US3620640A - Propeller or fan shrouds - Google Patents

Propeller or fan shrouds Download PDF

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Publication number
US3620640A
US3620640A US22748A US3620640DA US3620640A US 3620640 A US3620640 A US 3620640A US 22748 A US22748 A US 22748A US 3620640D A US3620640D A US 3620640DA US 3620640 A US3620640 A US 3620640A
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US
United States
Prior art keywords
shroud
propeller
along
flaps
movable flaps
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
US22748A
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English (en)
Inventor
Jean Soulez-Lariviere
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.)
Airbus Group SAS
Original Assignee
Airbus Group SAS
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
Priority claimed from FR6909125A external-priority patent/FR2034406A1/fr
Priority claimed from FR7007625A external-priority patent/FR2096639B2/fr
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Application granted granted Critical
Publication of US3620640A publication Critical patent/US3620640A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • An improved propeller shroud comprising a toroidal cavity formed on its inside surface along its entire periphery level with the blades of said propeller and along the meridian of the shroud and movable flaps mounted on downstream of same cooperating with a cavity bottom comprising a retractable wall with or without streamlined partition walls adapted within said toroidal cavity and along substantially meridian planes of said shroud.
  • the present invention concerns improvements to propeller or fan shrouds.
  • shroud is fonned with a toroidal peripheralcavitylevel with the propeller blades, within which the marginal eddies produced by the blade lift are trapped. In this way the flow continuity between the blades and the shroud 'is assured without the needto observe the close tolerances" referred to precedingly.
  • the cavity has disposed therein, alongithe substantially meridian plane of the shroud, partitionswhich'are'. so profiled-assto foster rotation of the air in a substantially meridian-direction. counter to the normal direction of rotation of theairdriven'by.
  • the toroidal cavity has a large diameter of the same order of magnitude-asih'e" thickness of the shroud, whereby it is possible if desired to eliminate the entire upstream portion of the-shroud, which becomes redundant.
  • the bottom of saidcavity may eitherbe fixed or be formed by a retractable wall.
  • the shroud for carrying the subject-method of this invention-into practice has movable flaps associated thereto, whereby-a-convergent or divergent stream. of fluid is obtained onexit :from the shroud.
  • the present invention includes in its scope such shrouds-as embody the subject method of this invention.
  • FIG. 1 is a highly diagrammatic perspective view of a shroud section according to the invention
  • FIG. 2 is a sectional view in elevation of an improved shroud according to an alternative embodiment of the invention.
  • FIG. 3 illustrates an improved shroud according to a third possible embodiment of the invention
  • FIGS. 4 and 5 are schematic sectional viewsin elevation of an improved shroud according to a fourth possible embodiment of the invention, with flaps andthe devices associated thereto depicted in their divergent efflux and convergent efflux positions respectively;
  • FIG. 6 is a perspective view of an example of a movable flap associated to the shroud of FIG. 2;
  • FIG. 7 is a schematic top view of a succession of movable flaps in their divergent efflux and convergent efflux" positions;
  • FIG. 11 is a sectional plan view-on a smaller scale of an improved shroud according to the invention.
  • FIGS. 12 and 13 are schematic sectional views in elevation of' an improved shroud accordingto yet another alternative embodiment,. with flaps and their associated devices shown respectively in their divergent efflux and convergent efflux positions;
  • FIGS. 14 and 15 are schematicsectional views in elevation on an enlarged scale, respectively) portraying the fitting method and the-flap actuating mechanism for the embodiment illustrated in FIGS. 12 and 13.
  • the flaps assume the form shownxi'n FIG. 6 and are. hingedly mounted about a hinge-pin Sfast with the trailing edge of the shroud, and these flapscoverone another partially after the fashion of. scales walls without flow separation phenomena are to be found once more in: the;case of the embodiment shown in FIG. 3, but with an additional advantage.
  • the toroidal. cavity 2 is-given a large diameter of the same order of magnitude as the thickness of the shroud, thereby enabling all the upflow portion of,the shroud (shown in dashlines in the drawings) to be dispensed with since it becomes redundant.
  • partitions 5 (shown in dashlines in the drawings) may or may not be provided.
  • FIGS. 4', 5 and 8 to 11 illustrate another possible embodiment of the invention which is especially advantageous in the case of vertical takeoff craft. It is well known, indeed, that the exhaust jet must be divergent in still air and that the ratio of the outer diameter to the inner diameter of the shroud must be greater than 1:20. In high speed forward flight, on the other hand, the shroud must be of small thickness in order not to create parasite drag, while the intake must be noncambered or cambered inwardly slightly, and the exit must be convergent.
  • the form of embodiment shown in these figures provides a compromise solution on the configurations imposed by limit operating conditions.
  • this alternative embodiment includes profiled partitions 5 positioned substantially along the meridians of the shroud and a bottom consisting of a retractable wall 9. These partitions are hollow and preferably sufficiently thick to house the various control means to be described hereinafter.
  • the retractable wall is preferably made of an elastic material and is rigidly united with the shroud at 1c; its trailing edge carries a rod 10 actuated by a link 11 housed within 5 and hinged at 12. Rod 10 is furthermore guided in its motion by a circular arc-shaped groove 13.
  • the elastic wall or membrane 9 can assume either of two limit positions depicted in solid lines and dashlines respectively in FIG. 9 and represented in FIGS. 4 and 5.
  • this membrane forms the bottom of the toroidal cavity, whereas in the position shown in FIG. 5 the bottom of the shown in FIG. 6 or be made, in accordance with an alternative embodiment, of some resilient material which can be fitted and controlled as follows (see FIG. 10).
  • the flap 7a has its leading edge 14 made fast with the partitions 5 by any convenient means (such as a keeper ring).
  • a metal reinforcement 15 is buried in its midst and carries a setsquare-shaped part 16 which is hinged at 17 and connected at 18 to a rod 19 which is controlled by a link 20 pivotally connected to the shroud 1 at 21.
  • the link 20 When the link 20 is in the position shown in solid lines in FIG. 10, the annular flap 7a will be in the position shown in solid lines on the same figure.
  • the link 20 is caused to move into the position shown in dashlines in FIG. 10
  • the part 16 pivots about the hinge point 17 and moves the flap 7a into the position shown in dashlines, whereupon the interconnection point 18 moves to the position 18a.
  • Actuation of retractable wall 9 (by means of link 11) and of flap 7a (by means of link 20) can be synchronized by any convenient means which it would be unnecessary to describe here since they are familiar to the specialist in the art.
  • retractable wall 9 and flap 7a may concurrently occupy variable positions, the limit positions being shown diagrammatically in FIGS. 4 and 5.
  • FIGS. 4 and 5 show that in case of a divergent exhaust for takeoff (FIG. 4), the stream escaping from the periphery of the propeller is impelled forwardly (arrows f3) and thereafter sucked in once more to form a trapped vortex in the partitioned cavity sections of the shroud (arrows f4).
  • An appropriate degree of twist to the blade tips will impart to the air recycled in said vortex and to the air immediately adjacent to the neighboring layer the high total head needed to stabilize the diffusion process on the streamlines flap 7a.
  • the inner wall surface of the shroud 1 connected to the engine pod la, by means of braces lb is formed with a toroidal cavity 2 level with the propeller blades 3, which cavity has a diameter of the same order of magnitude as the thickness of the shroud, thereby making the entire upstream portion of the shroud redundant and enabling it to be dispensed with.
  • streamlined partitions in dot-dash lines
  • the bottom of the shroud is formed by a retractable wall 9a which may be either rigid or elastic.
  • the upstream edge of said wall supports a rod 10a guided along a slideway 13a formed in the shroud 1.
  • This rod is connected to a nut or threaded sleeve 21 cooperating with a screw 1 lb which is rotated by a suitable gear train represented schematically on FIG. 15 by reference numeral 22.
  • Rod 10a also forms a hinge pin for the link 19a, the other end of which is pivotally connected at 8b to the upstream end of a flap 7c capable of pivoting about a downstream hinge pin 8a.
  • a well 23 is provided in the downstream part of the shroud for receiving the flap 70 when the same is in its convergent efflux" position (see FIG. 13 and the position shown in dot-dash lines in FIG. 15).
  • the links can be dispensed with.
  • FIGS. 12 and 13 corresponds to the divergent configuration of the streamlines F subsequent to trapping (F in the shroud with its toroidal cavity (provided or not with partitions 5), while FIG. 13 corresponds to the convergent configuration of said streamlines.
  • An improved propeller or fan shroud comprising on its inner surface and along its entire periphery a toroidal cavity having a width of the same order of magnitude as the thickness of the shroud, a cavity bottom comprising a retractable wall, movable flaps mounted on the downstream end of said shroud, and means operatively connected between said flaps and said bottom whereby to cause motion of the latter to impart motion to said flaps between two limit positions, to wit a divergent exhaust position and a convergent exhaust position.
  • a shroud according to claim 2 comprising a slidewayforming groove, one edge of said retractable wall sliding therein.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Toys (AREA)
US22748A 1969-03-27 1970-03-26 Propeller or fan shrouds Expired - Lifetime US3620640A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR6909125A FR2034406A1 (ja) 1969-03-27 1969-03-27
FR7007625A FR2096639B2 (ja) 1970-03-10 1970-03-10

Publications (1)

Publication Number Publication Date
US3620640A true US3620640A (en) 1971-11-16

Family

ID=26214928

Family Applications (1)

Application Number Title Priority Date Filing Date
US22748A Expired - Lifetime US3620640A (en) 1969-03-27 1970-03-26 Propeller or fan shrouds

Country Status (6)

Country Link
US (1) US3620640A (ja)
JP (1) JPS5018607B1 (ja)
BE (1) BE747870A (ja)
DE (1) DE2014864C3 (ja)
GB (1) GB1300661A (ja)
NL (1) NL7004146A (ja)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3893782A (en) * 1974-03-20 1975-07-08 Westinghouse Electric Corp Turbine blade damping
US3930480A (en) * 1974-05-02 1976-01-06 Yanmar Diesel Engine Co., Ltd. Fuel-injection pump for an internal combustion engine
US3934410A (en) * 1972-09-15 1976-01-27 The United States Of America As Represented By The Secretary Of The Navy Quiet shrouded circulation control propeller
US3986787A (en) * 1974-05-07 1976-10-19 Mouton Jr William J River turbine
US4061188A (en) * 1975-01-24 1977-12-06 International Harvester Company Fan shroud structure
US4086022A (en) * 1975-09-25 1978-04-25 Rolls-Royce Limited Gas turbine engine with improved compressor casing for permitting higher air flow and pressure ratios before surge
US4895489A (en) * 1986-11-14 1990-01-23 Yasuaki Kohama Axial flow fan
US5248224A (en) * 1990-12-14 1993-09-28 Carrier Corporation Orificed shroud for axial flow fan
WO1995006822A1 (en) * 1993-08-30 1995-03-09 Airflow Research Manufacturing Corporation Housing with recirculation control for use with banded axial-flow fans
US5423660A (en) * 1993-06-17 1995-06-13 Airflow Research And Manufacturing Corporation Fan inlet with curved lip and cylindrical member forming labyrinth seal
US5431533A (en) * 1993-10-15 1995-07-11 United Technologies Corporation Active vaned passage casing treatment
US5482150A (en) * 1992-03-31 1996-01-09 Ina Walzlager Schaeffler Kg Bushed overrunning clutches
US5489186A (en) * 1991-08-30 1996-02-06 Airflow Research And Manufacturing Corp. Housing with recirculation control for use with banded axial-flow fans
WO2003072910A1 (de) * 2002-02-28 2003-09-04 Mtu Aero Engines Gmbh Rezirkulationsstruktur für turboverdichter
US20030235495A1 (en) * 2002-06-25 2003-12-25 Rivers John F. Fan assembly for use in powered airborne vehicles
US20050226717A1 (en) * 2004-04-13 2005-10-13 Rolls-Royce Plc Flow control arrangement
US7997870B2 (en) 2007-08-14 2011-08-16 B N Balance Energy Solutions, Llc Turbine rotor for electrical power generation
CN113428355A (zh) * 2020-03-23 2021-09-24 三菱重工业株式会社 涵道风扇以及航空器
CN113425343A (zh) * 2021-07-02 2021-09-24 西安交通大学医学院第一附属医院 一种神经内镜立体定向手术辅助通道设备

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19541746C2 (de) * 1995-11-09 2001-07-12 Weis Heinz Antriebsvorrichtung

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3011762A (en) * 1956-03-28 1961-12-05 Pouit Robert Turbines and in particular gas turbines
US3230702A (en) * 1959-10-16 1966-01-25 Bertin & Cie Jet diffuser usable as a propeller shroud
US3447741A (en) * 1966-09-26 1969-06-03 Nord Aviat Soc Nationale De Co Faired propeller with diffuser

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3011762A (en) * 1956-03-28 1961-12-05 Pouit Robert Turbines and in particular gas turbines
US3230702A (en) * 1959-10-16 1966-01-25 Bertin & Cie Jet diffuser usable as a propeller shroud
US3447741A (en) * 1966-09-26 1969-06-03 Nord Aviat Soc Nationale De Co Faired propeller with diffuser

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3934410A (en) * 1972-09-15 1976-01-27 The United States Of America As Represented By The Secretary Of The Navy Quiet shrouded circulation control propeller
US3893782A (en) * 1974-03-20 1975-07-08 Westinghouse Electric Corp Turbine blade damping
US3930480A (en) * 1974-05-02 1976-01-06 Yanmar Diesel Engine Co., Ltd. Fuel-injection pump for an internal combustion engine
US3986787A (en) * 1974-05-07 1976-10-19 Mouton Jr William J River turbine
US4061188A (en) * 1975-01-24 1977-12-06 International Harvester Company Fan shroud structure
US4086022A (en) * 1975-09-25 1978-04-25 Rolls-Royce Limited Gas turbine engine with improved compressor casing for permitting higher air flow and pressure ratios before surge
US4895489A (en) * 1986-11-14 1990-01-23 Yasuaki Kohama Axial flow fan
US5248224A (en) * 1990-12-14 1993-09-28 Carrier Corporation Orificed shroud for axial flow fan
US5489186A (en) * 1991-08-30 1996-02-06 Airflow Research And Manufacturing Corp. Housing with recirculation control for use with banded axial-flow fans
US5482150A (en) * 1992-03-31 1996-01-09 Ina Walzlager Schaeffler Kg Bushed overrunning clutches
US5423660A (en) * 1993-06-17 1995-06-13 Airflow Research And Manufacturing Corporation Fan inlet with curved lip and cylindrical member forming labyrinth seal
WO1995006822A1 (en) * 1993-08-30 1995-03-09 Airflow Research Manufacturing Corporation Housing with recirculation control for use with banded axial-flow fans
US5431533A (en) * 1993-10-15 1995-07-11 United Technologies Corporation Active vaned passage casing treatment
US6935833B2 (en) 2002-02-28 2005-08-30 Mtu Aero Engines Gmbh Recirculation structure for turbo chargers
US20040156714A1 (en) * 2002-02-28 2004-08-12 Peter Seitz Recirculation structure for turbo chargers
WO2003072910A1 (de) * 2002-02-28 2003-09-04 Mtu Aero Engines Gmbh Rezirkulationsstruktur für turboverdichter
CN100395432C (zh) * 2002-02-28 2008-06-18 Mtu飞机发动机有限公司 用于涡轮压缩机的循环结构
US20030235495A1 (en) * 2002-06-25 2003-12-25 Rivers John F. Fan assembly for use in powered airborne vehicles
US6866475B2 (en) * 2002-06-25 2005-03-15 John F. Rivers Fan assembly for use in powered airborne vehicles
US20050226717A1 (en) * 2004-04-13 2005-10-13 Rolls-Royce Plc Flow control arrangement
US20090047117A1 (en) * 2004-04-13 2009-02-19 Rolls-Royce Plc Flow control arrangement
US7811049B2 (en) 2004-04-13 2010-10-12 Rolls-Royce, Plc Flow control arrangement
US7997870B2 (en) 2007-08-14 2011-08-16 B N Balance Energy Solutions, Llc Turbine rotor for electrical power generation
CN113428355A (zh) * 2020-03-23 2021-09-24 三菱重工业株式会社 涵道风扇以及航空器
EP3885581A1 (en) * 2020-03-23 2021-09-29 Mitsubishi Heavy Industries, Ltd. Ducted fan and aircraft
CN113425343A (zh) * 2021-07-02 2021-09-24 西安交通大学医学院第一附属医院 一种神经内镜立体定向手术辅助通道设备

Also Published As

Publication number Publication date
JPS5018607B1 (ja) 1975-07-01
GB1300661A (en) 1972-12-20
DE2014864C3 (de) 1975-04-17
DE2014864A1 (de) 1970-10-08
BE747870A (fr) 1970-09-24
DE2014864B2 (de) 1974-08-22
NL7004146A (ja) 1970-09-29

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