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US20060034697A1 - Propeller structure of a fan - Google Patents

Propeller structure of a fan Download PDF

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Publication number
US20060034697A1
US20060034697A1 US10/916,511 US91651104A US2006034697A1 US 20060034697 A1 US20060034697 A1 US 20060034697A1 US 91651104 A US91651104 A US 91651104A US 2006034697 A1 US2006034697 A1 US 2006034697A1
Authority
US
United States
Prior art keywords
base section
propeller
vane
section surface
airflow
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.)
Abandoned
Application number
US10/916,511
Inventor
Cheng-Kang Chen
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to US10/916,511 priority Critical patent/US20060034697A1/en
Publication of US20060034697A1 publication Critical patent/US20060034697A1/en
Abandoned legal-status Critical Current

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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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • 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

  • the present invention is related to an improved propeller structure of a fan, and more particularly a propeller structure in which multiple recesses are formed on the base section surface and the vane surfaces for reducing the flow resistance between the airflow and the base section surface and the vane surfaces produced when the propeller rotates.
  • the noise produced when the propeller rotates can be also reduced.
  • the propeller 20 of a conventional fan includes a base section 21 and several vanes 22 .
  • the base section 21 has a base section surface 23 and each vane 22 has a vane surface 24 .
  • the base section surface 23 and the vane surfaces 24 are all polished for reducing the flow resistance against the propeller 20 .
  • a parallel flow layer 25 is produced between the base section surface 23 and the vane surfaces 24 and the ambient airflow.
  • the parallel flow layer 25 cannot attach to the base section surface 23 and the vane surfaces 24 so that a frictional resistance exists between the base section surface 23 and the vane surfaces 24 and the airflow.
  • due to the frictional resistance between the base section surface 23 and the vane surfaces 24 and the airflow a noise will be produced.
  • Multiple recesses are formed on the base section surface and the vane surfaces of the propeller.
  • the turbulence layer is easier to attach to the base section surface and the vane surfaces to form a thin air film for spacing the airflow from the base section surface and the vane surfaces so as to reduce the frictional effect between the airflow and the base section surface and the vane surfaces. Therefore, the flow resistance between the airflow and the base section surface and the vane surfaces produced when the propeller rotates can be reduced.
  • the propeller structure of the fan of the present invention includes a base section and multiple vanes.
  • the base section has a base section surface and each vane has a vane surface for contacting with airflow.
  • the propeller has multiple recesses distributed over the vane surfaces of the vanes. The recesses are formed on the vane surfaces for reducing the flow resistance between the airflow and the vane surfaces of the propeller and the noise produced when the propeller rotates.
  • the recesses formed on the vane surfaces are concave faces.
  • the propeller structure of the fan of the present invention includes a base section and multiple vanes.
  • the base section has a base section surface and each vane has a vane surface for contacting with airflow.
  • the propeller has multiple recesses distributed over the base section surface of the base section and the vane surfaces of the vanes. The recesses are formed on the base section surface and the vane surfaces for reducing the flow resistance between the airflow and the base section surface and the vane surfaces of propeller and the noise produced when the propeller rotates.
