GB2296306B - Aeroengine low drag nacelle structure - Google Patents

Aeroengine low drag nacelle structure

Info

Publication number
GB2296306B
GB2296306B GB9524503A GB9524503A GB2296306B GB 2296306 B GB2296306 B GB 2296306B GB 9524503 A GB9524503 A GB 9524503A GB 9524503 A GB9524503 A GB 9524503A GB 2296306 B GB2296306 B GB 2296306B
Authority
GB
United Kingdom
Prior art keywords
boundary layer
panel section
pressure region
region
downstream
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 - Fee Related
Application number
GB9524503A
Other versions
GB9524503D0 (en
GB2296306A (en
Inventor
Stephen Carson Rolston
Edward Maurice Ashford
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.)
Short Brothers PLC
Original Assignee
Short Brothers 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
Priority claimed from GB9424495A external-priority patent/GB9424495D0/en
Application filed by Short Brothers PLC filed Critical Short Brothers PLC
Priority to GB9524503A priority Critical patent/GB2296306B/en
Publication of GB9524503D0 publication Critical patent/GB9524503D0/en
Publication of GB2296306A publication Critical patent/GB2296306A/en
Application granted granted Critical
Publication of GB2296306B publication Critical patent/GB2296306B/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/10—Influencing flow of fluids around bodies of solid material
    • F15D1/12—Influencing flow of fluids around bodies of solid material by influencing the boundary layer
    • 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
    • B64C21/025—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for simultaneous blowing and sucking
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/14—Boundary layer controls achieving noise reductions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/20—Boundary layer controls by passively inducing fluid flow, e.g. by means of a pressure difference between both ends of a slot or duct
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/22—Boundary layer controls by using a surface having multiple apertures of relatively small openings other than slots
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0226—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means
    • 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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Boundary layer separation at the surface of a structure such as an intake duct (18) (Fig. 1) of a turbofan aeroengine nacelle (12) at conditions of high incidence and high engine mass flow arises from shockwave induced pressure gradients in the boundary layer. To control separation, gaseous fluid is withdrawn from a high pressure region of the boundary layer downstream of a shock wave 27, conveyed within the intake duct structure and discharged upstream of the shockwave into a low pressure region of the boundary layer. The intake duct (18) embodies a noise attenuation panel 19, and fluid is withdrawn from the high pressure region of the boundary layer into a modified panel section 191 by passage through apertures 30 at a downstream region of the panel section, conveyed along a fluid communication path within the panel section 191 and discharged into the low pressure region of the boundary layer by passage through apertures 30 at an upstream region of the panel section 191. Gaseous fluid is conveyed solely as a consequence of the difference in pressures in the boundary layer at the downstream and upstream regions. The panel section 191 may comprise a cellular structure 151, sandwiched between a porous facing sheet 122 and a backing sheet 11, the cells communicating by means of slots 31. <IMAGE>
GB9524503A 1994-12-05 1995-11-30 Aeroengine low drag nacelle structure Expired - Fee Related GB2296306B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB9524503A GB2296306B (en) 1994-12-05 1995-11-30 Aeroengine low drag nacelle structure

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9424495A GB9424495D0 (en) 1994-12-05 1994-12-05 Aerodynamic low drag structure
GB9524503A GB2296306B (en) 1994-12-05 1995-11-30 Aeroengine low drag nacelle structure

Publications (3)

Publication Number Publication Date
GB9524503D0 GB9524503D0 (en) 1996-01-31
GB2296306A GB2296306A (en) 1996-06-26
GB2296306B true GB2296306B (en) 1999-05-26

Family

ID=26306114

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9524503A Expired - Fee Related GB2296306B (en) 1994-12-05 1995-11-30 Aeroengine low drag nacelle structure

Country Status (1)

