WO2008151843A4 - Engine nacelle of an aircraft comprising a vortex generator arrangement - Google Patents

Engine nacelle of an aircraft comprising a vortex generator arrangement Download PDF

Info

Publication number
WO2008151843A4
WO2008151843A4 PCT/EP2008/004841 EP2008004841W WO2008151843A4 WO 2008151843 A4 WO2008151843 A4 WO 2008151843A4 EP 2008004841 W EP2008004841 W EP 2008004841W WO 2008151843 A4 WO2008151843 A4 WO 2008151843A4
Authority
WO
WIPO (PCT)
Prior art keywords
nacelle
engine
point
circumferential
vortex generator
Prior art date
Application number
PCT/EP2008/004841
Other languages
French (fr)
Other versions
WO2008151843A1 (en
Inventor
Detlev Schwetzler
Original Assignee
Airbus Gmbh
Detlev Schwetzler
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 DE102007027697.6A external-priority patent/DE102007027697B4/en
Priority claimed from DE102008025152.6A external-priority patent/DE102008025152B4/en
Application filed by Airbus Gmbh, Detlev Schwetzler filed Critical Airbus Gmbh
Priority to US12/663,094 priority Critical patent/US8827210B2/en
Priority to EP08759254.9A priority patent/EP2167380B1/en
Priority to CN200880020369.1A priority patent/CN101687542B/en
Publication of WO2008151843A1 publication Critical patent/WO2008151843A1/en
Publication of WO2008151843A4 publication Critical patent/WO2008151843A4/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • B64C7/02—Nacelles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
    • 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
    • Y02T50/10—Drag reduction

Abstract

An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators (3, 4, 5) so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators (3, 4, 5) overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor (K31) situated between two boundary lines (51, 52), wherein: • the starting point (51 a) of the first boundary line (51) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 35 degrees and the engine-nacelle longitudinal coordinate X = L/4; • the end point (51 b) of the first boundary line (51 ) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 25 degrees and the engine-nacelle longitudinal coordinate X = L⋅2/3; • the starting point (52a) of the second boundary line (52) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 90 degrees and the engine-nacelle longitudinal coordinate X = L/4; • the end point (52b) of the second boundary line (52) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 55 degrees and the engine-nacelle longitudinal coordinate X = L⋅2/3.

