US3289922A - Air compressor - Google Patents

Air compressor Download PDF

Info

Publication number
US3289922A
US3289922A US422871A US42287164A US3289922A US 3289922 A US3289922 A US 3289922A US 422871 A US422871 A US 422871A US 42287164 A US42287164 A US 42287164A US 3289922 A US3289922 A US 3289922A
Authority
US
United States
Prior art keywords
rotor
stator
air
plates
members
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US422871A
Other languages
English (en)
Inventor
James G Sawyer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Utah Construction and Mining Co
Original Assignee
Utah Construction and Mining Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Utah Construction and Mining Co filed Critical Utah Construction and Mining Co
Priority to US422871A priority Critical patent/US3289922A/en
Priority to BE690692D priority patent/BE690692A/fr
Application granted granted Critical
Publication of US3289922A publication Critical patent/US3289922A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • This invention relates generally to the compressor art, and more particularly to a new and useful centrifugal air compressor. While not limited thereto, the compressor of my invention is designed for operation under flow conditions below those at which conventional centrifugal compressors operate.
  • the primary object of my invention is to provide a centrifugal compressor which is simple and relatively inexpensive in construction, while being extremely durable and dependable in operation and capable of a high degree of performance for its size.
  • Another important object of my invention is to provide a centrifugal compressor capable of highly eflicient operation under very low flow conditions.
  • a centrifugal compressor of my invention is characterized by the provision of a rotor, and a stator mounted at the periphery of the rotor, as described above, wherein the stator comprises a pair of members spaced apart in the direction of the shaft axis and having cover portions extending radially inwardly across the rotor plates in axially spaced relation thereto, and wherein both the rotor plates, and the cover portions of the stator members, are of shallow, frustoconical form converging toward the periphery of the rotor.
  • FIG. 1 is a somewhat schematic, longitudinal sectional view of a centrifugal air compressor constructed in accordance with my invention, taken about on line II of FIG. 2;
  • FIG. 2 is a transverse, half sectional view thereof, taken about on line II-1I of FIG. 1;
  • FIG. 3 is a fragmentary sectional view taken about on line III-III of FIG. 2;
  • FIG. 4 is a somewhat schematic, longitudinal quarter sectional view of another centrifugal air compressor constructed in accordance with my invention, taken about on line 44 of FIG. 6;
  • FIG. 5 is a view like that of FIG. 4 but showing a further modification
  • FIG. 6 is a transverse, half sectional view of the embodiment of FIG. 4, taken about on line 6-6 of FIG. 4.
  • a compressor of my invention is provided with an enclosing shroud or housing 1 of generally cylindrical, barrel form having end members 2 and 3 which journal a shaft 4 in bearings 5 and 6, respectively.
  • An air inlet open ing 7 is provided in end member 2, and an air outlet member 3 is provided intend member 3.
  • the compressor comprises a series of centrifugal rotors, generally designated 10, each having a'pair of plates '11 and 12 spaced apart in the direction of the axis of shaft 4.
  • the front plate 11 of each rotor is provided with a central opening 13, concentric with shaft 4, and comprising an air inlet opening into the rotor between plates 11, 12.
  • Each rear plate 12 is centrally apertured to receive shaft 4, and is connected to shaft 4 in a manner mounting the rotor 10 on the shaft for rotation therewith. This can be accomplished, for example, by the use of rotor spacers 14, and an end spacer 15, which latter bears against a shoulder 16 on the shaft.
  • the spacers 14 extend between adjacent rotors 1i), and are held in place by a lock nut 17, whereby each rotor plate 12 is clamped to the shaft for rotation therewith, the front end spacer 14 being keyed to the shaft as indicated at 18.
  • the front rotor plates 11 are mounted on the associated rear rotor plates 12 by the generally radially extending rotor vanes 20, which can be provided with any desired curvature, depending upon the characteristics desired.
  • each rotor comprises paired plates or walls 11, 12, with the plates 12 being connected to shaft 4 and supporting each rotor thereon, and with the plates 11 held in axially spaced relation to the plates 12 by the series of vanes 20 in each rotor.
