FR3065944B1 - TURBOMACHINE NACELLE INTENDED TO BE INSTALLED IN FRONT OF AN AIRPLANE SAIL - Google Patents

TURBOMACHINE NACELLE INTENDED TO BE INSTALLED IN FRONT OF AN AIRPLANE SAIL Download PDF

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Publication number
FR3065944B1
FR3065944B1 FR1753991A FR1753991A FR3065944B1 FR 3065944 B1 FR3065944 B1 FR 3065944B1 FR 1753991 A FR1753991 A FR 1753991A FR 1753991 A FR1753991 A FR 1753991A FR 3065944 B1 FR3065944 B1 FR 3065944B1
Authority
FR
France
Prior art keywords
longitudinal axis
nacelle
transverse plane
wing
leading edge
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.)
Active
Application number
FR1753991A
Other languages
French (fr)
Other versions
FR3065944A1 (en
Inventor
Christian Sylvain Vessot
Julien Antoine Henri Jean Szydlowski
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.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines 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
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1753991A priority Critical patent/FR3065944B1/en
Publication of FR3065944A1 publication Critical patent/FR3065944A1/en
Application granted granted Critical
Publication of FR3065944B1 publication Critical patent/FR3065944B1/en
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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
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • 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
    • 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)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Wind Motors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une nacelle (34) pour une turbomachine (1) destinée à être installée sous une aile (3) d'aéronef, ladite nacelle (34) délimitant une veine (18) de sortie de gaz de la turbomachine sensiblement annulaire autour d'un axe longitudinal (X) de la nacelle (34) et ayant sa lèvre d'entrée d'air (15) en amont d'un bord d'attaque (6) de ladite aile (3), en se référant à la direction d'un flux d'air extérieur selon ledit axe longitudinal (X), présentant en outre un bord de fuite (39) dont l'extension selon ledit axe longitudinal (X) est définie par un premier plan transversal (P1) situé en amont d'un point déterminé (61) du bord d'attaque (6) de l'aile (3) situé à la verticale de l'axe longitudinal (X) et un deuxième plan transversal (P2) situé en aval du premier (P1), ledit bord de fuite (39) rejoignant le deuxième plan transversal (P2) en un point haut (30) sensiblement à la verticale au-dessus de l'axe longitudinal (X), de manière à définir au moins une partie pleine supérieure (31) de la nacelle (34) s'étendant en aval du premier plan transversal (P1) de façon sensiblement symétrique autour d'un plan axial vertical, caractérisée en ce que le deuxième plan transversal (P2) est positionné de telle sorte que la droite (D) joignant ledit point haut (30) du bord de fuite (39) et ledit point déterminé (61) du bord d'attaque (6) de l'aile définit, avec l'axe longitudinal (X), un angle (α) ayant une valeur au moins égale à 45°, de préférence supérieure à 60°. Elle concerneaussi le procédé de conception de la nacelle.The invention relates to a nacelle (34) for a turbomachine (1) intended to be installed under an aircraft wing (3), said nacelle (34) delimiting a gas outlet stream (18) of the substantially annular turbomachine around a longitudinal axis (X) of the nacelle (34) and having its air inlet lip (15) upstream of a leading edge (6) of said wing (3), with reference to the direction of an outside air flow along said longitudinal axis (X), further having a trailing edge (39) whose extension along said longitudinal axis (X) is defined by a first transverse plane (P1) located upstream of a determined point (61) of the leading edge (6) of the wing (3) located vertically to the longitudinal axis (X) and a second transverse plane (P2) located downstream of the first (P1), said trailing edge (39) joining the second transverse plane (P2) at a high point (30) substantially vertically above the longitudinal axis (X), so as to define at least part full top ieure (31) of the nacelle (34) extending downstream of the first transverse plane (P1) substantially symmetrically about a vertical axial plane, characterized in that the second transverse plane (P2) is positioned in such a way that the straight line (D) joining said high point (30) of the trailing edge (39) and said determined point (61) of the leading edge (6) of the wing defines, with the longitudinal axis (X), an angle (α) having a value at least equal to 45 °, preferably greater than 60 °. It also concerns the nacelle design process.

FR1753991A 2017-05-05 2017-05-05 TURBOMACHINE NACELLE INTENDED TO BE INSTALLED IN FRONT OF AN AIRPLANE SAIL Active FR3065944B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1753991A FR3065944B1 (en) 2017-05-05 2017-05-05 TURBOMACHINE NACELLE INTENDED TO BE INSTALLED IN FRONT OF AN AIRPLANE SAIL

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1753991 2017-05-05
FR1753991A FR3065944B1 (en) 2017-05-05 2017-05-05 TURBOMACHINE NACELLE INTENDED TO BE INSTALLED IN FRONT OF AN AIRPLANE SAIL

Publications (2)

Publication Number Publication Date
FR3065944A1 FR3065944A1 (en) 2018-11-09
FR3065944B1 true FR3065944B1 (en) 2021-03-05

Family

ID=59649837

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1753991A Active FR3065944B1 (en) 2017-05-05 2017-05-05 TURBOMACHINE NACELLE INTENDED TO BE INSTALLED IN FRONT OF AN AIRPLANE SAIL

Country Status (1)

Country Link
FR (1) FR3065944B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4815680A (en) * 1984-12-28 1989-03-28 The Boeing Company Nacelle and wing assembly
JP2606289Y2 (en) * 1993-06-07 2000-10-10 富士重工業株式会社 Aircraft nacelle equipment
FR2902758B1 (en) * 2006-06-21 2009-04-10 Airbus France Sas PROPELLANT AIRCRAFT ASSEMBLY COMPRISING AN EJECTION DUCT WITH A LEAK EDGE OFFSET
US20150330254A1 (en) * 2014-05-15 2015-11-19 United Technologies Corporation Compact Nacelle With Contoured Fan Nozzle

Also Published As

Publication number Publication date
FR3065944A1 (en) 2018-11-09

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