _ _ _ - _ _ _ _  5 5 4 0 4 X  
( b )  means for imparting a whirling motion to a fluid 2,757,582 8/1956 Freeman et al. _ _ _ _ _ _  55-205 X 
within said separation chamber; 3,107,988 10/1963 Taylor et al. _ _ _ _ _ _ _ _  55-269 X 
(c) a tangential fluid inlet in said chamber wall near 3,161,490 12/1964 Dudek _ _ _ _ _ _ _ _ _ _ _ _ _ _  55-205 
said closed end; 3,257,780 611966 Webb _ _ _ _ _ _ _ _ _ _ _ _  5 5 4 0 4  X 
(d) a liquid collection manifold having a cross sec- 35 3,2'09,518 1011965 Spulgis et al. _ _ _ _ _ _  55-404 X 
tional diameter greater than said chamber wall and 
receiving said open end of said chamber with said 
open end opening into the interior of said manifold; 
RUBEN F*EDMANy Primary Examiner. 
R. W. BURKS, Assistant Examiner. 


Vapor liquid separator Patent

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