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FOREWORD
It is possible that your company's economic growth can be increased through the use of new and improved materials, equipment, and techniques developed by the aerospace industry. The results of the research and development efforts can assist you in ach ieving lower unit costs, an improved competitive position, developing new products, and increasing the profits of your business. By assisting you in realizing these goals, ASA's and SBA's Technology Util ization Programs are helping to apply the results of the aero space industry's research and development activities . Thus, the public earns an in creased return on their invest men t in the space effort.
Additional technical information on the material presented can be requested by circling the appropriate number on the Reader Service Card which is included in this compilation.
Unless otherwise stated, neither ASA nor SBA contemplates any patent action on the technology described.
NOTICE This document was prepared under the ponsorship of the ational Aeronau tics and Space Admini tration. Neither the United States Government nor any person acting on behalf of the United States Government assumes any li abi ljty resulting from the use of the information con tajned in this document, or warrants that such use will be free from privately owned rights.
For sale by the National Technical Information Service, Springfield, Virginia 22151. $1.00 CONTENTS
SECTION 1. SEALING TECHNIQUES Rubber and Alumin a Gasket~ Retain FOR CRYOGENIC FLUIDS Vacuum Seal in Hi gh -Temperature EMF Cell ...... 14 Hi gh -Pressure, Low-Temperature Combination Spacer andGasket Electrical Connector Makes Provides Effective Static Seal. . .. . 15 o-L eak Seal , ...... I Plug Repl aces Weld Filler as Seal Bimetallic Devices Help Maintain in Complex Casting...... 16 Constant Sealing Forces Down Static Seal to Accommodate Seat to Cryogenic Temperatures. . .2 Tolerances: 1\ Concept ...... 17 Between-Bearing Shaft Seal: Spiral-Grooved Shaft Seals A Concept ...... 2 Substantially Reduee Leakage Restrained, Pressure-Balanced and Wear...... 18 Pia tic Rubbing Rin g...... 3 VentedGasket ReducesLeakage Cryogenic Seal RemainsLeaktight into Vacuum Chamber . 19 During Thermal Di sp lacement. . .4 Formed-Flange Static Seal: Duct Flange Welded Seal: A Concept . .. 5 1\ Concep( ...... 19 Tem pera t ure-Co m pen sating One-Piece, Self-Sealing Copper Seats Flange Seal ...... 6 and Seals...... 20 Valve Poppet Seal for Cryogenic Double-Serrated Boss Seal...... 21 Flu id s ...... , .7 Seal for Insertable Probes...... 22 Seal for Cryogen ic Fluid Pump. . .. . 8 Integral Le akage Detecti on Port Seal Perform s Over Wid e Temperature for Static Seals...... 22 Range: A Concept ...... 8 Heel -Protected Seal: A Concept . .23 Simplified Orifice Seal Assembly ...... 24 SECTION 2. HIGH-PRESSURE Du al-Purpose Seall\dapter: APPLICA TIONS A Concept ...... 24 Uni\ ersal Conical Seal for Tubing .. . . 25 O-Ring Tube Fillings Form Leakproof Rubber Tubing Makes Hole- Plu g Seal . 26 Seal in Hyd rau li c System ...... 10 Terminal Hermeticall) Seal~ Pressure-Welded Flange ssembly Metal-Sheathed Cable...... 26 Provide Le aktight Seal at Re- duced Bolt Load ' ...... 10 Dynamic Captive Pl astic Seal ...... II Large Di ameter Metal Ring Seal Pre ventsGas Leakage at Hi gh Pres ' ures . .... ' ...... 12
SECTION 3. MODIFICATIONS FOR IMPR OVED PERFORMANCE
Fluid Damping Reduces Bell ows Seal Fati gue Failure ...... 13 Seal Surfaces Protected During A ssem bly ...... 13 Infl atable O-Ring Seal Eases Closing of Hatch Cover: A Concept ...... 14 i-- I SECTION 1. SEALING TECHNIQUES FOR CRYOGENIC FLUIDS
HIGH-PRESSLRE, LOW-TE;\IPER.\TL RE ELECTRICAL CO:'\:'\ECTOR :\I.\I\E '\O-LE \1\ E. \L
An electrica l Feed-through connector i:, de So lder Connection signed uch that ex tremely hi gh pressures and low temperatures contribute to its sealin g properties. This capabilit y is of parti ul ar value ""here elect ri ca ll y act ivated solenoid valves control the flow of cr) ogen ic fI u id s. In previous designs, Plastic Sea I hermetically scaled valves invoh ing an electrical cond uctor bonded to glass VI hich in turn was bonded to the va lve body, Frequently failed due to the disparity in thermal contraction coefficients of the various materials. In thi s design, a 'pherical glass poppet is molded around an integral beryllium-copper terminal screw. When assembled in a connector body seat that has been lapped fo r ze ro leakage, the poppet is held firmly sea ted by pressure from the cryogenic vessel. Additional seating force, provided by tightening the beryllium High Pressure From Cryogenic copper terminal nut, helps prevent le akage Vessel at the poppel. A plastic seal provides a tight fit about th e terminal screw. The plastic has a tendency to shrink at cryogenic temperatures: thus, the fit about the terminal screw becomes tighter as the temperature lo"ve r ', effecting a better seal. The bellville washer compensates for co ld flow in the plastic sea l by deflecting; a characteristic of bellville washe r is that a Ie er deflection will result in greater loading, This device is usefu l in cryogen ic industries ",.here storage vesse ls require self-contained elec trical connections \\ ithin the tank. The device co uld also be used in refri gera ti on sys tems re quiring electrical connections which must with stand environments having greatly varying temperature changes. Source: J. F. We ak ley of North American Rockwell Corp. under contract to Manned SpacecraFt Center (MSC-276)
Circle I 01/ Reader Serrice Card. BL\I ET.-\ LL'I C DEVI CES HELP .\ 1.\ I :'\T.-\ 1:\ CO:'\ST.\:,\T SE . \L1~ G FORCES DOW~ TO CRYOGE:\IC TDI PER . TL' RE Stainless Steel Th is device use - a bi metal Iic approach to com pen ate for the mismatch of thermal coefficients Stainless Steel Bolt of expansion existing in a seal made of -tainless steel and aluminum. Tantalum Washer ----.J Two pieces of stainless steel are vacuum ealed u ing an aluminum O-ring compressed with stainless steel bolts. Since aluminum has a greater thermal cocfficit.:nt of expansion than stainless steel over the critical distance of the compressed O-ring that separates the two surfaces being sealed, the aluminum will contract faster than the stainl ess stcel in passing from room to cryogenic temperature. Compensation for this factor is effected by introducing a washer material, uch as tantalulll, which has a lower thernlal coefficient of expansion than stainless steel (see fig.). The wa~hers are of sufficient thickness that the differential aluminum-stain less teel contraction is balanced by the stainless steel-t antalum differential expansion. This forces the one sea li ng surface to remain in contact with the aluminum O-ring, with only the original contact pressure. Source: W. R. DeBoskey of Melpar. Inc. under contract to Marshall Space Flight Center (M FS-800)
Circle:} 011 Reader Sel'l'ice Card.