Claims

AMENDED CLAIMS received by the International Bureau on 05 January 2009 (05.01.09)
1. An engine nacelle (20) of an aircraft, which engine nacelle (20) comprises a nacelle housing (19) with a first side (S1) and a second side (S2) and several fin- shaped vortex generators (21, 22, 23; 31 , 32) characterized in that the fin-shaped vortex generators (21 , 22, 23; 31, 32) are arranged at least on one of the two sides (S1 , S2) of the nacelle housing (19) and are arranged so as to overlap in longitudinal direction such that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by them overall extends over an increasing region of the wing in the direction of the wingspan.
2. The engine nacelle (20) according to claim 1 , characterised in that the frontmost point of a first vortex generator (31) is located within a positioning corridor (K31) situated between two boundary lines (51 , 52), wherein:
• the starting point (51a) of the first boundary line (51) is the circumferential point of the engine nacelle (20) with the engine-nacelle circumferential angle phi = 35 degrees and the engine-nacelle longitudinal coordinate X = L/4, wherein the angle phi is being defined such that phi has a value of zero at the position of a vertical axis of the housing (19) on the side of the engine pylon (13) and runs in the circumferential direction of the housing (19), wherein X is the position on a longitudinal coordinate(KL) extending along the longitudinal axis (AG) of the nacelle housing (19), with the point where the longitudinal axis (AG) intersects the area in which the rim line of the front end (30a) of the nacelle housing (19) is situated as the starting point of the longitudinal axis (AG), and wherein L is the length of the engine nacelle (20) along the longitudinal axis (AG) of the nacelle housing (19);
• the end point (51 b) of the first boundary line (51 ) is the circumferential point of the engine nacelle (20) with the engine-nacelle circumferential angle phi = 25 degrees and the engine-nacelle longitudinal coordinate X = L*2/3; • the starting point (52a) of the second boundary line (52) is the circumferential point of the engine nacelle (20) with the engine-nacelle circumferential angle phi = 90 degrees and the engine-nacelle longitudinal coordinate X = U4;
• the end point (52b) of the second boundary line (52) is the circumferential point of the engine nacelle (20) with the engine-nacelle circumferential angle phi = 55 degrees and the engine-nacelle longitudinal coordinate X = L»2/3;
wherein in each case the boundary line is the line that extends over the external circumference of the engine nacelle (20) and is the shortest line between the starting point of said external circumference and the end point of said external circumference.
3. The engine nacelle (20) according to claim 1 or 2, characterised in that the vortex generators are arranged on the side of the nacelle housing (19), which side faces towards the fuselage.
4. The engine nacelle (20) according to claim 2 or 3, characterised in that on the second side (S2) of the two sides (S1 , S2) of the nacelle housing (19) at least one fin- shaped vortex generator (21 , 22, 23; 31 , 32) is arranged.
5. The engine nacelle (20) according to claim 4, characterised in that on both sides of the nacelle housing (19) several fin-shaped vortex generators (21 , 22, 23; 31, 32) are arranged, wherein in each case the frontmost point of a first vortex generator (31) is located within a positioning corridor (K31) situated between two boundary lines, wherein:
• the starting point (51 a) of the first boundary line (51 ) is the circumferential point of the engine nacelle (20) with the engine-nacelle circumferential angle phi = 35 degrees and the engine-nacelle longitudinal coordinate X = L/4;
• the end point (51b) of the first boundary line (51) is the circumferential point of the engine nacelle (20) with the engine-nacelle circumferential angle phi = 25 degrees and the engine-nacelle longitudinal coordinate X = L*2/3; • the starting point (52a) of the second boundary line (52) is the circumferential point of the engine nacelle (20) with the engine-nacelle circumferential angle phi = 90 degrees and the engine-nacelle longitudinal coordinate X = L/4;
• the end point (52b) of the second boundary line (52) is the circumferential point of the engine nacelle (20) with the engine-nacelle circumferential angle phi = 55 degrees and the engine-nacelle longitudinal coordinate X = L*2/3;
wherein in each case the boundary line is the line that extends over the external circumference of the engine nacelle (20) and is the shortest line between the starting point of said external circumference and the end point of said external circumference.
6. The engine nacelle (20) according to any one of the preceding claims, characterised in that the second vortex generator is situated on the engine's circumferential angle of phi = 10 to 30 degrees below the first vortex generator.
7. The engine nacelle (20) according to any one of the preceding claims, characterised in that the longitudinal direction of the vortex generators is inclined by delta-theta = 0 to 10 degrees in relation to the longitudinal axis of the engine nacelle (20).
8. The engine nacelle (20) according to any one of the preceding claims, characterised in that the vortex generators, which in a connection region (V) of same with the outer flow surface (A) of the nacelle housing have a length (LG) that extends in longitudinal direction of the vortex generator, comprise an external contour (K2) that protrudes from the outer flow surface (A) and that extends, gradually rising, from the outer flow surface (A) of the nacelle housing to a maximum height (HG) at the rear end of the respective vortex generator.
9. The engine nacelle (20) according to claim 8, characterised in that the external contour of at least one vortex generator is a straight line.
10. The engine nacelle (20) according to claim 8 or 9, characterised in that the ratio of the overall length LG to the maximum height HG of the vortex generator is between 1.4 and 3.6.
11. The engine nacelle (20) according to any one of the preceding claims 8 to 10, characterised in that the overall length LG of the vortex generator relative to the length of the engine nacelle (20) is between 0.10 and 0.15.
12. An engine nacelle (20), of an aircraft, which engine nacelle (20) comprises a nacelle housing (19) with a first side (S1) and a second side (S2) and several fin- shaped vortex generators (21 , 22, 23; 31 , 32) characterised in that the fin-shaped vortex generators (21 , 22, 23; 31, 32) are arranged at least on one of the two sides (S1 , S2) of the nacelle housing (19) and the distance of the external contour (K) of the vortex generator from the outer flow surface (A) defined by the gradient of the connection region (V) in longitudinal direction (X) of the vortex generator is defined by the function Y = HG»[1 -(LG-X)2 / LG2], with:
• X being the longitudinal coordinate of the vortex generator with an overall length LG of the vortex generator;
• Y being the height coordinate of the vortex generator with a maximum height HG of the vortex generator in relation to the outer flow surface (A) on the longitudinal coordinate X=LG;
wherein the external contour (K) protruding from the outer flow surface (A) is within the range of ± 10% of the Y-value resulting from the function.
13. The engine nacelle (20) according to claim 12, characterised in that the area of the fins that form the vortex generators (3, 4, 5, 6) is arranged so as to be radial in relation to the engine nacelle (20).
14. The engine nacelle (20) according to claim 12 or 13, characterised in that the vortex generators are arranged on the side of the nacelle housing (19), which side faces towards the fuselage.
15. The engine nacelle (20) according to claim 12, 13 or 14, characterised in that on the second side (S2) of the two sides (S1, S2) of the nacelle housing (19) at least one fin-shaped vortex generator (21 , 22, 23; 31, 32) is arranged.
PCT/EP2008/004841 2007-06-15 2008-06-16 Engine nacelle of an aircraft comprising a vortex generator arrangement WO2008151843A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US12/663,094 US8827210B2 (en) 2007-06-15 2008-06-16 Engine nacelle of an aircraft comprising a vortex generator arrangement
EP08759254.9A EP2167380B1 (en) 2007-06-15 2008-06-16 Engine nacelle of an aircraft comprising a vortex generator arrangement
CN200880020369.1A CN101687542B (en) 2007-06-15 2008-06-16 Engine nacelle of an aircraft comprising a vortex generator arrangement

