US20120244008A1 - Impeller structure - Google Patents

Impeller structure Download PDF

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Publication number
US20120244008A1
US20120244008A1 US13/427,337 US201213427337A US2012244008A1 US 20120244008 A1 US20120244008 A1 US 20120244008A1 US 201213427337 A US201213427337 A US 201213427337A US 2012244008 A1 US2012244008 A1 US 2012244008A1
Authority
US
United States
Prior art keywords
blades
blade
reinforcing ribs
edge
impeller structure
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
US13/427,337
Other languages
English (en)
Inventor
Shun-Chen Chang
Wen-Bin Liu
Bo-Chun 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.)
Delta Electronics Inc
Original Assignee
Delta Electronics Inc
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 Delta Electronics Inc filed Critical Delta Electronics Inc
Assigned to DELTA ELECTRONICS, INC. reassignment DELTA ELECTRONICS, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: CHANG, SHUN-CHEN, CHEN, BO-CHUN, LIU, WEN-BIN
Publication of US20120244008A1 publication Critical patent/US20120244008A1/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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • 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
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • 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
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F04D29/329—Details of the hub

Definitions

  • the invention relates to an impeller structure, and in particular to an impeller structure with reinforcing ribs.
  • large-scale fans used in air-conditioning systems have a large size and high rotating speed.
  • one solution for impellers of large-scale fans are that they are made from metal.
  • the mold for making a metal impeller due to very high precision requirements for the mold for making a metal impeller, much labor and resources are needed, thus increasing development costs. Further, the consistency of the quality of the metal impeller made by a mold is not stable. Also, the cost of metal is high.
  • the impeller is made from plastic.
  • the strength of plastic may be inefficient. For example, under high temperatures at high rotation speeds, a plastic impeller may deform more easily.
  • FIG. 1 To improve the strength of the impeller 100 , a fixed ring 120 is disposed on ends of blades 110 .
  • the flow field of the impeller structure is completely separated by the fixed ring 120 , and the flow field within the fixed ring 120 interferes with the flow field on the outside of the fixed ring 120 . Note that the weight of the impeller 100 is greatly increased due to the fixed ring 120 .
  • the object of the invention is to provide an impeller structure and a fan.
  • the fan includes the impeller structure.
  • the impeller structure includes a plurality of reinforcing ribs and a plurality of blades.
  • the reinforcing ribs are disposed between the blades, and located between side edges and connecting edges of the blades, and thus the balance of the blades is improved without sacrificing strength thereof, and the interference of the flow fields is reduced.
  • the impeller structure includes a hub, a plurality of blades, and a plurality of reinforcing ribs.
  • the hub is rotated about a rotation axis, and has an outer surface.
  • the blades are extended from the outer surface.
  • Each of the blades has a windward surface and a leeward surface opposite to the windward surface.
  • each of the blades has a side edge, a connecting edge opposite to the side edge, a trailing edge, and a leading edge opposite to the trailing edge thereof.
  • the side edge is distant from the hub, and the connecting edge is connected to the hub.
  • the reinforcing ribs are annularly and separately disposed on the blades, and located between the side edges and the connecting edges of the blades.
  • An end of one of the reinforcing ribs is connected to the windward surface of one of the blades, and the other end of the one of the reinforcing ribs is connected to a leeward surface of an adjacent blade. Moreover, the end of the one of the reinforcing ribs is adjacent to the leading edge of the blade and is distant from the trailing edge of the blade. The other end of the one of the reinforcing ribs is adjacent to a trailing edge of the adjacent blade and is distant from a leading edge of the adjacent blade.
  • the impeller structure includes a hub, a plurality of sub-blades, a separation ring, a plurality of blades, and a plurality of reinforcing ribs.
  • the hub is rotated about a rotation axis, and has an outer surface.
  • the sub-blades are radiantly extended from the outer surface of the hub, respectively.
  • the separation ring is disposed on the end of the sub-blades.
  • the blades are extended from the separation ring opposite to the sub-blades.
  • Each of the blades has a windward surface and a leeward surface opposite to the windward surface.
  • each of the blades has a side edge, a connecting edge opposite to the side edge, a trailing edge, and a leading edge opposite to the trailing edge.
  • the side edge is distant from the separation ring, and the connecting edge is connected to the separation ring.
  • the reinforcing ribs are annularly and separately disposed on the blades, and located between the side edges and the connecting edges of the blades. An end of one of the reinforcing ribs is connected to the windward surface of one of the blades, and the other end of the one of the reinforcing ribs is connected to a leeward surface of an adjacent blade. Moreover, the end of the one of the reinforcing ribs is adjacent to the leading edge of the blade and is distant from the trailing edge of the blade. The other end of the one of the reinforcing ribs is adjacent to a trailing edge of the adjacent blade and is distant from a leading edge of the adjacent blade.
  • the strength of the impeller structure can be improved.
  • the impeller structure may be made by plastic, and the cost of the impeller structure can be decreased.
  • the manufacturing of the impeller structure is easier and more precise.
  • the weight of the blades is reduced due to the small size and light weight of the reinforcing ribs, and thus the balance of the rotation of the impeller structure is improved.
  • the blades are not completely separated into two parts by the reinforcing ribs, and thus the interference between the inner and outer flow fields of the impeller structure can be reduced.
  • FIG. 1 is a perspective view of an impeller structure of the prior art
  • FIG. 2 is a perspective view of an impeller structure of a first embodiment of the invention
  • FIG. 3 is a top view of the impeller structure of the first embodiment of the invention.
  • FIG. 4 is a side view of the impeller structure of the first embodiment of the invention.
  • FIG. 5 is a cross-sectional view of the reinforcing rib along AA line of FIG. 4 ;
  • FIG. 6 is a perspective view of an impeller structure of a second embodiment of the invention.
  • FIG. 7 is a top view of the impeller structure of the second embodiment of the invention.
  • FIG. 2 is a perspective view of an impeller structure of a first embodiment of the invention.
  • FIG. 3 is a top view of the impeller structure of the first embodiment of the invention.
  • FIG. 4 is a side view of the impeller structure of the first embodiment of the invention.
  • the impeller structure 200 may be connected to a motor (not shown in the figures) to form a fan.
  • the impeller structure 200 is driven by the motor to generate an air flow. It is noted that the impeller structure can be used in a fan.
  • the impeller structure 200 may be made from plastic.
  • the impeller structure 200 includes a hub 210 , a plurality of blades 220 , and a plurality of reinforcing ribs 230 .
  • the hub 210 is circular disc shaped with a hollow structure.
  • the hub 210 is disposed on the motor, and driven by the motor to rotate about a rotation axis AX 1 . Further, the hub 210 has an outer surface 211 .
  • Each of the blades 220 is a thin stripped structure, and may be made from plastic.
  • the blades 220 are radiantly extended from the outer surface 211 .
  • Each of the blades 220 has a windward surface 221 and a leeward surface 222 .
  • the windward surface 221 and the leeward surface 222 are located at two opposite sides of the blade 220 , and occupy most of the surface area of the blade 220 .
  • the windward surface 221 faces an area where the air flow flows into the impeller structure 200
  • the leeward surface 222 faces an area where the air flow flows out of the impeller structure 200 .
  • Each of the blades 220 has a side edge 223 , a connecting edge 224 , a trailing edge 225 , and a leading edge 226 .
  • the windward surface 221 and the leeward surface 222 are surrounded by the side edge 223 , the connecting edge 224 , the trailing edge 225 , and the leading edge 226 .
  • the side edge 223 and the connecting edge 224 are disposed on two opposite sides of the blade 220 .
  • the side edge 223 is distant from hub 210 , and the connecting edge 224 is connected to the hub 210 .
  • the trailing edge 225 corresponds to an area where the air flow flows into the impeller structure 200 .
  • the leading edge 226 corresponds to an area where the air flow flows out of the impeller structure 200 .
  • the trailing edge 225 and the leading edge 226 are disposed on two opposite sides of the blade 220 , and are connected to the side edge 223 and the connecting edge 224 . As shown in FIG. 4 , the leading edge 226 of the blade 220 is near a trailing edge 225 a of an adjacent blade 220 a , and is distant from a leading edge 226 a of the adjacent blade 220 a.
  • the reinforcing ribs 230 are annularly and separately disposed on the blades 220 , and are located between the side edges 223 and the connecting edges 224 of the blades 220 .
  • An end of the reinforcing rib 230 is connected to the windward surface 221 of the blade 220 , and the other end of the reinforcing ribs 230 is connected to the leeward surface 222 a of the adjacent blade 220 a .
  • the end of the reinforcing rib 230 connected to the windward surface 221 is adjacent to the leading edge 226 , and is distant from trailing edge 225 .
  • reinforcing rib 230 connected to the leeward surface 222 a of the adjacent blade 220 a is adjacent to the trailing edge 225 a , and is distant from the leading edge 226 a of the adjacent blade 220 a.
  • the blade 220 has a wing-tip chord length W 2 between the trailing edge 225 and the leading edge 226 .
  • the width W 1 of the reinforcing rib 230 is smaller than half of the wing-tip chord length W 2 of the blade 220 .
  • the width W 1 of the reinforcing rib 230 is smaller than one-third the wing-tip chord length W 2 of the blade 220 .
  • the reinforcing rib 230 is perpendicular to the blade 220 , and the reinforcing rib 230 is connected to the blade 220 at an area from one-third to two-third of the length L 1 , which is from the side edge 223 to the connecting edge 224 , of the blade 220 .
  • the strength of the blade 220 can be improved.
  • the reinforcing rib 230 is arranged along a circular track, wherein the rotation axis AX 1 is at the center of the circular track.
  • the separation space S 1 is between the windward surface 221 of the blade 220 and the leeward surface 222 a of the blade 220 a .
  • the reinforcing rib 230 is extended along an extension direction D 1 , and the air flow flows into the impeller structure 200 along an air intake direction D 2 .
  • the extension direction D 1 is 45 degrees to the air intake direction D 2 or the rotation axis AX 1 , and thus the flow resistance generated by the reinforcing rib 230 can be decreased.
  • the reinforcing rib 230 and the reinforcing rib 230 a are connected to two opposite sides of the blade 220 , and the extensions of the reinforcing rib 230 and the reinforcing rib 230 a are not overlapped or crossed along the extension direction D 1 or the air intake direction D 2 .
  • the separation space S 1 between the blade 220 and the adjacent blade 220 a are not completely separated into an inner zone Z 1 and an outer zone Z 2 (as shown in FIG. 3 ) by the reinforcing rib 230 .
  • the inner zone Z 1 and the outer zone Z 2 between the blade 220 and the blade 220 a are communicated to each other.
  • the flow field of the air flow will not completely be separated by the reinforcing rib 230 a between the blade 220 and the blade 220 a , and the interference between an inner flow field in the inner zone Z 1 and an outer flow field in the outer zone Z 2 can be reduced.
  • FIG. 5 is a cross-sectional view of the reinforcing rib 230 along AA line of FIG. 4 .
  • the extension direction D 1 (as shown in FIG. 4 ) is perpendicular to the cross section of the reinforcing rib 230 .
  • the cross section of the reinforcing rib 230 is rectangular with rounded ends.
  • the ends of the reinforcing ribs 230 have a conduction current function.
  • the shape of the cross section of the reinforcing rib 230 is not limited. In the other embodiment, the shape of the cross section of the reinforcing rib 230 may be rectangular, an ellipse, a trapezoid or wing shaped.
  • FIG. 6 is a perspective view of an impeller structure 200 a of a second embodiment of the invention.
  • FIG. 7 is a top view of the impeller structure 200 a of the second embodiment of the invention.
  • the differences between the second embodiment and the first embodiment are described as following.
  • the impeller structure 200 a further includes a plurality of sub-blades 240 and a separation ring 250 .
  • the sub-blades 240 are radiantly extended from the outer surface 211 of the hub 210 .
  • the separation ring 250 is a ring structure around the hub 210 .
  • the separation ring 250 is disposed on the ends of the sub-blades 240 .
  • the blades 220 are extended from the separation ring 250 .
  • the sub-blades 240 and the blades 220 are disposed on two opposite sides of the separation ring 250 . Moreover, the length of the sub-blade 240 is smaller than the length of the blade 220 , and the number of the sub-blades 240 is greater than the number of blades 220 .
  • the hub 210 is pivoted on a base (not shown in the figures), and a guide tube (not shown in the figures) is connected to the separation ring 250 .
  • An air flow is transmitted to the sub-blade 240 within the separation ring 250 by the guide tube to drive the sub-blade 240 to rotate.
  • the blades 220 of the impeller structure 200 a are rotated due to the sub-blades 240 , and the blades 220 drive an air flow, outside the guide tube, flowing.
  • the strength of the impeller structure can be improved.
  • the impeller structure can be made by plastic, and the cost of the impeller structure can be decreased.
  • the manufacturing of the impeller structure is easier and more precise.
  • the weight of the blades is reduced due to the small size and light weight of the reinforcing ribs, and thus the balance of the rotation of the impeller structure is improved.
  • the blades are not completely separated into two parts by the reinforcing ribs, and thus the interference between the inner and outer flow fields of the impeller structure 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)
US13/427,337 2011-03-25 2012-03-22 Impeller structure Abandoned US20120244008A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TW100110236A TWI418708B (zh) 2011-03-25 2011-03-25 葉輪結構
TW100110236 2011-03-25

Publications (1)

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US20120244008A1 true US20120244008A1 (en) 2012-09-27

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Family Applications (1)

Application Number Title Priority Date Filing Date
US13/427,337 Abandoned US20120244008A1 (en) 2011-03-25 2012-03-22 Impeller structure

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US (1) US20120244008A1 (zh)
TW (1) TWI418708B (zh)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USD782639S1 (en) * 2015-06-24 2017-03-28 Mitsubishi Electric Corporation Propeller fan
USD797917S1 (en) * 2015-08-17 2017-09-19 Delta T Corporation Fan with light
US10294965B2 (en) 2016-05-25 2019-05-21 Honeywell International Inc. Compression system for a turbine engine
USD859630S1 (en) * 2015-11-20 2019-09-10 Kichler Lighting Llc Ceiling fan
USD900994S1 (en) * 2019-02-06 2020-11-03 Camco Manufacturing, Inc. Replacement vent fan blade
US11053950B2 (en) 2018-03-14 2021-07-06 Carrier Corporation Centrifugal compressor open impeller
US20210262490A1 (en) * 2015-06-16 2021-08-26 ResMed Pty Ltd Impeller with inclined and reverse inclined blades
USD940759S1 (en) * 2015-12-01 2022-01-11 Transportation Ip Holdings, Llc Blower assembly
US11913355B2 (en) 2022-02-14 2024-02-27 General Electric Company Part-span shrouds for pitch controlled aircrafts