  • the recesses formed on the base section surface and the vane surfaces are concave faces.
  • FIG. 1 is a perspective view of the present invention
  • FIG. 2 is a front view of the present invention
  • FIG. 3 is a side view of the present invention.
  • FIG. 4 is a perspective view of the present invention mounted in a fan
  • FIG. 5 shows the airflow produced when the present invention is rotated
  • FIG. 6 is a perspective view of another embodiment of the present invention.
  • FIG. 7 is a perspective view of a conventional fan.
  • FIG. 8 shows the airflow produced when the conventional fan is rotated.
  • the propeller structure 10 of the fan of the present invention includes a base section 11 and multiple vanes 12 .
  • the base section 11 has a base section surface 13 and each vane 11 has a vane surface 14 for contacting with the airflow.
  • the present invention is characterized in that the propeller 10 has multiple recesses 15 distributed over the vane surfaces 14 of the vanes 12 and the base section surface 13 of the base section 11 .
  • the vane surfaces 14 include two main upwind faces.
  • the recesses 15 are formed on the base section surface 13 and the vane surfaces 14 for reducing the flow resistance between the airflow and the base section surface 13 and the vane surfaces 14 produced when the propeller 10 rotates. Also, the recesses 15 serve to reduce the noise produced when the propeller 10 rotates.
  • the recesses 15 formed on the base section surface 13 and the vane surfaces 14 are concave faces.
  • a turbulence layer 16 When the propeller 10 rotates, due to the recesses 15 formed on the base section surface 13 and the vane surfaces 14 , a turbulence layer 16 will be produced, which is not easy to separate from the base section surface 13 and the vane surfaces 14 . That is, the turbulence layer 16 is easier to attach to the base section surface 13 and the vane surfaces 14 to form a thin air film for spacing the airflow from the base section surface 13 and the vane surfaces 14 so as to reduce the frictional effect between the airflow and the base section surface 13 and the vane surfaces 14 . Therefore, the flow resistance between the airflow and the base section surface 13 and the vane surfaces 14 produced when the propeller 10 rotates can be reduced. In addition, the noise produced when the propeller 10 rotates can be reduced.
  • the propeller structure of the fan of the present invention has the following advantages:
  • a turbulence layer will be produced.
  • the turbulence layer is easier to attach to the base section surface and the vane surfaces to form a thin air film for spacing the airflow from the base section surface and the vane surfaces so as to reduce the frictional effect between the airflow and the base section surface and the vane surfaces. Therefore, the flow resistance between the airflow and the base section surface and the vane surfaces produced when the propeller rotates can be reduced.
  • the flow resistance between the propeller and the airflow can be reduced so that the noise produced when the propeller rotates can be reduced.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A propeller structure of a fan, including a base section and multiple vanes. The base section has a base section surface and each vane has a vane surface for contacting with airflow. The propeller has multiple recesses distributed over the base section surface of the base section and the vane surfaces of the vanes. The recesses are formed on the base section surface and the vane surfaces for reducing the flow resistance between the airflow and the base section surface and the vane surfaces of propeller and the noise produced when the propeller rotates.

Description

    BACKGROUND OF THE INVENTION
  • 1. Field of the Invention
  • The present invention is related to an improved propeller structure of a fan, and more particularly a propeller structure in which multiple recesses are formed on the base section surface and the vane surfaces for reducing the flow resistance between the airflow and the base section surface and the vane surfaces produced when the propeller rotates. In addition, the noise produced when the propeller rotates can be also reduced.
  • 2. Description of the Prior Art
  • Referring to FIGS. 7 and 8, the propeller 20 of a conventional fan includes a base section 21 and several vanes 22. The base section 21 has a base section surface 23 and each vane 22 has a vane surface 24. The base section surface 23 and the vane surfaces 24 are all polished for reducing the flow resistance against the propeller 20. However, when the propeller 20 rotates, a parallel flow layer 25 is produced between the base section surface 23 and the vane surfaces 24 and the ambient airflow. The parallel flow layer 25 cannot attach to the base section surface 23 and the vane surfaces 24 so that a frictional resistance exists between the base section surface 23 and the vane surfaces 24 and the airflow. In addition, due to the frictional resistance between the base section surface 23 and the vane surfaces 24 and the airflow, a noise will be produced.
    • SUMMARY OF THE INVENTION
  • It is therefore a primary object of the present invention to provide an improved propeller structure of a fan. Multiple recesses are formed on the base section surface and the vane surfaces of the propeller. When the propeller rotates, a turbulence layer will be produced. The turbulence layer is easier to attach to the base section surface and the vane surfaces to form a thin air film for spacing the airflow from the base section surface and the vane surfaces so as to reduce the frictional effect between the airflow and the base section surface and the vane surfaces. Therefore, the flow resistance between the airflow and the base section surface and the vane surfaces produced when the propeller rotates can be reduced.
  • It is a further object of the present invention to provide the above propeller structure of the fan. By means of the recesses formed on the base section surface and the vane surfaces of the propeller, the flow resistance between the propeller and the airflow can be reduced so that the noise produced when the propeller rotates can be reduced.
  • According to the above objects, the propeller structure of the fan of the present invention includes a base section and multiple vanes. The base section has a base section surface and each vane has a vane surface for contacting with airflow. The propeller has multiple recesses distributed over the vane surfaces of the vanes. The recesses are formed on the vane surfaces for reducing the flow resistance between the airflow and the vane surfaces of the propeller and the noise produced when the propeller rotates.
  • In the above propeller structure, the recesses formed on the vane surfaces are concave faces.
  • Still according to the above objects, the propeller structure of the fan of the present invention includes a base section and multiple vanes. The base section has a base section surface and each vane has a vane surface for contacting with airflow. The propeller has multiple recesses distributed over the base section surface of the base section and the vane surfaces of the vanes. The recesses are formed on the base section surface and the vane surfaces for reducing the flow resistance between the airflow and the base section surface and the vane surfaces of propeller and the noise produced when the propeller rotates.
  • In the above propeller structure, the recesses formed on the base section surface and the vane surfaces are concave faces.
  • The present invention can be best understood through the following description and accompanying drawings wherein:
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a perspective view of the present invention;
  • FIG. 2 is a front view of the present invention;
  • FIG. 3 is a side view of the present invention;
  • FIG. 4 is a perspective view of the present invention mounted in a fan;
  • FIG. 5 shows the airflow produced when the present invention is rotated;
  • FIG. 6 is a perspective view of another embodiment of the present invention;
  • FIG. 7 is a perspective view of a conventional fan; and
  • FIG. 8 shows the airflow produced when the conventional fan is rotated.
    • DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
  • Please refer to FIGS. 1 to 6. The propeller structure 10 of the fan of the present invention includes a base section 11 and multiple vanes 12. The base section 11 has a base section surface 13 and each vane 11 has a vane surface 14 for contacting with the airflow.
  • The present invention is characterized in that the propeller 10 has multiple recesses 15 distributed over the vane surfaces 14 of the vanes 12 and the base section surface 13 of the base section 11. (The vane surfaces 14 include two main upwind faces.) The recesses 15 are formed on the base section surface 13 and the vane surfaces 14 for reducing the flow resistance between the airflow and the base section surface 13 and the vane surfaces 14 produced when the propeller 10 rotates. Also, the recesses 15 serve to reduce the noise produced when the propeller 10 rotates.
  • In a preferred embodiment, the recesses 15 formed on the base section surface 13 and the vane surfaces 14 are concave faces.
  • When the propeller 10 rotates, due to the recesses 15 formed on the base section surface 13 and the vane surfaces 14, a turbulence layer 16 will be produced, which is not easy to separate from the base section surface 13 and the vane surfaces 14. That is, the turbulence layer 16 is easier to attach to the base section surface 13 and the vane surfaces 14 to form a thin air film for spacing the airflow from the base section surface 13 and the vane surfaces 14 so as to reduce the frictional effect between the airflow and the base section surface 13 and the vane surfaces 14. Therefore, the flow resistance between the airflow and the base section surface 13 and the vane surfaces 14 produced when the propeller 10 rotates can be reduced. In addition, the noise produced when the propeller 10 rotates can be reduced.
  • According to the above arrangement, the propeller structure of the fan of the present invention has the following advantages:
  • 1. When the propeller rotates, due to the recesses formed on the base section surface and the vane surfaces, a turbulence layer will be produced. The turbulence layer is easier to attach to the base section surface and the vane surfaces to form a thin air film for spacing the airflow from the base section surface and the vane surfaces so as to reduce the frictional effect between the airflow and the base section surface and the vane surfaces. Therefore, the flow resistance between the airflow and the base section surface and the vane surfaces produced when the propeller rotates can be reduced.
  • 2. By means of the recesses formed on the base section surface and the vane surfaces of the propeller of the present invention, the flow resistance between the propeller and the airflow can be reduced so that the noise produced when the propeller rotates can be reduced.
  • The above embodiments are only used to illustrate the present invention, not intended to limit the scope thereof. Many modifications of the above embodiments can be made without departing from the spirit of the present invention.

Claims (4)

1. A propeller structure of a fan, comprising a base section and multiple vanes, the base section having a base section surface and each vane having a vane surface for contacting with airflow, said propeller structure being characterized in that the propeller has multiple recesses distributed over the vane surfaces of the vanes, the recesses being formed on the vane surfaces for reducing the flow resistance between the airflow and the vane surfaces of the propeller and the noise produced when the propeller rotates.
2. The propeller structure as claimed in claim 1, wherein the recesses formed on the vane surfaces are concave faces.
3. A propeller structure of a fan, comprising a base section and multiple vanes, the base section having a base section surface and each vane having a vane surface for contacting with airflow, said propeller structure being characterized in that the propeller has multiple recesses distributed over the base section surface of the base section and the vane surfaces of the vanes, the recesses being formed on the base section surface and the vane surfaces for reducing the flow resistance between the airflow and the base section surface and the vane surfaces of propeller and the noise produced when the propeller rotates.
4. The propeller structure as claimed in claim 3, wherein the recesses formed on the base section surface and the vane surfaces are concave faces.
US10/916,511 2004-08-12 2004-08-12 Propeller structure of a fan Abandoned US20060034697A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US10/916,511 US20060034697A1 (en) 2004-08-12 2004-08-12 Propeller structure of a fan

Applications Claiming Priority (1)

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US10/916,511 US20060034697A1 (en) 2004-08-12 2004-08-12 Propeller structure of a fan

Publications (1)

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US20060034697A1 true US20060034697A1 (en) 2006-02-16

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070269312A1 (en) * 2006-05-22 2007-11-22 Delta Electronics, Inc. Assembly of blade units for wind power generation
GB2452104A (en) * 2008-01-14 2009-02-25 Flakt Woods Ltd A meridional fan
US20090232648A1 (en) * 2008-03-14 2009-09-17 Wayne State University Reduction of flow-induced noise in a centrifugal blower
US20150050133A1 (en) * 2013-08-15 2015-02-19 Aerocool Advanced Technologies Corporation Fan structure
EP3534014A1 (en) * 2018-02-28 2019-09-04 Garrett Transportation I Inc. Turbocharger compressor having adjustable-trim mechanism including vortex reducers

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US998889A (en) * 1910-08-19 1911-07-25 Daniel Fraser Rotary fan.
US1130616A (en) * 1911-08-19 1915-03-02 Thomas P Kingsford Balancing device for centrifugal pumps, turbines, blowers, and the like.
US1157240A (en) * 1913-02-28 1915-10-19 Fairbanks Morse & Co Balanced centrifugal pump.
US1563129A (en) * 1921-11-30 1925-11-24 Weil Ludwig Centrifugal pump or blower and similar machine
US3414188A (en) * 1966-11-25 1968-12-03 American Radiator & Standard Fan having hollow blades
US5244349A (en) * 1992-09-24 1993-09-14 Wang Sui Mu Air fan with lightly-constructed reinforcing fan blades

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US998889A (en) * 1910-08-19 1911-07-25 Daniel Fraser Rotary fan.
US1130616A (en) * 1911-08-19 1915-03-02 Thomas P Kingsford Balancing device for centrifugal pumps, turbines, blowers, and the like.
US1157240A (en) * 1913-02-28 1915-10-19 Fairbanks Morse & Co Balanced centrifugal pump.
US1563129A (en) * 1921-11-30 1925-11-24 Weil Ludwig Centrifugal pump or blower and similar machine
US3414188A (en) * 1966-11-25 1968-12-03 American Radiator & Standard Fan having hollow blades
US5244349A (en) * 1992-09-24 1993-09-14 Wang Sui Mu Air fan with lightly-constructed reinforcing fan blades

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070269312A1 (en) * 2006-05-22 2007-11-22 Delta Electronics, Inc. Assembly of blade units for wind power generation
GB2452104A (en) * 2008-01-14 2009-02-25 Flakt Woods Ltd A meridional fan
GB2452104B (en) * 2008-01-14 2009-07-22 Flakt Woods Ltd A meridional fan
US20090232648A1 (en) * 2008-03-14 2009-09-17 Wayne State University Reduction of flow-induced noise in a centrifugal blower
US8231331B2 (en) 2008-03-14 2012-07-31 Wayne State University Reduction of flow-induced noise in a centrifugal blower
US20150050133A1 (en) * 2013-08-15 2015-02-19 Aerocool Advanced Technologies Corporation Fan structure
US9562536B2 (en) * 2013-08-15 2017-02-07 Aerocool Advanced Technologies Corporation Fan structure
EP3534014A1 (en) * 2018-02-28 2019-09-04 Garrett Transportation I Inc. Turbocharger compressor having adjustable-trim mechanism including vortex reducers

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