US3009630A - Axial flow fans - Google Patents

Axial flow fans Download PDF

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Publication number
US3009630A
US3009630A US733066A US73306658A US3009630A US 3009630 A US3009630 A US 3009630A US 733066 A US733066 A US 733066A US 73306658 A US73306658 A US 73306658A US 3009630 A US3009630 A US 3009630A
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Prior art keywords
impeller
blade
hollow
blades
axial flow
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Expired - Lifetime
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US733066A
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Jan C Busquet
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KONINK MASCHINENFABRIEK Gebr S
Koninklijke Maschinenfabriek Gebr Stork & Co N V
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KONINK MASCHINENFABRIEK Gebr S
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    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps

Definitions

  • This invention relates to an axial flow fan, the impeller of which is provided with hollow blades and the invention has for its object to increase the output of the fan and to vary the output, if required.
  • the wall of the hollow blades near the outflow side of the impeller is provided with at least one discharge opening for a pressure fluid entering the interior of the blade and having a pressure exceeding that at the outflow side of the impeller and said discharge openings being located at the front face of the blades as viewed in the direction of rotation.
  • a fan the casing of which is widened behind the impeller to constitute a diffuser the fluid to be introduced into the cavity of the impeller blades may be withdrawn from said diffuser.
  • the output of the fan may be varied by adjusting the supply of the pressure fluid entering the hollow blades. It appeared namely that at the pressure side of the blade, where the pressure fluid flows out through the holes in the blade wall a more uniform pressure is built up whereas at the low pressure side of the blade the pressure is not increased.
  • the pres sure fluid flowing out of the opening or openings in the blade wall forms a shield, which apparently prevents the flow of fluid from the pressure side at the rear end of the blade to the low pressure side of the blade.
  • the outflowing pressure fluid thereby performs the function of a pivotal blade part of adjustable blades, so that when varying the supply of pressure fluid enter-ing in the interior of the blades also the output of the impeller is varied.
  • the fan adjustable guide vanes may be arranged at the inflow side of the fan casing.
  • FIG. 1 is a longitudinal sectional view of the fan.
  • FIG. 2 is a cross-section taken on the line II-II of FIG. 1 and FIG. 3 is a section of two adjacent blades taken on the line III-HI of FIG. 2, the direction of rotation of the impeller being indicated by the arrow a.
  • the bearing 4 is located in a stationary more or less conical body 6 of sheet metal mounted adjacent the impeller hub and also the bearing 5 is mounted in a stationary hollow conical body 7.
  • Adjustable guide vanes 9 are arranged at the inflow side of the casing 8 and the casing is conically widened to constitute a ditfusor 10 behind the impeller 1.
  • an adjustable valve 11 is mounted, which has its rod 13 connected to an arm of a bell crank lever 12 by means of which the valve may be adjusted.
  • valve 11 When valve 11 is in open position air-from the difiuser 10 will flow into the hollow body 7 and through the hollow impeller hub enter the interior of the hollow blades 3 by means of holes 14 provided in the circumferential wall of the hub in order to flow out through a slot 15 at the rear end of each blade.
  • the valve 11 By adjusting the valve 11 the quantity of air flowing out through the slots 15 and, therefore, the output of the fan may be varied. As shown in FIG. 3 the air flows out through the slot 15 in a direction substantially perpendicular to the front face of the blade.
  • auxiliary blades 16 are provided in the hollow impeller hub.
  • An axial flow fan comprising an impeller having a hollow hub with a circumferential wall carrying hollow blades, a casing surrounding said impeller and being widened at the discharge side of the impeller to constitute a diffuser, a stationary hollow conical body within said diffuser and adjacent the impeller, said body having an inlet opening and at its end facing the impeller an outlet opening, said hollow impeller hub having an inlet opening in communication with said outlet opening and at least one opening in its circumferential wall and in communication with each hollow blade, each blade having at least one discharge opening for the fluid flowing from the interior of said conical hollow body into the interior of the blade, said discharge opening being located in the front wall of the blade immediately upstream of the trailing edge of the blade as viewed in the direction of rotation to discharge the fluid which defines a shield disposed at an angle with said front wall.
  • An axial flow fan comprising an impeller having a hollow hub with a circumferential Wall carrying hollow blades, a casing surrounding said impeller and being widened at the discharge side of the impeller to constitute a diffuser, a stationary hollow conical body within said diffuser and adjacent the impeller, said body having an inlet opening and at its end facing the impeller an outlet opening, said hollow impeller hub having an inlet opening in communication with said outlet opening and at least one opening in its circumferential wall and in communication with each hollow blade, and an adjustable valve arranged at the inlet opening of said hollow conical body, each blade having at least one discharge opening for the fluid flowing from the interior of said conical hollow body into the interior of the blade, said discharge opening being located in the front wall of the blade immediately upstream of the trailing edge of the blade as viewed in the direction of rotation to discharge the fluid which defines a shield disposed at an angle with said front wall.

Description

Nov. 21, 1961 J. c. BUSQUET 3,009,630
AXIAL FLOW FANS Filed May 5, 1958 INVENTOR A ORNEY Unite States This invention relates to an axial flow fan, the impeller of which is provided with hollow blades and the invention has for its object to increase the output of the fan and to vary the output, if required.
According to the invention the wall of the hollow blades near the outflow side of the impeller is provided with at least one discharge opening for a pressure fluid entering the interior of the blade and having a pressure exceeding that at the outflow side of the impeller and said discharge openings being located at the front face of the blades as viewed in the direction of rotation. With a fan the casing of which is widened behind the impeller to constitute a diffuser the fluid to be introduced into the cavity of the impeller blades may be withdrawn from said diffuser.
It appeared that by the discharge of said pressure fluid through the openings in the blade wall the output of the fan for unchanged dimensions of the impeller is considerably increased. Moreover the output of the fan may be varied by adjusting the supply of the pressure fluid entering the hollow blades. It appeared namely that at the pressure side of the blade, where the pressure fluid flows out through the holes in the blade wall a more uniform pressure is built up whereas at the low pressure side of the blade the pressure is not increased. The pres sure fluid flowing out of the opening or openings in the blade wall forms a shield, which apparently prevents the flow of fluid from the pressure side at the rear end of the blade to the low pressure side of the blade. The outflowing pressure fluid thereby performs the function of a pivotal blade part of adjustable blades, so that when varying the supply of pressure fluid enter-ing in the interior of the blades also the output of the impeller is varied. In order to still increase the range of outputs of the fan adjustable guide vanes may be arranged at the inflow side of the fan casing.
In the accompanying drawing, which illustrates an embodiment of the fan according to the invention, FIG. 1 is a longitudinal sectional view of the fan.
FIG. 2 is a cross-section taken on the line II-II of FIG. 1 and FIG. 3 is a section of two adjacent blades taken on the line III-HI of FIG. 2, the direction of rotation of the impeller being indicated by the arrow a.
The shaft 2 of the impeller 1 having a series of hollow blades 3 at its circumference, is supported at the suction side in a bearing 4 and at the pressure side in a bearing 5. The bearing 4 is located in a stationary more or less conical body 6 of sheet metal mounted adjacent the impeller hub and also the bearing 5 is mounted in a stationary hollow conical body 7.
Adjustable guide vanes 9 are arranged at the inflow side of the casing 8 and the casing is conically widened to constitute a ditfusor 10 behind the impeller 1.
At the apex of the conical body 7 an adjustable valve 11 is mounted, which has its rod 13 connected to an arm of a bell crank lever 12 by means of which the valve may be adjusted. When valve 11 is in open position air-from the difiuser 10 will flow into the hollow body 7 and through the hollow impeller hub enter the interior of the hollow blades 3 by means of holes 14 provided in the circumferential wall of the hub in order to flow out through a slot 15 at the rear end of each blade. By adjusting the valve 11 the quantity of air flowing out through the slots 15 and, therefore, the output of the fan may be varied. As shown in FIG. 3 the air flows out through the slot 15 in a direction substantially perpendicular to the front face of the blade.
In order to further increase the pressure of the air entering the hollow blades 3 auxiliary blades 16 are provided in the hollow impeller hub.
What I claim is:
1. An axial flow fan comprising an impeller having a hollow hub with a circumferential wall carrying hollow blades, a casing surrounding said impeller and being widened at the discharge side of the impeller to constitute a diffuser, a stationary hollow conical body within said diffuser and adjacent the impeller, said body having an inlet opening and at its end facing the impeller an outlet opening, said hollow impeller hub having an inlet opening in communication with said outlet opening and at least one opening in its circumferential wall and in communication with each hollow blade, each blade having at least one discharge opening for the fluid flowing from the interior of said conical hollow body into the interior of the blade, said discharge opening being located in the front wall of the blade immediately upstream of the trailing edge of the blade as viewed in the direction of rotation to discharge the fluid which defines a shield disposed at an angle with said front wall.
2. An axial flow fan comprising an impeller having a hollow hub with a circumferential Wall carrying hollow blades, a casing surrounding said impeller and being widened at the discharge side of the impeller to constitute a diffuser, a stationary hollow conical body within said diffuser and adjacent the impeller, said body having an inlet opening and at its end facing the impeller an outlet opening, said hollow impeller hub having an inlet opening in communication with said outlet opening and at least one opening in its circumferential wall and in communication with each hollow blade, and an adjustable valve arranged at the inlet opening of said hollow conical body, each blade having at least one discharge opening for the fluid flowing from the interior of said conical hollow body into the interior of the blade, said discharge opening being located in the front wall of the blade immediately upstream of the trailing edge of the blade as viewed in the direction of rotation to discharge the fluid which defines a shield disposed at an angle with said front wall.
References Cited in the file of this patent UNITED STATES PATENTS 2,294,586 Troller Sept. 1, 1942 2,578,478 Janes Dec. 11, 1951 2,599,470 Meyer June 3, 1952 2,618,433 Loos et a1. Nov. 18, 1952 2,749,027 Stalker June 5, 1956 2,759,663 Stalker Aug. 21, 1956 2,830,754 Stalker Apr. 15, 1958 2,874,894 Goldschmied Feb. 24, 1959 2,935,245 McDonald May 3, 1960 FOREIGN PATENTS 754,579 Great Britain Aug. 8, 1956 802,811 France June 22, 1936 1,009,308 France Mar. 5, 1952 1,016,738 France Sept. 3, 1952
US733066A 1957-05-10 1958-05-05 Axial flow fans Expired - Lifetime US3009630A (en)

