US3680977A - Framed impeller - Google Patents

Framed impeller Download PDF

Info

Publication number
US3680977A
US3680977A US50052A US3680977DA US3680977A US 3680977 A US3680977 A US 3680977A US 50052 A US50052 A US 50052A US 3680977D A US3680977D A US 3680977DA US 3680977 A US3680977 A US 3680977A
Authority
US
United States
Prior art keywords
ring
groove
duct
impeller
shoulders
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
US50052A
Other languages
English (en)
Inventor
Denis Rabouyt
Charles Louis Marsot
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
Application granted granted Critical
Publication of US3680977A publication Critical patent/US3680977A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

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

Definitions

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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
US50052A 1969-07-01 1970-06-29 Framed impeller Expired - Lifetime US3680977A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR6922183A FR2051912A5 (es) 1969-07-01 1969-07-01

Publications (1)

Publication Number Publication Date
US3680977A true US3680977A (en) 1972-08-01

Family

ID=9036714

Family Applications (1)

Application Number Title Priority Date Filing Date
US50052A Expired - Lifetime US3680977A (en) 1969-07-01 1970-06-29 Framed impeller

Country Status (3)

Country Link
US (1) US3680977A (es)
DE (1) DE2032328A1 (es)
FR (1) FR2051912A5 (es)

Cited By (47)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3932055A (en) * 1974-08-05 1976-01-13 Flatland Lloyd P Vacuum turbine for a drill
US3986787A (en) * 1974-05-07 1976-10-19 Mouton Jr William J River turbine
DE2648850A1 (de) * 1975-10-31 1977-05-18 Hitachi Ltd Axialluefter
US4131156A (en) * 1976-10-12 1978-12-26 Caterpillar Tractor Co. Fan shroud
FR2429914A1 (fr) * 1978-06-26 1980-01-25 United Technologies Corp Joint d'etancheite de tete d'aube pour une machine rotative a flux axial
US4398508A (en) * 1981-02-20 1983-08-16 Volvo White Truck Corporation Engine cooling fan construction
US4406581A (en) * 1980-12-30 1983-09-27 Hayes-Albion Corp. Shrouded fan assembly
US4441859A (en) * 1981-02-12 1984-04-10 Rolls-Royce Limited Rotor blade for a gas turbine engine
US4457519A (en) * 1977-12-12 1984-07-03 Harrington George H Sealing ring
US4491330A (en) * 1983-08-01 1985-01-01 Franklin Electric Co., Inc. Rotary lip seal
US4548548A (en) * 1984-05-23 1985-10-22 Airflow Research And Manufacturing Corp. Fan and housing
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
US4596054A (en) * 1984-07-03 1986-06-24 Air-Lock, Incorporated Pressure sealing bearing assembly for use in environmental control suits and environmental suits containing such bearing assemblies
US4949022A (en) * 1989-01-27 1990-08-14 Lipman Leonard H Solid state DC fan motor
US5075606A (en) * 1989-01-27 1991-12-24 Lipman Leonard H Solid state DC fan motor
US5183382A (en) * 1991-09-03 1993-02-02 Caterpillar Inc. Low noise rotating fan and shroud assembly
US5577888A (en) * 1995-06-23 1996-11-26 Siemens Electric Limited High efficiency, low-noise, axial fan assembly
US5740766A (en) * 1997-03-25 1998-04-21 Behr America, Inc. Automotive fan and shroud assembly
US5791876A (en) * 1997-03-25 1998-08-11 Behr America, Inc. Floating drive assembly for an automotive cooling fan
US5906179A (en) * 1997-06-27 1999-05-25 Siemens Canada Limited High efficiency, low solidity, low weight, axial flow fan
US5957661A (en) * 1998-06-16 1999-09-28 Siemens Canada Limited High efficiency to diameter ratio and low weight axial flow fan
EP1001138A1 (de) * 1998-11-10 2000-05-17 Asea Brown Boveri AG Spitzendichtung für Turbinenlaufschaufeln
US6065937A (en) * 1998-02-03 2000-05-23 Siemens Canada Limited High efficiency, axial flow fan for use in an automotive cooling system
WO2001083950A1 (en) * 2000-05-03 2001-11-08 Siemens Automotive Inc. Turbomachine with rotor-shroud seal structure
US6450760B1 (en) * 1999-11-22 2002-09-17 Komatsu Ltd. Fan device
US6508624B2 (en) * 2001-05-02 2003-01-21 Siemens Automotive, Inc. Turbomachine with double-faced rotor-shroud seal structure
EP1426559A1 (fr) * 2002-12-03 2004-06-09 Techspace Aero S.A. Virole interieure pour compresseur axial
US20040156712A1 (en) * 2003-01-29 2004-08-12 Siemens Vdo Automotive Inc. Integral tip seal in a fan-shroud structure
US6899339B2 (en) * 2001-08-30 2005-05-31 United Technologies Corporation Abradable seal having improved durability
US20060216147A1 (en) * 2005-03-26 2006-09-28 Halla Climate Control Corporation Fan and shroud assembly
US20070231128A1 (en) * 2006-03-31 2007-10-04 Caterpiller Inc. Fan assembly
US7549841B1 (en) 2005-09-03 2009-06-23 Florida Turbine Technologies, Inc. Pressure balanced centrifugal tip seal
EP2184804A1 (en) * 2008-11-07 2010-05-12 Honeywell International Ducted fan unmanned aerial vehicle conformal antenna
US20100158675A1 (en) * 2008-12-23 2010-06-24 Snecma Turbomachine rotor having blades of composite material provided with metal labyrinth teeth
US7997870B2 (en) 2007-08-14 2011-08-16 B N Balance Energy Solutions, Llc Turbine rotor for electrical power generation
US20120087791A1 (en) * 2009-06-12 2012-04-12 Johannes Waarseth-Junge Wind turbine device
US20120301277A1 (en) * 2011-05-26 2012-11-29 Chih-Hsiang Chang Fan
EP2570341A1 (de) * 2011-09-14 2013-03-20 Becker Marine Systems GmbH & Co. KG Propellerdüse
CN106628120A (zh) * 2016-12-06 2017-05-10 湖南星思科技有限公司 一种高效气动涵道体
CN107672802A (zh) * 2017-10-24 2018-02-09 南京航空航天大学 开槽涵道式卷流旋翼飞行器
US20180306207A1 (en) * 2017-04-24 2018-10-25 Asia Components Co., Ltd. Fan structure
CN111086624A (zh) * 2020-01-20 2020-05-01 张世栋 一种涵道螺旋桨用围带式桨尖扰流阻拦装置
US10724535B2 (en) * 2017-11-14 2020-07-28 Raytheon Technologies Corporation Fan assembly of a gas turbine engine with a tip shroud
US11286036B2 (en) * 2018-10-12 2022-03-29 Textron Innovations Inc. Ducted rotor blade tip extension
US11286037B2 (en) * 2018-10-12 2022-03-29 Textron Innovations Inc. Ducted rotor blade tip extension
US11448231B2 (en) * 2020-07-21 2022-09-20 Brose Fahrzeugteile SE & Co. Kommanditgesellschaft, Würzburg Cooling fan module
US11565799B2 (en) 2020-06-12 2023-01-31 Textron Innovations Inc. Adjustable ducted rotor blade tip extension

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3842710C1 (es) * 1988-12-19 1989-08-03 Mtu Muenchen Gmbh
FR2713709B1 (fr) * 1993-12-08 1996-01-12 Snecma Paroi de turbomachine comprenant un corps d'étanchéité.
DE59710621D1 (de) * 1997-09-19 2003-09-25 Alstom Switzerland Ltd Vorrichtung zur Spaltdichtung
FR3070424B1 (fr) * 2017-08-29 2020-07-03 Safran Aircraft Engines Roue de turbomachine, telle par exemple qu'un turboreacteur ou un turbopropulseur d'avion

Citations (6)

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

Patent Citations (6)

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

Cited By (60)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3986787A (en) * 1974-05-07 1976-10-19 Mouton Jr William J River turbine
US3932055A (en) * 1974-08-05 1976-01-13 Flatland Lloyd P Vacuum turbine for a drill
DE2648850A1 (de) * 1975-10-31 1977-05-18 Hitachi Ltd Axialluefter
US4131156A (en) * 1976-10-12 1978-12-26 Caterpillar Tractor Co. Fan shroud
US4457519A (en) * 1977-12-12 1984-07-03 Harrington George H Sealing ring
US4238170A (en) * 1978-06-26 1980-12-09 United Technologies Corporation Blade tip seal for an axial flow rotary machine
FR2429914A1 (fr) * 1978-06-26 1980-01-25 United Technologies Corp Joint d'etancheite de tete d'aube pour une machine rotative a flux axial
US4406581A (en) * 1980-12-30 1983-09-27 Hayes-Albion Corp. Shrouded fan assembly
US4441859A (en) * 1981-02-12 1984-04-10 Rolls-Royce Limited Rotor blade for a gas turbine engine
US4398508A (en) * 1981-02-20 1983-08-16 Volvo White Truck Corporation Engine cooling fan construction
US4491330A (en) * 1983-08-01 1985-01-01 Franklin Electric Co., Inc. Rotary lip seal
US4548548A (en) * 1984-05-23 1985-10-22 Airflow Research And Manufacturing Corp. Fan and housing
US4596054A (en) * 1984-07-03 1986-06-24 Air-Lock, Incorporated Pressure sealing bearing assembly for use in environmental control suits and environmental suits containing such bearing assemblies
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
US4949022A (en) * 1989-01-27 1990-08-14 Lipman Leonard H Solid state DC fan motor
US5075606A (en) * 1989-01-27 1991-12-24 Lipman Leonard H Solid state DC fan motor
US5183382A (en) * 1991-09-03 1993-02-02 Caterpillar Inc. Low noise rotating fan and shroud assembly
US5577888A (en) * 1995-06-23 1996-11-26 Siemens Electric Limited High efficiency, low-noise, axial fan assembly
US5740766A (en) * 1997-03-25 1998-04-21 Behr America, Inc. Automotive fan and shroud assembly
US5791876A (en) * 1997-03-25 1998-08-11 Behr America, Inc. Floating drive assembly for an automotive cooling fan
US5906179A (en) * 1997-06-27 1999-05-25 Siemens Canada Limited High efficiency, low solidity, low weight, axial flow fan
US6065937A (en) * 1998-02-03 2000-05-23 Siemens Canada Limited High efficiency, axial flow fan for use in an automotive cooling system
US5957661A (en) * 1998-06-16 1999-09-28 Siemens Canada Limited High efficiency to diameter ratio and low weight axial flow fan
EP1001138A1 (de) * 1998-11-10 2000-05-17 Asea Brown Boveri AG Spitzendichtung für Turbinenlaufschaufeln
US6450760B1 (en) * 1999-11-22 2002-09-17 Komatsu Ltd. Fan device
WO2001083950A1 (en) * 2000-05-03 2001-11-08 Siemens Automotive Inc. Turbomachine with rotor-shroud seal structure
US6471472B1 (en) 2000-05-03 2002-10-29 Siemens Canada Limited Turbomachine shroud fibrous tip seal
US6508624B2 (en) * 2001-05-02 2003-01-21 Siemens Automotive, Inc. Turbomachine with double-faced rotor-shroud seal structure
US6899339B2 (en) * 2001-08-30 2005-05-31 United Technologies Corporation Abradable seal having improved durability
EP1426559A1 (fr) * 2002-12-03 2004-06-09 Techspace Aero S.A. Virole interieure pour compresseur axial
US20040156712A1 (en) * 2003-01-29 2004-08-12 Siemens Vdo Automotive Inc. Integral tip seal in a fan-shroud structure
US6874990B2 (en) * 2003-01-29 2005-04-05 Siemens Vdo Automotive Inc. Integral tip seal in a fan-shroud structure
US20060216147A1 (en) * 2005-03-26 2006-09-28 Halla Climate Control Corporation Fan and shroud assembly
US7481615B2 (en) * 2005-03-26 2009-01-27 Halla Climate Control Corp. Fan and shroud assembly
US7549841B1 (en) 2005-09-03 2009-06-23 Florida Turbine Technologies, Inc. Pressure balanced centrifugal tip seal
US20070231128A1 (en) * 2006-03-31 2007-10-04 Caterpiller Inc. Fan assembly
US7997870B2 (en) 2007-08-14 2011-08-16 B N Balance Energy Solutions, Llc Turbine rotor for electrical power generation
EP2184804A1 (en) * 2008-11-07 2010-05-12 Honeywell International Ducted fan unmanned aerial vehicle conformal antenna
US20100328169A1 (en) * 2008-11-07 2010-12-30 Honeywell International Inc. Ducted Fan Unmanned Aerial Vehicle Conformal Antenna
US8870531B2 (en) * 2008-12-23 2014-10-28 Snecma Turbomachine rotor having blades of composite material provided with metal labyrinth teeth
US20100158675A1 (en) * 2008-12-23 2010-06-24 Snecma Turbomachine rotor having blades of composite material provided with metal labyrinth teeth
US20120087791A1 (en) * 2009-06-12 2012-04-12 Johannes Waarseth-Junge Wind turbine device
US9163640B2 (en) * 2011-05-26 2015-10-20 Delta Electronics, Inc. Fan
US20120301277A1 (en) * 2011-05-26 2012-11-29 Chih-Hsiang Chang Fan
CN102991659A (zh) * 2011-09-14 2013-03-27 贝克船舶系统有限及两合公司 螺旋桨导流管
EP2570341A1 (de) * 2011-09-14 2013-03-20 Becker Marine Systems GmbH & Co. KG Propellerdüse
US9322290B2 (en) 2011-09-14 2016-04-26 Becker Marine Systems Gmbh & Co. Kg Propeller nozzle
CN102991659B (zh) * 2011-09-14 2017-04-12 贝克船舶系统有限及两合公司 螺旋桨导流管
CN106628120B (zh) * 2016-12-06 2019-08-27 湖南星思科技有限公司 一种高效气动涵道体
CN106628120A (zh) * 2016-12-06 2017-05-10 湖南星思科技有限公司 一种高效气动涵道体
US20180306207A1 (en) * 2017-04-24 2018-10-25 Asia Components Co., Ltd. Fan structure
US10808726B2 (en) * 2017-04-24 2020-10-20 Asia Vital Components Co., Ltd. Fan structure
CN107672802A (zh) * 2017-10-24 2018-02-09 南京航空航天大学 开槽涵道式卷流旋翼飞行器
CN107672802B (zh) * 2017-10-24 2023-10-27 南京航空航天大学 开槽涵道式卷流旋翼飞行器
US10724535B2 (en) * 2017-11-14 2020-07-28 Raytheon Technologies Corporation Fan assembly of a gas turbine engine with a tip shroud
US11286036B2 (en) * 2018-10-12 2022-03-29 Textron Innovations Inc. Ducted rotor blade tip extension
US11286037B2 (en) * 2018-10-12 2022-03-29 Textron Innovations Inc. Ducted rotor blade tip extension
CN111086624A (zh) * 2020-01-20 2020-05-01 张世栋 一种涵道螺旋桨用围带式桨尖扰流阻拦装置
US11565799B2 (en) 2020-06-12 2023-01-31 Textron Innovations Inc. Adjustable ducted rotor blade tip extension
US11448231B2 (en) * 2020-07-21 2022-09-20 Brose Fahrzeugteile SE & Co. Kommanditgesellschaft, Würzburg Cooling fan module

Also Published As

Publication number Publication date
DE2032328A1 (de) 1971-03-18
FR2051912A5 (es) 1971-04-09

Similar Documents

Publication Publication Date Title
US3680977A (en) Framed impeller
US4190397A (en) Windage shield
US2404767A (en) Jet propulsion plant
KR900001301B1 (ko) 전동송풍기
US2963268A (en) Pressurized seal
JPS5898604A (ja) 軸流型ガスタ−ビンエンジンのタ−ビン排気ケ−ス組立体
GB1281786A (en) Turbine nozzles
GB1088360A (en) Improvements in gas turbine ducted fan engine sealing means
GB2081392A (en) Turbomachine seal
GB1129410A (en) Improvements in or relating to fluid flow machines
US3396905A (en) Ducted fan
EP0482791B1 (en) Windage shield
JPS6332105A (ja) ガスタ−ビンエンジン組立体
GB1008526A (en) Axial flow bladed rotor, e.g. for a turbine
US4668167A (en) Multifunction labyrinth seal support disk for a turbojet engine rotor
GB1195012A (en) Rotor for Bladed Fluid Flow Machines.
US4747750A (en) Transition duct seal
ES453880A1 (es) Maquina dinamoelectrica.
GB1109457A (en) Segmented diaphragm assembly for turbines
US2594808A (en) Means for supporting the nozzles of the combustion chambers of internal-combustion turbines
US4648792A (en) Stator vane support assembly
JPH0429850B2 (es)
GB2046849A (en) Turbomachine strut
US3909155A (en) Sealing of vaned assemblies
GB931904A (en) Fluid flow machine