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Publication numberUS2394154 A
Publication typeGrant
Publication dateFeb 5, 1946
Filing dateMay 27, 1942
Priority dateMay 27, 1942
Publication numberUS 2394154 A, US 2394154A, US-A-2394154, US2394154 A, US2394154A
InventorsWilliam H Curtis, Russell R Curtis
Original AssigneeCurtis Pump Co
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Booster pump
US 2394154 A
Abstract  available in
Images(2)
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Claims  available in
Description  (OCR text may contain errors)

` Patented Feb. 5, 1946 BOOSTER PUMP William H. Curtis, Los Angeles, Calif., and Russell R. Curtis, Dayton, Ohio, assignors to Curtis Pump Company, Dayton,

Ohio, a corporation Application May 27, 1942, Serial No. 444,644

4 Claims.

'I'his invention relates to centrifugal booster pump assemblies having bubble generating and separating means for acting on liquid material The copendin-g application of Russell R. Curtis,

Serial No. 409,647, filed September 5, 1941, entitled Booster pump, describes and claims a centrifugal pump, now Patent No. 2,306,298, granted December 22, 1942, assembly including a pump having a volute chamber and an outwardlyflared throat converging to for-m a central inlet for the chamber which is in full communication with the liquid to be pumped. The impeller assembly spans the inlet 'and the pumping vanes of the assembly underlie the throat to form therewith open endedpumping channels and opening into the volute chamber at their outer ends. 'I'he copending application further provides an impeller assembly including auxiliary propeller means in or ahead of the mouth of the outwardly flaring the liquid to be pumped and thereby liberating bubbles of gases and vapors from the liquid. These bubbles rise through the liquid along an outwardly aring path and burst at the surface of the liquid to release the gases and vapors.

lsas) tanks. Even if not spaced from the bottom of the fuel.tank, such alining of self-sealing material raises the Veffective bottom level of thle'tank .above the level of the inlet throat and the auxiliary propeller means of the copending application. Since the pump cannot be flxedly mounted on the deformable lining of a bullet proof tank, the inlet throat and propeller assembly of the pump disclosed in the referred to copending applicationwould be disposed below the top of a well having sides formed by the self-sealing lining when the pump is mounted on the rigid outer wall of such a bullet proof tank. Such walls Aof self-sealing material rising about the auxiliary propeller means to a higher level will interfere with the free y outward movement of gas bubbles away from the path of liquid entering the pump, unless, of course, the self-sealing material is not brought into close proximity to the pumpassembly. But

. communicating with the inlet at their innerends this latter arrangement will leave a wide unprotected zone around the pump assembly, which is highly undesirable.

The present invention provides a, pump'assembly including an extended or deep flared throat and an auxiliary propeller means at the level of the mouth of the extended or deep ared throat for agitating and beating The auxiliary propeller means not only beats out entrained gases and vapors from the liquid but also serves to liberate fixed or dissolved gases by generating the same in bubble form.

Thus by the time the liquid has moved along a central downward path into the pumping channels of the pump itis in a stabilized or fully liquid condition so that only fully bubble freed liquid material is pressured into the volute chamber of the pump because the previously separated gas bubbles have risen outside of the central path of the liquid iiowing into the mouth of the flared throat.

The flared throat of the pump assembly of the copending application is not particularly deep or the pump assemblyv so throat. This extension or deepening of the throat and this positioning of the propeller means are arranged to dispose the auxiliary propeller means and the throat mouth at least level with the inner face of the self-sealing material, so that this material will not interfere with the separation and escape of gas bubbles from liquid ventering the pump. In pump assemblies according to the present invention, the self-sealing material'can be brought into close proximity or-contact with that no unpretectedazone is left thereabout. it

The self-sealing material conventionallyfused as a fuel tank lining to protect the tank against leakage due to perforating bullet holes` has but little rigidity and ability to support the weight of fuel contained in thetank. This weightis carried, as a rule, by outer metal walls similar to the walls of conventional fuel tanks. Where, as in the pump assemblies of thepresent invention, the self-sealing lining covers the inside of the fuel tank continuously without leaving any interspace betweenthe lining and the fuel pump assembly, the problem arises of providing a tight joint ,or connection between the tank and the pump assembly so as to preventleaks therebetween and at the same time to hold the lining in place around the pump assembly. d p

