GB1209723A - Improvements in or relating to boundary layer air flow - Google Patents

Improvements in or relating to boundary layer air flow

Info

Publication number
GB1209723A
GB1209723A GB30258/69A GB3025869A GB1209723A GB 1209723 A GB1209723 A GB 1209723A GB 30258/69 A GB30258/69 A GB 30258/69A GB 3025869 A GB3025869 A GB 3025869A GB 1209723 A GB1209723 A GB 1209723A
Authority
GB
United Kingdom
Prior art keywords
duct
air
casing
fan
boundary layer
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
Application number
GB30258/69A
Inventor
Geoffrey William Morris
Leslie John Brooks
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB30258/69A priority Critical patent/GB1209723A/en
Publication of GB1209723A publication Critical patent/GB1209723A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • B64D29/04—Power-plant nacelles, fairings, or cowlings associated with fuselages
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/52—Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/04—Boundary layer controls by actively generating fluid flow
    • 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

1,209,723. Boundary layer control. ROLLSROYCE Ltd. 14 June, 1969, No. 30258/69. Heading F2R. A gas turbine jet propulsion ducted fan engine 22 is supported from an aircraft by a beam 18 which penetrates the fan duct 30 and connects with the engine proper, an outer skin or casing 20 surrounding the beam 18 and the space 34 between them receiving air from the duct 30 and guiding it to a slot-shaped outlet 36 on the beam outer surface downstream of the duct outlet, whereby to re-energize the boundary layer air flow. The beam 18 may be two separate pieces, or may be one member which passes through the aircraft fuselage 10, and in either case forms the central rigid structure of stub wings 14, 16 projecting one from each side of the fuselage 10. Normally the slight obstruction 32 presented by the beam 18 and casing 20 extending across the duct 30 would cause an unacceptable disruption in the fan duct air flow because air would strike the upstream edge of casing 20 and be deflected to either side thereby, thus deflecting adjacent ambient air and so spoiling the aerodynamic efficiency of the duct. Moreover, undesirable pressure fields would be created between the fan blade trailing edges and the upstream edge of casing 20, which would have a hammering effect on the fan blades. However, that portion 20a of the upstream edge of casing 20 which lies across duct 30 is cut back (Fig. 2) so as to remove these pressure fields. Lateral deflection of the fan air is substantially obviated for the cut edge of casing 20 is so thin as to cause little or no deflection of air passing outwardly of it. The air passing through space 34 is caused to expand spanwise of the stub wings 14, 16 by shaping the space 34 such that its cross-sectional area increases in a downstream direction. The expelling of the air through outlet 36 over the full span of the stub wings 14, 16 re-energizes the boundary layer air flow over these wings, causing it to flow smoothly and rapidly, instead of breaking away from the wing upper surface and creating vortices and adverse pressures. In an alternative construction (Fig. 3, not shown), the invention is applied to a pylon by means of which a ducted fan engine is suspended from the under-surface of an aircraft main wing.
GB30258/69A 1969-06-14 1969-06-14 Improvements in or relating to boundary layer air flow Expired GB1209723A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB30258/69A GB1209723A (en) 1969-06-14 1969-06-14 Improvements in or relating to boundary layer air flow

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB30258/69A GB1209723A (en) 1969-06-14 1969-06-14 Improvements in or relating to boundary layer air flow

Publications (1)

Publication Number Publication Date
GB1209723A true GB1209723A (en) 1970-10-21

Family

ID=10304799

Family Applications (1)

Application Number Title Priority Date Filing Date
GB30258/69A Expired GB1209723A (en) 1969-06-14 1969-06-14 Improvements in or relating to boundary layer air flow

Country Status (1)