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US4181A (en) * 1845-09-09 John ericsson
US265984A (en) * 1882-10-17 Fan-wheel
US937006A (en) * 1906-03-03 1909-10-12 Allis Chalmers Steam-turbine.
US2472886A (en) * 1946-11-01 1949-06-14 Westinghouse Electric Corp Turbine blade lashing
US2872988A (en) * 1954-09-10 1959-02-10 Westinghouse Electric Corp Air translating apparatus
US3131461A (en) * 1961-04-20 1964-05-05 Carrier Corp Method of making vibration damped turbo machinery
US3527546A (en) * 1969-01-02 1970-09-08 Gen Electric Tie pins for turbine buckets
US3635589A (en) * 1969-03-31 1972-01-18 Nordisk Ventilator Double impeller wheel
US3708244A (en) * 1970-04-13 1973-01-02 Rolls Royce Bladed rotor for a gas turbine engine
US4734010A (en) * 1985-05-31 1988-03-29 Bbc Brown, Boveri & Company, Limited Damping element for independent turbomachine blades
USRE32737E (en) * 1980-06-30 1988-08-23 Southern California Edison Continuous harmonic shrouding
US5454695A (en) * 1994-07-05 1995-10-03 Ford Motor Company High output engine cooling fan
US5498136A (en) * 1993-09-17 1996-03-12 Hitachi, Ltd. Fluid machinery having blade apparatus and blade apparatus for fluid machinery
US5755557A (en) * 1995-08-03 1998-05-26 Valeo Thermique Moteur Axial flow fan
US5829956A (en) * 1997-04-22 1998-11-03 Chen; Yung Fan blade assembly
US20020141871A1 (en) * 2001-01-30 2002-10-03 Lakshimikantha Medamaranahally Axial-flow fan having inner and outer blades
US6591873B1 (en) * 2001-11-21 2003-07-15 Air Cruisers Company Turbo fan aspirator
US20070031248A1 (en) * 2005-08-04 2007-02-08 Delta Electronics, Inc. Passive fan assembly
US20080056899A1 (en) * 2006-08-30 2008-03-06 Delta Electronics, Inc. Fan and impeller thereof
US20090004011A1 (en) * 2007-06-27 2009-01-01 Kabushiki Kaisha Toshiba Steam turbine, and intermediate support structure for holding row of long moving blades therein
US7484925B2 (en) * 2005-05-10 2009-02-03 Emp Advanced Development, Llc Rotary axial fan assembly
US20090196744A1 (en) * 2008-02-01 2009-08-06 Delta Electronics, Inc. Fan and impeller thereof
US20100068060A1 (en) * 2006-12-11 2010-03-18 Hidetake Ota Cooling fan
US20100086405A1 (en) * 2008-10-08 2010-04-08 Nidec Servo Corporation Impeller, fan apparatus using the same, and method of manufacturing impeller
US7758303B1 (en) * 2006-07-31 2010-07-20 General Electric Company FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween
US20110014052A1 (en) * 2007-09-13 2011-01-20 Borgwarner Inc. Fan with structural support ring
US8192141B1 (en) * 2007-04-05 2012-06-05 The United States Of America As Represented By The Secretary Of The Air Force Dual compression rotor

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US6537030B1 (en) * 2000-10-18 2003-03-25 Fasco Industries, Inc. Single piece impeller having radial output
TWM241513U (en) * 2003-10-22 2004-08-21 Jin-Chin Gu Anti-oscillation structure for DC heat-dissipation fan
TWM250230U (en) * 2004-01-13 2004-11-11 Forcecon Technology Co Ltd Wind-blocking ring body structure of centrifugal type heat dissipation fan
TWI284708B (en) * 2004-07-16 2007-08-01 Hon Hai Prec Ind Co Ltd Fan blade set
US20100232948A1 (en) * 2009-03-10 2010-09-16 Alex Horng Fan Housing

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4181A (en) * 1845-09-09 John ericsson
US265984A (en) * 1882-10-17 Fan-wheel
US937006A (en) * 1906-03-03 1909-10-12 Allis Chalmers Steam-turbine.
US2472886A (en) * 1946-11-01 1949-06-14 Westinghouse Electric Corp Turbine blade lashing
US2872988A (en) * 1954-09-10 1959-02-10 Westinghouse Electric Corp Air translating apparatus
US3131461A (en) * 1961-04-20 1964-05-05 Carrier Corp Method of making vibration damped turbo machinery
US3527546A (en) * 1969-01-02 1970-09-08 Gen Electric Tie pins for turbine buckets
US3635589A (en) * 1969-03-31 1972-01-18 Nordisk Ventilator Double impeller wheel
US3708244A (en) * 1970-04-13 1973-01-02 Rolls Royce Bladed rotor for a gas turbine engine
USRE32737E (en) * 1980-06-30 1988-08-23 Southern California Edison Continuous harmonic shrouding
US4734010A (en) * 1985-05-31 1988-03-29 Bbc Brown, Boveri & Company, Limited Damping element for independent turbomachine blades
US5498136A (en) * 1993-09-17 1996-03-12 Hitachi, Ltd. Fluid machinery having blade apparatus and blade apparatus for fluid machinery
US5454695A (en) * 1994-07-05 1995-10-03 Ford Motor Company High output engine cooling fan
US5755557A (en) * 1995-08-03 1998-05-26 Valeo Thermique Moteur Axial flow fan
US5829956A (en) * 1997-04-22 1998-11-03 Chen; Yung Fan blade assembly
US20020141871A1 (en) * 2001-01-30 2002-10-03 Lakshimikantha Medamaranahally Axial-flow fan having inner and outer blades
US6591873B1 (en) * 2001-11-21 2003-07-15 Air Cruisers Company Turbo fan aspirator
US7484925B2 (en) * 2005-05-10 2009-02-03 Emp Advanced Development, Llc Rotary axial fan assembly
US20070031248A1 (en) * 2005-08-04 2007-02-08 Delta Electronics, Inc. Passive fan assembly
US7758303B1 (en) * 2006-07-31 2010-07-20 General Electric Company FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween
US20080056899A1 (en) * 2006-08-30 2008-03-06 Delta Electronics, Inc. Fan and impeller thereof
US20100068060A1 (en) * 2006-12-11 2010-03-18 Hidetake Ota Cooling fan
US8192141B1 (en) * 2007-04-05 2012-06-05 The United States Of America As Represented By The Secretary Of The Air Force Dual compression rotor
US20090004011A1 (en) * 2007-06-27 2009-01-01 Kabushiki Kaisha Toshiba Steam turbine, and intermediate support structure for holding row of long moving blades therein
US20110014052A1 (en) * 2007-09-13 2011-01-20 Borgwarner Inc. Fan with structural support ring
US20090196744A1 (en) * 2008-02-01 2009-08-06 Delta Electronics, Inc. Fan and impeller thereof
US20100086405A1 (en) * 2008-10-08 2010-04-08 Nidec Servo Corporation Impeller, fan apparatus using the same, and method of manufacturing impeller

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20210262490A1 (en) * 2015-06-16 2021-08-26 ResMed Pty Ltd Impeller with inclined and reverse inclined blades
US11846303B2 (en) * 2015-06-16 2023-12-19 ResMed Pty Ltd Impeller with inclined and reverse inclined blades
USD800889S1 (en) 2015-06-24 2017-10-24 Mitsubishi Electric Corporation Propeller fan
USD782639S1 (en) * 2015-06-24 2017-03-28 Mitsubishi Electric Corporation Propeller fan
USD803378S1 (en) 2015-06-24 2017-11-21 Mitsubishi Electric Corporation Propeller fan
USD800890S1 (en) 2015-06-24 2017-10-24 Mitsubishi Electric Corporation Propeller fan
USD797917S1 (en) * 2015-08-17 2017-09-19 Delta T Corporation Fan with light
USD859630S1 (en) * 2015-11-20 2019-09-10 Kichler Lighting Llc Ceiling fan
USD965764S1 (en) * 2015-11-20 2022-10-04 Kichler Lighting Llc Ceiling fan
USD940759S1 (en) * 2015-12-01 2022-01-11 Transportation Ip Holdings, Llc Blower assembly
US10294965B2 (en) 2016-05-25 2019-05-21 Honeywell International Inc. Compression system for a turbine engine
US11053950B2 (en) 2018-03-14 2021-07-06 Carrier Corporation Centrifugal compressor open impeller
USD900994S1 (en) * 2019-02-06 2020-11-03 Camco Manufacturing, Inc. Replacement vent fan blade
US11913355B2 (en) 2022-02-14 2024-02-27 General Electric Company Part-span shrouds for pitch controlled aircrafts

Also Published As

Publication number Publication date
TWI418708B (zh) 2013-12-11
TW201239202A (en) 2012-10-01

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AS Assignment

Owner name: DELTA ELECTRONICS, INC., TAIWAN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:CHANG, SHUN-CHEN;LIU, WEN-BIN;CHEN, BO-CHUN;REEL/FRAME:027912/0012

Effective date: 20111028

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION