ad 27m, 954 - dticmost pronounced for high values of the bearing number a (i. e. at high speeds),...
TRANSCRIPT
tI
UNCLASSI FIED
AD 27m,3 954
ARMED SERVICES TECUICAL INFORMAMO AGENCYARLINGTON HALL STATIONARLINGTON' 112, VIRGINIA
UNCLASSIFIED
I
NOTICE: Nhen government or other drawings, speci-fications or other data are used for any purposeother than in connection with a definitely relatedgovernment procurement operation, the U. S.Government thereby incurs no responsibility, nor anyobligation whatsoever; and the fact that the Govern-ment may have formulated, furnished, or in any waysupplied the said drawings, specifications, or otherdata is not to be regarded by implication or other-wise as in any manner licensing the holder or anyother person or corporation, or conveying any rightsor permission to manufacture, use or sell anypatented invention that may in any way be relatedthereto.
";J1 ECH AN ICAL
TECHNOLOGY
I NCO RPORATED
TI -62TR2
ON THE HYBRID GAS LUBRICATED
JOURNAL BEARING
by
J.W. Lund
Contract Nonr 3730(00)Task NR 06t-131
Trechnical Report MTI-62TR2March 15, 1962
ON THE HYBRID GAS LUBRICATED JOURNAL SEARING
by
J.W. Lund
Prepared under
Contract Nonr-3730(OO)Task NR 061-131
Jointly Supported by
DEPARMENT OF DEFENSEAIUSIC ERGMY CMWUSSION
N&TIONAL AERONAUTICS AND SPACE ADM INI STRATION
Administered by
OFFICE OF NAVAL RESEARCHDepartment of the Navy
Reproduction in Whole or in Part is Permittedfor any Purpose of the U.S. Government
NECHNICAL 1ZGHNOLOGY IN.ZAIIIAN, N. Y.
TABLE OF CONTENTS
ABSTRACT 1
INTRODUCTION 2
RESULTS 3
DISCUSSION OF ANALYSIS 4
CONCLUSIONS 9
RECOMMENDATIONS 10
REFERENCES 11
NOMENCLATURE 12
APPENDIX 15
ABSTRACT
The purpose of this report is to analyze the load carrying capacity of an
external pressurized gas journal bearing including the hydrodynamic effect
caused by the rotational speed of the journal. The analysis is an approximate
first order pertubation solution, i.e. it assumes small bearing eccentricity
ratio. Furthermore, it is assumed that the gas feeding takes place through
orifices in the centerplane of the bearing and that the number of feeding holes
is sufficiently large to be considered a line source.
Results are given for the load carrying capacity and for the attitude
angle. In addition an investigation is made of the validity of the approxima-
tion used in arriving at the solution.
INTRODUCTION
Gas journal bearings are principally of two types: 1) self acting, and
2) externally pressurized. The self acting bearing works by hydrodynamic
action and, therefore, has limited load capacity. It requires a small
clearance and tight manufacturing tolerances. The externally pressurized
bearing relies on hydrostatic pressure to generate its load carrying
capacity. It is used in applications with higher load requirements and with
less manufacturing precision but requires an external pressure supply.
Although the externally pressurized bearing is primarily hydrostatic,
the rotation of the journal causes some hydrodynamic action. This effect is
in most cases negligible because of the relatively large clearance but may
become significant at higher speeds and at large eccentricity ratio. Since
in recent times such cases have been encountered it is of value to develop
an analysis for the combined hydrostatic-hydrodynamic gas journal bearing.
This is the purpose of the present report.
2
RESULTS
The results of the analysis are presented in Figures 1-12 where curves
for load carrying capacity and attitude angle are given. Four dimensionless
numbers are necessary for a bearing calculation:
the bearing number i= (
the bearing length-to-diameter ratio = L/D
the feeding parameter =-
the pressure ratio = Psupply /Pamb
An estimate of the validity of the results can be obtained from Figures
21-28 where the dotted curves are the previous results and the solid curves
present an improved analysis. The improved analysis, however, only
satisfies the analysis within a certain error which is marked on the curves.
Thus a comparison between the two analyses is only valid when the error
is small.
3
DISCUSSION OF ANALYSIS
Theoretical analyses exist separately for the self acting bearing and for
the externally pressurized bearing under the assumption that the eccentricity
ratioe is small (Ref. 2 and 3). Both these solutions are first order pertuba-
tion solutions around E = 0 such that the bearing load becomes proportional
to 6 . The results are in good agreement with more extensive solutions and
with experimental results. Thus it seems logical to attempt an analysis that
combines the two solutions.
Assuming isothermal conditions in the gas film the exact equation for the
problem under consideration is Reynolds' equation:
where P = film pressure, 9 = gas density, h = film thickness, R = journal
radius, Wj = angular speed of journal, ju = gas viscosity, x = circurnferen-
tial coordinate, z = axial coordinate and m = mass flow per square inch from
the external pressure source (m is a function of the local pressure P). This
mass flow enters the equation only at the discreet points at which flow is
introduced. For this reason it is extremely difficult to obtain a solution of
the above equation even in approximate form. To circumvent this difficulty
an assumption shall be made in regard to the nature of the gas feeding. The
gas feeding takes place through orifice restricted feeding holes in the center-
plane of the bearing. It shall be assumed that the number of feeding holes is
sufficiently large to be treated as a line source. Thus the gas feeding no
4
longer enters the differential equation but instead becomes a boundary condi-
tion.to the equation. This boundary condition stipulates that at the centerplane
of the bearing the pres3ure gradient must be such that the flow into the
bearing is equal to the outflow from the feeding holes. The flow through the
feeding holes is restricted by orifices. Any restriction due to the annular
flow area existing between the edge of the feeding hole and the journal surface
is neglected.
The normal equation for flow through an orifice has a discontinuity when
the pressure ratio reaches a critical value. This discontinuity is eliminated
by using a modified orifice flow equation which has proven to give satisfactory
results.
Based on the above assumptions the equation defining the gas feeding can
be set up. It is found to be governed by the dimensionless feeding parameter:
A.t = 6.Au , & Io."
(I4A= viscosity, Pa = ambient pressure, C = radial clearance, N = number of
feeding holes, a = orifice coefficient, a = orifice radius, m = number of
orifices in series, R = gas constant, T = total temperature.
and the ratio of supply pressure to ambient pressure:
V A~
Returning to Reynolds' equation it is written in dimensionless form disclosing
two additional dimensionless parameters: the bearing number
(w = angular journal speed, R = journal radius)
5
tI
and the bearing length-to-diameter ratio:
D
The solution will be a function of these 4 parameters. A first order pertuba-
tion solution of Reynolds' equation is desired.
Thus the film pressure is approximated by:
PM P +eP,
Po is the pressure distribution when the journal is concentric in the bearing,
and is found to be:
where t is a constant determined by the bearing-feeding system and
is the axial distance measured from the end of the bearing, i. e. P is a0
linear function. Substituting the above first order expression for the pressure
into Reynolds' equation yields the first order pertubation equation with
boundary conditions, see Appendix, eq. 5:
.69, it s-o = A Pine
Unfortunately this equation has no simple solution due to the form of P 0
Instead the nature of the solution is explored. This is done by approximating
Sby a constant:
where P is the average value of P . Then the equation is similar toO, av o
Ref. I and 2 and a solution can be obtained. Numerical values of the dimen-
sionless load carrying capacity and the attitude angle are given in Figs. 1-12
as a function of A for a wide range of .At-values, two L/D-ratios and
6
three pressure ratios.
The second part of the analysis evaluates the validity of the approxi-
mation A = constant and establishes the regions in which the results are
valid. Whereas previously A was constant throughout the bearing, it2
now varies along the length of the bearing. Since P is linear it is0
reasonable to replace * with a linear or almost linear expression.
This leads to a solution involving Bessel functions of a complex variable
which is rather impractical to evaluate and instead the Bessel functions
are approximated by complex trigonometric functions. Hence the solution
does not satisfy the differential equation exactly and the discrepancy is
presented in Figures 13-20. This error must be small compared to 1.
Otherwise the analysis proceeds as before and results for load carrying
capacity and attitude angle are given in Figures 21-28. In the same figures
are also shown the results for f = constant for comparison. In addition
the error in using the trigonometric approximation is indicated on the
curves as taken from Figures 13-20. For A less than 1. 1 the agreement is
good for the load carrying capacity and reasonably good for the attitude
angle. No obvious correlation can be found between the magnitude of the
calculated error and the point of divergence of the results. For the parti-
cular case of L/D = 2, V = 2, and "At = . 5, the error never exceeds 2%
and even so the results of the two analyses differ considerably. This points
to the need for future investigation.
Finally, it shall be investigated if the total load carrying capacity can be
7
considered as a simple superposition of the hydrodynamic and the hydre-
static load. Figures 21-24 indicates that this is not the case. However,
since At - , where Pa can be interpreted as being the mean
film pressure for a purely hydrodynamic bearing, A. should be replaced
by A. #: in applying the superposition for the hydrodynamic-hydro-
static bearing. This has been done in Figures 29-32. It is seen that even
with the modified A the superposition still is not valid. This is not
surprising since the hydrodynamic and the hydrostatic action are coupled
in a "non-linear" way through the feeding conditions.
8
CONCLUSIONS
1. The load and the attitude angle of the hybrid bearing are determined by
4 dimensionless numbers, A. , L/D, At and Ps/Pa.
2. The rotation of the shaft increases the load carrying capacity and the
attitude angle of the externally pressurized bearing. The effect is
most pronounced for high values of the bearing number A (i. e. at high
speeds), for low values of the supply pressure and for high values of
the bearing length-to-diameter ratio.
3. The load carrying capacity of the hybrid bearing is not a superposition
of the hydrostatic and the hydrodynamic load even if the bearing number
A is based on the average film pressure instead of, as usual, the
ambient pressure.
9
RECOMMENDATIONS
1. The analysis should be extended to obtain the complete solution of
the first order pertubation equation.
2. An investigation of the effect of higher values of the eccentricity ratio
should be undertaken.
3. The stability of the hybrid bearing should be studied especially to find
out how hydrostatic pressure influences the stability of hydrodynamic
bearings.
10
REFERENCES
1. Ausman, J. S., "An Improved Analytical Solution for Self-Acting, GasLubricated Journal Bearings of Finite Length", Journal of Basic Engi-neering, June 1961.
2. Ausman, J. S., "Finite Gas-Lubricated Journal Bearing", The Institutionof Mechanical Engineers, Proceedings of the Conference on Lubricationand Wear, London 1957.
3. Heinrich, G. , "The Theory of the Externally-Pressurized Bearing withCompressible Lubricant", First International Symposium, Gas LubricatedBearings, edited by D. D. Fuller. ONR/ACR-49, 1959, pp. 251-265.
11
NOMENCLATURE
Constants specifically defined in the analysis for the purpose of sim-
plification only are not listed below.
a Orifice radius inch
C Radial bearing clearance inch
Co , d Constants given by equation (20) - (21)0 (st part) and (55) - (56) (2nd part)
Fr , Ft Radial and tangential force components lbs.
G Complex form of H, see equation (12a)
g(, g2 () Functions defined by equation (15) - (16)( I st part) and (48) - (49) (2nd part)
H up Po1
h Film thickness inch
h Dimensionless film thickness = -C
L Bearing length inch
M Mass flow through one feedinghole lbs. secin
m Number of orifices in series in onefeeding hole
N Number of feeding holes around circum-ference
P Pressure in gas film psia
P Dimensionless gas film pressure u pa
P Dimensionless gas film pressure at 0 = ,see equation (4)
PI First order term in pertubation solution,see equation (3)
P ofv Average value of Pot see equation (31)
Pa Ambient pressure psia
12
P Gas film pressure at 0 psia
P5 Supply pressure psia
i2 Slope of P 0, see equation (9)
q Constant defined by equation (35)
R Bearing radius inch
R Gas constant insec 2 .0O R
T Absolute temperature ORP
V Pressure ratio = F-8
a
W Total bearing load lbs.
X, Z Circumferential and axial coordinatesfor gas film inch
Z Variable in 2nd part only, defined byequation (35a)
Orifice coefficient
its isDefined by equation (17), 1at part, and byequation (43) - (44), 2nd part
SBearing eccentricity ratio
G, . Dimensionless circumferential and axialcoordinates for gas film
*Constant defined by equation (34)
Constants defined by equation (22) - (23)
Constants defined by equation (57) - (58)
ACompressibility number =Z_
At Feeding parameter N t O T"
P C3a
/A Gas viscosity lbs. sec
in
13
L5Bearing length -to diame~ter ratio 6
Attitude angle
Gi)Angular speed of journal rad/ sec
14
APPENDIX
The Combined Hydrostatic-Hydrodynamic Gas Journal BearingAn Approximate 1St Order Pe rtubation Solution
The Journal bearing is pressure-fed from orifice restricted feeding holes
around the circumference in the centerplane of the bearing. For a sufficiently
large number of feeding holes these may be approximated by a line source
such that the gas feeding becomes a boundary condition to the differential
equation describing the flow in the bearing (Ref. 1). The differential equation
is Reynolds equation which for a perfect gas under isothernal conditions may
be written:
To make dimensionless set:
Then:
where:
A let order pertubation solution with respect to the eccentricity reio a around
e a 0 shall be tried. Therefore set:
(3) P- P., e rt---andam, a
P u.'+ 2t P.eP+ -Due to symmetry P is a function of t only, i.e.. U
Thus the zero order equation becomes:
15
or
tSi c :0 the 1 st order equation becomes:
(5) 1+ * Iine-AP.sina
where:
(6) H- P P,
The boundary conditions for eq. (5) are:
a)Ou.Ur H(el)- H(e+21)
b) Cut H(eV)u0
c) mass flow through feeding holes = mass flow through bearing
For a supply pressure of P' a downstream pressure of Pi. gas constant R,
absolute temperature T, orifice radius a, orifice coefficient s and ,F orifices
in series the mass flow M for one feeding hole is approximately:
For N feeding holes around the circumference the flow per inch is
Equating this flow to the flow through the bearing yields:
Substituting dimensionless parameters gives:
where
16
Iand
(8) V=
Introducing e-. (3) and (4) yields and the boundary conditions. at
or
(9)
and
Approximate solution of differential equation
To evaluate eq. (5) set
(ll) H h,() sine + hz() cose
which gives:
21) -0* 'PLOU)G a-A P.
where:
U Za) G t ,{' hz(O
Eq. (12) is not readily solved considering that P is given by eq. (4). Eveno
if an exact solution could be obtained it would be very complex and therefore
be outside the scope of the present analysis which is approximate anyway.
Instead the analysis will be performed in two parts. In the first part
is set equal to a constant. In the second part this assumption will be
17
6-
investigated.
Rewrite eq. (1):
2which becomes linear in P when P is a known function. In order to arrive
at a manageable solution we set P equal to a constant, unspecified for the
time being. Furthermore, only the lot order pertubatio, solution is consi-
dered which is derived by substituting eq. (3):
Proceeding as earlier we get:
with the particular solution:
(13) G- P. F y0 i
The solution to the homogenous equation is:
(14) G+" q,({) +{q,(O
where:
(15) 9(1) - ( .c.oW4 + d sinhut) Casp " -(CoS6 t, Sinho) SI,,
(17) 9,{"(&0 daw)o c s.~s
(see Ref. 1)
18
Thus the complete solution is:
(18) H~ W at_1 (Sine *Coss) +q(061110 + 9.0)Co~sa
Boundary Condition at H~ s~oFrom the boundary condition we get:
which gives:
where
ch24-cs~nI
(M) COI'C6 +coSin SI'hW-C
+ (*T cosh& 2,-cos205
(23) 04 c,-zM
c' th ?4- Cos 2a
19
Boundary Condition at 1-0 , eq. (10)
Introducing eq. (18) into eq. (10) and setting 'O gives:
(24) am 6 + - , +,,C.-A + -w, +,3.+,d.- As1
(b) 6- a -&2 ,'] -[p &-1[-k.c.- .c,-.4 +d ,+ I3,l1+13 ,-,Ar]
where
(26) AX-1
Together with eq. (19) this defines the arbitrary constants in eq. (15) and
(16), thus completing the solution of Reynolds equation.
Force Calculation
The radial and tangential force components are:
Fra - S.e Pose do dg 2ae le coso do dg
F: 2 PR' Psiho do d -2t sin do d.
where H in given by eq. (18) and P by eq. (4). Then:0
(27) ~ [Q5A - q)d
(28) 'SO LPI t +
20
the integrals are evaluated by numerical integration.
The attitude angle T is given by:
(29) f = Arc ton(Q)
The total bearing load is given by:
(30) W i
Curves of the attitude angle (9 and the dimensionless bearing load MI
are given in Fig. l-Z4 for P . (i.e. P=Pa)andfor P
where P is the average value of P and consequently of P. The averageO. aV o
value of P is:0
(31) zog "/,
No Feeding, .A. -0
In this case we get:
W+14 T+-r " s111h',f+ cos'pg
and therefore c = d = 0. Comparing these results to Ref. I it is seen that
AV TI B and 6, 6 A. Thus the presen analysis reduces to
Ref. I (the Ist order pertubation solution) for the case of kt=O
No Rotation, A&'0In this case aa c z0and
21
dl', - cosht b - ¢osh R' - lsrnhi $|hg snhI
Therefore the tangential force F t = 0, i.e., f , and the bearing load
becomes equal to F . We get:r
ff DLPe +Eoh+In~ )*Fg"(-)
or
where
(- dt x) (x)a& ettdt
This may be compared to Ref. 3 by means of the following equations:
Then eq. (32) may be rewritten:
IrDL&E U coshf.* f Sinh
which is the same as eq. (19A), page 259, of Ref. 3.
A Check on the Assumption P = constant
Since P . 4I gt( i) is reasonably linear we shall substitute linear
22
expressions for P and .AP into eq. (5 and thereby obtain an indication0 2of the validity of the previous assumption P * constant.
Homogenous Equation
In eq. (12) we introduce the approximation
who re
(34)
(35)
Furthermore set:
(35&) ZW1i~f =+e(*+*.
Then the homogenous part of eq. (12) becomes:t
(36) 9 + Z GC'Wu
with the solution:
G:=V [ A' 3(fjz%) B.3.j(1qz'4)1
Since Z is a complex variable this expression is rather cumbersome to
evaluate. Instead the following approximation shall be used:
(37) G - z - cos(f 1. z%) + B-s!(|z%)]
To evaluate this approximation insert eq. (37) into eq. (36) to get:
(38) (+) 4 z
23
bMipa ring the real and the imaginary components:
(39) real part: VW J
(40) imaginary part: +At)- (+A-L)[i+ j '
Thus for eq. (37) to be a good approximation the remainders inside the above
brackets must be small compared to unity. The maximum values of the
remainders are:
(41) Max. remainder for real part: 6
(42) Max. remainder for imaginary part: I
These equations have been plotted in Fig. 13-20 for a few representative
values of At jV and A. and thus indicates the regions where the results
of the analysis is valid.
Returning to eq. (37) we set:
and
From eq. (35a) we get:
(43) ~2
24
(45) V Vt*- 2 r[1+W 1l
t,+ (1+ +
where
(47)+
Introducing the above equations into eq. (37), setting A - a+ib avd B * c+id
and using eq. (12a) yields:
(48) = alt coswcosh p+JS Sinh e s ] -b[d cos t-csi,, VA;Ihh]
4c [r' Is.j?-C@hA -dcoa sip,] -d [si, coshP +t cOU sil,h]
(49) AOk) [d coow C06 - ir strhb +b[t Co, cohP 4 dsii sith#]
+c U srWm cosh + YCoSt s ,I) +d (Isu, cos -dcosA swAp]
Complete Equation
A particular solution to the complete inhomogenous eq. (12) can be found
either by using the substitution given by eq. (35) to obtain a series solution
or by proceeding with the homogenous solution by means of variation of
parameters. Neither method yields very practical results. Instead we
return to eq. (5) and make the following approximations:
25
AP. A_. s-,,i,( '-+axsihht
sInhj
Note that for g -l these two approximations for P are nearly identical.o
Then a particular solution of eq. (5) is:
(50) Hm - I) 't-h$10"
Combining eq. (11), eq. (48), eq. (49), and eq. (50) givbi the complete
solution to eq. (5).
Boundary Condition at -4: H =0The boundary condition becomes:
(51) 9,(-) Ct J'L C4@cSint,(_ [IAP,, ,,-b[hICoA,(,-3,i) i
(52) q,(i'1. -j~ ',,,,(u, ,- , s, ,]g + b[ COkP@ Sipftco , SA
+c [4 siIW 1 ,.)Co...,,,I,',3+dC~ i, C s~,-c6 s ,pJ
where A, • , , and j are derived from eq. (43)-(46) by setting
tat (i.e., P 0 1).
Solving eq. (51) and (52) with respect to c and d yields:
(53) C co- ,4-X, 5
(54) d d.+ka -A, 6
26
wherwe:
(55) C0- 21(, g,(c4d,.u,(f))hSnt~ COshA + (rj gajf -Jdg,()) CO rhil.
(r"+a)(cosh2p, -cosu,)
(56) dou2[(. ~)- e%(d)Sing, -oip -(4fg()&aI)~~ i~4
(t+ d,') (CO sh 2p -cos 2o,)
(57) S' c 24cs&
(58) =CShMp-COZ8
Boundary Condition at "Osee eq. (10)
Introduce the following constant:
(59) at ( 0)u
(60) A6
(61) as
(62) IL
(64) j -(A _____ t_
27
(67) V ' 4 co. j3N . Sa. Siruvh N
(69) 6 , S* rKl, coshp, -CF COS1 SiDnho'.
(70) do c sit*. cos* + ye m4. sihhj%3
(7z) q CW J* OfP~?SihI1A;. Si,1D -4 -:
(74) T' 6sihA4 ohp.4..' cow., Silb44+df +%
(75) 5'
(77) I~d T
28
(80) n'uj ~ w (IA , +A (d'-46) C. -C(T' OT)d.
Then we get from the boundary condition eq. (10):
(83) bI
Force Calculation
The radial and tangential force components are:
(84) rr 2 Vosd
(85) Ft 2P e Sir* do d
where:
29
(86 H {jJ (-q(oi -j -cagh) + 9,(Q) Sino
and ,(Cand ) are given by eq. (48) and (49). Then:
(89) -= * S+
These integrals are evaluated numerically. The total force is:
(90) = r Ft
and the attitude angle is determined by:
30
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pestmla I2IA4g U. a. Aoomi bUWr a~ls
Chief of level Reearch DXeWWeeigI.. 23, D. C. l vasfeem 25. D. C.Director~ Atts Wo. Clarene 3. Miler,Jr
Attas Code 4s38 10 Attas Code 2000 6 U. 6. Ar omineeer Up jobrsorj" Mr. a. 0. Mordlifger, mawe5b23 1 5230 1 For Selvoir, Virgin" ft$eGUIaer Dkve1WAm bm-
knAtlas V. N. Cris, bmliear pos fteetor 3evlgem Ohsfvsi5 Cl.Field offiee g U. N. Atmc bw Owmelasi
Cmeliej Speia D prtomothe Offic Dieto . .Sehioas 25, D. C.ICmadnOfie a goo25, D. C. Mroti U. . AmySmoor Deeamrtr. ike
WOc of Revel Researchs At.: Code 5U3-A (15. DOWA 1 and~ Doeloqeirt VLs1abor.to. l adatue Librry eibranch Offic pat10.,VrgnaU .AoicEeg o~l
Towt Floor. Sed Boorig a Seale Branh Atta: Tenl baona ~en.ter 1 wablastm, D. C.I
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Chief, Pusoe of Sips Atte: Norm L. 91010 1 Attis R.. W-Ro~ary Ode me ceeael DivieionDepartawat of the MayVrigbt-lmteree Al Doe, Ohio 1 apohbilo IremoWeehington 25 D. C. Fuels h Lidomt Sectims Non btorrtle, AlahamaAtln: Code 94i (Jese C. Reid, Jr.) 2 Reeeerch2 &GOOD Arme Sevie v.hnsa biageit
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Professor A. Charemes Atlas Library, W1-109 1 Moomee , Doa 5, xah..t.The Technological letuU5S aahAasaAt;Sr 7 hyalP4atfs"Northeastern thVelsti tFroeor F. F. 1kots-si bhi Veea Allnoi AtI . .l1r ejc *e
mvwaele, Illinois 1 a*~ Institute of Teehelegr Da . "oNeobem, Nec a"er I Charma ofea a ealo
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ar.±3 NobTchialBff Atlas S. L. Urn, Visa Freseee J . P. MMrhev & AseociatesNo. 0. K. Flasher M Federal laeelteelee Geel mhmmo 1C-e.,luft DegameeFleeroh Laheevtteriee for Use Dviion at Internatinl fth3. 390 an afteeorie Sale*"@e eem ?ldro crortion 3ee- Shoering; cow lnt..c 2, 1
boam1.115131 lReU.. the Industrial parkOnivereity of Virgin" S Frmane, Caiflornia 1 Feel Veeibige Fe-MylVMSi 1 Mr S. V. u3iumb
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jet Fqoaieleetaborsairy F. 0. Ren Sb no Domain Corporation ReIder, Celowude 2Calif mae Institute of Teolser Sea Dao, California all - -AMW80 Oa at v Avstan Atlas Babra N. Probact I uG., Raw York Cwt~se VrIgbt corpartarremhesm osurlfe At%&s Mr. Russell 9. db" 1 righ Awanswtieeal Division
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Atta l Pbrt ojt 22 Ml. I,-, lai Vi2 vill, catela 2 500 But n AMe" 9 Asme
31-10 Thne Aveue Mecaical Deealq.M sot. 1 umsweUN3 ma MoeraleeloIsl3and City 1, MW 1--k A. C. Spurs Plu Aiiso vo""Kloiaue"e00Sn" street g~rsiAtte: Wa. Jamvie 2I Ge~ aer Calv 0 eratien osgilaM obseebe1 tmaenebe 2, WUSnoma Mr. A. N. lba Atlas Wa. R. L. BSIa., TO*b. A4101.Re. Adolf ta~u Atta: A Ll.. A 1 ve mlato PrOOeSeIe Pt*AG~t q~maFor Rotor Comayow- usesahIseasrint amd moeeareb staff Pa. lalter camn kg5 kt ew est Pa htmyAvr.P~. 0. box 2053 Scarfott Metal.. 1665,4 atlep aUeas -at 0 s W ,rDearborn, Nichiga .1 Omeral Prelio lYn Il P.fe~ 0. Dvana 6u11" "c"Al . - Mr. K~m1. Pw.m u steen QI~ sDr. John S. lay.., Jr. Little Pallss, Sam Jersey 1M Fresspmal (RA) Atlas ibrarin'iSon-latallic. Section
MdaalAvrf N0AApplied Science Deartent NO. Job C. Stile. Instat ft. -St. Invit Libemep, WASg. 1".-5Scientific laboratory Kearfastt DMotel.. um AxprFord Motor Company General Prealem In, o'ajj' a, o-i-P. 0. BcZ 2053 11" NWI& Avt. - asi . ]Maaw IDearborn, Michigan 1 Little Falie, is Jeremy I W. neter 3. gleamor.~Pa SABA a.rme 100' ISAllaaearch NaaatacteriagMvIaiue Or- Aircraft RAO-alog Corp. Gesa'.3 ternITebtmnyIsNIOE"sbvThe Garrett Corporation vethpago Ilm, sees~ad k Task 1 Moemrive (A33 cae Am9651 S. Sepuflveda Boulevard Attat Wa. David W. Craig, Jr. latm ke York 3 oleco park, Gallgends 3L'" dAse", California lassbaaica2. Moeag SeatS.Atta, Jerry Glaeeer, Svqereleor asghasrieg Departmant I o r. J. W. I~e SPUR as AWMU 1CUbcebaaical lab -Dapt. 93-17 1 ftw, coe-s Atlas -iera - . 0 eryrmat.cs, Incrporated Mupsi Awedae UIVgrI 11.21nGeeal Atomics Division 20D "o street a"N aidmy ad S"a 260411 2, Oalifea aGeneral Ojenatte Corporatism lockvilUe, acylead I inumuseu, Emeata 1P.O0. Box 606
Mr. M. A. YbeelaMSee Diego 12, Cl~fornia Intertinal Socia Resumee Corp. W. oarl F. DA e, Jr. angen a PorteAtta, Mr.?P. W. Singeoa i Research laboratory irector at mameb 1 vau SaettSee Joe., "Wria. Sor 1e16ia Mau serlew, lag. kgr York 3, kgr YarkSean ead Lubrican Center Attn: Dr. W. B. Leeglele 5 Ftaa"~ kgx I AWowa IGenerat Segleng Laboratory Jack & Metls, A Division atGeneral Electric Cman W. B. A. Dollar, &W. Ede. NW. ON. Allee Vat, Librrn kg llelor 0nserartiem1 River Road Lear, Incorporated uviajen atIG Of Ated. Aeran Corp. 1725 Ive Street, "ato M0cbacectaly, Ney York 110 Icm Avene NO stim streethkise 6, D. C.1Atta: 0. X. Fox, Negago 5 Grand Rapids, 'games I Barst, Cna'ueut 1 r t .Ftt iePe~Mr. L. W. Will Mr. 1. 1. Darr, T. P. or .16v1iu , D/30t8-5 3/5 Sgem a RsearchbGeneral Blectric Company Lar-Romc rivielas Asbtgmtics Dival..essArmtAircraft Aosco"Torbin Dearat Abbe Aced. Moa Amria Aelabl ns. amO pagine AsM5 Ventere AT* 24ria, Ohio 1 923 ft" ea ZR.WI SeaYft Diego 2, 0@alfrla,
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