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Deolassified by authority of W A Classification Change Notices 2%- - . -.
'*.-
I
MEASUREMENTS OF PRESSURE DROP WITH NO HEAT ADDITION I
RESEARCH MEMORAN-DUMI 1
ON MOCKUP SEGMENTS OF THE GENERAL ELEC TRIG
AIR-COOLED AIRCRAFT REACTOR -
By Eldon W. Sams and Tibor I?. Nagey
Lewis Flight Propulsion Laboratory Cleveland, Ohio
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
WASHINGTON
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
RESEARCH MEMORANDUM
MEASUREMENTS OF PRESSURE DROP WITH NO HEAT ADDITION ON MOCKUP SEGMENTS
OF THl3 GENERAL ELFCTRIC AIR-COOLED AIRCRAFT REACTOR
Eldon W . Sams Aeronautical Research S c i e n t i s t
Propulsion Systems
Tibor F. Nagey Aeronautical Research s c i e n t i s t
Propulsion Systems
Approved: &- ~ e r o y V . Humble
Aeronautical Research S c i e n t i s t
Benjamin Pinkel chi&, ate rial and Thermodynamics
Research Division
-
NACA RM E52105
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
RESEARCH MEMORANDUM
MEASUREMENTS OF PRESSURE DROP W I T H NO HEAT ADDITION ON MOCKUP SEGMENTS
OF THE GENERAL ELECTRIC AIR-COOLED ALRCRAFT REACTOR
By Eldon W. Sams and Tibor F. Nagey
SUMMARY
An inves t iga t ion was conducted a t t h e NACA Leuis labora tory t o obta in pressure-drop da ta f o r flow of a i r with no heat addi t ion through mockups of two reac to r segments of t h e proposed General E l e c t r i c Company a i r c r a f t r eac to r . Pressure-drop data were obtained over a range of Reynolds numbers from 4000 t o 80,000, a i r i n l e t Mach numbers from 0.02 t o 0.40, i n l e t pressures up t o about 40 inches of mercury absolute, and ambient air temperatures. The r e s u l t s ind ica te t h a t t h e f r i c t i o n f a c t o r s , correc ted f o r entrance, vena contracta, momentum, and e x i t losses , a r e considerably higher at t h e high R repor ted f o r turbulent flow i n smooth pipes.
INTRODUCTION
An air-cooled reac to r is being b u i l t by t h e General E l e c t r i c Company f o r a i r c r a f t propulsion. The proposed reac to r i s a r i g h t c i r c u l a r cylinder approximately 5 f e e t i n diameter and 3 f e e t long, with cooling air passing a x i a l l y through the reac to r . Axially, t h e reac to r i s composed of t e n segments, each 3.5 inches long, with an a x i a l spacing of 0.125 inches between segments. Each reac to r segment is composed of a s e r i e s of con- c e n t r i c r i n g s between which a r e sandwiched t r i angu la r passages. The cooling a i r flows a x i a l l y through these t r i angu la r passages and i s allowed t o expand i n t o t h e 0.125-inch spacing between segments before flowing through t h e next annular segments. The equivalent diameter of each passage i s va r ied a x i a l l y . The mate r i a l forming t h e concentric rings and t h e tri- angular passages i s a s ta in less-s tee l -c lad uranium oxide core, t h e thickness of t h e sandwich being approximately 0.012 inch.
I n view of the complex geometry of ' the a i r - f low passages, predic t ion of t h e air pressure drop i n t h e reactor from da ta ava i l ab le i n t h e l i t e r - a t u r e i s d i f f i c u l t . I n order t o gain some ins igh t i n t o t h e pressure-drop c h a r a c t e r i s t i c s of t h e reac to r , mockups of s m a l l por t ions of t h e f i f t h and t e n t h annular r eac to r segments were t e s t e d by t h e NACA kwis laboratory.
* . * 0 . .
NACA RM ~52105
The t e s t s were conducted over a range of i n l e t Mach numbers from about 0.02 t o 0.40 wi th i n l e t p ressures up t o about 40 inches of mercury abso lu t e a t ambient a i r temperature. The range of Reynolds numbers i n v e s t i g a t e d was from about 4000 t o 80,000 f o r each of t h e t e s t s e c t i o n s . The r e s u l t s of t h e s e t e s t s are presented h e r e i n i n t h e form of curves of average h a l f - f r i c t i o n f a c t o r p l o t t e d a g a i n s t Reynolds number f o r each of t h e t e s t segments. Both measured and c a l c u l a t e d d a t a a r e a l s o presented i n t a b u l a r f o m .
