US20110200431A1 - Jet engine nacelle with dampers for half-shells - Google Patents

Jet engine nacelle with dampers for half-shells Download PDF

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Publication number
US20110200431A1
US20110200431A1 US12/673,324 US67332408A US2011200431A1 US 20110200431 A1 US20110200431 A1 US 20110200431A1 US 67332408 A US67332408 A US 67332408A US 2011200431 A1 US2011200431 A1 US 2011200431A1
Authority
US
United States
Prior art keywords
nacelle
limiting
turbojet engine
torque
jacks
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.)
Abandoned
Application number
US12/673,324
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English (en)
Inventor
Stephane Lederle
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 Nacelles SAS
Original Assignee
Aircelle SA
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 Aircelle SA filed Critical Aircelle SA
Assigned to AIRCELLE reassignment AIRCELLE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: LEDERLE, STEPHANE
Publication of US20110200431A1 publication Critical patent/US20110200431A1/en
Abandoned legal-status Critical Current

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Classifications

    • 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
    • B64D29/08—Inspection panels for power plants

Definitions

  • the invention relates to a turbojet engine nacelle of an aircraft.
  • An aircraft is driven by a plurality of turbojet engines, each accommodated in a nacelle likewise housing an assembly of accessory actuating devices linked to its operation and ensuring various functions when the turbojet engine is in operation or at a standstill.
  • These accessory actuating devices comprise, in particular, a mechanical system for the actuation of thrust reversers.
  • a nacelle generally has a tubular structure comprising an air inlet in front of the turbojet engine, a middle section intended for surrounding a blower of a turbojet engine, a rear section capable of housing thrust reversal means and intended for surrounding the combustion chamber of the turbojet engine, and generally terminates in an ejection nozzle, the outlet of which is located downstream of the turbojet engine.
  • Modern nacelles are often intended for housing a double-flow turbojet engine capable of generating, by means of the rotating blades of the blower, a stream of hot air (also called a primary stream) coming from the combustion chamber of the turbojet engine.
  • a nacelle generally has an external structure, called an outer fixed structure (OFS), which, with a concentric internal structure, called an inner fixed structure (IFS), comprising a cowl surrounding the actual turbojet engine structure at the rear of the blower, defines an annular flow channel, also called a flow section, intended for channeling a stream of cold air, called a secondary stream, which circulates outside the turbojet engine.
  • OFS outer fixed structure
  • IFS inner fixed structure
  • the primary and secondary streams are ejected from the turbojet engine at the rear of the nacelle.
  • Each propulsive assembly of the aircraft is thus formed by a nacelle and a turbojet engine and is suspended on a fixed structure of the aircraft, for example under a wing or on the fuselage, by means of a pylori or mast attached to the turbojet engine or to the nacelle.
  • the rear section of the external structure of the nacelle is normally formed from two half-parts of substantially semi-cylindrical shape, on either side of a vertical longitudinal plane of symmetry of the nacelle, and mounted movably so as to be capable of being deployed between an operating position and a maintenance position for the purpose of giving access to the turbojet engine.
  • the two half-parts are generally mounted pivotably about a longitudinal axis forming a hinge in the upper part (at 12 o'clock) of the reverser.
  • the half-parts are held in the closing position by means of locking bolts arranged along a junction line located in the lower part (at 6 o'clock).
  • Each half-part is opened with the aid of at least one jack and is kept open with the aid of at least one telescopic rod serving as a prop, said jack and said telescopic rod each having a first end generally fastened to the turbojet engine and a second end fastened in a front frame of said half-part, this front frame being the element making it possible to attach the rear section to a fixed part of the middle section of the nacelle.
  • these half-parts are actuated by hydraulic or pneumatic jacks which require a network for the transport of fluid under pressure which is obtained either by the tapping of air or by extraction from a hydraulic circuit of the aircraft.
  • the electromechanical actuators likewise have some disadvantages which are to be overcome so as to be able to benefit fully from the advantages which they afford in terms of a saving of mass and of overall size.
  • a situation where damage frequently occurs is when an operator forgets to release the prop before triggering the jack for closing purposes. When such an omission happens, the electric motor is in a blocked situation.
  • the power for closing is lower than the maximum power of the jack, the power of the motor may rise in order to attempt to overcome the obstacle.
  • the rod is then generally not sufficiently resistant and therefore risks breaking under the stress exerted by the electrical jack.
  • an oversizing of the prop would bring about an undesirable increase in mass.
  • the disclosure provides a turbojet engine nacelle comprising a front air inlet section, a middle section intended for surrounding a blower of the turbojet engine, and a rear section formed from at least two half-parts mounted movably in terms of rotation so as each to be capable of being deployed between an operating position and a maintenance position under the action of at least one jack and at least one telescopic rod capable of being locked in the deployed position, and each having respectively a first end fastened to the turbojet engine and a second end fastened in the corresponding half-part, characterized in that the jacks are associated with one or more actuating means equipped with at least one device limiting the active torque during a retraction phase of said jacks.
  • the actuating means are equipped with a device limiting the active torque during opening.
  • a device limiting the active torque during opening makes it possible to limit the forces exerted on the half-part during its opening, these forces being capable of causing deformations in the half-part due to their highly localized nature.
  • the device limiting the active torque during closing and the device limiting the active torque during opening are combined in a single double-acting device.
  • the torque-limiting device possesses different calibration values for opening and closing.
  • the jacks are jacks actuated by means of at least one electric motor.
  • the torque-limiting devices are mounted on a driveshaft of the electric motor.
  • the torque-limiting device or torque-limiting devices comprises or comprise at least one ball-type torque-limiting device.
  • the present invention also relates, on the one hand, to a propulsive assembly comprising a nacelle according to the invention arranged around a turbojet engine and, on the other hand, to an aircraft comprising at least one such propulsive assembly.
  • FIGURE is a diagrammatic illustration of a nacelle, seen from the front, having a rear section produced in the form of two half-parts shown in the opening position.
  • a nacelle 1 as illustrated in the single FIGURE, constitutes a tubular receptacle for a double-flow turbojet engine 5 and serves for channeling the airstreams which it generates by means of the blades of a blower (not illustrated), namely a stream of hot air passing through a combustion chamber of the turbojet engine and a stream of cold air circulating outside the turbojet engine.
  • the nacelle 1 is intended to be attached to a fixed structure of an aircraft, for example under a wing or in the region of the fuselage, by means of a mast 10 .
  • the nacelle 1 possesses a structure comprising a front section 2 forming an air inlet, a middle section 3 surrounding the blower of the turbojet engine 5 , and a rear section 4 surrounding the turbojet engine.
  • the rear section 4 comprises, on the one hand, an external structure 4 a generally incorporating a thrust reversal system and also forming an ejection nozzle and, on the other hand, an internal structure 4 b as the fairing of the turbojet engine 5 , said internal structure defining with the external structure 4 a a flow section 7 intended for the circulation of the cold stream.
  • the external structure 4 a comprises a front frame 8 intended for making the connection between the external downstream structure 4 a and the middle part 2 .
  • the rear section 4 is produced in the form of two half-parts 9 surrounding the turbojet engine 5 and each articulated about a hinge line located in the vicinity of the mast 10 , so as to be capable of changing alternately from an operating position, in which it is nearest to the turbojet engine and therefore closes the nacelle 1 , to a maintenance position, in which it is deployed outward, as illustrated in the single FIGURE.
  • the opening and closing of the half-parts 9 takes place under the action of at least one jack 11 and of at least one telescopic rod 12 , each having respectively a first end 13 , 14 fastened in the turbojet engine and a second end 16 , 17 fastened in a front frame 8 of the corresponding half-part 9 .
  • the rod 12 is capable of being locked reversibly in the deployed position in which it then supports the corresponding half-part 9 .
  • the jack 11 is a jack of the screw/ball type capable of being actuated by means of an electric motor (not shown).
  • This electric motor comprises an output shaft, on which a torque-limiting device is arranged according to the invention.
  • a torque limiter makes it possible to decouple a transmission when the transmission torque overshoots a certain predetermined value, called the calibration value.
  • Such devices are known and are commercially available.
  • the limiter device installed will be active at least during a retraction movement of the jack 11 corresponding to the closing of a half-part 9 .
  • a device limiting the active torque during opening may be provided.
  • the device limiting the active torque during opening may or may not be separate from the device limiting the active torque during closing.
  • there are double-acting torque limiters making it possible to fix different calibration values for each direction of rotation of the shaft of the electric motor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
  • Vibration Dampers (AREA)
US12/673,324 2007-08-20 2008-05-05 Jet engine nacelle with dampers for half-shells Abandoned US20110200431A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0705900A FR2920139B1 (fr) 2007-08-20 2007-08-20 Nacelle de turboreacteur a amortisseurs pour demi-coquilles
FR0705900 2007-08-20
PCT/FR2008/000626 WO2009024654A1 (fr) 2007-08-20 2008-05-05 Nacelle de turboreacteur a amortisseurs pour demi-coquilles

Publications (1)

Publication Number Publication Date
US20110200431A1 true US20110200431A1 (en) 2011-08-18

Family

ID=39153751

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/673,324 Abandoned US20110200431A1 (en) 2007-08-20 2008-05-05 Jet engine nacelle with dampers for half-shells

Country Status (10)

Country Link
US (1) US20110200431A1 (ru)
EP (1) EP2190741B1 (ru)
CN (1) CN101784446A (ru)
AT (1) ATE522440T1 (ru)
BR (1) BRPI0813039A2 (ru)
CA (1) CA2696346A1 (ru)
ES (1) ES2372234T3 (ru)
FR (1) FR2920139B1 (ru)
RU (1) RU2453478C2 (ru)
WO (1) WO2009024654A1 (ru)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150166193A1 (en) * 2013-12-18 2015-06-18 Rolls-Royce Plc Gas turbine cowl

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9701414B2 (en) 2013-09-16 2017-07-11 Honeywell International Inc. Aircraft engine cowl door movement control system and method
US9702176B2 (en) 2014-07-07 2017-07-11 Itt Manufacturing Enterprises Llc Spring loaded actuator assembly
CN105508053A (zh) * 2015-12-29 2016-04-20 中国航空工业集团公司沈阳发动机设计研究所 一种内安装边结构的燃汽轮机进气内流道结构
CN107757862B (zh) * 2016-08-23 2021-05-14 空客直升机德国有限公司 具有能相对于机身转动和平移的整流罩的旋翼飞行器

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4399966A (en) * 1980-12-31 1983-08-23 The Boeing Company Power opening system for engine cowl doors
US6227485B1 (en) * 1997-12-03 2001-05-08 Aerospatiale Societe Nationale Industrielle Opening device common to two adjacent aircraft engine nacelle covers
US6622963B1 (en) * 2002-04-16 2003-09-23 Honeywell International Inc. System and method for controlling the movement of an aircraft engine cowl door
US6974107B2 (en) * 2003-06-18 2005-12-13 Honeywell International, Inc. Thrust reverser system actuator having an integral torque limiter

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US622963A (en) * 1899-04-11 Necktie-fastener
RU1766020C (ru) * 1989-12-20 1994-08-15 Авиационный комплекс им.С.В.Ильюшина Створка гондолы двигателя летательного аппарата

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4399966A (en) * 1980-12-31 1983-08-23 The Boeing Company Power opening system for engine cowl doors
US6227485B1 (en) * 1997-12-03 2001-05-08 Aerospatiale Societe Nationale Industrielle Opening device common to two adjacent aircraft engine nacelle covers
US6622963B1 (en) * 2002-04-16 2003-09-23 Honeywell International Inc. System and method for controlling the movement of an aircraft engine cowl door
US20030192987A1 (en) * 2002-04-16 2003-10-16 Ahrendt Terry J. System and method for controlling the movement of an aircraft engine cowl door
US6974107B2 (en) * 2003-06-18 2005-12-13 Honeywell International, Inc. Thrust reverser system actuator having an integral torque limiter

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150166193A1 (en) * 2013-12-18 2015-06-18 Rolls-Royce Plc Gas turbine cowl
EP2886841A1 (en) * 2013-12-18 2015-06-24 Rolls-Royce plc Gas turbine cowl having a variable area fan nozzle
US9776726B2 (en) * 2013-12-18 2017-10-03 Rolls-Royce Plc Gas turbine cowl

Also Published As

Publication number Publication date
EP2190741A1 (fr) 2010-06-02
ES2372234T3 (es) 2012-01-17
CN101784446A (zh) 2010-07-21
RU2010109817A (ru) 2011-09-27
WO2009024654A1 (fr) 2009-02-26
CA2696346A1 (fr) 2009-02-26
BRPI0813039A2 (pt) 2014-12-16
ATE522440T1 (de) 2011-09-15
EP2190741B1 (fr) 2011-08-31
RU2453478C2 (ru) 2012-06-20
FR2920139B1 (fr) 2009-09-18
FR2920139A1 (fr) 2009-02-27

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Legal Events

Date Code Title Description
AS Assignment

Owner name: AIRCELLE, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:LEDERLE, STEPHANE;REEL/FRAME:023932/0604

Effective date: 20100111

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION