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US3680977A - Framed impeller - Google Patents

Framed impeller Download PDF

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Publication number
US3680977A
US3680977A US50052A US3680977DA US3680977A US 3680977 A US3680977 A US 3680977A US 50052 A US50052 A US 50052A US 3680977D A US3680977D A US 3680977DA US 3680977 A US3680977 A US 3680977A
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Prior art keywords
ring
groove
duct
impeller
shoulders
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US50052A
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Denis Rabouyt
Charles Louis Marsot
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/001—Shrouded propellers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • An impeller with a rotor carrying a set of fan blades has a circular duct of streamlined profile surrounding the rotor blades, the latter having their tips interconnected by a ring receivedwith small clearance in an annular groove on the inner duct periphery so that this periphery is flush with the inner ring surface.
  • Elastic inserts in the gap between the ring and the duct may be used to minimize or eliminate the intervening clearance.
  • the intensity of a flow generated by such an impeller can be enhanced by channeling this flow through a short duct or shroud of air-foil cross-section presenting a streamlined profile to the fluid stream, this duct framing the rotor of the impeller whose blades terminate at a short distance from the inner duct periphery.
  • the duct has the dual purpose of concentrating the flow by converging in the direction of fluid passage and of minimizing turbulence in a zone surrounding the rotor blades with resulting increase in operating efficiency.
  • the latter function calls for a minimum spacing between the blade tips and the stationary duct, yet a certain tolerance must always be maintained to allow for unavoidable eccentricities of the rotor mounting with reference to the duct axis.
  • our invention aims at providing an improved impeller of the framed-rotor type wherein peripheral turbulence is effectively suppressed with avoidance of the aforestated drawbacks.
  • A- more particular object is to provide a combination of a flow-guiding duct with a ring-reinforced rotor enabling the utilization of the entire cross-sectional area of the flow channel defined by the duct for the generation of forced circulation or thrust.
  • the inner duct periphery with an annular groove receiving, with small clearance, a ring interconnecting the free ends of the blades, the ring preferably having a substantially flat inner peripheral surface flush with the inner duct periphery so as to form part of a channel wall free from major discontinuities.
  • the ring may be a relatively thin ferrule of cylindrical shape somewhat smaller than the relative shallow groove.
  • this gap may be further reduced or eliminated with the aid of preferably elastic sealing means in actual or potential contact with the rigid ring.
  • the latter may be formed with one or more outwardly directed radial flanges which, in co-operation with an insert or filler interleaved therewith, lengthen the flow path around the rotor periphery and which could also be used to shield a set of swivel heads in the ring facilitating an adjustment of the blade pitch.
  • the problem of fitting the blade ring in the groove of the duct may be solved in various ways, as by making the duct in several axially or peripherally adjoining sections or by molding the duct directly about the rotor. If the ring is a sufiiciently deformable ferrule, it could also be'snapped into the groove of an integrally constructed duct.
  • FIG. 1 is an axial view, partly in section, of an impeller embodying-our invention
  • FIG. 2 is a face'view of the impeller shown in FIG. 1;
  • FIG. 3 is a fragmentary sectional view taken on the line III III of FIG. 2 but drawn to a larger scale;
  • FIGS. 4 and 5 show, on a still larger scale, modifications of the assembly illustrated in FIG. 3;
  • FIGS. 6 and 7 are enlarged views generally similar to FIG. 3, showing further modifications.
  • FIGS. 8 and 9 are views similar to part of FIG. 5, illustrating yet other variants.
  • FIGS. 1-3 we have shown an impeller which may be used as an air screw on an aircraft not further illustrated and which comprises a motor 1 driving a streamlined hub 2 of a rotor having several (here four) propeller blades 3 radiating from that hub.
  • the free ends of these blades are interconnected by a ring 4 in the form of a thin ferrule received within an annular groove 8 on the inner peripheral surface 7 of a duct or shroud 5 of streamlined cross-section.
  • Duct 5 is supported by struts 6 on the stationary engine housing of motor 1.
  • the inner peripheral surface 4a of ring 4 is flush with the inwardly convex surface 7 of duct 5 so as to define therewith a substantially continuous channel wall.
  • the circular edges 10 of ring 4 are closely spaced from similar edges 9 of a sheet-metal sheath 5a which envelops the body of duct 5 and extends slightly past the sides of groove 8.
  • FIGS. 1-3 The thrust of the propeller shown in FIGS. 1-3 is somewhat diminished by an equalizing flow passing through the narrow gap between edges 9 and. 10 from the high-pressure region behind the rotor blades 3 to the low-pressure region ahead of these blades.
  • This bypass path canbe blocked, as shown in FIG. 4, by the provision of a seal generally designated 11.
  • Seal 11 comprises a pair of strips l2, 13, of rubber or other elastomeric material, mounted on a pair of shoulders 5, 5" which are formed by the projecting edges of sheath 5a inside groove 8 so as to bear upon the outer peripheral surface of ring 4.
  • FIG. 4 also shows a screw 24 serving to fasten this ring to a corresponding blade 3.
  • FIG. 5 we have illustrated a modified ring 4 of U- profile formed with two radial flanges l4, 15 received in the groove.8. Sealing strips 16 and 17, similar to those of the preceding embodiment, bear upon the outer surfaces of these flanges at locations spaced radially outwardly from the supporting shoulders 5,5".
  • the flanged ring 4' co-operates with a tripartite insert, also preferably of elastic material, consisting of three labyrinth sections 18, 18' and 18" axially separated by narrow gaps which receive the ring flanges l4 and I5.
  • an elastic filler 19 of polyurethane foam or other cellular material forms similar annular recesses 19a, 19b to accommodate the flanges l4 and 15. a
  • FIGS. 8 and 9 illustrate the possibility of using a flanged ring 4' as a journal bearing for the rotor blades 3 whose pitch can be controlled from within the hub 2 (FIG. 1), by conventional means not shown, and which terminate in studs 20 (FIG. 8) or 20' (FIG. 9) received in respective sockets 22, 23.
  • These sockets may be formed by individual bosses, as in FIG. 8, or by a continuous hollow ridge, as in FIG. 9, with interposition of bearing sleeves 25, 25' around the studs.
  • FIG. 9 shows the bearing sleeve 25' as a spherically convex bushing 21 on stud 20'.
  • Antifriction layers e.g. of Teflon, not shown, may be inserted between these bearing sleeves and the coacting stud surfaces.
  • An impeller for the circulation of an ambient fluid comprising a rotor with a set of blades radiating from an axis; a circular duct of airfoil cross-section fixedly centered on said axis, said duct having an inner periphery provided with an annular groove and lined with a sheet-metal sheath projecting beyond the edges of said groove to form a pair of annular shoulders within said groove; a ring centered on said axis and interconnecting said blades, said ring projecting radially into said groove with small axial clearance from said shoulders; and sealing means in said groove bridgeing said axial clearance, said sealing means including a pair of elastic annular strips mounted in said groove on said shoulders and extending therefrom into contact with said ring.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Abstract

An impeller with a rotor carrying a set of fan blades has a circular duct of streamlined profile surrounding the rotor blades, the latter having their tips interconnected by a ring received with small clearance in an annular groove on the inner duct periphery so that this periphery is flush with the inner ring surface. Elastic inserts in the gap between the ring and the duct may be used to minimize or eliminate the intervening clearance.

Description

United States Patent Rabouyt et al.
1151 3,680,977 [451 Aug 1,1972
[54] FRAMED IMPELLER [72] Inventors: Denis Rabouyt, 6 bis rue Blanche Clamart department des l-Iauts de Seine; Charles Louis Marsot, 152 Champs Elysees department de Seine 75, both of Paris, France 221 Filed: June 29,1970
21 Appl. No.: 50,052
[30] Foreign Application Priority Data July 1, 1969 5 France ..6922183 [52] US. Cl. ..415/172, 277/65, 415/210 [51] Int. Cl. ..F0ld 9/00, F16j 15/38 [58] Field of Search ..415/170, 171,172, 173, 174, 415/210; 277/65, 95
[56] References Cited UNITED STATES PATENTS 1,876,067 9/1932 Lorenzen ..415/172 10/1960 Stalker ..415/172 2,956,733 3,112,610 12/1963 Jerger ..60/221 3,306,223 2/1967 Liebig ..415/173 A 3,531,214 9/1970 Abramson ..415/119 3,519,367 7/1970 Lariviere ..415/185 FOREIGN PATENTS OR APPLICATIONS 314,062 l/l934 Italy ..415/172 Primary Examiner-l-lenry F. Raduazo Attorney-Karl F. Ross [57] ABSTRACT An impeller with a rotor carrying a set of fan blades has a circular duct of streamlined profile surrounding the rotor blades, the latter having their tips interconnected by a ring receivedwith small clearance in an annular groove on the inner duct periphery so that this periphery is flush with the inner ring surface. Elastic inserts in the gap between the ring and the duct may be used to minimize or eliminate the intervening clearance.
3 Claims, 9 Drawing Figures PATENTEDAUB' 1 I972 SHEET 1 OF 3 v Y Denis Rabouyf Charles Louis Marsof I N VEN TORS PATENTEDAUB 1 I972 SHEET 2 BF 3 Denis Rabo Charles L. :INVE
uyf Marsof N TORS'.
Attorney P'A'TENTEDAUQ 1 I972 SHEH 3 UF 3 FIG. 9
FIG. 8
Denis Rabouyf Charles L. Marsof I N VEN TOR S.
Attorney FRAMED IMPELLER Our present invention relates to an impeller, such as a blower or fan, for circulating air or some other ambient fluid.
The intensity of a flow generated by such an impeller can be enhanced by channeling this flow through a short duct or shroud of air-foil cross-section presenting a streamlined profile to the fluid stream, this duct framing the rotor of the impeller whose blades terminate at a short distance from the inner duct periphery. The duct has the dual purpose of concentrating the flow by converging in the direction of fluid passage and of minimizing turbulence in a zone surrounding the rotor blades with resulting increase in operating efficiency. The latter function, of course, calls for a minimum spacing between the blade tips and the stationary duct, yet a certain tolerance must always be maintained to allow for unavoidable eccentricities of the rotor mounting with reference to the duct axis.
Attempts to minimize this tolerance by interconnecting the free ends of the blades with the aid of a concentric ring inside the duct have not solved the problem. Though such a ring reinforces the rotor structure, it does not eliminate existing eccentricities and requires, therefore, a certain radial spacing from the duct in order to prevent contact between the two relatively rotating bodies. Moreover, the presence of such a ring diminishes the effectiveness of the rotor, by reducing the cross-sectional area of the channel swept by the blades, and creates added discontinuities giving rise to further turbulence. I
Thus, our invention aims at providing an improved impeller of the framed-rotor type wherein peripheral turbulence is effectively suppressed with avoidance of the aforestated drawbacks.
A- more particular object is to provide a combination of a flow-guiding duct with a ring-reinforced rotor enabling the utilization of the entire cross-sectional area of the flow channel defined by the duct for the generation of forced circulation or thrust.
These objects are realized, in accordance with our present invention, by providing the inner duct periphery with an annular groove receiving, with small clearance, a ring interconnecting the free ends of the blades, the ring preferably having a substantially flat inner peripheral surface flush with the inner duct periphery so as to form part of a channel wall free from major discontinuities.
In the simplest case, the ring may be a relatively thin ferrule of cylindrical shape somewhat smaller than the relative shallow groove. In a more sophisticated arrangement, designed to throttle the fluid flow through the meandering gap between the ring and the groove wall, this gap may be further reduced or eliminated with the aid of preferably elastic sealing means in actual or potential contact with the rigid ring. The latter may be formed with one or more outwardly directed radial flanges which, in co-operation with an insert or filler interleaved therewith, lengthen the flow path around the rotor periphery and which could also be used to shield a set of swivel heads in the ring facilitating an adjustment of the blade pitch.
The problem of fitting the blade ring in the groove of the duct may be solved in various ways, as by making the duct in several axially or peripherally adjoining sections or by molding the duct directly about the rotor. If the ring is a sufiiciently deformable ferrule, it could also be'snapped into the groove of an integrally constructed duct.
The above and other features of our invention will be described in detail with reference to the accompanying drawing in which:
FIG. 1 is an axial view, partly in section, of an impeller embodying-our invention;
FIG. 2 is a face'view of the impeller shown in FIG. 1;
FIG. 3 is a fragmentary sectional view taken on the line III III of FIG. 2 but drawn to a larger scale;
FIGS. 4 and 5 show, on a still larger scale, modifications of the assembly illustrated in FIG. 3;
FIGS. 6 and 7 are enlarged views generally similar to FIG. 3, showing further modifications; and
FIGS. 8 and 9 are views similar to part of FIG. 5, illustrating yet other variants.
In FIGS. 1-3 we have shown an impeller which may be used as an air screw on an aircraft not further illustrated and which comprises a motor 1 driving a streamlined hub 2 of a rotor having several (here four) propeller blades 3 radiating from that hub. The free ends of these blades are interconnected by a ring 4 in the form of a thin ferrule received within an annular groove 8 on the inner peripheral surface 7 of a duct or shroud 5 of streamlined cross-section. Duct 5 is supported by struts 6 on the stationary engine housing of motor 1.
As best seen in FIG. 3, the inner peripheral surface 4a of ring 4 is flush with the inwardly convex surface 7 of duct 5 so as to define therewith a substantially continuous channel wall. The circular edges 10 of ring 4 are closely spaced from similar edges 9 of a sheet-metal sheath 5a which envelops the body of duct 5 and extends slightly past the sides of groove 8.
The thrust of the propeller shown in FIGS. 1-3 is somewhat diminished by an equalizing flow passing through the narrow gap between edges 9 and. 10 from the high-pressure region behind the rotor blades 3 to the low-pressure region ahead of these blades. This bypass path canbe blocked, as shown in FIG. 4, by the provision of a seal generally designated 11. Seal 11 comprises a pair of strips l2, 13, of rubber or other elastomeric material, mounted on a pair of shoulders 5, 5" which are formed by the projecting edges of sheath 5a inside groove 8 so as to bear upon the outer peripheral surface of ring 4. FIG. 4 also shows a screw 24 serving to fasten this ring to a corresponding blade 3.
In FIG. 5 we have illustrated a modified ring 4 of U- profile formed with two radial flanges l4, 15 received in the groove.8. Sealing strips 16 and 17, similar to those of the preceding embodiment, bear upon the outer surfaces of these flanges at locations spaced radially outwardly from the supporting shoulders 5,5".
According to FIG. 6, the flanged ring 4' co-operates with a tripartite insert, also preferably of elastic material, consisting of three labyrinth sections 18, 18' and 18" axially separated by narrow gaps which receive the ring flanges l4 and I5.
As shown in FIG. 7, an elastic filler 19 of polyurethane foam or other cellular material forms similar annular recesses 19a, 19b to accommodate the flanges l4 and 15. a
FIGS. 8 and 9 illustrate the possibility of using a flanged ring 4' as a journal bearing for the rotor blades 3 whose pitch can be controlled from within the hub 2 (FIG. 1), by conventional means not shown, and which terminate in studs 20 (FIG. 8) or 20' (FIG. 9) received in respective sockets 22, 23. These sockets may be formed by individual bosses, as in FIG. 8, or by a continuous hollow ridge, as in FIG. 9, with interposition of bearing sleeves 25, 25' around the studs. FIG. 9 shows the bearing sleeve 25' as a spherically convex bushing 21 on stud 20'. Antifriction layers (e.g. of Teflon), not shown, may be inserted between these bearing sleeves and the coacting stud surfaces.
We claim:
1. An impeller for the circulation of an ambient fluid, comprising a rotor with a set of blades radiating from an axis; a circular duct of airfoil cross-section fixedly centered on said axis, said duct having an inner periphery provided with an annular groove and lined with a sheet-metal sheath projecting beyond the edges of said groove to form a pair of annular shoulders within said groove; a ring centered on said axis and interconnecting said blades, said ring projecting radially into said groove with small axial clearance from said shoulders; and sealing means in said groove bridgeing said axial clearance, said sealing means including a pair of elastic annular strips mounted in said groove on said shoulders and extending therefrom into contact with said ring.
2. An impeller as defined in claim 1 wherein said ring has a substantially flat inner peripheral surface flush with the inner periphery of said sheath.
3. An impeller as defined in claim 1 wherein said ring is provided with two outwardly directed radial flanges confronting said shoulders, said strips bearing upon said flanges at locations spaced radially outwardly from said sheath.

Claims (3)

1. An impeller for the circulation of an ambient fluid, comprising a rotor with a set of blades radiating from an axis; a circular duct of airfoil cross-section fixedly centered on said axis, said duct having an inner periphery provided with an annular groove and lined with a sheet-metal sheath projecting beyond the edges of said groove to form a pair of annular shoulders within said groove; a ring centered on said axis and interconnecting said blades, said ring projecting radially into said groove with small axial clearance from said shoulders; and sealing means in said groove bridgeing said axial clearance, said sealing means including a pair of elastic annular strips mounted in said groove on said shoulders and extending therefrom into contact with said ring.
2. An impeller as defined in claim 1 wherein said ring has a substantially flat inner peripheral surface flush with the inner periphery of said sheath.
3. An impeller as defined in claim 1 wherein said ring is provided with two outwardly directed radial flanges confronting said shoulders, said strips bearing upon said flanges at locations spaced radially outwardly from said sheath.
US50052A 1969-07-01 1970-06-29 Framed impeller Expired - Lifetime US3680977A (en)

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Cited By (47)

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US3932055A (en) * 1974-08-05 1976-01-13 Flatland Lloyd P Vacuum turbine for a drill
US3986787A (en) * 1974-05-07 1976-10-19 Mouton Jr William J River turbine
DE2648850A1 (en) * 1975-10-31 1977-05-18 Hitachi Ltd AXIAL FAN
US4131156A (en) * 1976-10-12 1978-12-26 Caterpillar Tractor Co. Fan shroud
FR2429914A1 (en) * 1978-06-26 1980-01-25 United Technologies Corp BLADE HEAD GASKET FOR AN AXIAL FLOW ROTARY MACHINE
US4398508A (en) * 1981-02-20 1983-08-16 Volvo White Truck Corporation Engine cooling fan construction
US4406581A (en) * 1980-12-30 1983-09-27 Hayes-Albion Corp. Shrouded fan assembly
US4441859A (en) * 1981-02-12 1984-04-10 Rolls-Royce Limited Rotor blade for a gas turbine engine
US4457519A (en) * 1977-12-12 1984-07-03 Harrington George H Sealing ring
US4491330A (en) * 1983-08-01 1985-01-01 Franklin Electric Co., Inc. Rotary lip seal
US4548548A (en) * 1984-05-23 1985-10-22 Airflow Research And Manufacturing Corp. Fan and housing
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
US4596054A (en) * 1984-07-03 1986-06-24 Air-Lock, Incorporated Pressure sealing bearing assembly for use in environmental control suits and environmental suits containing such bearing assemblies
US4949022A (en) * 1989-01-27 1990-08-14 Lipman Leonard H Solid state DC fan motor
US5075606A (en) * 1989-01-27 1991-12-24 Lipman Leonard H Solid state DC fan motor
US5183382A (en) * 1991-09-03 1993-02-02 Caterpillar Inc. Low noise rotating fan and shroud assembly
US5577888A (en) * 1995-06-23 1996-11-26 Siemens Electric Limited High efficiency, low-noise, axial fan assembly
US5740766A (en) * 1997-03-25 1998-04-21 Behr America, Inc. Automotive fan and shroud assembly
US5791876A (en) * 1997-03-25 1998-08-11 Behr America, Inc. Floating drive assembly for an automotive cooling fan
US5906179A (en) * 1997-06-27 1999-05-25 Siemens Canada Limited High efficiency, low solidity, low weight, axial flow fan
US5957661A (en) * 1998-06-16 1999-09-28 Siemens Canada Limited High efficiency to diameter ratio and low weight axial flow fan
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US6508624B2 (en) * 2001-05-02 2003-01-21 Siemens Automotive, Inc. Turbomachine with double-faced rotor-shroud seal structure
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US6899339B2 (en) * 2001-08-30 2005-05-31 United Technologies Corporation Abradable seal having improved durability
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CN106628120A (en) * 2016-12-06 2017-05-10 湖南星思科技有限公司 Efficient pneumatic duct body
CN107672802A (en) * 2017-10-24 2018-02-09 南京航空航天大学 Fluting culvert type plume rotor craft
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US10724535B2 (en) * 2017-11-14 2020-07-28 Raytheon Technologies Corporation Fan assembly of a gas turbine engine with a tip shroud
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US11286036B2 (en) * 2018-10-12 2022-03-29 Textron Innovations Inc. Ducted rotor blade tip extension
US11448231B2 (en) * 2020-07-21 2022-09-20 Brose Fahrzeugteile SE & Co. Kommanditgesellschaft, Würzburg Cooling fan module
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FR3070424B1 (en) * 2017-08-29 2020-07-03 Safran Aircraft Engines TURBOMACHINE WHEEL, SUCH AS FOR example A TURBOJET OR AN AIRPLANE TURBOPROPELLER

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US3112610A (en) * 1961-02-27 1963-12-03 Joseph J Jerger Constant pressure shrouded propeller
US3306223A (en) * 1964-10-22 1967-02-28 Illinois Milling Inc Water pump seal
US3519367A (en) * 1967-05-23 1970-07-07 Nord Aviat Soc Nationale De Co Auxiliary faired section for a fluid inlet
US3531214A (en) * 1968-12-09 1970-09-29 Franz W Abramson Radial-driven,multistage jet pump

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US1876067A (en) * 1926-09-20 1932-09-06 Bendix Aviat Corp Blade structure for turbines
US2956733A (en) * 1954-09-28 1960-10-18 Stalker Corp Fluid turning wheels for compressors
US3112610A (en) * 1961-02-27 1963-12-03 Joseph J Jerger Constant pressure shrouded propeller
US3306223A (en) * 1964-10-22 1967-02-28 Illinois Milling Inc Water pump seal
US3519367A (en) * 1967-05-23 1970-07-07 Nord Aviat Soc Nationale De Co Auxiliary faired section for a fluid inlet
US3531214A (en) * 1968-12-09 1970-09-29 Franz W Abramson Radial-driven,multistage jet pump

Cited By (60)

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Publication number Priority date Publication date Assignee Title
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Publication number Publication date
DE2032328A1 (en) 1971-03-18
FR2051912A5 (en) 1971-04-09

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