EQUIPMJiTIT AND 1NTRUME.NTATION
Reactor segments. - Two reac to r segments, number 5 and number 10 i n a x i a l spacing of t h e complete reac tor , were t e s t e d ; bo th were f a b r i c a t e d of 0.012-inch shee t aluminum. Figure l ( a ) shows segment number 5, which had f i v e rows of t r i a n g u l a r passages, and f i g u r e l ( b ) shows segment number 10, which had s i x rows of t r i a n g u l a r passages.
P e r t i n e n t geometr ica l c h a r a c t e r s i t i c s f o r t h e two segments a r e pre- s en ted i n t h e fo l lowing t a b l e :
I
A i r system. - A schematic diagram of t h e t e s t s e c t i o n and experimental s e t u p used i n t h i s i n v e s t i g a t i o n i s shown i n f i g u r e 2. F igure 2 ( a ) shows I t h e g e n e r a l p ip ing layout . Serv ice a i r a t 110 pounds pe r square i nch gage I
i s passed through a f i l t e r , through a pressure- regula t ing valve, and then 1 th rcugh an o r i f i c e run, c o n s i s t i n g of an air s t r a i g h t e n e r and an A.S.M.E.- t ype f l a t - p l a t e o r i f i c e where t h e a i r f low i s measured be fo re e n t e r i n g t h e i n l e t tank. From t h e i n l e t tank, the air f lows through t h e t e s t s e c t i o n and i s discharged t o atmosphere. The o r i f i c e and t e s t - s e c t i o n i n l e t - a i r
I temperature i s measured by a thermocouple j u s t downstream of t h e o r i f i c e p l a t e .
I I
Reactor segment number
5
10
Tes t - sec t ion ins t rumenta t ion . - The r e a c t o r segment w a s mounted i n a r e c t a n g u l a r wood duct provided with a rounded en t rance s e c t i o n . Three s t a t i c p re s su re t a p s were loca t ed i n t h e wood duct a t both t h e en t rance , s e c t i o n and t h e e x i t s e c t i o n as shown i n f i g u r e 2(b) ; one t a p was l o c a t e d a t t h e bottom and one t a p on each s ide of t h e duct a t bo th sec t ions . The s t a t i c p re s su re drop was taken as the d i f f e r e n c e between t h e average i n l e t
Length ( i n . )
3.5
3.5
Width ( i n . )
3
3
Height ( i n . )
2
2
Equivalent diameter
( f t )
0.0208
0.0201
Length t o diameter
r a t i o
~ / " e
14.0
14.45
F ree f low a r e a
( s q f t )
0.0385
0.0386
Free-flow f a c t o r
0.92
9.90
N cn t-' Cn
NACA RM E52105 3
and t h e average o u t l e t measured s t a t i c p re s su re s . I n s e v e r a l cases , a s a check on t h e instrumentat ion, t h e s t a t i c p re s su re drop w a s ob ta ined by t h e use of a micromanometer connected d i r e c t l y ac ros s one i n l e t and one o u t l e t t ap . These p re s su re drops were i n good agreement wi th t h e average p re s su re -drops.
I n f i g u r e 3 a r e photographs of segment number 5 mounted i n t h e wood duct , showing t h e rounded s e c t i o n and t h e r e l a t i v e l o c a t i o n of t h e t h r e e i n l e t s t a t i c p r e s s u r e t aps .
SYMBOLS
The fo l lowing symbols a r e used i n t h i s r e p o r t :
A f ree- f low area , s q f t
D e e f f e c t i v e diameter of r e a c t o r segment, ~ A / P , f t
F f r ee - f low f a c t o r ( f ree- f low a r e a / t o t a l f r o n t a l a r e a )
( f / 2 ) ' average h a l f - f r i c t i o n f a c t o r c o r r e c t e d f o r momentum l o s s
4 ( f / 2 ) " average h a l f - f r i c t i o n f a c t o r c o r r e c t e d f o r entrance, e x i t , vena-contracta , and momentum l o s s e s
G mass v e l o c i t y (mass f l ow per u n i t c r o s s - s e c t i o n a l f r e e f l ow
a r e a ) , (t ) , m / ( s e c ) ( sq ~t )
Q a c c e l e r a t i o n due t o grav i ty , 32.2 f t / s e c 2
Kc vena-cont rac ta pressure- loss c o e f f i c i e n t
L l eng th of r e a c t o r segment, f t
P we t t ed perimeter of r eac to r segment, f t
P s t a t i c pressure , lb/sq f t
AP ' measured p re s su re drop co r rec t ed f o r momentum l o s s , lb / sq f t
Ap" measured p re s su re drop co r rec t ed f o r en t rance , e x i t , vena con t r ac t a , and momentum los ses , lb/sq f t
Aheas o v e r - a l l measured s t a t i c pressure drop a c r o s s r e a c t o r segment, lb / sq f t
. . . NACA RM E52105
. . A ~ e n ent rance p res su re drop, lb/sq f t . Apex e x i t p re s su re drop, lb /sq f t
AP, momentum pres su re drop, 1b/sq f t
vena-contracta pressure drop, %/sq f t
\ R gas cons tant f o r a i r , 53.35 f t - l b / ( l b ) ( O ~ )
R e Reynolds number, D,G/~
t s t a t i c temperature at entrance of t e s t s e c t i o n ( i n l e t - a i r tempera ture) , OR
At s t a t i c temperature d i f fe rence between ent rance and e x i t of t e s t s e c t i o n ( taken as zero f o r t h e s e t e s t s ) , OR
V ve loc i ty , f t / s ec
W air flow, lb/sec
a# A P / P ~
P ~ t / t l
)I absolu te v i s c o s i t y of a i r , lb/sec - f t
P air dens i ty , lb/cu f t
to shear ing s t r e s s defined a s average f r i c t i o n f o r c e p e r u n i t a r e a
Subscr ip ts
The fo l lowing diagra-tic sketch of t h e t e s t s e c t i o n d e f i n e s t h e s u b s c r i p t s p e r t a i n i n g t o t h e var ious s t a t i o n s
a i r f l o w
NACA RM E52105
#
RESULTS AND DISCUSSION
A l l t h e p e r t i n e n t measured and c a l c u l a t e d d a t a presented i n f i g u r e s 4 and 5 a r e t a b u l a t e d i n t a b l e s ~ ( a ) and ~ ( b ) . Values f o r en t rance l o s s and e x i t p re s su re recovery a r e not tabula ted , inasmuch as they were about t h e same o rde r of magnitude.
F r i c t i o n f a c t o r s based on measured o v e r - a l l s t a t i c p re s su re drop co r rec t ed f o r momentum l o s s . - The average h a l f - f r i c t i o n f a c t o r s ob ta ined f o r r e a c t o r segments 5 and 10 a r e shown i n f i g u r e 4, where t h e average h a l f - f r i c t i o n f a c t o r co r r ec t ed f o r momentum p res su re l o s s ( f / 2 ) ' i s p l o t t e d a g a i n s t Reynolds number D , G / ~ . The average h a l f -f r i c t i o n @
f a c t o r ( f / 2 ) ' i s based on t h e measured o v e r - a l l s t a t i c p re s su re drop co r rec t ed f o r momentum p res su re l o s s a s given i n t h e fo l lowing equat ion:
where
and
These equat ions and subsequent equat ions a r e der ived i n appendix A and a sample c a l c u l a t i o n i s shown i n appendix B. The u n i t s r e q u i r e d a r e g iven i n t h e s e c t i o n of t h e r e p o r t e n t i t l e d "Symbols".
Inc luded i n t h e f i g u r e , f o r ccnparison, i s t h e von Karman-Nikuradse l i n e ( s o l i d ) , r ep re sen t ing t h e r e l a t i o n between f r i c t i o n f a c t o r and Reynolds number f o r t u r b u l e n t f low i n smooth p ipes , t h e equat ion of which i s :
The dashed l i n e , i n t h e f i g u r e , r e p r e s e n t s t h e h a l f - f r i c t i o n f a c t o r r e l a t i o n i n t h e laminar region, t h e equat ion of which i s :
The d a t a f o r r e a c t o r segments 5 and 10 a r e not i n agreement w i th t h e r e f e r e n c e l i n e f o r t u rbu len t flow i n smooth p ipes ; t h e f r i c t i o n f a c t o r s f o r bo th r e a c t o r segments a r e h igher t han t h o s e f o r smooth p ipes . The f r i c t i o n - f a c t o r d a t a f o r each segment can, however, be w e l l r ep re sen ted
NACA RM ~52105
by a s i n g l e l i n e , t h e d a t a f a l l i n g wi th in +5 percent of a mean l i n e through t h e data f o r each r e a c t o r segment. Check p o i n t s were obta ined f o r bo th r e a c t o r segments and, a s shown i n t h e f igu re , i n d i c a t e good r e p r o d u c i b i l i t y of t h e da ta . A t t h e h ighes t Reynolds number obta ined (about 70,000), t h e f r i c t i o n f a c t o r s f o r segments 5 and 10 a r e h ighe r by about 44 and l l 0 percent , r e spec t ive ly , t h a n t h o s e g iven by t h e von Karman-Nikuradse l i n e f o r smooth p ipes .
F r i c t i o n f a c t o r s based on co r rec t ed p re s su re drops. - The average h a l f - f r i c t i o n f a c t o r s f o r r e a c t o r segments 5 and 10 are presented i n m
I+ (D
f i g u r e 5 wi th t h e same coord ina tes a s used i n f i g u r e 4. I n t h i s case , cu however, t h e average h a l f - f r i c t i o n f a c t o r s (f/2)11 a r e based on measured o v e r - a l l s t a t i c p re s su re drops which were co r r ec t ed f o r entrance, vena- con t r ac t a , momentum, and e x i t p ressure l o s s e s as g iven i n t h e fo l lowing equat ions :
Ap" 1
(f/2)" = 8m pv2,2g
where
and
No p re s su re - lo s s c o r r e c t i o n was app l i ed f o r v e l o c i t y p r o f i l e development. Both r e a c t o r segments had an L / D ~ of approximately 14, which might be t o o s h o r t a length t o cause a f u l l p r o f i l e development. Rather t han assume a f u l l o r some p a r t i a l l y developed p r o f i l e , t h i s c o r r e c t i o n w a s not included i n t h e ca l cu la t ions .
For t h e data r epor t ed here in , the use of t h e i n l e t a i r d e n s i t y i n p l ace of a i r average d e n s i t y introduced no s i g n i f i c a n t e r r o r . I n c a s e s where t h e r e would b e h e a t add i t i on i n t h e r e a c t o r segment o r longer s e c t i o n s of g r e a t e r p re s su re drop, t he c a l c u l a t i o n s should be based on an average o r some weighted a i r densi ty .
NACA RM E52105
A s i n f i g u r e 4, the f r i c t i o n f a c t o r s f o r both segments 5 and 10 f a l l above t h e reference l i n e . The correc t ions applied, however, tend t o cause the d a t a f o r both r e a c t o r segments t o approach t h e reference l i n e . I n t h i s case, t h e data f o r segments 5 and 10 a r e higher by about 26 and 95 percent than those given by t h e von Karman-Nikuradse l i n e at a Reynolds number of about 70,000.
Although t h e f r i c t i o n f a c t o r s a re somewhat higher than t h e reference l i n e , t h e slope of t h e da ta f o r both segments i s e s s e n t i a l l y t h a t of t h e reference l i n e a t Reynolds numbers below 10,000; a t Reynolds numbers g rea te r than 10,000, the slope becomes appreciably l e s s than t h a t f o r t h e smooth-pipe l i n e .
The r e s u l t s of t e s t s t o obtain air-pressure-drop d a t a with no heat addi t ion on two reac to r segments of a proposed a i r c r a f t a i r -cooled r e a c t o r can be summarized a s follows:
1. The measured average h a l f - f r i c t i o n f a c t o r s (correc ted only f o r momentum) obtained f o r each r e a c t o r segment can be well represented by a s i n g l e l i n e throughout t h e range of Reynolds numbers inves t igated . However, t h e l i n e s a r e not i n agreement i n magnitude o r s lope wi th t h e von Karman-Nikuradse reference line representing turbulent flow i n smooth pipes . The slopes of t h e l i n e s through t h e da ta a r e e s s e n t i a l l y t h e same a s t h e reference l i n e at Reynolds numbers below 10,000, but become con- s ide rab ly l e s s a t the higher Reynolds numbers. The f r i c t i o n f a c t o r s f o r segments 5 and 10 a re higher than the reference l i n e by about 44 and U 0 percent , respectively, a t a Reynolds number of about 70,000.
2. Correct ion of t h e measured pressure drop far momentum, entrance, e x i t , and vena-contracts losses tends t o b r i n g the f r i c t i o n f a c t o r f o r both segments nearer t o the reference l i n e . However, t h e s lope of the l i n e s at t h e higher Reynolds numbers is s t i l l appreciably l e s s than t h a t f o r t h e smooth-pipe l i n e . The corrected f r i c t i o n f a c t o r s f o r segments 5 and 10 a r e higher than t h e reference l i n e by about 26 and 95 percent, respect ively , a t a Reynolds number of about 70,000.
3. The displacement of t h e curves above t h e reference l i n e would i n d i c a t e t h a t some re-evaluation of the e f f e c t i v e diameter, or inc lus ion of o the r parameters pe r t inen t t o t h e geometry of t h e segment would be required f o r cor re la t ion of t h e da ta f o r both segments.
Lewis F l i g h t Propulsion Laboratory National Advisory Committee f o r Aeronautics
Cleveland, Ohio, August 24, 1952
a*. .- NACA RM E52105
APPENDIX A - DERIVATION OF THE PRESSURE DROP EQUATIONS
A schematic diagrain of the test sec t ion showing t he various s t a t i ons i s given below:
a i r flow d
I I
The f r i c t i o n fac to r can be defined by t he following general equation:
where TO is t he shearing s t r e s s defined as t he average f r i c t i o n fo rce per u n i t area.
Equation (1) can a l so be wri t ten as:
Ap " Ap" ( f /2)" = a
8 L/D, p ~ 2 / 2 g 8 L/D, ~ ~ / 2 ~ ~
The following equation defines the Ap" of equation ( 2 )
The f r i c t i o n f ac to r a s calculated by equations (2 ) and ( 3 ) does not represent t h e exact value of t he r a t i o of t he shearing stress at t h e w a l l t o t h e dynamic pressure of t he stream, inasmuch a s no pressure-loss correct ion was applied t o equation ( 3 ) t o account f o r ve loc i ty p r o f i l e development. The reac to r segments t e s ted had an L/D, of approximately 1 4 , which were f e l t t o be too shor t a length f o r full p r o f i l e development. Rather than assume a f u l l or some p a r t i a l l y developed prof i l e , t h i s cor rec t ion w a s not applied i n t he calculat ions.
The various terms of equation (3) a r e derived as follows:
Entrance pressure loss , Ape,. - Losses of mechanical energy occur
i n t h e flow stream i n the region of contract ion from s t a t i o n (1) t o ( 2 ) . The genera l energy equation between these s t a t i o n s can be wr i t t en :
Assuming no f r i c t i o n and incompressibi l i ty of the f l u i d , t h e follow- i n g r e l a t i o n s apply:
PI = P2
and
Hence,
where A ~ / A ~ i s defined as t h e free-flow f a c t o r F, and rewr i t ing equation ( 5 ) i n terms of mass veloci ty i n t h e t e s t sec t ion r e s u l t s i n :
Ex i t r ega in Apex. - The momentum change between s t a t i o n s (3) and (4 )
where an expansion occurs can be s t a t e d as follows:
Assuming incompress ib i l i ty , equation ( 7 ) can be wr i t t en as :
A s before, % / A ~ = F and A ~ / A ~ = F; the re fo re ,
. . NACA
I n o rde r t o w r i t e equat ion (9) i n terms of en t rance cond i t i ons a t s t a t i o n (1) t h e fo l lowing was assumed:
I n t h i s case t h e Ap used i n equat ion (10) i s an approximation i n t h a t t h e va lue f o r Aheas was used i n o rde r t o avoid a t r i a l - a n d - e r r o r s o l u t i o n . The e r r o r i ncu r red by t h i s assumption i s n e g l i g i b l e .