  • the plates 11 and 12 can be joined to the directing vanes 24) by welding, or any desired means of fabrication.
  • An air outlet opening 21 is provided at the periphery of each rotor, between the spaced plates 11, 12. Thus, air enters each rotor through the central inlet opening 13, and is discharged peripherally through the outlet opening 21.
  • the stators are positioned at the periphery of the associated rotor.
  • Each stator comprises plates or wall members 23 and 24, spaced apart in the direction of the shaft axis.
  • the front stator member 23 extends radially outwardly to the enclosing housing 1, thereby providing the necessary barrier between successive impellers, and is positioned thereby.
  • the rear stator member 24 terminates short of the housing, to provide an air outlet opening 25 around the outer periphery of the stator and directed rearwardly in the direction of the shaft axis.
  • Each stator member 23, 24 has a cover portion 26, 27, respectively, extending generally radially inwardly across the front and rear rotor plates 11, 12 respectively, to cover and enclose the same.
  • Cover portions 26 extend radially inwardly to about the periphery of the air inlet openings 11, thereby forming a barrier to reverse air flow.
  • the rear stator cover portions 27 extend inwardly to about the spacer members 14, 15, and also function as a barrier to reverse air flow.
  • stator extensions 26 and 27 form an enclosing housing for the associated rotor.
  • Stators 22 are spaced apart by stator spacing members 28 which extend between adjacent stators, at spaced points therearound, being provided with oppositely directed, terminal flanges 29 for securing the same to the stator members.
  • End walls 2 and 3 are removable, and. stator structures 22 and rotors 10 are removable from housing 1 through either end thereof.
  • the front stator members 23 extend outwardly to the housing 1.
  • the rear stator members 24 are positioned axially relative to the front members by decelerating stator vanes generally designated 30, Vanes 30 preferably are paired, and fabricated from a single piece of material to provide paired vanes integral with a connecting web 31. Vanes 30 are caused to diverge outwardly, having an inlet angle matching the angle of the air as it leaves the rotor. This provides air passages of increasing cross-sectional area from the stator air inlet 32, which is positioned in radially spaced relation to the peripheral air outlet opening 21 of the associted rotor, to the stator outlet 25.
  • the partially compressed air is decelerated sufliciently to permit loss free passage through outlet 25 to the inlet 11 of the subsequent rotor.
  • a discharge passage 25 of sufiicient area to efficiently conduct the air to the next stage, all within the confines of the circular compressor housing 1.
  • the vane webs 31 provide a convenient means of attaching the vanes to the stator members 23, as by spot welding or rivets 31.
  • Each rotor plate 11, 12 is constructed in a shallow, frusto-conical form, converging toward the periphery of the rotor.
  • each stator cover portion 26, 27 is shaped to a shallow, frusto-conical form, converging toward the rotor periphery, and joined to the working stator portions peripherally beyond the rotor by the more sharply converging connecting portions 32.
  • This shallow, dish shaped or frusto-conical form provides the requisite structural stability, while permitting'the use of thin sheet material.
  • Shaft 4 is releasably held in axial position by shoulder 33 mounted between washers 34 held in housing 35, with the shaft extending therebeyond for attachment to any desired driving source.
  • the compressor of my invention is especially designed for operation under low flow conditions, for example in the rangeof 80-100 c.f.m. and is capable of eflicient operation at flow ranges in which conventional centrifugal compressors simply do not operate.
  • a major factor in achieving this result is the provision of a stator having a large number of thin diffuser vanes, for example forty, located very close to the rotor tip, as shown at 30 in FIGS. 1-3 and 30' in FIGS. 4-6.
  • Essentially only working clearance is provided between the rotor periphery and the stator inlet, the spacing therebetween being exaggerated in the drawings for greater clarity and ease of illustration.
  • the distance which a stream of air can travel before its energy is dissipated is proportional to its width.
  • the rotor outlet necessarily is very narrow, with the result that air leaving the rotor is capable of traveling only a very short distance without substantial energy loss.
  • the radial clearance between the rotor outlet and the diffuser vanes is such that the air path from the rotor outlet to the inlet ends of the diffuser vanes is essentially no greater and preferably less than the distance which the air stream exiting from the rotor will travel Without substantial energy loss.
  • I provide a radial clearance which is less than 1% of the rotor diameter, for example 0.040 inch with a rotor having a diameter of 6 inches.
  • the diffuser has a large number of closely spaced, thin blades.
  • Vaneless diffusers while suitable for high flow compreasors are entirely unsuitable for a compressor operating under low flow conditions. This is because in a vaneless diffuser the air must travel its natural path wherein velocity is inversely proportional to the distance from the center of rotation. This gives good efiiciency at high flows. In a low flow compressor the width of the air stream is greatly reduced, as previously pointed out. However, the air still must travel the same distance for the same degree of diffusion. As a result, the ratio of the distance traveled to the channel width is much greater than in high flow compressors, introducing prohibitive friction losses.
  • vanes are essential to a low flow diffuser.
  • Conventional vaned diffusers have a relatively small number of relatively widely spaced blades. In a low flow diffuser the channel width is so small compared to the relatively large distance between adjacent blades that the resulting air passage is inefficient. Further the expansion angle provided by such conventional diffuser lading is such that air separation occurs under low flow conditions.
  • I provide a large number of closely spaced diffuser blades, providing an eificiently proportioned passageway and an expansion angle favorable to low flow conditions. However, if too many blades are provided excessive skin friction is developed. I have determined that the optimum expansion angle is 7 to 10 degrees, requiring from 36 to 52 blades. To avoid crowding in the air passageways, I make the blades of thin sheet material. Also, the diffuser blades of my invention are essentially flat and straight, avoiding disturbances resulting from blade curvature.
  • stator performance is greatly influenced by rotor design.
  • Pressure development in the rotor is accomplished by centrifugal forces, which are not particularly disturbed by air separation or air turbulence.
  • the development of pressure within the stator representing approximately one-half the total pressure rise, is accomplished by the conversion of velocity to pressure. This is a diffusion process wherein it is difficult to maintain eflicient flow with turbulent air.
  • Turbulence is produced by the separation of air in the rotor. Such separation occurs at the trailing, rearward surfaces of impeller vanes 20, looking in the direction of rotor rotation. Air tends to separate and move away from the suction side of the vanes, as it moves progressively outwardly therealong. As a result, a boundary layer of relatively stagnant air tends to form along the trailing surface of impeller vanes 20. Such stagnant air produces turbulence in the air leaving the rotor.
  • FIGS. 46 The compressor of FIGS. 46 is generally similar to that of FIGS. 1-3, comprising a series of centrifugal rotors 19' each having a pair of plates or walls 11, 12 spaced apart in the direction of the axis of shaft 4.
  • the front wall 11 of each rotor is provided with a central air inlet opening, concentric with shaft 4 and opening into the rotor between walls 11, 12'.
  • the front rotor walls 11' are mounted on the associated rear rotor walls 12' by generally radially extending rotor vanes which can be provided with any desired curvature, depending upon the characteristics de sired, and the rear rotor walls 12 are secured to shaft 4, as previously described.
  • each radially extending vane in fact comprises a series of vane segments 20' extending from the inlet of the rotor to the outlet in radially stepped, overlapping, circumferentially spaced relation as clearly illustrated in FIGS. 4 and 6.
  • the inner ends of the outer segments overlap the outer ends of the inner segments, on the leading faces thereof, at locations therealong where separation of air normally would start to occur.
  • Deflectors 36 and 37 are concentric with each other and with shaft 4. Also, they are of semi-circular, transverse sectional form, being curved about their annular axes, as clearly illustrated in FIGS. 4 and 5. Deflector rings 36 are mounted along their outer, upper sides on the lower end of front stator skirts 26', and curve downwardly, inwardly and then upwardly, terminating in closely spaced relation to the lower edge of the front rotor wall 11', leaving only working clearance therebetween.
  • Deflector rings 37 are positioned, in the illustrated embodiment, approximately midway between deflectors 36 and spacing collars 14, having upwardly curving ends positioned one adjacent the bottom edge of the inner vane segments 29', in closely spaced relation thereto with substantially only working clearance therebetween, and the other between adjacent pairs of stators 22', as shown in FIG. 4.
  • Deflectors 37 are carried by deflectors 36, being mounted thereon by connecting web plates 38 spaced around shaft 4, being for example four in number and extending axially of shaft 4 for minimum interference with air flow through the rotor inlet.
  • deflectors 36, 37 provide rotor inlet passages having radially directed inlets receiving air passage between adjacent rotor-stator assemblies, and radially directed outlets into the rotors.
  • the inlet air is controlled and there is provided a stream of air directed along the inner face of rotor walls 11'. This provides a boundary layer control avoiding the layer of stagnant air which otherwise tends to form on that surface.
  • a centrifugal compressor comprising a shaft mounted for rotation about its lengthwise axis, a rotor having a pair of sheet metal plates spaced apart in the direction of said axis, one of said plates being connected to said shaft and mounting said rotor on said shaft for rotation therewith, the other of said plates having a generally central air inlet opening therethrough into said rotor, said rotor having a peripheral air outlet opening between said plates, a stator encircling said rotor, said stator having a pair of substantially parallel sheet metal members spaced apart in the direction of said axis, an air inlet opening between.
  • a centrifugal compressor comprising a shaft mounted for rotation about its lengthwise axis, a rotor having a pair of sheet metal plates spaced apart in the direction of said axis, one of said plates being connected to said shaft and mounting said rotor on said shaft for rotation therewith, the other of said plates having a generally central air inlet opening therethrough into said rotor, said rotor having a peripheral air outlet opening between said plates, a stator encircling said rotor, said stator having a pair of substantially parallel sheet metal members spaced apart in the direction of said axis, an air inlet opening between said members in radial alinement with said rotor air outlet opening, an air outlet opening from said stator adjacent the outer periphery thereof, and a series of rectilinear decelerating vanes between said members in spaced apart relation around said axis, said vanes defining air passages therebetween of continuously increasing crosssectional area from said stator air inlet opening to said stator outlet opening, wherein said stator members extend
  • a centrifugal compressor comprising a shaft mounted for rotation about its lengthwise axis, a sheet metal rotor mounted upon said shaft for rotation therewith and having a pair of walls spaced apart in the direction of said axis, one of said walls having a generally central air inlet opening therethrough into said rotor, said rotor having a peripheral air outlet opening between said walls, air directing vanes between said rotor walls extending substantially from said rotor inlet opening to said rotor outlet opening in spaced apart relation around said axis, a sheet metal stator encircling said rotor and having a pair of wall members spaced apart in the direction of said axis, an air inlet opening between said stator wall members in closely spaced radial alinement with said rotor outlet opening, an air outlet opening from said stator adjacent the periphery thereof, substantially flat plate decelerating vanes in fixed position between said stator walls extending substantially rectilinearly from said stator inlet opening at the periphery of said rotor
  • a compressor as defined in claim 3 wherein said decelerating vanes extend in a generally tangential fixed direction outwardly from substantially the periphery of said rotor; and annular deflecting vanes in said inlet opening and arranged to direct incoming air radially into said rotor.
  • a compressor as defined in claim 3 including impeller vanes extending between said rotor plates, each impeller vane comprising radially spaced segments arranged with their ends in overlapping and circumferentially spaced relation to the ends of adjacent segments.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US422871A 1964-10-30 1964-10-30 Air compressor Expired - Lifetime US3289922A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US422871A US3289922A (en) 1964-10-30 1964-10-30 Air compressor
BE690692D BE690692A (fi) 1964-10-30 1966-12-05

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US422871A US3289922A (en) 1964-10-30 1964-10-30 Air compressor

Publications (1)

Publication Number Publication Date
US3289922A true US3289922A (en) 1966-12-06

Family

ID=23676770

Family Applications (1)

Application Number Title Priority Date Filing Date
US422871A Expired - Lifetime US3289922A (en) 1964-10-30 1964-10-30 Air compressor

Country Status (2)

Country Link
US (1) US3289922A (fi)
BE (1) BE690692A (fi)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4022541A (en) * 1976-04-12 1977-05-10 General Motors Corporation Assembled diffuser
US5292088A (en) * 1989-10-10 1994-03-08 Lemont Harold E Propulsive thrust ring system
US5393197A (en) * 1993-11-09 1995-02-28 Lemont Aircraft Corporation Propulsive thrust ring system
EP0715081A1 (en) * 1994-11-23 1996-06-05 AMETEK Inc. Rotating fan having tapered disk component
US20160195107A1 (en) * 2013-08-19 2016-07-07 Dynamic Boosting Systems Limited Diffuser for a Forward-Swept Tangential Flow Compressor

Citations (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US835570A (en) * 1905-04-03 1906-11-13 Organ Power Company Blower for musical instruments.
FR435755A (fr) * 1910-10-31 1912-03-09 Eberhard Seger Appareil de nettoyage par le vide
US1075300A (en) * 1904-12-10 1913-10-07 Gen Electric Centrifugal compressor.
US1158738A (en) * 1912-09-13 1915-11-02 Organ Power Company Organ-blower.
US1263056A (en) * 1916-02-07 1918-04-16 Escher Wyss Maschf Ag Operation of centrifugal-compressor plants.
US1288728A (en) * 1915-09-18 1918-12-24 Spencer Turbine Co Rotary blower.
US1633609A (en) * 1920-10-29 1927-06-28 Westinghouse Electric & Mfg Co Radial-flow pump
US1745854A (en) * 1926-12-18 1930-02-04 Worthington Pump & Mach Corp Rotary hydraulic machine, especially centrifugal pump
DE581164C (de) * 1933-07-22 C H Jaeger & Co Pumpen U Gebla Kreiselmaschine, insbesondere Kreiselgeblaese
GB419544A (en) * 1934-01-12 1934-11-14 G & J Weir Ltd Improvements in centrifugal pumps
US2139112A (en) * 1936-12-11 1938-12-06 Lamson Co Blower
FR889341A (fr) * 1941-12-22 1944-01-06 Westfalia Dinnendahl Roue à ailettes pour ventilateurs centrifuges
US2366964A (en) * 1941-05-05 1945-01-09 Howard Giles Philip Eliot Centrifugal pump
FR971515A (fr) * 1940-09-03 1951-01-18 Pierre Remy & Cie Ets Compresseur-épurateur centrifuge pour gazogènes
US2641191A (en) * 1946-11-12 1953-06-09 Buchi Alfred Guide means on impeller for centrifugal pumps or blowers
US2671604A (en) * 1950-12-29 1954-03-09 Westinghouse Electric Corp Multiple-stage, centrifugal, refrigerant compressor
FR1113658A (fr) * 1954-11-23 1956-04-03 Comm Materiel Et D Outil Soc I Dispositif pour le refroidissement d'un compresseur
US2899129A (en) * 1959-08-11 schwaiger
US2932444A (en) * 1957-09-13 1960-04-12 Spencer Turbine Co Blower
FR1227952A (fr) * 1958-07-08 1960-08-26 Svenska Flaektfabriken Ab Perfectionnements aux ventilateurs centrifuges

Patent Citations (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2899129A (en) * 1959-08-11 schwaiger
DE581164C (de) * 1933-07-22 C H Jaeger & Co Pumpen U Gebla Kreiselmaschine, insbesondere Kreiselgeblaese
US1075300A (en) * 1904-12-10 1913-10-07 Gen Electric Centrifugal compressor.
US835570A (en) * 1905-04-03 1906-11-13 Organ Power Company Blower for musical instruments.
FR435755A (fr) * 1910-10-31 1912-03-09 Eberhard Seger Appareil de nettoyage par le vide
US1158738A (en) * 1912-09-13 1915-11-02 Organ Power Company Organ-blower.
US1288728A (en) * 1915-09-18 1918-12-24 Spencer Turbine Co Rotary blower.
US1263056A (en) * 1916-02-07 1918-04-16 Escher Wyss Maschf Ag Operation of centrifugal-compressor plants.
US1633609A (en) * 1920-10-29 1927-06-28 Westinghouse Electric & Mfg Co Radial-flow pump
US1745854A (en) * 1926-12-18 1930-02-04 Worthington Pump & Mach Corp Rotary hydraulic machine, especially centrifugal pump
GB419544A (en) * 1934-01-12 1934-11-14 G & J Weir Ltd Improvements in centrifugal pumps
US2139112A (en) * 1936-12-11 1938-12-06 Lamson Co Blower
FR971515A (fr) * 1940-09-03 1951-01-18 Pierre Remy & Cie Ets Compresseur-épurateur centrifuge pour gazogènes
US2366964A (en) * 1941-05-05 1945-01-09 Howard Giles Philip Eliot Centrifugal pump
FR889341A (fr) * 1941-12-22 1944-01-06 Westfalia Dinnendahl Roue à ailettes pour ventilateurs centrifuges
US2641191A (en) * 1946-11-12 1953-06-09 Buchi Alfred Guide means on impeller for centrifugal pumps or blowers
US2671604A (en) * 1950-12-29 1954-03-09 Westinghouse Electric Corp Multiple-stage, centrifugal, refrigerant compressor
FR1113658A (fr) * 1954-11-23 1956-04-03 Comm Materiel Et D Outil Soc I Dispositif pour le refroidissement d'un compresseur
US2932444A (en) * 1957-09-13 1960-04-12 Spencer Turbine Co Blower
FR1227952A (fr) * 1958-07-08 1960-08-26 Svenska Flaektfabriken Ab Perfectionnements aux ventilateurs centrifuges

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4022541A (en) * 1976-04-12 1977-05-10 General Motors Corporation Assembled diffuser
US5292088A (en) * 1989-10-10 1994-03-08 Lemont Harold E Propulsive thrust ring system
US5470202A (en) * 1989-10-10 1995-11-28 Lemont; Harold E. Propulsive thrust ring system
US5651707A (en) * 1989-10-10 1997-07-29 Lemont; Harold E. Propulsive thrust ring system
US5393197A (en) * 1993-11-09 1995-02-28 Lemont Aircraft Corporation Propulsive thrust ring system
EP0715081A1 (en) * 1994-11-23 1996-06-05 AMETEK Inc. Rotating fan having tapered disk component
US20160195107A1 (en) * 2013-08-19 2016-07-07 Dynamic Boosting Systems Limited Diffuser for a Forward-Swept Tangential Flow Compressor
US10174766B2 (en) * 2013-08-19 2019-01-08 Dynamic Boosting Systems Limited Diffuser for a forward-swept tangential flow compressor

Also Published As

Publication number Publication date
BE690692A (fi) 1967-05-16

Similar Documents

Publication Publication Date Title
US3861826A (en) Cascade diffuser having thin, straight vanes
US3243102A (en) Centrifugal fluid pump
US3824029A (en) Centrifugal supersonic compressor
US2435236A (en) Superacoustic compressor
US4395197A (en) Centrifugal fluid machine
US2618433A (en) Means for bleeding air from compressors
US2925952A (en) Radial-flow-compressor
US3171353A (en) Centrifugal fluid pump
US3460748A (en) Radial flow machine
US3986791A (en) Hydrodynamic multi-stage pump
US5810557A (en) Fan wheel for an inline centrifugal fan
JPH0262717B2 (fi)
US2419669A (en) Diffuser for centrifugal compressors
US2727680A (en) Centrifugal fan
US3944406A (en) Centrifugal pump for pumping liquids with heavy gas content
US3936223A (en) Compressor diffuser
US4415306A (en) Turbine
US3759627A (en) Compressor assembly
JP3802572B2 (ja) 吸込案内装置を有するターボ形ポンプ
US3781128A (en) Centrifugal compressor diffuser
US3059833A (en) Fans
EP2221487A1 (en) Centrifugal compressor
JPH0610610A (ja) タービンブレード組立体
US3724968A (en) Axial supersonic compressor
US3289922A (en) Air compressor