BETWEE:,\-BEARI:\'G SHAFT SEAL: CO:\'CEPT A conceptual turbopump seal assembly can be placed between the bearings to reduce the shaft overhang length and overa ll turbopump length. rotating end cap is placed around the turbine end bearing to prevent leakage into the turbine and to upport the mating ring. The end cap also acts a a support for a mating ring located between the pump bearings. The turbine end bearing, supported by a sleeve of smaller inside diameter than the mating ring, pa e in ide 2 the mating ring. The nose-riding seal i located between the bearings, which are lubricated by the pumped fluids. The shaft seal leakage gas is -eparated from the turbine gases by a double labyrinth seal that incorporates an intermediate purge and is located at the outside diameter of the rotating cap. This arrangement removes the seals from the hot turbine region and results in a significant reduction in turbo pump overall length. Source: R. B. Furst of North American Rockwell Corp. Seal Nose Piece under contract to Marshall Space Fli ght Center Rotating End Cap and Mating Ring Mating Ring Mount (M FS- IS I79) Circle J 01/ Reader Se r ~ ' ice Card.
RE TR.-\I~ED, PRESSL ' RE-B . \ L-\~CED PL. \ STlC RL ·BBI.'\G RI.'\G A plastic rubbing rin g locked within a metal housing provides dimensional stabilit y when the ring is subjected to cryogen ic temperatures. The metal housing contains vent passages whi ch are used for pressure balancing under Met?' Housing hi gh fluid pressure co nditions. Prev iously, \.\ hen plastic was required because of its superior rubbing characteri tics with clo e-fitting seal or other components, cold flow of the Vent Passage --4::~~~~~~ plastic was encountered, causing an interference fit whi h resulted in looseness of the ring . The relatively thin sections of the ru bbing Rubbing Ring ring are locked into a metal housing with only the rubbing portion exposed . The stronger metal housing controls the dimensional stability and determines the th ermal contraction rate of Retention the ring at cryogenic temperature. Unde r high Lock Rubbing Surface fluid pressures, the loading and deflectiol~, which result from pressu re differential, are minimized by pressure balancing using the con tro ll ed ve nt passages in th e metal hou in g. Source: R. E. Burcham of North merican Rockwell Corp. under con tract to Marshall Space Flight Center (MFS-2152)
Circle 4011 Reader Senia Card. 3
, _ ----l CRYOGE:\1JC SEAL REM .-\J;\iS LE.-\KTIGHT Dl'RJ"G THERMAL DJSPL.-\CE:\JE"T In a cryoge ni c bubble chamber, th e plas ti c chamber len di spl ace ment rate, ve rsus th at of its mating chamber surfaces, is co mpe nsated fo r by a new co mpos ite sea l. -The dev ice (see fi g.) has an o uter seal co n 'isting of a sin gle-co nvo lutio n a lum inum expa n sio n rin g bo nd ed to th e lens o uter surface, a nd an inner seal co nsisting of a resin-filled aluminum U-ring bonded to the lens inner surface . The outer se al , which perfo rm s the critical task of iso lating the cryoge ni c liquid fr om th e vac uu m space, maintain s it s seal by ben ding ax ia ll y and sliding during both radi al and ax ial len s movement. The inner seal maintai ns slidin g se al co ntact during radi al ex pansion o r con tracti o n of th e lens. The a luminum -ring (inner seal) is bo nd ed to th e lens, and bears on a sil ve r-i ndium ri ng loc ked to th e chamber body. The sil ve r-in d ium ring, which is initiall y ro un d, is squeezed into a V-shaped groove th at co nt a in s a slippery filler rin g made of wove n fa bric coated with res in . This fill er rin g suppo rt s th e legs of th e -ring to permit th e applica ti o n of a la rge sealin g force, but is sli ppery -: no ugh to all ow a rela ti ve radi al di spl acement between th e upp-:r and lowe r -ring legs. The ri ght fl ange of th e co nvo luted a lum in um ex pansio n rin g (o uter seal) is bo nded to th e lens with th e U-shaped co nvolutio n ex tending be twee n th e lens and th e body. The left fl ange re ts o n a le ad ring whi ch is locked to th e chamber body by a n interl ocki ng ann ul a r V-rib Clamping Ring and groove arrange ment. A no tched rin g rest o n th e o uter surface of th e co nvo luted rin g, and a spring rin g bears o n the notched rin g under press ure fr o m a se ri es of loading sc rews. Ring Wh en th e lens ex pa nd s o r co ntracts radi a ll y, th e ri ght fl a nge o f the aluminum ex pansio n rin g whi ch i ' bo nded to and th erefo re moves with the lens, lid es alo ng th e lowe r surface of th e notched rin g. Simulta neo usly, the aluminum R-ring o n th e lower len s surface fl exes at its base to a ll ow radi al shifting of o ne leg in relation to th e oth er. This shifting occurs be 4 ca u e th e upper leg is bo nd ed to th e lens a nd
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th e lowe r leg tend s to sti ck to th e sil ve r-indium rin g. As th e len di spl aces ax ia ll y, th e co nvo luted rin g (o uter sea l) 'a nd notched rin g fo ll ow this movement by bend in g with res pec t to th eir left-h and portions, whi ch a re clamped so lidl y to th e body. Thi ben ding i po ibl e because of the thin sec ti on in th e notched rin g. The ri ght lobe of th e spring rin g fo ll ows th e bendin g notched rin g, a nd maint ains suit abl e ealin g press ure becau e the rounded lobe tcnd s to roll on th c notched rin g surface. The two lobe of th e spring a n; eccen tric with res pec t to th e loading sc rew ce nterlines. Th e left lobe, whi ch is nea rer th e sc rew ce nter lin es, cxe rts mo re axial fo rce th an th e ri ght lobe when th e crews are tightened. The sma ll er force of th e ri ght lobe all ows radi al slippage of th e U-ri ng and co nvo luted expansion ri ng. Th e greater fo rce of th e left lobe maint ain s a po iti ve seal be twee n th e body, th e lead ri ng , and th e ex pansio n rin g. ny chamber atm osphere whi ch does leak past th e -ring (inner seal) is evacuated by a vacuum lin e. Additional de ta il s are con tain ed in U.S. Patent o. 3,238,574, whi ch is ava ilable fr om .S. Patent Office , price 50.50. Source : K . B. Martin , E. G. Pew itt , an d T. H. Field s of High Energy Di vision Argo nne ati onal Laboratory (A RG-96) Pr eassembly-Brazed Sheet St ock OCCT FL. \ ~GE WELDED SEAL: .\ CO~CEPT co nce ptual meth od of sealin g a spheri cal, se lf- a li gnin g fl ange in cryogen ic se rvice in vo lves Swivel Flange welding form ed sheet stock toge th er to form a sea l. The co nve ntio nal gaskets previou Iy lI sed so metimes res ul ted In leakage . The proposed seal has roten ti al applica ti on in in sta ll ati ons where b; ro-Ieakage joints are re quired. The co nfigurati on and co nstru cti on of the we lded seal are shown in igures I and 2. The sea l is fabrica ted by we ldin g or braz in g formed shee t stock to each of th e matin g spheri cal L fl anges . The shee ts are placed so th at they Figure 1. Figure 2. 5 ___J extend outside the flange diameter. The exce metal i then trimmed off and the heets are welded or soldered together, seali ng the flange. Source: J. D. McGroarty of North American Rockwell Corp. under con tract to Marshall Space Flight Center (MFS-2IS6)
Circle 50/1 Reader Service Card.
TEMPERATURE-COMPENSATING FLANGE SEAL Flange - Sea I ing surfaces Through the proper choice of materials and the can be serrated. closing angle of incline, this eal can tolerate any range of temperatures (room temperature to cryogenic and room-to-elevated) likely to be encountered in normal industrial applications. The sketch show a typical application In which the valve is used to pass liquid oxygen, which is alway at cryogenic temperatures. Due \0 compatibility, the only plastic materials uitable for the ga ket are PTFE or Kel-F. Although both of these materials are ubject to cold flow under load at room temperature, such action is precluded here because the gasket is completely trapped within the cavity by the flange and the inclined rings. When the connec tion is chilled down, the gasket, which has a contraction coefficient that is much greater than that of the metal, tends to shrink away from the sealing surfaces of the flanges, and Lower Inclined Ring ca uses a leak. (Low Coef. of Contraction for Cold Appl ication. However, if the lower ring were made of a High Coef. of Exp. for Hot) steel with a very low coefficient of contraction, it would contract very little. If the upper ring were made of aluminum, it would contract con iderably more than the steel ring. Under these conditions, as the upper ring contracts diametrically, it must move up the inclined plane. By se lecting the proper angle, the upper ring can take up the amount of shrinkage of the gasket, keeping it tight against the fl a nges. Conversely, for high temperature application, the lower ring hould be made of a material with a high coefficient of expansion and the upper 6 ring of a low coefficient of expansion material. __ JI The novel feature of the invention is the use of the inclined ring which keep the load on the gasket constant and / or in creasing through a wide temperature range. Source: A. S. Cousin of McDonnell Douglas Corp. under contract to Marshall Space Flight Center (MFS-1 3392) Circle 601/ Reader Service Card.
VALVE POPPET SEAL FOR CRYOGENIC FL IDS A 7075 T-73 aluminum a ll oy spherical body Valve Poppet t 7075-T-73 Aluminum Valve Travel Spherical Body Seal seal mating with a conical 304 stainless steel Poppet poppet sealing surface forms a reliable, low maintenance, low leakage seal for a liquid ---- hydrogen (LH 2) tank valve servll1g a 20.32 cm (8 in.) line . Organic seal material and flat metallic eals have both proven unsatisfactory in a liquid hydrogen environment. The valve poppet (see fig.) is like a stopper 304 SS or plug. Valve opening and closing is accom Conical plished by pneumatic operations (not shown). Seat The valve body i mounted in the bottom of the LH2 storage tank, with the output (bottom) end attached to the drain pipe. The enlarged ketch shows the detail of the sealing surfaces and the direction of flow of the LH2 when the valve i opened. Leakage rales of less than I scc/ ec of G H) at 34.475 k / m2 (50 psi) after 300 open / c1os~ cycles in LH2 have been recorded. Source: V. A. Smith, L. D . Johnson, R. L. Goudrey, and J . A. Aquilar of Aerojet-General Corp. under contract to Space uclear System Office ( UC- 1008 1)
No jilrliJer docl/lIlel/la I iOI/ is a lIailable.
7 St ationary Carbon Ring
1-1---- Bellows
SEAL FO R CRYOGE;\IIC FLelD Pl);vIP A new seal design (see fig.) replaces the secondary sealing surface of a standard, com - Pump Sh aft Center - mercial ly avai lable seal with a taper-faced, Manufacturer's Seal Design stationary carbon ring. This presents only one seali ng surface and appreciably extends the operating life of the seal. The previous design ( ee fig.) used in a cryogenic fluid pump would typically fa il after 40 to 70 hours of operation. The new design, which was intended Flat Faced Rotating to have a minimum 300 hour service life, has Steel Ring performed satisfactorily for 500 hour. Source: C. L. Smith of orth American Rockwell Corp. under contract to Mar hall Space Flight Center Pump Shaft Center - (MFS- 18749)
New Seal Design Circle 701/ Reader Sen'ice Card.
SEAL PERFO RMS OVER WIDE TEMPERATURE RANGE: A CONCEPT A new three piece eal configuration (see fig.) embodies a split ring for minimum thermal expansion effects, a crescent joint for excellent sealing regardle s of wear or circumferential thermal contraction, a coil spring expander with uniform radial expanding action, and a backing ring for free floating action independent of compressor piston cyclic side motion . The configuration wa devi ed for improved seal ing at cryogenic temperatures. The sealing element i a flexible filled plastic ring with a patented crescent joint. The crescent J01l1t i superior to conventional butt or lap joint in its ability to accommodate ring wear and geometry change whi le main taining an excellent joint eal. Thermal con traction of the pli t ring du ring cooldown from room temperature to near liquid hydrogen temperature produces geometry changes similar to wea r-associated change . The sp li t ring requ ire only moderate expander forces com pared to full circle unsplit rings uch as those used 111 several commercial "U" cup-style 8 eals. r--
The coil spring expander provides uniform radial expanding force all along the inner sur ~l face of the piston ring. Several types of spring I construction are applicable: One example would be to deflect the coils of a round wire pnng into a flatted or skewed position, a econd example involves direct radial compression -1st Stage of the coils of a wire or flat strip -wound coil spring. The springs provide con trolled radial expanding force wit hout the preci e manufactur ing control required In fabricating the flat sp rin g expander. The flat pring expander must be formed to a precise non circul ar shape in order to provide reasonably uniform radial ~ r-- expanding force when compre sed from its free elliptical appearance into a true circul ar confined installation. The proposed coil spring 2nd Stage expander provides uniform radial expanding --- load without the tooling, etup, delivery, and possible nonuniform loads associated with the flat spring expander. The full circle backing ring or support ring element provides the opposin g contact urface for radially compressing the coil spring expander. The material for the backing ring can be selected to minimize or counteract relative thermal contraction effects in a given piston / cy l inder / sealing a.ssembly situation. The backing ring element al lows the seal assembly to be radially free floating with respect to the piston. This is an important function ina much as most compressor pistons have some cyclic si de load ing and ide motion. The combination of features summarized above con titutes a unique sealing concept which i expected to provide effective sealing over a range of operatin g temperatures from Coi I Spring Flat Spring Floating Coi I Springs 505 to 1. 0 K ( +450° to - 450°F). Expander Expander The seal configuration is significant in that no known seal can provide such broad tempera ture sealin g capability along with so many cycles of operating life. Source: R. E. Luybli and H. R. Sell of Air Products and Chemicals, In c. under contract to Marshall Space Flight Center (MFS-2 103 2) 9 Circle 801/ Reader Service Card. SECTION 2. HIGH-PRESSURE APPLICATIONS
O-RING TUBE FITTI NGS FORM LEAKTIGHT SEAL I N HYDRA L1C SYSTEM Specia ll y designed fillings, welded to the ends of hydraulic system tubing and then mated, form a leaktight sea l that uses only one O-ring at the joint. Standard flared fittings on the ends of tubing lengths to be joined present inter faces at the two ends where the fittings are coupled to a union. Previously, to provide leak tight joint at the e interfaces, expensive, close to lerance machining of the mating surfaces was necessary. Boss Mount ing The new fillings have flanged male and female sealing surfaces incorporating an annular foi-- -liI--_ _ Tubing groove arrangement for a single O-ring between Weld th e flanges. The flanges are bolted together to produce an effective seal. Possible variations in fillings may include a means for bracket mounting, or for sealin g directly to a com ponent boss. Since the fittings are coupled at only one joint, they tend to be more reliable than standard fittings coupled to a union at two joints. With slight modification, the fittings can be adapted for use with liquids at cryogenic Bulkhead or elevated temperature. Source: orth meri can Rockwell Corp. under contract to Female Marshall Sp ace Flight Center Fitting (M FS-481)
Circle 9 011 Reader Serl'ice Ca rd. Bracket Mounting
PR ESSU RE-WELDED FL.-\~GE ASSEi\ IBLY PROVIDES LEAKTIGHT SEAL AT REDUCED BOLT LOADS Two sets of stainless steel split dies, con taining annular projections on their inner sur faces, are in serted into recesses in the main flan ges, whi ch are made of stainless stee l. connector assembly, consisting of ductile metal plate that are pressure we lded between dies mounted in recessed flanges, provides a le ak tight seal with re latively light bolt loading. Two round plates of type 2S aluminum are fusion we ld ed to the outer peripheries of th e 10
------._------main flange s. An aluminum retaining ring IS positioned in side the bolt circle and ecured with se tscrews to hold the dies in place. The ring has several iewing ports to permit visual inspection of the dies during the bolt tightening operation . As the bolts are tightened under a specified torque, the soft a luminum plate are forced together b<.:tween the dies to effect a pres ure welded seal at the aluminum interfaces. Should the original tensile forces applied to the bolts b(;come relaxed during service, the altern ate load Pressure-Weld path provided by the geometry of the die rings Seam minimizes the amount of displacement in the weld area. To disassemble the conncctor, the bolted flange and retaining ring are removed, and the main flanges arc sli ghtly se parated to al low the weld ing dies to be removed aDd replaced with a set of cutting dies. When the bolts are retightened, the 2S aluminum plates are severed ju t in ide the pre sure weld, and the Aluminum Plate Setscrew connector i disassembled. To reassemble the connector, two other sets of we lding dies with projections placed closer to the center of the connector are used. Cutting dies with a smaller radius are used to Main Flange disassemble th e connector a second time. Die Retaining Ring Source: A. J. Martenson et al of General Electric Co. Detail , Lower Die Section under contract to Marshall Space Flight Center (M FS-640)
Circle 10 Oil Reader Senice Card.
DY~Ai\IIC C. PTIVE PL.-\ TIC SEAL A f1uoroplastic material, held captive between va lve sealing surfaces that approach optical flatnes, provides ze ro leakage to a hi gh-pres sure lin e over a wide temperatu re range, when ubjected to sufficient stress. This technique has been used to control fluid s at pressures of 86, 187 k / m2 ( 12,500 psi) through a tempera ture range of 530 to 14.4 K ( 500· to - 430°F). In a typical appli cation in a modified globe valve, a fluoroplastic sealant material is en- II trapped betwee n in dividua ll y spring-l oaded inner and o uter li p rin gs , the va lve sea li ng urface, Va Ive Actuator and th e va lve actuato r. Sealing press ure is appl ied by the valve actu ator to the f1u oro Inner SI ip Ring pl asti c, whi ch is in a totall y co nfin ed pockel. Force t Because th e pl asti c mate ri al has no escape, and sin ce the co mbined temperat ure and actu ator pressure are below th e embrilliement co m pre sive stra in poi nt of the f1u o ropl astic, it beco mes an inco mpressible fluid hav ing high Valve Seat Entrapped Fluoroplastic viscosity and surface tensio n. This sea li ng tech nique makes the use of "superfinished" va lve sealin g surfaces unnecessary, since the capti ve f1u o ropl ast ic is fo rced into a ny surface im pe r fec ti o ns, achiev ing a no-leakage sea l. Source : E. O. Drye r of o rth American Rockwell Corp. under con tract to Marsha ll Sp ace F li ght Center (M FS-1 2988)
Circle II 0 11 Reader Sel'l'ice Card.
LARGE DIAMETER M ETAL RI. G SEAL PREVE:"JTS GAS LEAKAGE AT HIGH PRESS RES
A grooved, metal ring seal containing elastomer O-rings, in sta ll ed betwee n the access cove r and th e nec k of a high press ure sto rage bo ttle, prov id es a re li able seal fo r gas storage up to pressures of 34,475 kN j m2 (5,000 ps i). As th e access cover i ti ghtened, the metal rin g and th e O-rings are co mpressed, extruding th e O-rings O-Ring fr o m th e grooves so th at they make co nt act with the mating fa ces of the acce cover and sto rage bOllle. Thi s ealin g technique can be readil y adapted to the chemi cal, petroleum , medical suppl y, a nd related ind us trie where hi gh Storage Bottle pressure sto rage bottles and tank s are used. Source : J. H. Middelkoop of orth Ame ri ca n Rockwe ll Corp. under co ntract to Ma rshall Space Flight Ce nter (M FS-I064)
Circle 11 0 11 Reader Serl'ice Card.
12
L_. __ _ ------I I I i SECTION 3. MODIFICATIONS FOR IMPROVED PERFORMANCE
FLUID DAMPI;\IG REDUCES BELLOWS SEAL FATIG E fA I LU RES
Bell ows fati gue Failures have bee n signifi ca ntl y redu ced by a system of interconllected be ll ows in whi ch th e interve nin g cavities are fill ed with a fluid th at reduces th e peri odic det'lecti on ampli tude of th e sealing bell ows. The system is made up of four metal bell ows, consisting o f a main bell ows pair and damping bell ow pair. Each pa ir has a cav ity fill ed with th e damping fluid , and th e pairs are interco nn ected by an orifice in a member of th e Outer Bellows main seal body to permit th e fluid to fl ow fr eely between th em. The main bell ows co n Damping tracts and ex pand s with th e seal as it vibrates. Chamber This movement of the main bell ows ca uses the Section fluid to fl ow back a nd fo rth through th e orifi ce . The fl ow in turn exe rts a co unterforce th at reduces the amplitude of the de fl ection a nd les- ens th e in cid ence of fati gue failure. Different fluid s may be used acco rd in g to en viro nm ental co nditions. For example, liquid nitrogen may be used in cryoge ni c applications, o il for room temperature, or liquid metals for high temperatures. Source: North America n Rock we ll Corp . under co ntract to Marshall Space Flight Cen ter (M FS-S 6S)
Circle I J 0 1/ Reader Serpice Card.
SEAL SU RfACES PROTECTED D U R I ~G ASS E:\IBLY To pro tect th e hi ghl y po li shed seal surfaces at th e entrances of tapped bosses, a surface protec ti on dev ice is placed over th e poli shed urface and removed aft er th e fillin g ha been engaged with th e bo s threads. Pin Tapped Boss split seal surface protector fit s over the chamfered portion of th e boss while th e threaded male fittin g is in se rted into th e tapped boss aga ins t spring tensio n. Wh en seve ral threads have beco me engaged, th e urface protector is withdrawn by pulling it s attaching pins and remov in g the two se pa rated halves . The male fillin g is th en torqued as required to effec t the 13 sea l.
---~ Alth o ugh the sketch depicts an app li cation involving a K-seal surface, the technique lend itself to a va riety of seal types. Source: G. L. Ri chard on of Aerojet-General Corp. under contract lO Space uclear Systems Office (NUC-0067) Nojltrllier dOCl/lllell{({tioll is Gl'ai/ab/e.
INFLATABLE O-RI. G SEAL EASES CLOSI NG OF HATCH COVER: A CO;\lCEPT An inflatable O-ring in serted between the sea lin g surfaces may ease the closing and opening of a rotary-type hater. cover. This would provide a positive means of sealin g without the manual , 1 app li cation of a large compressive force during open in g or closing. Inflatable O-Ring Befo re the hatch cover plate is rotated to the ~~§§ closed position, the ho ll ow O-ring is deflated. After the cover plate is closed, the O-ring is in fI a ted, usi ng a gas p ressu re so u rce, to effect \ a positive seal, even in the presence of surface irregularities. To disengage the cover plate, the hollow O-ring is first deflated. Source: K. J. earyof North American Rockwell Corp. under contract to Manned Spacecraft Center (MSC-740) .Vojltrllier dOCl/lllellta tioll is ami/able.
RUBBER A;\IO AU:M I ;\IA GASKETS RETA\~ VACUUM SEAL \;\1 HIGH-TEiVIPERATl'RE EMf CELL A silicone rubber ga ket and an alumina gasket, each held between two flanges that extend out ward from the edges of the upper and lower halves of an EM F cel l, preserve the cell's vac uum seal wh il e electrical ly isolating its two halves. A heat dissipating flange extends horizontally from the bottom edge of the upper cell half, 14
------and a simil a r fl a nge ex tend fr om th e upper Lower edge of th e lower ce ll half. An alumin a gasket Density Metal Upper Half (Stainless Stee l) is positi oned betwee n th e upper and lower fl a nge 0 th at. it s inner edge is close to th e inner surfaces of th e ce ll halves. A ili cone Insulating rubber gasket is also placed betwee n th e fl anges, Sleeve but outside the alumina gasket. Bolt s hold ing th e two ce ll halves toge th er pass through in Bolt sul atin g sleeve in th e fl anges but out sid e th e silico ne rubber ga ket positi o n. The alumina gasket se rves as th e liquid seal a nd at th e same time elec tricall y se parates th e H igher upper and lower ce ll halves. The fu sed salt Lower Ha lf Density Metal electrolyte in co nt act with the alu mina gasket (Stainless Stee l) may penetrate alo ng it s edges, but such penetra ti ons wi ll fr eeze-seal th emse lve so that neither the electri cal in sul ating effect nor th e vacuum seal maintain ed by the sili cone rubber gasket is di sturbed. The sili co ne rubber gasket i far eno ugh removed fr om th e electrolyte so th at most of th e hea t transmitted alo ng the fl anges is di ss ip ated to th e outside atmosphere befo re it reaches th e rubber gasket. Source: J. C. Hesso n Chemical Engineering Di vision Argo nne National Laboratory (A RG-1 7)
.VIi/ill·llIer dOC l!lI1 ellf{[lioll is ell'ailable.
COi\IBI X T10:'>! SPACER . :'\ 0 CASKET PROVIDE EFFECTI VE STATIC SEAL A new dev ice consists of a closely machined tee l rin g with narrow sealin g land s o n both faces and a thin coati ng of a co mmerciall y availabl e halocarbon (trifluorochl oroeth ylene) polymer. The space r- eal permits high unit loading on th e sea lin g land s with a nomin al torque on th e cla mpi ng bolt. Conventi onal practice has bee n to use one or more space rs with a se parate gasket pl aced in co nt act with each face of each space r. An a se mbl y con Halocarbon Fi 1m sisting of one spacer and two gaskets wo uld prese nt at least four potenti al leak paths an d wo uld permit o nl y relati ve ly low unit loading on th e sealin g la nd s. 15
---~ In th is design, disks of a selected th ick ness steel-pl ate stock are machined and ground to form spacer rings with narrow sealing lands on both faces of each ring. The rings are dis per ion-coated with a uniform film of the halo carbon polymer, the. film is cured, and the sea lin g lands are lapped to eliminate surface irregulari ties and voids. The co ld-flow characteristics of the polymer film enable it to fill minor vo id s in mating surfaces. Several spacer-seal rings of preselected thicknesses may be stacked as required to com pensate for different clearances between mating urface . Becau e of the intimate contact between th e polymer films, a spacer-seal stack will have on ly two potential leak paths. The sealing lands will also bea'r higher unit loads, which will en sure more po itive sea lin g at all points of con tact. Soulce: F. B. Jones of North Ame ri can Rockwell Corp. under contract to Marshall Space Flight Center (M FS-13 97)
Circle 14 01/ Reader Serl'ice Card.
PLUG REPLACES WELD FILLER AS SEAL 1;'11 COMPLEX C \STI:\'G
Plug Expansion Pin Casting chap let used in casting a complex convolute can be drilled ou t and an expandable metal plug (see fig.) inserted to provide the seal, rather than drilling and back-filling with we ld metal. The chaplets are small blocks which support th e mold core used for casting a complex convolute. These chaplets become an integral part of the housing. But they frequently fail to fuse completely with the poured metal, and a leakage path results. Previously, the outer end of the chaplet was drilled out and then backfilled with weld metal. This is an expensive process, requiring X-ray inspection to assure
16 weld integrity. In addition, warpage sometimes occurs during welding, and subsequent heat treatments are required to restore the casting to design dimensions. In the new technique, the mold is supported in the normal manner with chaplets. Follow ing the pouring process, the casting is heat treated to the desired condition. Then the end of each chaplet is drilled out so that a close-fitting expandable plug can be inserted. Source: R. L. Goundrey and C. L. Harris of erojet-General Corp. under contract to Space Nuclear Systems Office (NUC-0049)
Circle 15011 Reader Sen'ice Card.
STATIC SEAL TO ACCOMMODATE SEAT TOLERA~CES: A CO~CEPT A proposed static seal has design charac teristics that permit compensation for flange separation and flange-groove tolerances without large sea l-l eg deflections. With present seals, sign ifi cant deflections, due to tolerances and flange separation, cause considerable deviation from design requirements. I n the suggested design, two deflections take place: one in the seal leg, resulting in tip loading, and the other at the rear of the seal. The deflection in the rear of the seal allows for tolerances and flange separation by keeping the tip loading practically constant. Both the legs and back of the seal are pressure actuated, as illu trated. Source: J. F. Hardy, Ill, of orth American Rockwell Corp. under contract to Marshall Space Flight Center (MFS-18S4) Circle 16011 Reader Sef"l'ice Card.
17 I _J SPIRAL-GROOVED SHAFT SEALS SU BSTANTIALLY RED UCE LEAKAGE AI D WEAR Rotating shaft seals for use in space powe r ys tems mu st operate reli abl y for peri ods of several yea rs with out maintena nce o r attenti on . Ch aracteri sti c requirements include minim al le akage and wear, simplicity of design, minimal weight, adaptability to ex treme tempe ratures, a nd capability of co ntaining pumped fluid s such as liquid sodium or potassium. Conven ti onal shaft seals are in adequate beca use lea kage rates are too hi gh. Therm al and press ure di s tortions re sult in rubbing co ntact, which ca uses wear, co rin g, and in creased leakage rates. A new seal, whi ch incorp orates spiral grooves ( ee fig .) in one or both of th e oppo in g seal fa ces, overcomes th ese problems. The groove induce a pumping action, whi ch displ aces th e interve nin g fluid radi all y in wa rd towa rd th e shaft and co unters th e ce ntrifugal fo rces whi ch tend to di spl ace th e fluid outward. Th e net effect mainta in s hydrodynamic se pa rati on of th e seal faces, thus preve nting seal face co nt act a nd wea r. Spiral grooved seals have been tes ted aga in st co mparable co nve ntional seals for use in a liquid sodium pump operating at over 977 .5 K ( 1300 °F) and 138 kN/ m2 (20 psig). Th e re ults showed th at: ( I) The piral grooved eal leak rate was less th an th e detectable limit, with ge nerall y no detecta ble in crease in leakage afte r pro longed operati on. By compari son, con ve ntional seals had appreciable initial leak rates whi ch as mu ch as doubled with pro longed operation. (2) The spiral grooved eals showed neg li gibl e wear at th e co mpleti on of the test run . (3) Static leakage of th e spiral grooved seals was co mpa rable to th at of th e conven ti onal seals. Source: T. N. Strom, L. P. Lud wig, G . P. A ll en, a nd R. L. John son Lewis Research Ce nter (LEW-I0397) 18 Circle 1701/ Reader Sen 'ice Card. VENTED GASKET RED UCES LEAKAGE INTO VACUl';\1 CHAMBER
A gasket with a vacuum vent facilitate testing Notch liquid hydrogen in sta ll ation va lves. Liquid or gaseous hydrogen t'hat previously le aked pa t the inner rim of the gasket from the main ~ fluid supply line can now be removed. Thus, when liquid hydrogen valves are tested in a vacuum chamber, no fluid leaks into the chamber through the flanges th at attach the va lve to the plumbing. Vented gaskets may be used in any installation where ze ro leakage to the surround in g area i a requirement, and where a low pres sure source is avai lable. The ven ted ga ket is a mod i fied standard gasket constructed from a material which is sui table for use at cryogenic temperatures. Two slots are cut out of the gasket, midway Figure 1. between the inner and outer rim , a::. shown in Figure I. The spaces between the slots a re notched to permit flow between them. A vent Vacuum hole is drilled through one of the flanges, in line Environment Vent Hole with the slot, as shown in Figure 2. T-he vent hole is connected to a low pressure source by means of a standard pipe fitting. If the pressure appli ed to the vent i lower than that of the I vacuum chamber, leakage occurring from the main line pa t the inner rim of the gasket will be drawn off through th e vent. Source: H. Brittan of General Dynamics/Convair under contract to Lewis Resea rch Center (LEW-362) Main Line Gasket NoJi/rtfler do clIIllelllalioll is al'ailable. Figure 2.
FORMED-FLA I GE STATIC SEAL: A CO~CEPT
A formed, sheet-metal sealing-member insert can increa e the sealin g capabilities of aflex seals, eliminating such problems as in ufficient flexing or tip load, and creep relaxation. The conceptual lip seal insert is constructed from formed heet metal, with the sea lin g lips spaced widely apart, as shown in the figure (part 19
___ ..-.J Seal Assemb ly Sea ling Insert
A). The seal is then placed into th e spacer (see part 8). The insert is preset between the two plates which permit abo ut 0.8 % yie ld (see part C), and the surface of the in se rt is placed in co m pression . After the prese t operati on, th e insert is coated o r plated to preve nt damage. Flex i bility of th e in se rt is in cre ased by th e deflection A B of th e web joining the two legs, as a stressed Spin , heat treat, trim. Roll into spacer . mem ber. Parts D, E, and F show ome of th e various in se rt cross sectio ns th at may be used. The sea l ca n be effected by a machined surface as in part A, o r a rolled surface as in parts D and E. In either case, th e curva ture of the sea lin g lip can be sli ght to spread the contact, o r sharp to in sure pl as ti c defo rm ation. In add iti on, mUltiple seal in se rts ca n be arranged in sid e each Preset between C D smooth, flat, hard , other to give seve ral contact areas and to im para lle l p lates . prove the probability of bridgin g a surface defect, Coat or plate after pr eset. as shown in part F. Source: F. . Jennings of o rth American Rockwell Corp. under contract to Mar ha ll Sp ace FI igh t Cen ter (MFS-755)
E F Circle 18 OJ! Reader Sef"l'ice Card. Alternate Inserts (D ,E,F) ONE-PIECE, SELF-SEALING COPPER SEATS AND SEALS
One-p iece annealed copper valve seats and seals have bee n designed th at reduce leakage
Fin Sealing problems in liquid fluorine and hot gas sy tems. Surfaces Previou sly, the seats a nd seals were made of a combination of sta inl ess steel a nd Kel-F materials. However, when the va lves were used in liquid flu orine and hot-gas system s, the Kel-F, though fluorine tabilized, deteriorated quickly, causing le akage. The ann ealed co pper unit are sho wn in stall ed in a va lve. The body half of the valves mu st be se rrated and the fin sealin g surfaces mu st be no rmalize d in o rd er to adapt th e one-piece seats to standard va lve . The use of th ese seats decreases the rewo rk and replacement opera tions normally req uired , and extends the service 20
J life of the va lves in sys tems in vo lvin g co rrosive fluid s. Source : H. W. DeWitt of orth America n Rockwell Co rp. under contract to Marsha ll Sp ace Flight Ce nter (M FS-1 287)
Circle 19011 Reader Sen 'ice Card.
DO LJ BLE SERRATED BOSS SEAL
A so ft metal seal effecti ve ly sea ls again st Standard a cocked co nical ealin g surface. Prev iously, AN814 Union sealin g di ffi culties were experi enced when co nve ntional seals we re used with A D 10050 Standard AN D 10050 boss sealing gla nd s, due to ma nufacturing di s Soft Metal Boss Sealing Gland crepancies be twee n sta nd ard A threaded Seal fillin gs and th e boss ealin g gland s. The new seal (see fi g.) co nsists of a so lid ring of oft mell eable metal. The top sealin g surface has a se ri es of conce ntric V- shaped grooves, with the top edges fo rming a fi at pl ane. The bottom surface also has a series of co ncen tric g rooves, but the edges form a co ni cal plane. The a ngle of th e bo tto m co nical pl ane aprroxima te!> the ang le of th e co ni ca l sealing !> urfacc of th e boss se ali ng gland. When th e seal is ins talled on th e surface of th e boss sealin'g gland and torque is applied on an 8 14 unio n positio ned above th e seal, th e Fluid Pressure sea l shifts slightl y to match th e cocked positi on of th e bas gland . Th e press ure o n the seal ca uses th e so ft co nce ntric sealin g edges to form Illultiple gas-tight sealin g barriers. Source: J. H. Middelk oop Marsha ll Space Flight Ce nter (MFS-S I5)
Circle ]0 0 11 Reader Senice Card.
21
_J SEAL FOR I NSE RT BLE PROBES
A sealing gland uses a soft O-ring to seal and retain thermocouples or other variable immersion sensors, wi th out damaging their protective sheaths by frequent adjustments of immer ion depth. Previously, the surfaces of the probes were degraded due to frictional contact with the gland packing during immersion depth adjust ments and during removal for ca li bration. The use of the O-ring ignificantly in creases the life of the sensors. The sealing gland as embly is shown in the figure. It consists of an MS fitting, modified by facing and counterboring the flare seal. Bushing A bushing is machined to provide the required O-ring deformation and cleranace for the senso r sheath, and a standard A 818 coupling nut and an elastomeric O-ring are included. The O-ring is made from a soft material, the nature of which Elastomeric AN818 Coupl ing depends on the specific se nsor used. The sea ling O-Ring Nut gland as embly may be secured to the vessel by welding, threading, brazing, or any other suitable method. It is advisable to use a new O-ring each time the ensor is installed in o rd er to avoid the tendency for the elastomeric O-ring material to co ld flow under extreme deformation. Source: R. R. Doubleday of orth American Rockwell Corp. under contract to Marshall Space Flight Center (MFS-1524)
Circle]1 01/ Reader Senice Card.
I;\ITEGRAL LEAKAGE DETECTIO~ PORT FOR STATIC SEA LS A port for detecting leakage between primary and secondary sealing surfaces can now be located in the flange seal. Previously, the port wa located in the flange, (see Figure I) a practice which required consid erable machining. In addition, the port location was often inacces sibl e, and the detection tube or pin wa s su - Flange ceptible to being damaged or broken during Seal Figure 1. remova l. 22 The static seal leakage port (see Figure 2) is a permanent part of the flange sea l. Leakage Tube Using the stati c seal as the location for th e leakage detection port provides the following advan tages: The fl ange design I implified; the asse mbl y weight i reduced; the seal design ~~~~I fle xibi lity is in creased; flange machining is re duced; and the as embly in spection and rejection rate is reduced. Leakage Source: G. L. Duse nberry of Detection Port North Ameri can Rockwe ll Corp. Flange FigIJre 2.
Circle II 011 Reader Sen 'ice Card.
HEEL-PROTECTED SE .\L: A CO;\iCEPT
A conceptual heel bumper ca n be att ached to th e outside diameter of a fl ange eal to protect the sealin g surfaces from damage during handl ing prior to in sta ll atio n. Prev iously, seals wae frequently sc ratched, nicked, or dented, with Sealing Surface Heel Bumper the re sult that th ey failed to mainta in an adeq uate seal after in ta ll ation. To protect the con tact portion of a fl ange sea l, a hee l bumper, made fr om PTFE, Kel-F, or a ):=::::w'ft*r:::n"'tiF( ? ,; ? ?uJ, 2 ? ? ? ? , re silien t metal, can be attac hed to th e hee l of th e seal by we ldi ng, fitting, or th e use of an adhesive . Fiqure 1. The hee l bumper, (see Figu re I ) receive the punishment that normally wou ld injure th e sea l. When th e seal is in sta ll ed and the fl ange torqued, the bumper bend back , actin g as a secondary sea l (see Figur ~ 2). The heel bumper concept may be appli ed to sea ls of va rious configurati ons to insure that th ey retain reliable sealin g su rfaces. Source: G. A. Peters and K. Wa rming of North meri can Rockwell Corp. under contract to Marsha ll Sp ace Flight Center (M FS-1884)
Circle lJ 011 Reader Service Card. Figure 2.'
23
I I ------SIMPLIFIED ORIFICE SEAL ASSEi\IBLY
A sp lit PTFE ring can be used as a JOining elem en t between an orifice plate and a seal, in th e flange assembly of a liquid coolant lin e. Previous assembly methods required elaborate machining and the use of adhesives, exposing sealin g -urfaces to possible damage. The sp lit PTFE ring is installed around the inside diameter of the sea l, as shown in Figure I. The rin g is radially compre sed until its outside diameter slips into the inner groove of the eal. The ring is then released and per mitted to expand into the seal groove. Since Figure 2. the PTFE ring is pliable, the orifice plate Split Naflex Seal can be forced through the ring until the ring PTFE Ring engages the retaining groove on the circum ference of the plate. The completed assembly with the flange installed is shown in Figure 2. The assembly functions best when the orifi ce plate used is the same thickness as the sea l, and when the PTFE split ring is replaced each time the orifice plate is changed . o Source: W. J. Mah of o North American Rockwell Corp. under contract to Marshall Space Flight Center Figure 1. (M FS-2043)
Circle::4 Oil Reader Sen'ice Card.
DUAL-PURPOSE SEAL ADAPTER: A CO~CEPT
A conceptual seal becomes an integral part of the adapter or flange, combining half of the typical V-seal configuration with the adapter. In stall ation is thereby simplified and ealing sur face requirements are reduced by 50%. The proposed configuration (see fig.) would provide a one-piece, se lf-cen tering sealing plug or flange for static application in extreme environments, where higher reliability is required and space is limited. Commercially available seals have two sealing Proposed Configuration surfaces and are very difficult to center
24 r------
Two Seal ing Surfaces ~> r ""90 Circle l5 01/ Reader Senice Card. Proposed Configuration l ' ~IVER AL CO;\i I CAL EAL FO R TL.;BI;\iC A uni ve rsal conical seal, developed in proto type, can produce a leak tight seal with only minor modification to tandard flare-t ype tube fittings. The standard fitting I parted and faced to eliminate exces material and re duce the assembly weight. The male portion of the threaded filling is then chamfered to ac commodate the flare. The conical seal is made with a 0.646 rad (37") angle (referenced from both sides). By joining the modified fitting to the sleeve and B-nut, a leak tight eal is achieved . Source: L. E. Grant and B. T. Howland of orth American Rockwell Corp. under contract to Manned Spacecraft Center (MSC- 15865) Conical- .M .\ 'oJill·llIer dOClI lIlelllalioll is available. Seal --~ 25 R BBER TUBING MAKES HOLE-PLUG SEAL A hole-plug seal can be tightened in place without damaging fragile or brittle material, and will form a gas-tight seal up to the rupture Preassembly pressure of the material it seal. Sections of rubber tubing (see fig.) are as embled with a 6-32 machine screw, a hex nut and two washers. The parts are assem bled, the nut is very Iigh tly tightened onto the screw, and the assembly is inserted into the hole to be plugged. The screw Assembly is then tightened until compression of the rubber Installed tubing expands it to fill the hole and provide the seal. The size of the washer at the left (screw head) end of the assembly is slightly larger than that of the hole to be plugged, preventing in advertent movement of the assembly beyond the hole. A sealed cylindrical graphite drum with several holes plugged in this fashion was proof tested to a pressure of 13.79 k / m2 (200 psi). Source: R. W. Lister of Westinghouse Astronuclear Laboratory under contract to Space uclear System Office ( UC-I0020) ,Vo }llf'lher doclIlllelltatiol/ is available. TERMINAL HERM ETICALLY SEALS METAL-SHEATHED CA BLE A metalized ceramic termination seal permits metal-sheathed cables to be integrated into other hermetically sealed electrical assemblies. Commonly used termination seals, such as organic and glass seals, do not function reliably Linder thermal shock and vibration. The male portion of a multiconductor metal sheathed cable termination that can al 0 26 I ------~ r- I be applied to single-conductor metal cable, i shown in the sketch. The male adapter hou ing is designed to mate with any female connector geometric design. The metal sheath is removed to expose a sufficient length of the conductor, Sheath Insulation and the adapter housing is slid over the end. The metalized conductor pilot ceramiC, ca t to Braze or Weld Sleeve the elected geometric design, is in erted over to Cable the conductors and pushed again t the metal cable sheath end. The pilot orients the conductor and supports them to prevent the cable in su lation from flaking out. The ca t metalized header ceramic, with internally brazed short length tubing, is inserted over the conduc Metal ized Pi lot tors. The as embly is a ligned in parallel to Ceramic the metal sheath, and a ll but one of the con Adapter Housing ductor are brazed to the tubing. The adapter hou ing is then slid forward again t the pilot ceramic and brazed or welded as shown. When the de ired level of insulation resistance i ob tained, the remaining conductor is brazed to form the hermetic seal. I n the case shown, the in sulation material was magnesium oxide, the metalized ceramics were aluminum oxide, and the small tubing was nickel. With proper materials and fabrication, this design operates reliably 111 thermal hock, vibration, and hazardou environments .at temperature In excess of 1088.5 K (1500· F). Braze Housing to Metalized Ceramic Source: H. A. Fox of Aerojet-General Corp. under contract to Space Nuclear Systems Office (NUC-10035) .VojilrtherdoclIlIlelllalioll is available. 27 NASA-Langley, 1972 I'iJAIl§A~ - mlI"l ::> \\~-- -- SEALS AND SEALI NG TECHNIQUES NAME ______TITLE ______ COMPANY ______DIVISION STREET ______PHONE ______o CITY ______STATE ______ZI P ______PLEASE SEND ME PRODUCT Mfd. ______INFORMATION ON OTHER TECHNOLOG ICAL UTILIZATION PLEASE CONTACT ME PLEASE SEND SPECIFIC TECHNOLOGICAL PUBLICATIONS AND I NEED TECHNOLOGICAL ASSISTANCE WITH INFORMATION AS CIRCLED SERVICES. 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