Equation ( 9 ) can be r e w r i t t e n with t h e a i d of equat ion (10) as fo l lows :
where
and
I n t h e s e p a r t i c u l a r - tes t s , wi th no h e a t add i t i on , f3 was, of course , always equa l t o zero.
T
Vena-contracta pressure l o s s Apvc. - The vena-contracta p re s su re
l o s s was taken as a f a c t o r K, times t h e v e l o c i t y head of t h e s t ream i n t h e t e s t s e c t i o n s and i s given by t h e fo l lowing equat ion:
+
where Kc i s a func t ion of on ly the f r ee - f low f a c t o r of t h e t e s t s e c t i o n . Values of K, a r e g iven i n r e f e rence 1 p l o t t e d aga ins t f r ee - f low f a c t o r .
Momentum p res su re l o s s Apm. - Using t h e gene ra l momentum equat ion and assuming p1 = P2 r e s u l t i n the fo l lowing equat ion;
. . a .
NACA RM ~52105 . . .
Rewriting equation (15) by means of equations ( l o ) , (12) and (13) gives :
I n the calcula t ions just described, t h e t o t a l and s t a t i c tempera- t u r e s were assumed t o be the s e e . Several check calcula t ions which were made a t the highest flow conditions showed t h a t t h i s assumption gave negl ig ible e r ro r . With heat addit ion and at high flow r a t e s t h i s assumption i s obviously not t o be expected t o remain va l id .
e.. NACA RM E52105
APPENDIX B - SAMFm CALCULATION - RUN NUMBER 1 FOR
R~ACTOR SEGMENT NUMBER 5
Effect ive diameter, De = 0.0208 f t
Free-flow area, A = 0.0385 f t 2
Corrected a i r flow, U = 1.712 lb/sec = 6162 lb/hr
Absolute v i scos i ty of a i r , p ( a t 506' R ) = 0.0426 lb/hr-ft
I n l e t - a i r temperature = 506' R
I n l e t - a i r pressure = 39.66 in . Hg abs. = 2804 lb/sq f t abs
Free-flow fac tor , F = 0.92
NACA RM E52105 e m em* . where Kc = 0.5 (from re fe rence 1)
REFERENCE
1. McAdams, William, H. : Heat Transmission. 2nd ed., McGraw-Hill Book Co., Inc . , ( ~ e w York and ond don), 1942, p. 122.
TABLE I - MEASURED AND CALCULATED DATA FOR REACTOR SEGMENT ISOTHERMAL PRESSURE DROP TESTS
( a ) 3ea:tor seg-.er,t nurker 5. Free-flaw area. 0.2345 sq-are fee:; f ree- f lcw f a c t o r 0.32; eqiilvale7.t diaz.eteF 3,, 2.3235 f e e t ; ler.gtP. t o dla-.eter r a t i o L/3e, 14.2.
-
1
2
3
1.712
1.673
1.644
h a l f - f r i c t i o n
f a c t o ~ (f/2)
Aeasured pr+ssure
drop AP
( lb /sq f t )
Calcula ted c o n t r a c t a pres-
s u r e drop
APvc (1b/sq f t )
xa lcula ted ms2cntun pressure
drop APm
( lb /sg f t )
I n l e t a i r pressure
(lb/sq f t abs)
v e n a - C o r r e c t e z c o r r e c t e d half-
f r i c t i o r , f a c t y a ( f / 2 )
I n l e t a l r temperature
(OR)
Run
506
516
508
4 1.515 i 5 1.493
6 1.433 7 1.299 8 1.283
9 ' 1.134
10 / 1.043
~ 1 r Ilow ( l b / s e c )
C u r r e c t e d f o r monentum, .ena c o n t r a c t a , e r t r a r c e , and e x i t _ O S S ~ S .
514
538
507
512 511
508
516
508
520 510
518
512
512 518
522
512
518 508
11
12 1 3
14
15
16 17
18
19
20 21
Reynolds number
2804
2768
2732
.868
,834 .730
.721
.689
.651
.651
.604
.590
.562
.507
I n l e t a l r Mach
number
2659
2632
2573 2514 2500
2389
2369.
2252
2267 2254
2210
2210
2213 2184
2181
2207
2156 2127
78,300
75,500
74,900
22 1 .478 23 / .420
68,500
68,000
65,400 58,900 58,303
51,730
47,100
39,500
37,400
33,300
32,400
31,200
29,500 29,300
27,000
26,700
25,200 23,100
14.8 I 11.7 7.85
8.11 5.67 4.89
4.78
3.93 3.43
3.05
2.91
2.29 2.00 2.00 1.04
.749
.653
512 / 2176 ' 2 1 , 7 J O ! . I 4 1
518 2120 1 1 8 , 9 0 0 .I28 24
25 26 27
28 29
30
31
32
33 34 35 36
37
38
0.339
.386
.384
.344
.344
.288
.263
.255
.234
.224
.203
.202
.I82
. I62
.162
.I11
.093
.080
147
144
140
.366
.362
.355
.331
.328
.303
.283
.246 ,
.237
.237
.210
.200
.I88
. I92
.I79
. I71
.I68 5 2
:corrected f o r
512
526 517 523
524 522 514
524
522
518 522 524 524
524
524
119
117
110 92.1 88.4
73.2
63.0
44.5
42.5 31.7
32.2
28.7
26.0 26.3
23.5
21.5
19 .3 16 .5
momentum l o s s .
2148
2116 2095 2091
2090 2089 2132
2082
2084
2081 2079 2081 2076
2074
2074
15,600 1 . l o 3
15,300 13,000 11,700
11,400 10,400 10,100
3.100
9,000
8,200
7,300 7.200 4.900
4,100
3,600
. l o 3
.089
.081
.079
.072
.067
.063
.063
.056
.050
.050
.035
.029
.025
- Run
TABLE I - Concluded. MEASURED AND CALCULATED DATA FOR REACTOR SEGMENT ISOTHERMAL PRESSURE DROP TESTS Zi' (b) Reactor segment number 10. Free-flow area, 0.0386 square feet; free flow factor, 0.90;
equivalent diameter De, 0.0201 feet; length to diameter ratio L/D,, 14.45.
Air flow (lb/sec)
(lb/sq ft abs)
a Corrected for momentum loss.
- - - - - - -
Reynolds Inlet air n3mber Mach
nuntber
Measured pressure drop AP
lb/sq ft)
Calculated mome n turn pxssure drop APm
f lb/sq f t
Calculated vena contracta pres-
sure drop APvc
( lb/sq f t
Corrected for momentum, vena contracta, entrants, and exit losses.
(a) Number 5 reactor segment.
Figure 1. - Photographs of reactor-segment mockups.
(b) Number 10 reactor segment.
Figure 1. - Concluded. Photographs of reactor-segment mockups.
Air supply
r Pressure Filter, / regulating
vn1 vr
'-+--I r Valve
/ / Wood duct
Flat plate Inlet tank rice \
( a ) General piping layout. Thermocouple Test Measured t static - - - pressure
(b) Installation and ins trunentation of reactor sement.
piare 2 - - Schematic diagram of experimental setup.
section
Figure 3. - Photograph showing instal lat ion of number 5 reactor segment, rounded entrance, and location of pressure taps.
Number "10 ( t a i l e d symbols i n d i c a t e
F igu re 4 . - Average h a l f - f r i c t i o n f a c t o r ( f / 2 ) ' p l o t t e d a g a i n s t Reynolds number f o r r e a c t o r se-ents numbers 5 and 10. Fr ic t , ion f a c t o r c o r r e c t e d f o r momeritum l o s s .
0 Number 5 0 Number 1 0
( t a i l e d , symbols i n d i c a t e check p o i n t s ) -- --- Laminar f l ow
Von Karman-Nikarad.se
hLl cd k Q,
4
/ *001400 GOO 900 1000
1 2 000 4000 6000 10,000 20,000
-557 40,000 60,000 100,000 200,000
DeG Reynolds number, - CI
Figu re 5 . - Average h a l f - f r i c t i o n f a c t o r ( f / 2 ) l t p l o t t e d a g a i n s t Reynglds number f o r r e a c t o r segment numbers 5 and 10. F r i c t i o n f a c t o r c o r r e c t e d f o r momentum, vena c o n t r a c t a , en t r ance , and e x i t l o s s e s .
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