Country Link
GB (1) GB2296306B (en)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6176964B1 (en) * 1997-10-20 2001-01-23 Vought Aircraft Industries, Inc. Method of fabricating an acoustic liner
US6179251B1 (en) * 1998-02-06 2001-01-30 Northrop Grumman Corporation Thin inlet lip design for low drag and reduced nacelle size
GB9914652D0 (en) 1999-06-24 1999-08-25 British Aerospace Laminar flow control system and suction panel for use therein
NZ511661A (en) 2001-05-11 2003-09-26 Graham Bond Grove An improved aerofoil
GB2383093A (en) * 2001-12-12 2003-06-18 Rolls Royce Plc Flow turbulence reduction downstream of diverted flow
DE10317509A1 (en) * 2003-04-16 2004-11-18 Daimlerchrysler Ag Fahrtwindbeaufschlagte edge of a motor vehicle component
GB2402196B (en) 2003-05-29 2006-05-17 Rolls Royce Plc A laminar flow nacelle for an aircraft engine
DE102004011030B4 (en) 2004-03-04 2006-04-13 Siemens Ag Cover with integrated polymer actuator for deformation of the same
GB2453941B (en) * 2007-10-22 2012-01-11 Yen Tuan Aero-acoustic aviation engine inlet for aggressive noise abatement
FR2968636B1 (en) 2010-12-09 2013-01-18 Airbus Operations Sas AIR INTAKE FOR AIRCRAFT PROPULSIVE ASSEMBLY HAVING A SURPRISING RESISTANT STRUCTURE AND METHOD FOR REPAIRING AN AIRCRAFT PROPULSIVE ASSEMBLY AIR INTAKE
CN102777261B (en) * 2011-05-13 2016-02-10 中国商用飞机有限责任公司 Inlet flap substrate and comprise the inlet flap of this substrate

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4522360A (en) * 1983-04-27 1985-06-11 Rensselaer Polytechnic Institute Passive drag control of airfoils at transonic speeds
GB2187261A (en) * 1986-01-06 1987-09-03 Secr Defence Controlling boundary layer
US4749150A (en) * 1985-12-24 1988-06-07 Rohr Industries, Inc. Turbofan duct with noise suppression and boundary layer control
US4863118A (en) * 1988-09-30 1989-09-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Passive venting technique for shallow cavities
US5167387A (en) * 1991-07-25 1992-12-01 Vigyan, Inc. Porous airfoil and process
US5297765A (en) * 1992-11-02 1994-03-29 Rohr, Inc. Turbine engine nacelle laminar flow control arrangement
US5335885A (en) * 1992-03-06 1994-08-09 Deutsche Aerospace Airbus Gmbh Aircraft wing having a super critical profile and a venting device for reducing compression shock
US5366177A (en) * 1992-10-05 1994-11-22 Rockwell International Corporation Laminar flow control apparatus for aerodynamic surfaces

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4522360A (en) * 1983-04-27 1985-06-11 Rensselaer Polytechnic Institute Passive drag control of airfoils at transonic speeds
US4749150A (en) * 1985-12-24 1988-06-07 Rohr Industries, Inc. Turbofan duct with noise suppression and boundary layer control
GB2187261A (en) * 1986-01-06 1987-09-03 Secr Defence Controlling boundary layer
US4863118A (en) * 1988-09-30 1989-09-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Passive venting technique for shallow cavities
US5167387A (en) * 1991-07-25 1992-12-01 Vigyan, Inc. Porous airfoil and process
US5335885A (en) * 1992-03-06 1994-08-09 Deutsche Aerospace Airbus Gmbh Aircraft wing having a super critical profile and a venting device for reducing compression shock
US5366177A (en) * 1992-10-05 1994-11-22 Rockwell International Corporation Laminar flow control apparatus for aerodynamic surfaces
US5297765A (en) * 1992-11-02 1994-03-29 Rohr, Inc. Turbine engine nacelle laminar flow control arrangement

Also Published As

Publication number Publication date
GB9524503D0 (en) 1996-01-31
GB2296306A (en) 1996-06-26

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee

Effective date: 20091130