Country Link
GB (1) GB1209723A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2613688A1 (en) * 1987-04-13 1988-10-14 Gen Electric PYLONE FOR AIRPLANE
US4966338A (en) * 1987-08-05 1990-10-30 General Electric Company Aircraft pylon
EP0884469A1 (en) * 1997-06-12 1998-12-16 Hispano-Suiza Aérostructures Turbofan with a thrust reverser provided with a fairing attached thereto in the fluid stream
EP2256327A1 (en) * 2008-02-25 2010-12-01 IHI Corporation Noise reducing device, and jet propulsion system
CN109996721A (en) * 2016-09-26 2019-07-09 通用电气公司 Aircraft with rear engine

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2613688A1 (en) * 1987-04-13 1988-10-14 Gen Electric PYLONE FOR AIRPLANE
GB2203710A (en) * 1987-04-13 1988-10-26 Gen Electric Aircraft pylon for engine support
DE3811019A1 (en) * 1987-04-13 1988-10-27 Gen Electric AIRCRAFT EXTERIOR CARRIERS
GB2203710B (en) * 1987-04-13 1991-03-27 Gen Electric Aircraft pylon
US5156353A (en) * 1987-04-13 1992-10-20 General Electric Company Aircraft pylon
US4966338A (en) * 1987-08-05 1990-10-30 General Electric Company Aircraft pylon
EP0884469A1 (en) * 1997-06-12 1998-12-16 Hispano-Suiza Aérostructures Turbofan with a thrust reverser provided with a fairing attached thereto in the fluid stream
WO1998057055A1 (en) * 1997-06-12 1998-12-17 Hispano-Suiza Aerostructures Turbofan associated with a thrust reverser with shroud directly mounted in the filament of flow
FR2764644A1 (en) * 1997-06-12 1998-12-18 Hispano Suiza Sa DOUBLE-FLOW TURBOREACTOR ASSOCIATED WITH A PUSH-INVERTER WITH AN ADJUSTED FAIRING IN THE FLUID Vein
US6068213A (en) * 1997-06-12 2000-05-30 Societe Hispano Suiza Aerostructures Aircraft engine ducted fan cowling with thrust reverser section and fairings for fan shroud brace members in fan exhaust duct
EP2256327A1 (en) * 2008-02-25 2010-12-01 IHI Corporation Noise reducing device, and jet propulsion system
EP2256327A4 (en) * 2008-02-25 2012-05-16 Ihi Corp Noise reducing device, and jet propulsion system
US8904795B2 (en) 2008-02-25 2014-12-09 Ihi Corporation Noise reducing device and jet propulsion system
CN109996721A (en) * 2016-09-26 2019-07-09 通用电气公司 Aircraft with rear engine

Similar Documents

Publication Publication Date Title
US2841344A (en) Boundary layer control
US3355125A (en) Flap systems for aircraft
US3524458A (en) Intakes for fluid flow
US2408788A (en) Airfoil
US2916230A (en) Supersonic airfoil
US2650781A (en) Boundary layer control for aircraft
US2699906A (en) Air inlet for airplane gaseous combustion turbine engines
GB1306169A (en)
FR2062611A5 (en)
US3109610A (en) Combined aircraft air intake scoop, foreign material ingestion inhibitor, and aerodynamic flap
US5037044A (en) Aerodynamic or hydrodynamic surfaces
GB1174497A (en) Jet Flaps.
US3724784A (en) Wing with thrust augmentor
US2991961A (en) Jet aircraft configuration
US3333794A (en) Guards for air intakes of jet engines
US9701399B1 (en) Parasitic drag induced boundary layer reduction system and method
GB1107011A (en) Improvements in or relating to aircraft
US3974987A (en) Cascade effect blown flap
GB1209723A (en) Improvements in or relating to boundary layer air flow
US2805032A (en) Supersonic flight control device
UA28455U (en) Vertical take-off and landing flight vehicle
US3016213A (en) Blunt-tailed jet airfoil
US2479487A (en) Jet propelled airplane with wing discharge slot
GB1196756A (en) Improvements in Aerofoils.
US3276727A (en) Compensating boundary layer control nozzle

Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees