national advisory committee for aeronautics/67531/metadc62451/m... · advance restricted report...
TRANSCRIPT
..
-2
ARR fiO. “E4H22
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
WARTIME Iuwolu’ORIGINALLY ISSUED
August 1944 asAdvance Restricted Report E4H22
PERFORMANCE TESTS OF NACA TYPE A FINNED-TUBE
EXHAUST HEAT EXCHANGER
By J. George Rater and S. V. Manson
Aircraft Engine Research LaboratoryCleveland, Ohio
NACA
NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution ofadvance research results to an authorized group requiring them for the war effort. They were pre-viously held under a security status but are now unclasstiied. Some of these reports were not tech-nically edited. AU have been reproduced without change in order to expedite general distribution.
E -97 —
Il. .
... .
31176013647322. . . —
NACA ARR NO ● 9H22
}lATIuI;~L KDVIWIW COM.TITEE
,. .,, .-— ..
AIWWCE RHi’RICTED
FOR A.ERCX:.WTICS
-...,- .-.-----..
R= ORT
FEMWWANCE TllWS OF MACA TYF’E4 J?IhlWWTTJBE
EXHAUST i~T EXCHANGER
By J. George Reuter and S. V. %nson
The exhnust-pns heat excnmlvw is of’current int.~restac amwns nsl only of prov”i-linpheat-d air for aircraft,de-iclnq andcabin Iwatinq but alSC)of renderim~?t,%=~vlkaust.~1.esinvisib].eby reducing its tmprntu r-. In the past few ,ysars~ variety ofdesiqns have been constructed ~..iti;stwllarfle~vunder I&w sJmn-sorship of the NACA. (bee refmvmcen 1 to 6.) Tne success ofmany of these invest,iflations;IascreateA a grtin?~ interest inthe f.;meralimprovcxwnt of the exh.aust=)ys heat exchan~er.
The problem of the desi,rnof an ~xhaust-heqt exchanger 1slargely a question of .wlectinv a care str~ctnre that Ccmbinus
mcll m No. E4H22 3
The tubes era in st~red az’ran@mellt wlt?l exhaust-gas f 19Wacross seven bmks of n5ne tubes each. These tubes are Insertedinto punche~ holes -in the header. plates and qre f leqe=@Lded atthe @met ion tips, as shown in f @zres 1 and 2. Thik construction-shoul.dprovide flexibllity. The tube-end welds are exposed to thecoolti~air flow and are shielded from the exhaust -s. Thisposltlon~of extended surface and nlded Joints should favor thedurabllity of the ex-er.
The might of this heat exohanger, aO received fmnn the fac-tory and as shown ia figure 2J was 25.5 pounds lncludl~ flangesand rib- strengthened plates cover-. the no-flow faoes. Beforethe exchmger was mounted for test-, the flang~ was changedto provide a more cofivenlentand leak-proof Installation, Thewoi@t might be reducsd lJythe use of thlnrxw metal for tube WCLUSand fIna, but In this connection there is a question of drrabilttythat requires further lnve~ti~t Ion.
!Iv2 WmIe
A dlagmcu of the test setup Is ehown h fi.~e 3, The testoq~’ipmentconsisted ossentidly of an cxhaust-gas prcducorj theheat-exchang~r test unit, dwcting} flouceters, and teqe~ature- andp.resmre-moasuri~ Instruments, Both the cooltiJgalr and the airroqulmd for comlm.at1on wore otta~d from the laboratory cacbustion-air supply; t% roepecii-ieflows were controlled by pressuro-regulntedbutterfl; velvos. !iZtecooli.w a:r flowed through the tubes and theorhanst Gas flowed across the tubes of the exchanger. Flow rateswore mec6urod upatroam from t]l~G.xchangerby means of calibrated thti-plate orifices installed escmdlng to A.S.M,E. speclficatdons.
Entrance and e.xltflui~ temperature were meamred by %ermo-couples placed QCIWSS each flow oection at distances from the corefaces as shown by figuw 4. Cooling-air teqeratu-es were indi-cated on a self-bakncing, direct-readlxg pcteaticmmter; exhaust-gas temperatures were Indicated on a manually balanced potontiazeter.Tn the exhaust stream wero quadruple-shlolded chromel-alumelthermo-COUP1OS, three at ths entrance of the heat exchanger and three atthe exit. One of each set of three was a General.Electric thermo-couple; tho other two wore constricted at this laboratory with aSPH ehlold of four turns. The rGadinge obtahed from tho threethermocouples at each station were h god agreement,. Unehieldodiron-conetantanthermocouples were used In the coolfn&alr stream,two at the upstream sldo of the exchanger and sets of six plaooddla@naUy across each of two sections downstream from the exqer.
■ � 11
.—— adEmam+gas f lo’n Cooling-air flow Range of gas-inletrats, We rate, Wa t~.%r~tur=s (in sh?J6
@.@J-- . . . . ..-lW,M). b. . . . . . ..- . . . . . . . . . - of approximatdy 200 F(%’)—. ——
3590 3500 1100 to UjmO5400 !300to l~oo7200 90G to UjUO9300 900 to I.gso
54(-)() I:% ?~o to lyw1- l(mo to U@O
7!@0 ~yj La ].dj~
9450 e.y to 13q).—— .. —-— .—72w 570LJ ~~fj to 1$~
q,$J Ilcu to 1$0171~’.Y) lC)OOto Iq)op!@o ‘YM to lqll
..—— — .-—- — .—- ———
AP
specif1c hnst,at const.arltprfi.ssl~r[=,(Rt’1)/(lb)(%’)
no-flow lew@h, (in.)
.M tswpera.turechange cf fl’Jidacross exchmlger,(%)
6TCI temperature chance of exhaust gas comsuted from heat bahnce
molin~ effect.iwmss of exchzmger,
r
I ATe1
1~)— - (%)en
en 1
:. ATa 1—.——
1‘(Tej - (Ta)
en en1
I?AC.4!lKRNo~ I?14.H22
—..
7
and
l’he syecifie heat of exhaust gas ~as assumed the mm as that ofRir because of the ext.reneleanness of the exhaust-gasmixtures.An rxxct?ssof heat absorb~d by the cooling air over that dissipatedby the exhaust gas at the hi~her heat flows is shown in the figmre.The cause of this discre~ancy is probqbQ in the e.xkust+as stream,and for this reason the thermal performance has been evalu~ted frommeasurements on the cooling-air side.
[n figure 6 is shown the best output of the heat [email protected] ccmlimy-air flow for exhaust-gas flows of Z$410,5~@U, and 7200pounds per hour and for an entr-ante-tmperaturediffsrmce of l~@ F. ‘!hes~valnas of heat output are th9 valuesof he~t.Rbsorbeclby the cookhg air a:;computed frcrntest dataobtainwl at an zxhaust-~as entr,amcct~:m!~eratureof about l~W” Fcorrectw.1to an ent,rance-tempe.r&tnrcdl.fferenceof.17Q0 l?. Thecorrection w= mad~ by muans of the following rul?t.ion:
Ths cc)rrq,onding temper~turo rise of the cooling air is shown infiqnre 7. Examination of fipures 6 and 7 k!ic?t~s a cooling-airt~~l,ara?.urerisa of bo~ F and a heat output of 2~3,UO0 Btu perhour for an exhaust-gas flow rate d 7.200 pounds per hcmr (corre-s},onclingto enfiineopcrntion at approximately 1000 hp) and for acoolinr+ir flow of 3000 IJounds per hour. }.tthe same coolinpai.rflowbut with an axhaust.-gasflow of 4000 pounds per hour thecooljn~-air temperature rise is j~OO F and the heat output is255,000 Btm per hour.
The cooling and heating effectiveness of the exchanger as afunction of the fluid flows is shown in figure 8. The heatingeffectiveness is defined as
ATana =
(Te)M - (T=),n
Because thz temperature mcasuremsnts on the cooljn~-air side areconsidered more reliable thm thosa on the exhaust-qas side, thecoolin~ effectiveness is Ikfjnsclas
. ,...
where
Tb+ en.m?ssion for LIef is obtained frcm the he~t-halmce equa-tian,
Te(cp) 4Te1 ‘~a(c,3)a ATae
rreater than unity for nani~ot.hermalflow, because the density Of theps increases when it flows through the exch.mger. Figure 11show a greater sc~tt.erof the test data than ~h~wn in fiemre 9
-—- —.. .—-. — . . . . .. . .— -.. . .-. —-. —
f m Iim cooling air~ furthermore the exaonent 2.1 of We, which~Jasfcund to best.fit the c?qta,is ~reatm than theory would infli-cate. Ko definite explanation can.be offered for these conditions;hmwwsr, during the tests it was”noted that under some test condi-tions a whistling sound was produced by the flow of the ex!~au~t;3s acros3 tk exc%n~er tubes. TMs cmc!ition was attended byerrzt.tcbehavior of the .manumetersthat meamred the pressure drop.liot,~it]lstandjngthe fore~min~ considerations,it c,anhe stat.cd thattk curves of figure 12 represent the test values of pressure clroy-.tithiuCm< inch of water.
Althou~h t!lethermal end the preeoare-dro~jperformances shownin fi:=mres6, 7, 8, W, ,md 12 are given for the test exchanflm‘xit,la no-flow len~~h of 12_7~ ~nches, the curv~s are, of cuursn,a(J,lljc~bleto my nu-flex ler.gthof an otherwise identical e.xcllmerU the heat out~ut %(?st wd the fl.liriflows (’;?e) aud
~~~t
(1)
— . .. . . .
RACA MR Uo ● dJH22 “ 11
10. From it~m 6 and 9:
“ ,’.
n. A
.-. . r--- -“. .- . . . . . . . . . ‘b”2-‘--ii~i- if hat trial)-—..-
Apa =0s516
second approx3mat.ionof o~om cm now be obtatiecl fromit,tmsh, j, 7, and 10 md equation (1).
0.~67 (second trial)—
115+ 460
12, From it:m.s1 md 11 arclfikpre 10:
!1.3‘% = I-J[!1<,-——= ~1.3(wc?nd trial.)
●.
Ap=-—
(Pe)= 1 (den.— E
(I@en ~ ATO I
1- (Te)en + 460
12
SUM !AIWOF lWHJLi’S
1. ‘RIPfhermal output of the N45A me A exhaust-heat exchangerwas 2~g,00@ 1’.tnIJerhour nt a coolhg-air flow of 3000pounds perham nnd an etilaust-gasflow of @OO pounds per hour. The prns-Surn dropE, unilerthese conditions, were b.? inches of’Y!atw forthe coclinq air at se~-level d~xm~tyo(~.d76~ lb/ cu f%) and 2.s inch~s~~fwater for the m!.aust gas at l~C)O .*and 29.92 inches of mercur~.
. .
rum ARR Ho. E4H22 13
5. Boelter, L. M. K., DennisOn, H. G., Gulbert, A. G., ardMorrin, E. H.: An Investigation of Alromf% Heaters.
‘‘ KIZ + Perf~oe of a Fozmed-Plate.Oross-Flow..ExhaustGas and Alr Heat Exchanger. HACAARRHo. KEIO, 194S.
6. Boelter, L. M. K., Gulbort, A. G., Miller, M. A., andMorrin, E. H.: An ~est igat Ion of Alrcmft Heaters.XIII - Pe~Womnanoeof Corrugated and lfonoorru@ed FlutedT~e Exhaust Gas-Ah Heat Exchangers. llACAARR ~o. 5)326,1943.
7. Reuter, J. Geor@, and Valerino, Mlohel F.: Design Chartsfor Cross-Flow Tubular Interooolers - Chmge-acrose-TubeT~e. NACA ACR, Jan. 1941.
101-ng-lr
lb/hr )
.011*
tr-Ce ,
●)en
‘F)
7877676’76768646464
263656460606162636463
%626364646465676769
E7272707069676772727067
::62616161563654345536576768
air t em-
3753752622.5329831516917421021326826528929016016219319623924522723213616817110419722022226226632.23293013s9389311309272229228327327326170169
::2412412s2211209145144161163108194230
%AT=
‘F)
~:dT:0 I-.1 e, We:001 lngiir, Ha
(BtJ ( lb/lir ;
252,000 3620256, COO 35a5172,000 3680173,000 368o220,020 3602213,000 3600136,000 3495145,000 3495le9,000 3400195, 0i30 3480259,000 3345255, OCQ 3450295,0W 3495295,00CI 3485173,000 3435176,000 3435230,W2 3345232,000 334530S,000 3425316,000 3300206,000 3425291,009 3505171,000 3400236,000 3390240,000 33402@9,000 3335296, ooO .3335350,000 Xoo347,0i30 3335160,000 5345163,’300 3345212,020 %05214,000 S95255,000 34152?3,000 5.355274,000 5315319,260 3415316,000 5405268,000 5W5214,000 .5s95213,000 3395324, CO0 3300324,000 5335325,000 S2401E12, 000 3-3051.24,2-20 538s252,000 3400250,000 5445320, COO 1 M85
1
317,000 5485393,000 5405352, COO 5425348, c0O 546020E ,000 5530204,000 5475242,0CWJ 6885241,000 6S85295,000 69402E1 ,000 6025362,000 6910
Sxha.
--FE!!tntr-
“Ce,
T,)en
(“F)
G==-l“r.tXit,Te )ex
(“F)
12611270
935931
10671142
669697869900
1119llmlzm1204
743763923946
1167119511081131
7G291.5932
1073lm612111221
813034
10561064125613281329122412241064
877074
129412’971296
r-?,hTe
OF~
—
2202161641681801931511612051912482562692691851992242382872902092691792302402852983233161211131461311491611E41871001’691331401921561971493
036 705 131E43 722 121
1073 900 1651093 925 lm13M 11261317 1 1103
19s214
1544 ! 1315 2291328 I 11X2 ! 2051312 j 1110 I 202
065 731 I 134046 12091s
k
127144140100
rmciriBat ofrha.. tm , cc
6tu )6lb)( F
0.272.273.262.262.263.269.254.255.261.262.269.269.272.272.256.257.263.264.271.2’72.269.270.255.263.264.26S.269.273. 2?3.258.230.266.266.271.274.2-4.2’71.271.266.260.260.273.2’73.273.254.255.262.262.s,68,266.274.269.260.255.255.257.’257.262.262.267
TA6LE 1
SU!4NARY OF TEST OA?A ON NAcA TYPE A HtAT 2KCHANG2R
Heat Pe-Jected
bYexhaustgas, He
(Btufhr
217,000219,0001Y3,000162,300171,0001.27,000134,0W143,000186,000174,000223,000237, W225S ,000255,00016s,000176,00019?,000210,000266,000267,0LM267,300234,0001.59,000212,000211,000255,0W267,000299,000207,000lc~, oao15 E,000210,000160,000219,000236, @O0238,0’302.4,000Y?5,0C0242, 000186,000196,000278, 000205,000287,000179, CO0166, C”32236,000240,000291,000314,000339, coo304,000296,00016!2, 00017U, coo21e, r002?5, 0002G2,’3002E4, V30332, 2’20
!at-dance
,tio,,/Ha
3er-:ent )
0606929486w999990
%93068694
100:;
880493079390w089005e3
1049E99068606870607900?92068886909094969199060685928790930994~z
Heat 1np,.rr.c-tlve”ess ,
?.
(pmcent 1
0.212.211.109.190.194.195.139.130.144.146.157.15s.159.160.116.113.121.11’4,127.127.123.125.092.037.097.100.101.107.107.z~~
.226
.220
.231
.233-ppa
.223
.160
.170
.174
.172
.l~o
.161
.180
.100
.134
.135
.13e
.139
.145
.143
.140
.122
.122
.112
.113
.123
.124
.126
.128
.135
mper-tulwhangerXlmus tas ,&Te ‘
(“F)
2562551791802112201331632082142802753103111971992612633253433103081922652723233303703811161161471501’/510710921 B2161871.531522242232231331341751?521721526S24023915114913?136162138196
Oollngrrec -lv*-.ss,
%
% )
o.le3.lal.173.174.177.174.202.205.206.208.220.212.220.221.227.221.241.234.234.241.232.230.234.243.246.250.250.237.259.134.134.130.133.131.132.133.163.161.160.162.160.15e.156.156.173.173.1?3.171.174.172.179.166.190.18s.189.132.158.157.159.164
EE7ure, drop,Pa )*n AP=
in. Hg (in.abao- .ater)lute)
29.46 5.829. S5 6.029.02 5.429 .S2 5.429.23 5.620. e.3 5.s31 .m 8.931. ca 9.030.68 9.730.613 9.830.6N 9.830.83 10.630.00 11.030.88 11.031.6s 15.231.68 15.231.23 16.031.78 16.031.93 10.932. m 17.132. m 16.732.40 16.633.18 23.233.29 24.133.33 24.233.53 25.233.33 25.233.60 25.733.63 25.920.50 4.529.33 4.629.63 5.029.63 5.029. eo 5.329.56 6.229.5430.93 1:::30,03 12.030. s3 11.432.60 10.73n.73 10.830.56 12.030.56 II .e30.57 11.931.79 16.231.79 ::::31.9431.94 17.032.09 18. C32.o9 16.C32.20 18.833.79 26.133.79 26,433.29 23. s.3’.29 23.533 .*4 23.033.39 23.633.59 24.032.97 24.433.22 26.0
xhaua taanletre s-ure ,Pe )a”
in. HEabs.a -l“te)
29.382’4.34!29.4729.4729.4729.4729.9829,6829. W29. S829.5829.6B29.6229.64329.382D.3a29 .S829.3s29. S29.3s29.6330.0029.5S29.5B29.5829.$329.5020,502!3,6330,[email protected],3830,1830.1030.2830.2S30.2829.9930.0930.2930.2930.4930.4930.6930.6930.6930.3930.3931.1931.1931.4931.0231.32
codGacrec -urerep,
ms
In...ter
2.82.8
;:;1.91.91.31.31.51.61.81.92.12.01.41.41.51.61 .s
i::1.81.41.s1.51.7
;::1.93.33.34.04.04 .Z4.54.54.24.23.83.33.34.44.44.43.C3.03.43.63.93.94.34.24.23.43.34.64.65.25.46.7
IONALEE FOR
atlo c.Olinflr exindntr-ncem-ltlcls,
~
‘en
0.651.531.709.7W.6S3.670.816.010.765.757.701.7(2?.679.Wll.810.EIM.75a.766.717.712.730.729.2s5.7N6.786. 73i.755.727.727.721.720.663.6o3.622.614.614.E612.668.7M.74a.74a.655.655.65S.80s.802.759.755.716.71s.674.727.729.797.000.787.7e7.7S6.762.722
ISORYRONAUTI——Iltio 01,xhaust.;as 9x11md ●n-,J-ulc,len-lities,
be)+(P=].”
msur
rop ofOollng1P,
*en Pa
In..ater)
5.65,74.B4.85.04.99.29.29.9
10.010.010.611.211.216.016.016.916.017.916.117.717.s25.626.626.728.028,020.626.B
4.44.54.94.95.26.0
1:::12.211.510.810.911.911.811.916.916,017.918.019.219.220.329.630.026.426.427.126.92EI.326.8
*
Naauremp ofmmJ8tam,
P*
GAPS
in.mtar)
2 .s2A2.22.2/?.22.22.02.01.92.1e.11.92.$42.11.’41.91,91.01.91.91.02.02.01.81.81.91.81.81.84.84.74.94.94.74.74.74.64.64.64,64:54.64.54.64.74.74.54.64.54.44.44.64.95.25.17.07.06.87.4
&
\
NATIONAL AOVISORYCOMlil TTEE FOR AERONAUTICS
TABLE I - Concluded
22JNXARY OF TEST DATA ON HACA TYPE A HEAT SXCHANG2R - Cone luded—
eatingrrec-iveness
4a
emner oollngrfec-lve-0s3,
%’
P* r-cent )
:oolln~*lr.nletn.es -mre,
% )“”
In. Hgabso-lute )
T1001- cool
.nw aIir t‘low ●ntr-,at* , mce ,
% (Ta)●
>rs8mlrImp of
!OollngIir,
“d%
‘in.inter)
28.7S.o.sSoos18.418.420.219.920.s20.612.512.56.46.419.619.55.75.911.811.s11.011.0
4.44.5
10.s10.210.416.619.727.427.617.417.9
0.49.65.14.6
4.6
9.69.5
16.416.327.226.527 .S
27.217.017.010.310.36.36.2
Dollnglrres -urePop,
A Pa
in.inter)
ExRnga~inletprea-aure,[Pe)
●n
( lnno;2
lute )
-:oollngIir ●xiM!:mt~,“calen-Ilt LeB,
●ex
~
Ratio o,txhausbKm ●xlnnd sn-trance39n-litl*s,
(Pe)
(Qa)-n
,-air tem- B.haust-zas tem- ;peclrlc Heat mwat of Jetted,xhau, t bv
e.t-alwxatio,#Ha
per-cent )
E
t
Xlt,T.)a
(%)
!ise&Ta
OP)
0s rlorite, W
( lb/hr
690069406915723072557260734072207165730573057370733552755290‘736073507250726072757205525552655s15654553403345528033355570732072507250733072753505
3505
350535053510345534603445936593C594609450
94?C
9470
9545
9360
ctXit,Te )ex
(OF)
1093120s12s9
065865
111411161285130513121326134413441254125’71150117211541146
973963049
:8859063846862060078898892915910930852
873
057851
826036042S30e80
896G99838
933
9359 &-j
936
bropAT~
‘F)
—17420-7223127128166167194187180lml13012s223217119116139141124116123
yntr-
nce,
Te )er
(°F)
—
126714951492
992993
128012s31479149214921494147414721477147412691288129312E1710971079
9721053104610141013102110241030103310371024103?103010341020
1043
104I3104910331064105910561023lce5101710281038
lMO
1032
1035
hanuefxhau3ao,hTe $
(OF)
:.s, Cpe exh. ”~tgas , HP
lBtu)/[~b)(op) ‘Btu*r
lb/ (‘F)k)
— —%?75 699260 71!3260 727425 757465 7474Q0 767430 717315 667270 665440 733440 743715 663715 687265 677350 663629 723575 705400 703400 693395 693403 66
0.267.273.273.259.259.26I3.268.273.273.273.274.274.2?4.273.273.260.269.260.268.263
321,0003!22 ,000304,000236,000241,0003$23.000329,000
1~:~
336:000‘262, 000237,000321,’300313,’300234,000229,000270.’300
89060397’37969693Ml97’30868407050390089096
1%9?
1:99
107100
96
1:
1:1031 m
’36
96
949em929198
106100103112100
101
91
1 m
0.135.145.144.150.131.157.159.165.16.2.198.200.243.244.147.146.242?.243.193.193.186.166.222.225.171.171.169.136.134.111.111.150.150.la7.109.229.190
.195
.148
.147
.116
.117
. oa2
.090
.14s
.149
.178
.170
.212
.212
.250
.240
19624224113113217417520921418510715115225125412012915?1571291291211291s213315116216317?182134136115119
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I
HACA ARR NO. E4H22 Fig. Ia,b,c,d
(o) Cool ing-o!r face.
A;r floit —
No-flou sidesIop-uelded onhgoder Rlote-
%+FW---m-?r--?i+-u---i+‘
II
o
0
0. .—---. —...-. —a. ___ _. ....- .. ... ...= .,.-=. .. .... ,. ... .. ___......__. _ ._ ----.. . ..— ..— =41n
. ..--__————___________—__________g___Q___Q-––Q.--Q-_9-._Q_–-Q
(b) Exhoust-gos foce.
NAT IC)NAL ADVISORYCOMMITTEE FOR AERONAUTICS
I
mGUS f I Ou
{c) Heoder-plote detoll.
45°
Yr?
#header
(d) Tube-spocing ondf\nned-tub8 detoll.
F!gure 1. - Sketch of WACAtype 4 heot-exchonger detolls.
(
I NACA”ARR NO. E4H22Fig. 2
I
NACA ARR No. E4H22 Fig. 3
,
,“----+E5ZI
.
1
/7-——.., \/ \
\ Supply heoder
—.—11—–”~
I
i
,\ll 1-
~!l 1-
1.1~Flou-regulotlng uolue~
/
Cooling-oir duct
Combustion-olr duct
\
\ Flow4eosuring orifice
\
/
Heot exchanger Gas
t
producer
/
——.D
-—-
1-1
—= -0 I
-——-- -——__-l/
i
~-----+a%a
NATIONAL ADVISORYCOMMITTEE FOR AERONAUT ICS
Figure 3. - Diagrcin of test equipment.
NACA ARR NO, E~H22
/ //’
v
//
/
~ “&+ ~. ‘-
/
/1
///////// ///A’z’v, 0’/// 7 ‘“7~
Exhoust gOS—z ——— &w.—
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v///////////////////,>,
/// 7/// “///////zl
q
+ +
High-temperature insulotlon k
+/ - k
v
/o A
// nun nnn ~ _-!-L ——Stotion B
/
/ /
Baffles-—, /“”j ~ ~$tot Jon ct ,/
0 I
K*YJ’”’?
-14“
nn
NATIONAL ADVISORYCOMMITTEE FOR AERONAUTICS
Figure 4. -
x Iron-constonton thermocoupleoAstotlc-pressura piezometer ond
toto/-heod tubes‘shielded chromel-alunel thermoco,upl#%HIxIng boffles
Dlogrmuotfc sketch shou~ng positions ofthermocouples, pressure tops, ond boffle plotesIn heot-exchonger duct. -
Heat dissipated by exhaust gas, Btu/hr
Ii !3o
[ I I I I I I I I I ! i a
liACA
400
300
200
100
ARR ~Oo E4H22 Fig. 6 and 7
d
/ ‘17 X– - —
— —
1 / 1 ~ -
3000 3000 7000 9000Cooling-alrflow rate, lb/hr
Figure 6.- Heat output of the NACA t pe A heat exohanger. En-~trance-temperaturedifference,1600 F.
we(lbh ‘)
3000 3000 7000 9000Cooling-airflow rate, lb/k
Figure 7.- Cooling-airtemperaturerise in the NAC type A heatexchanger. bEntrance-temperaturedifference, 1300 F.
NATIONAL ADVISORYCOMMITTEE FOR AERONAUTICS
— * . .
-we— — — — — —-
lb/hr )●2 / ~
3300 ~+ x’k
-R+
5400 ~ -
T
.1 .+- ~7200 -
0’
7200
●1
0.2000 3000 4000
Figure 8.- Cooling and
!5000 6000 7000 8000 9000Cooling-air flow rate, lb/hr
heating effectiveness of the NACAtype A heat exchanger.
RACA AR-R No. EbH22 Fig. 9 and 11
4
NATIONAL ADVISORY WaCQMMITTEE FOR AERONAUTICS ( lb~ )
Isother $M1 data
1.0 “ - ‘. .’
0.●45 ●5 .6 ●7.. .8 .9 1.0
‘ex/GenFigure 9.- Correlationof coollng-alrpressure-dropdata.
.l~-6
Wa
(lb/hn‘i
.5 ●IQ +t 171— 0
R“_ ❑ vTw
Q a3
gf.os
VI I I I I I I 1 I I I I.85 .9
1ho 1.1 1.2 1.3
‘ex’pen
Fi@re 11.- Correlatlonof exhaust-gaspressure drop data.
.
I--
I(ACA ARR NO. EUH22
40
30
2s
20
15
3
NATIONAL ADVISORYCOMMITTEE FOR AERONAUTICS
/
I /
/
// !/ L’
// / ///
1
//
,
/// ‘
/ L/h
// / /,/
/
2. s {
2
105
/
Fig. 10
.-1 1*5 2 2.5 3 4 5 6 7 8 910 15 x 10”
Cooling-air flow rate, lb/hr
Figure 10.- Pressure drop of cooling air across the NACA typeA internally finned tubular heat exchanger.
I
Ilmmlm IllImmII■IlmmmmllIII ■ m Ill ImlEmml,, .,,, ■,, , ,,,, .,.,,,,,, ,,---.-. -,-.-,,-,- -,-.—- .,..,,, , , , ,, -.-,,,., ,, .,.. .,,.- . . . -,.. ,,.- ,---.—.
HACA ARR ~00 EUH22 Figo 12
05a)
\QQ“ 4
3
40
30
26
20
15
109
8
7
6
NATIONAL jCOMMITTEE FOR
I
2.6
2
1.5
b
7IV ISORY
CsIERONAUT
dr’
—
— —
—
—
/
!
——
tt-1
(Pn) /( Pa)ex en
1 1.5 2 2.6 3 4 s 678910 15 x 10Exhaust-gas flow rate, lb~r
Fi@re 12.- Exhaust-gas pressure drop across the NACA typeA internally rimed tubular heat exchanger.