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Cited By (49)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3237850A (en) * 1964-08-24 1966-03-01 Borg Warner Axial flow fan with boundary layer control
US3363419A (en) * 1965-04-27 1968-01-16 Rolls Royce Gas turbine ducted fan engine
US3405865A (en) * 1966-10-18 1968-10-15 Lagelbauer Ernest Turbofan bladings
JPS52106609U (en) * 1976-01-08 1977-08-13
WO2006060010A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Compressor inlet guide vane for tip turbine engine and corresponding control method
WO2006059986A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US20080093174A1 (en) * 2004-12-01 2008-04-24 Suciu Gabriel L Tip Turbine Engine with a Heat Exchanger
US20080124211A1 (en) * 2004-12-01 2008-05-29 Suciu Gabriel L Diffuser Aspiration For A Tip Turbine Engine
US20090071162A1 (en) * 2004-12-01 2009-03-19 Suciu Gabriel L Peripheral combustor for tip turbine engine
US20090142184A1 (en) * 2004-12-01 2009-06-04 Roberge Gary D Vectoring transition duct for turbine engine
US20090232650A1 (en) * 2004-12-01 2009-09-17 Gabriel Suciu Tip turbine engine and corresponding operating method
US7607286B2 (en) 2004-12-01 2009-10-27 United Technologies Corporation Regenerative turbine blade and vane cooling for a tip turbine engine
US7631480B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Modular tip turbine engine
EP2228542A1 (en) * 2003-11-26 2010-09-15 Rolls-Royce Deutschland Ltd & Co KG Turbo compressor or pump with fluid injection to influence the boundary layer
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
US7878762B2 (en) 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
US7887296B2 (en) 2004-12-01 2011-02-15 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
US7927075B2 (en) 2004-12-01 2011-04-19 United Technologies Corporation Fan-turbine rotor assembly for a tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
US8061968B2 (en) 2004-12-01 2011-11-22 United Technologies Corporation Counter-rotating compressor case and assembly method for tip turbine engine
JP2011529551A (en) * 2008-07-28 2011-12-08 シーメンス エナジー インコーポレイテッド Diffuser in turbomachine
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
US8087885B2 (en) 2004-12-01 2012-01-03 United Technologies Corporation Stacked annular components for turbine engines
US8104257B2 (en) 2004-12-01 2012-01-31 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
US8152469B2 (en) 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US8807936B2 (en) 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone

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FR802811A (en) * 1935-06-01 1936-09-16 Device for adjusting a blowing propeller
US2294586A (en) * 1941-08-04 1942-09-01 Del Conveyor & Mfg Company Axial flow fan structure
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FR1009308A (en) * 1948-06-04 1952-05-28 Rateau Soc Improvements to axial fan installations, particularly for mine ventilation
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FR1016738A (en) * 1950-04-26 1952-11-20 Mabag Axial fan or blower, in particular for conveying hot gases
US2749027A (en) * 1947-12-26 1956-06-05 Edward A Stalker Compressor
GB754579A (en) * 1953-06-01 1956-08-08 Garrett Corp Improvements in or relating to a turbine-driven impeller or fan
US2759663A (en) * 1953-01-12 1956-08-21 Stalker Dev Company Slotted compressor blades
US2830754A (en) * 1947-12-26 1958-04-15 Edward A Stalker Compressors
US2874894A (en) * 1957-03-01 1959-02-24 Westinghouse Electric Corp Gas reaction rotors
US2935245A (en) * 1956-12-10 1960-05-03 Westinghouse Electric Corp Gas reaction rotors

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR802811A (en) * 1935-06-01 1936-09-16 Device for adjusting a blowing propeller
US2294586A (en) * 1941-08-04 1942-09-01 Del Conveyor & Mfg Company Axial flow fan structure
US2578478A (en) * 1947-06-26 1951-12-11 Rolls Royce Gas-turbine engine
US2599470A (en) * 1947-10-22 1952-06-03 Bbc Brown Boveri & Cie Axial flow compressor, particularly for combustion gas turbine plants
US2830754A (en) * 1947-12-26 1958-04-15 Edward A Stalker Compressors
US2749027A (en) * 1947-12-26 1956-06-05 Edward A Stalker Compressor
FR1009308A (en) * 1948-06-04 1952-05-28 Rateau Soc Improvements to axial fan installations, particularly for mine ventilation
US2618433A (en) * 1948-06-23 1952-11-18 Curtiss Wright Corp Means for bleeding air from compressors
FR1016738A (en) * 1950-04-26 1952-11-20 Mabag Axial fan or blower, in particular for conveying hot gases
US2759663A (en) * 1953-01-12 1956-08-21 Stalker Dev Company Slotted compressor blades
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Cited By (66)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3237850A (en) * 1964-08-24 1966-03-01 Borg Warner Axial flow fan with boundary layer control
US3363419A (en) * 1965-04-27 1968-01-16 Rolls Royce Gas turbine ducted fan engine
US3405865A (en) * 1966-10-18 1968-10-15 Lagelbauer Ernest Turbofan bladings
JPS52106609U (en) * 1976-01-08 1977-08-13
EP2228542A1 (en) * 2003-11-26 2010-09-15 Rolls-Royce Deutschland Ltd & Co KG Turbo compressor or pump with fluid injection to influence the boundary layer
EP2226510A3 (en) * 2003-11-26 2011-06-15 Rolls-Royce Deutschland Ltd & Co KG Turbo compressor or pump with fluid injection to influence the boundary layer
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US20090148272A1 (en) * 2004-12-01 2009-06-11 Norris James W Tip turbine engine and operating method with reverse core airflow
US20090071162A1 (en) * 2004-12-01 2009-03-19 Suciu Gabriel L Peripheral combustor for tip turbine engine
US20090142184A1 (en) * 2004-12-01 2009-06-04 Roberge Gary D Vectoring transition duct for turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US20090232650A1 (en) * 2004-12-01 2009-09-17 Gabriel Suciu Tip turbine engine and corresponding operating method
US7607286B2 (en) 2004-12-01 2009-10-27 United Technologies Corporation Regenerative turbine blade and vane cooling for a tip turbine engine
US7631480B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Modular tip turbine engine
US7631485B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Tip turbine engine with a heat exchanger
US20080093174A1 (en) * 2004-12-01 2008-04-24 Suciu Gabriel L Tip Turbine Engine with a Heat Exchanger
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
US7878762B2 (en) 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
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