For this purpose Athe pumpassemblles according to the present invention are formed with casings having outturned. flanges covering a Portion of the fuel tank wall. A relatively rigid annular member is iaid upon the inner surface of the tank lining about the pump assembly and clamping bolts extend between the annular member and the pump flange to mount the pump on the tank wall. An annular rigidifying ring may also be inserted in the self-sealing lining portion thus clamped betweenthe tank wall and the annular member disposed on the inner face of the lining to rigidify the well dening wall of the lining which receives the -pump throat.

It is, therefore, an important object of the present invention to provide a centrifugal booster pump assembly particularly adaptedl for use 1n fuel tanks of military aircraft having self-sealing fuel tank linings.

A more specific Vobject of this invention is to provide a pump assembly of the type indicated including impeller means and auxiliary propeller means ahead o f the impeller means together with a flared throat delining a liquid path from the propeller to the impeller, and having a mouth extended at least to the level of the inside of the .fuel tank lining.

Another specific object of the invention is to provide a pump assembly of the type indicated for seating in an aperture through a self-sealing tank lining andprovided with appropriate flanges and annular members for effecting a tight' connection between the pump assembly and the tank.

Other and further objects and features of this invention will be apparent to those skilled in the art by the following detailed description of the annexed sheets ofy drawings which by way of preferred examples show several embodiments of the iinvention.

n the drawings:

I with parts shown in plan view, taken along the line IV-IVof Figure 3.

Like parts aredesignated with the same reference numerals in all the figures As shown onthe drawings: In Figure l .the reference numeral I0 designates generally a fuel tank vented as at I0a, and

lined 'internally with self-sealing material I-l which may have a laminated structure. The bot` tom wall of the tank and the bottom tank lining are pierced by registering circular apertures defining a well IIa. The tank bottom margins I2 around this well or passage are thickened considerably relative to the walls of the tank I 8.

A booster pump I3 of the centrifugal type is mounted on the tank to extend into the well or passage IIa and includes a casing I4 defining a volute chamber I5. a discharge outlet I6 for the volute chamber and a shaft housing I1. The casing I4 is connected to the casing of an electric motor (not shown) which drives ashaft I8 in the Figure 1 is a fragmentary vertical cross-sec- 10 bedded a metal ring 2Iservlng to rigidify the iining margin about the well Ila. The rings and 2l, the lining margin about the well I Ia, the tank bottom margin I2 and the casing flange I9 are all apertured to receive studs 22'therethrough at spaced intervals. The studs are threaded into the ring 20 at their inner ends and receive nuts 23 on their outer ends. When these nuts are tightened, a tight Seal is formed between the pump, the fuel tank bottom and the lining. For added sealing effect, an annular gasket 24 may be interposed between the fuel tank bottom margin I2 and the top face of the casing to extend over flange I9.

The top face of the pump casing I4 has a.cir cular opening 21 therein. A throat ring 28 is mounted on the top faceof the casing and is secured to the casing by means such as screws 29. The periphery of the throat ring projects above the top face of the casing I4 and forms a pilot portion snugly tting in the aperture in the bottom wall of the tank. The throat ring 28 also seats in the opening 21 of the casing and extends upwardly beyond the level of the lining .II and has an aperture 30 therethrough for joining the interior of the tank I8 with the volute chamber I5. The aperture 38-ilares outwardly to provide converging inlet for the pump I3 having a wide mouth with horizontally outturned lips.

The throat ring 28 receives the flange 32 of a cylindrical screen 33 having a screened top wall 34 spaced materially above the bottom of the lining Il. The flange 32 may suitably be interposed between the throat ring 28 and the heads of the screws 29 for being secured by the latter. The screen 33 carries an inverted frusto-conical hollow shield 35 in spaced relation above the throat ring. .As shownin Figure l, the throat ring 28 extends upwardly into the inner screenv space.

The booster pump I3 has an impeller-propeller assembly indicated generally at 31. This assentibly includes a disk or flange portion 38 spanning the inlet or aperture of the throat ring and communicating freely around the periphery thereof with the inner rim of the volute chamber I5.

Curved pumping vanes 33 are mounted on the iiange 38 around the periphery thereof to underlie the throat ring 28. These pumping vanes define with the throat ring 28 and the flange 38 open ended pumping channels communicating at their outer ends with the volute chamber I5 and at their inner ends with the inlet of the throat ring.

The impeller flange 38 is integral with an irnpeller hub 48 slidingly embracing the shaft I8 and keyed thereto in driven relationship. TheA i1. A seal S may be associated with p abutment means (not shown) on the shaft I8 by a nut 43 threaded over the threaded free end of the shaft I8. The impeller hub 40 and sleeve 4I are keyed (not shown) to the shaft I8 and the propeller 42 is locked to the -sleeve (not shown) so that both the impeller and propeller are driven .by the shaft.

The free end of the shaft I8 and beyond the throat ring 28. The impeller sleeve 4I is so proportioned andso positioned on the shaft that the blades of the propeller 42 are disposed above the throat ring 28 with the lower propeller blade edges on a level with the top of the throat ring and below the shield 35.

The propeller 42 acts as a low pressure liquid pump urging several times as much liquid toward the impeller 39 as may pass through the latter. For instance, the propeller may, at normal low pressure operating speeds, deliver approximately '7200 pounds of fuel per hour to the impeller, if operating at an assumed slippage factor of 0.60. This delivery to the impeller is to be compared with a probable maximum output of 1800 pounds extends through per hour from the impeller to the volute. The

excess of liquid fuel amounting to about 5400 pounds per hourmust escape in a direction other than through the impeller. 'There is no other avenue of escape than the lateral path aorded by the space, outside of the propeller tips, above the contoured throat and below the. sloping 'outsides of the shield 35.

The high slippage factor stated herein above is indicated by the severe beating action of the propeller that has been observed. I'his beating action is accomplished by cavitation, which effects volution of bubbles of dissolved vgases and also vapors from lighter fuel frac-tions. The bubbles thus generated tend to rise and are therefore preferentially carried along by the fuel streaming radially outwardly between the coptoured throat and the shield rather than by the fuel flowing downward into the impeller space.

Thus the propeller 42 creates a whirlpool in the liquid'in the tank with the liquid flowing down through the shield 35 and with the bubbles.

rising outside of the shield tothe surface of the liquid.

The position of the flared or belled lip of the throat ring 28 at least level with the inner face of the lining and the position of the propeller 42 above or beyond the inner face level of the lining, will eliminate interference with the outward course of bubbles effected by the propeller.

Improved flow of liquid and improved bubble separation are obtained by the bell shape of the the screen they become larger so that they can not re-enter the screen.l

The pump assembly of Figures 3 and 4l includes a pear shaped mounting member having two apertures therethrough. The mounting .member 50 overlies the inner face oi the lining with the larger aperture of the member in registry with a well 5I deiined by an aperture through the lining II and the tank bottom wherein the pump is seated. The second and smaller mounting member aperture forms a discharge outlet for the pump, being formed as a pipe 52 extending transversely to the plane of the mounting member up through the fuel tank and down into the i volute chamber I5 through an aperture 53y in the 'casing I4 has an outturned flange-54. about the volute chamber I5 with edges co-extensive with t the edges of the mounting member 50 for mounting on the bottom wall of the tank I 0. The flange 54 receives screws 55 at spaced intervals therearound which are threaded into blind tapped wells in the mounting member 50. 'Ihe mounting member overlaps an outturned flange 545 on the throat ring to hold the throat ring in place .when the screws 55 are threaded home.

A rigidifying member 51 having apertures larger than the Well 5I and the aperture 532 may be embedded in the lining II about the well 5I and the aperture 53. A gasket 58 having holes adapted to register with the well 5I and the aperture 53 may be interposed between the outside tank bottom and the flanges 54 and 56.v

Apart from the facts that the discharge line of the pump of Figures 3 and 4'extends upwardly through the fuel tank and that the connections between the fuel tank bottom and the pump have been modified accordingly, the construction and functioning of the pump of Figures 3 and 4 are essentially similar to those of the pump of Figures 1 and 2.

It will be apparent from the foregoing that the present invention provides a fuel tank-booster pump assembly including a fuell tank lined with formed by apertures through the tank lining and y the tank bottom. The pump includes an impeller throat ring lip, the disposal of the propeller blades with their lower edges flush with the top of the belled lip, the provision of propeller blades terminating short of the belled lip but outside of the shield 35, and the provision of a relatively deep shield with steeply sloping walls. For example, -the bell shaped lip gathers liquid over a large area and the throat then converges at a rate that will not require increased head pressure for high capacity liquid flow. 'I'he bvbblesare ldirected outwardly from the incoming liquid 'over the lip and the shield prevents entrainment of the bubbles in the incoming liquid. As any bubbles rise in the screen, they must pass around the outer face of the shield in isolated relation from the incoming liquid passing through the shield. Most of the bubbles, however, are carried by the laterally streaming fuel outwardly through the screen and as they rise outside of underlying the tank bottom wall anda propeller having a larger pumping capacity than the impelleroverlying the tank lining as well as a throat member extending through said well and defining a liquid path from the propeller to the impeller and permitting unobstructed outward movement of excess fuel moved by the propeller toward the impeller. This laterally and outwardly streaming fuel carries with it the bubbles generated by the cavitating action of the propeller. Specifically, the pump impeller and the pump propeller are aligned but are separated by appropriate spacing means dimensioned in proportion to the thickness of the tank lining, as is also the throat member of the pump, and the propeller is disposed at a level immediately above the top of the throat member, which is ared to'dene horizontal lips thereabout extending beyond the ends of the propeller blades.v Further, the pump has an outturned flange underlying the margins of the tank bottom about the pump well, and a separate mounting member is disposed on topv This correlation between the structure of the fuel tank and the construction of the fuel pump makes for efficient removal of bubbles and xed gases from liquid fuel handled by the pump while affording protection against leakage due to perforating bullet holesfrom the Whole tank wall, wherein the pump is securely and tightly mounted. Many details of construction may be varied within a wide range without departing from the ended passage, a rigidifying ring embedded in said self -sealing material around said aperture therein, a pump casing closing the bottom end of said passage and having a portion underlying the bottom wall of the tank, a rigid mounting ring in said tank overlying the bottom Wall of the liner bag around the aperture therein, and bolt means extending through said ring embedded in the liner bag and clampingly connecting said mounting ring and said portion of the pump casing underlying the tank wall to suspend the pump casing on the bottom wall of the tank.

2. In a fuel system, a fuel tank, relatively thick self-sealing material lining said tank, Said tank and lining having aligned apertures therethrough ing said throat ring in said first passageway, and connection means extending through said mounting ange, said tank and said lining into said mounting member for securing the pump casing to the tank and for sealingly clamping the lining against the tank.

3. In a fuel system, a fuel tank, a liner bag in said tank composed of self-sealing material, aligned apertures through the bottom of the liner bag and tank forming an open-ended passage, a centrifugal pump closing the outer end of said passage and having a mounting flange underlying the tank around the aperture thereof, mounting means in saidbag overlying the portion of the bag immediately surrounding the aperture therethrough, a throat ring on said pump having an inlet mouth-defining portion projecting through said passageway into the interior of said bag in spaced relation from the ba'g together with a pilot portion surrounding said inlet mouthdefining portion in snug seating engagement with the aperture-defining wall of the tank, and clamping bolts extendingthrough the mounting ilange,

the tank and the bag into the mounting means for clamping the pump and liner respectively to the outer and inner faces of the tank whereby the snug-fitting relationship of the 'pilot portion and 'the tank will hold the pump casing against cooking relative to the tank.

4. In combination a tank, a bag of relatively soft self-sealing material lining said tank, aligned forming rst and second passageways, a mounting member in said tank overlying the lining having an aperture aligned with the rst passageway, an upstanding discharge nipple integral with said mounting member having a depending portion projectingthrough said second passageway and extending beyond the tank, a pump casing 'havl ing a first aperture, a second aperture, and a mounting iiange therearound, a throat member on said pump casing defining an inlet for said rst aperture thereof and extending through said first passageway into said tank in spaced relation from the lining, said second aperture ofy the pump casing snugly receiving said extending portion of the discharge nipple and centrally alignapertures through said bag and tank providing an open-ended passage, a rigidifying ring embedded in said bag around the aperture thereof, a pump casing closing the outer end of said passage and having a portion overlying the tank, a rigid mounting ring in said bag around the aperture thereof, and bolt means extending through said ring embedded in the bag and clampingly connecting said mounting ring and said portion of the pump overlying the tank to suspend the pump casing on the tank and to seal theginterior of the bag from the interior of the tank by sealingly drawing the bag against the tank around the aperture in the bag.

WILLIAM H. CURTIS. RUSSELL R. CURTIS.

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2544990 *Jan 4, 1947Mar 13, 1951Vickers IncPower transmission
US2628745 *Jan 12, 1946Feb 17, 1953Daniel MurphyPump apparatus
US2775348 *Sep 30, 1953Dec 25, 1956Taco Heaters IncFilter with backwash cleaning
US3014623 *Jan 29, 1958Dec 26, 1961Borg WarnerMotor and pump mounting means
US3090421 *Mar 25, 1957May 21, 1963Daimler Benz AgFuel supply system for an internal combustion engine
US3409135 *Nov 4, 1966Nov 5, 1968Acf Ind IncReplaceable filter liquid pump
US3610416 *Aug 22, 1969Oct 5, 1971Julius L EnglesbergPump for liquids
US4853125 *Jun 11, 1987Aug 1, 1989Toyoda Gosei Co., Ltd.Fluid chamber having a tubular filter and a securing recess for mounting the same
US5357883 *Jun 24, 1992Oct 25, 1994Wic Inc.Method and apparatus for spreading a liquid slurry
US5595397 *Oct 25, 1994Jan 21, 1997Wic Inc.Method and apparatus for spreading a liquid slurry
US5772082 *Jan 17, 1997Jun 30, 1998Depault; MarcelMethod and apparatus for spreading a liquid slurry
US6890161 *Mar 31, 2003May 10, 2005Assistive Technology Products, Inc.Disposable fluid delivery system
US8372278 *Mar 21, 2012Feb 12, 2013GM Global Technology Operations LLCLiquid fuel strainer assembly
US8851122 *Jun 29, 2011Oct 7, 2014Airbus Operations (S.A.S.)Aircraft including a fuel pump fastened to a tank panel
US20120006943 *Jun 29, 2011Jan 12, 2012Airbus Operations (S.A.S.)Aircraft including a fuel pump fastened to a tank panel
US20130092267 *Oct 18, 2012Apr 18, 2013Airbus Operations LimitedFuel tank installation
USRE37863 *Jun 30, 2000Oct 1, 2002Marcel DepaultMethod and apparatus for spreading a liquid slurry
EP0579540A1 *Jul 13, 1993Jan 19, 1994COMPAGNIE PLASTIC OMNIUM Société Anonyme dite:Intake assembly with integrated filter for fuel tank
EP0856658A2 *Jul 31, 1997Aug 5, 1998Mitsubishi Denki Kabushiki KaishaVehicular fuel supplying apparatus
WO2004088136A2 *Mar 29, 2004Oct 14, 2004Assistive Technology ProductsDisposable fluid delivery system
Classifications
U.S. Classification222/383.2, 415/143, 415/217.1, 415/108, 210/416.4, 415/121.3, 210/172.3
International ClassificationF02M37/20, F02M37/10, F04D9/00
Cooperative ClassificationF04D9/002, F02M37/10, F02M37/20
European ClassificationF02M37/20, F02M37/10, F04D9/00B2