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
DE102007027697.6 2007-06-15
DE102007027697.6A DE102007027697B4 (en) 2007-06-15 2007-06-15 Vortex generator arrangement on the engine nacelle of an aircraft
US5603808P 2008-05-26 2008-05-26
DE102008025152.6A DE102008025152B4 (en) 2008-05-26 2008-05-26 Engine nacelle of an aircraft with a vortex generator arrangement
DE102008025152.6 2008-05-26
US61/056,038 2008-05-26

Publications (2)

Publication Number Publication Date
WO2008151843A1 WO2008151843A1 (en) 2008-12-18
WO2008151843A4 true WO2008151843A4 (en) 2009-02-26

Family

ID=39869698

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/004841 WO2008151843A1 (en) 2007-06-15 2008-06-16 Engine nacelle of an aircraft comprising a vortex generator arrangement

Country Status (4)

Country Link
US (1) US8827210B2 (en)
EP (1) EP2167380B1 (en)
CN (1) CN101687542B (en)
WO (1) WO2008151843A1 (en)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2167380B1 (en) 2007-06-15 2015-03-25 Airbus Operations GmbH Engine nacelle of an aircraft comprising a vortex generator arrangement
US8087617B2 (en) * 2008-08-15 2012-01-03 The Boeing Company Retractable nacelle chine
IN2012DN02495A (en) * 2009-09-18 2015-08-28 Massachusetts Inst Technology
US8916795B2 (en) 2011-03-28 2014-12-23 Lockheed Martin Corporation Plasma actuated vortex generators
US20130047978A1 (en) * 2011-08-31 2013-02-28 Massachusetts Institute Of Technology Vortex-induced cleaning of surfaces
US20130237302A1 (en) * 2012-03-09 2013-09-12 Pac Gaming Llc Poker table accommodating multiple dealers to facilitate play of multiple poker games simultaneously
EP2644496B1 (en) * 2012-03-29 2015-07-01 Airbus Operations GmbH Surface element for an aircraft, aircraft and method for improving high-lift generation on a surface element
EP2644497B1 (en) * 2012-03-29 2016-01-20 Airbus Operations GmbH Wing for an aircraft, aircraft and method for reducing aerodynamic drag and improving maximum lift
GB2523026B (en) * 2013-04-05 2016-08-31 Bacon Andy Improvements in the fuel efficiency of road vehicles
CN106461270B (en) 2014-05-13 2019-07-26 麻省理工学院 For concentrating the parabolic cylinder slot of the low cost of solar power generation
US10858089B2 (en) * 2017-04-10 2020-12-08 The Boeing Company Stall recovery chine spoiler system
RU2666093C1 (en) 2017-04-25 2018-09-05 Сергей Николаевич Низов Aerodynamic surface of an aircraft
US10618625B2 (en) * 2017-07-12 2020-04-14 The Boeing Company Integrated slat chine apparatus and methods
US10974813B2 (en) 2018-01-08 2021-04-13 General Electric Company Engine nacelle for an aircraft
FR3081830A1 (en) * 2018-05-30 2019-12-06 Airbus Operations AIRCRAFT AIRCRAFT WALL COMPRISING AT LEAST ONE TOURBILLON GENERATOR AND AIRCRAFT COMPRISING SAID AIRCRAFT WALL
CN111038691B (en) * 2018-10-14 2023-09-05 张发林 System for improving lift force
US11148782B2 (en) * 2018-12-13 2021-10-19 Rohr, Inc. Aerodynamic nacelle strakes as axial locator
US11440671B2 (en) * 2019-01-24 2022-09-13 Amazon Technologies, Inc. Adjustable motor fairings for aerial vehicles
US11745860B2 (en) * 2019-05-20 2023-09-05 The Boeing Company Aircraft nacelles having adjustable chines
US11591097B2 (en) 2019-05-20 2023-02-28 The Boeing Company Aircraft nacelles having adjustable chines
US11613345B2 (en) 2019-05-20 2023-03-28 The Boeing Company Aircraft nacelles having adjustable chines
US11873078B2 (en) 2019-05-20 2024-01-16 The Boeing Company Aircraft nacelles having adjustable chines
US11535362B2 (en) 2019-05-20 2022-12-27 The Boeing Company Aircraft nacelles having adjustable chines
US11267577B2 (en) 2019-12-06 2022-03-08 General Electric Company Aircraft having an engine wing assembly
CN114715416A (en) * 2022-03-22 2022-07-08 中国商用飞机有限责任公司北京民用飞机技术研究中心 Aviation turbofan engine and outer duct nozzle

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2800291A (en) * 1950-10-24 1957-07-23 Stephens Arthur Veryan Solid boundary surface for contact with a relatively moving fluid medium
US3741285A (en) * 1968-07-09 1973-06-26 A Kuethe Boundary layer control of flow separation and heat exchange
US3744745A (en) * 1971-09-30 1973-07-10 Mc Donnell Douglas Corp Liftvanes
US4466587A (en) 1981-12-21 1984-08-21 General Electric Company Nacelle installation
US4685643A (en) * 1983-08-04 1987-08-11 The Boeing Company Nacelle/wing assembly with vortex control device
US4540143A (en) * 1983-08-04 1985-09-10 The Boeing Company Nacelle/wing assembly with wake control device
US5833389A (en) * 1996-12-09 1998-11-10 Orlev Scientific Computing Ltd. Apparatus for controlling turbulence in boundary layer and other wall-bounded fluid flow fields
GB0213551D0 (en) * 2002-06-13 2002-07-24 Univ Nottingham Controlling boundary layer fluid flow
US6964397B2 (en) * 2003-07-18 2005-11-15 The Boeing Company Nacelle chine installation for drag reduction
NL1029708C2 (en) * 2005-08-10 2007-02-13 Kick Off Ltd Turbulence foil.
FR2891525B1 (en) * 2005-09-30 2007-11-09 Airbus France Sas DEVICE FOR CONTROLLING A TOURBILLONARY WAKE GENERATED BY AN OBLONG ELEMENT ON THE EXTRADOS OF A CARRYING SURFACE OF AN AIRCRAFT.
EP2167380B1 (en) 2007-06-15 2015-03-25 Airbus Operations GmbH Engine nacelle of an aircraft comprising a vortex generator arrangement
DE102007027697B4 (en) 2007-06-15 2014-01-02 Airbus Operations Gmbh Vortex generator arrangement on the engine nacelle of an aircraft
US8087617B2 (en) * 2008-08-15 2012-01-03 The Boeing Company Retractable nacelle chine

Also Published As

Publication number Publication date
US8827210B2 (en) 2014-09-09
WO2008151843A1 (en) 2008-12-18
EP2167380B1 (en) 2015-03-25
CN101687542B (en) 2015-01-14
CN101687542A (en) 2010-03-31
US20100176249A1 (en) 2010-07-15
EP2167380A1 (en) 2010-03-31

Similar Documents

Publication Publication Date Title
WO2008151843A4 (en) Engine nacelle of an aircraft comprising a vortex generator arrangement
US6708711B2 (en) Air inlet for commercial aircraft jet engine nacelle
US10526073B2 (en) Wingtip device of a wing, and also a wing with such a wingtip device
EP3369651B1 (en) The split spiroid
WO2008081098A8 (en) Aircraft with rear annular tail
US11673653B2 (en) Wingtip device
US8651427B1 (en) Wing tip device with recess in surface
WO2016041751A1 (en) A wing for an aircraft, and an aircraft comprising such a wing
CA2974992A1 (en) Airframe-integrated propeller-driven propulsion systems
KR20110132310A (en) Ship propulsion device and ship with same
US20070262205A1 (en) Retractable multiple winglet
CN103693187B (en) A kind of wing structure
US20170233065A1 (en) Curved wingtip for aircraft
CN203593160U (en) Wing structure
WO2019194623A3 (en) Vortex generator having case so as to enable generation of multiple whirlwind
WO2012141770A3 (en) Laminar flow wing optimized for transonic and supersonic cruise aircraft
US8910910B2 (en) Wing comprising a flow fence, and aircraft having such wings
CA2398528A1 (en) Passive aerodynamic sonic boom suppression for supersonic aircraft
WO2016133427A3 (en) Vertical take-off and landing aircraft (variants)
WO2013030498A3 (en) Assembly consisting of a turbine engine, and system for attaching same to an aircraft structure
CN102642613A (en) Low-resistance fairing of corrugate sheath
US20120048995A1 (en) Method For Enhancing The Aerodynamic Efficiency Of The Vertical Tail Of An Aircraft
CN107021202B (en) Aircraft nose with edge
CN105000159A (en) U-type sail structure
US9868525B2 (en) Low speed airfoil design for aerodynamic improved performance of UAVs

Legal Events

Date Code Title Description
WWE Wipo information: entry into national phase

Ref document number: 200880020369.1

Country of ref document: CN

121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 08759254

Country of ref document: EP

Kind code of ref document: A1

WWE Wipo information: entry into national phase

Ref document number: 12663094

Country of ref document: US

NENP Non-entry into the national phase

Ref country code: DE

WWE Wipo information: entry into national phase

Ref document number: 2008759254

Country of ref document: EP