Classifications

• • 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
  • F02C7/28—Arrangement of seals
• • 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
  • F02C7/24—Heat or noise insulation
  • F02C7/25—Fire protection or prevention
• • 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
  • F02K1/78—Other construction of jet pipes
  • F02K1/80—Couplings or connections
  • F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
• • 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

Definitions

• the present invention relates to a seal for a pylon and a turbojet engine nacelle, and a turbojet tower and nacelle assembly incorporating such a seal.
• a propulsion unit for an aircraft may comprise a nacelle surrounding a turbojet engine.
• the upstream part of the nacelle is intended to channel the air towards the turbojet engine inlet, and the downstream part of the nacelle makes it possible to reject at high speed the air which has passed through the turbojet engine, thus making it possible to generate the thrust required for the propulsion of the aircraft.
• a nacelle typically comprises an outer fairing defining the aerodynamic external profile of the nacelle, and an internal fairing surrounding the turbojet engine, the space between these two fairings defining the cold flow vein of the nacelle.
• the internal fairing often referred to as the "fixed internal structure" of the nacelle, or “IFS”, is extended in its downstream part by a primary nozzle for the ejection of the combustion gases, making it possible to channel the outlet of hot air coming from the heart of the turbojet.
• the outer and inner fairings (fixed internal structure) are articulated about axes substantially parallel to that of the turbojet engine.
• the platform is opened by separating the two half-shells formed by the two halves of the outer and inner fairings of the nacelle, and by making each of them rotate around their respective longitudinal axes.
• the seal between the fixed internal structure and the primary gas ejection nozzle then interacts and must be designed to allow this opening movement in axial rotation.
• the fire seal of this state of the art is disposed between the body of the gas ejection nozzle and a portion of the outer structure associated with the support tower of the turbojet engine.
• the fire seal is composed of two plates in contact. The two plates overlap and are bounded around them by fire barriers.
• the outer and inner fairings of the nacelle each form, or both, a unitary annular assembly, so that access to the turbojet engine for maintenance operations is effected by sliding these fairings towards the downstream of the nacelle, along rails arranged on the suspension pylon of the propulsion unit formed by the nacelle and the turbojet engine.
• nacelle it is commonly referred to as an "O-Duct" nacelle, such examples of nacelles being disclosed, for example, by FR07 / 03607 and FR09 / 05687.
• the present invention provides a remedy for this drawback of the state of the art. It relates in fact to a fire seal for pylon assembly and turbojet nacelle including O-duct type, this nacelle comprising a fixed internal nacelle structure and a primary nozzle for ejection of combustion gas that can at least a part be im ied by a relative longitudinal translational movement in the direction of the longitudinal axis of the nacel le, during the maintenance operation.
• the seal comprises a plurality of baffles arranged longitudinally so as not to interfere during a longitudinal translation movement the fixed internal structure of the nacelle and the primary nozzle for ejection of combustion gases .
• the seal is such that, on at least a portion of the seal, the baffles comprise a plurality of annular edges concentric to the longitudinal axis of the nacelle.
• the seal is made in two parts, a first part integral with the fixed internal structure and / or said pylon and a second part integral with the primary nozzle for ejection of the combustion gases, a part comprising a plurality of baffles whose edges are intended to interpenetrate with the edges of the plurality of baffles of the other part.
• the plurality of baffles of a first portion of the seal has two edges and the plu ur ity of ch icanes of the second portion vis-à-vis has two edges.
• the seal extends at least over the angular extension of an angular sector in which the risk of flame passing has been assessed, generally +/- 45 ° with respect to the vertical.
• the materials and the dimensions of the edges and grooves constituting the baffles of the seal are determined so as to ensure a lack of contact between the edges and the bottoms of the grooves when the platform is in working condition and that vibration regimes are established between the two parts of the seal.
• a first portion of the seal is adapted to be integral with a collar of the primary ejection nozzle disposed at the outlet of the jet engine burned compartment and the second portion of the seal is adapted to be secured to the downstream portion of the internal structure fixed nacelle
• the invention also relates to a pylon and nacelle assembly comprising a fixed nacelle internal structure and a primary combustion gas ejection nozzle that can adopt a longitudinal translation movement relative to each other.
• the assembly comprises a seal according to the invention.
• FIG. 1 is a perspective view, with exploded views, of a turbojet engine, its nacelle and its pylon, of the type used in the present invention
• FIG. 2 is a diagrammatic sectional view of the part of a nacelle surrounding a turbojet, equipped with the seal according to the invention, in a first relative position of the fixed internal nacelle structure and the primary nozzle of FIG. ejection of the combustion gases of the nacelle;
• FIG. 3 is a diagrammatic sectional view of the rear part of the turbojet engine equipped with the seal according to the invention, in a second relative position of the fixed internal nacelle structure and of the primary nozzle for the ejection of the combustion gases. the nacelle; and
• FIG. 4 is a diagrammatic sectional view of the attachment of the seal according to the invention, to the primary exhaust nozzle for the combustion gases and to the fixed internal nacelle structure and to the primary ejection nozzle. combustion gases from the nacelle.
• FIG 1 there is shown a perspective view, with exploded, of a turbojet 8, its nacelle and its pylon 3, of the kind used in the present invention.
• the propulsion unit composed of the pylon, the nacelle and the turbojet engine is presented with an upstream side to the left of the drawing and a downstream side to the right of the drawing.
• the air represented by the arrow 30 is sucked into the air inlet 35 by the fan (not shown). Part of the air propelled by the blower (not shown) is then em is in the annular space forming the cold vein represented by the arrow 32, between the hood or outer fairing 33 and a fixed internal structure 4.
• the blower (not shown) is driven by the heart of the turbojet engine 8 which comprises a combustion chamber and a turbine (not shown).
• the combustion gases obtained by the combustion of fuel and the air taken at the outlet of the fan are ejected by a hot stream represented by the arrow 31 between the primary gas ejection nozzle 5 and the gas ejection cone 34.
• the assembly is built and installed along a longitudinal axis A.
• the pylon 3 allows the suspension of the nacelle and the turbojet engine
• the flame / fire problem occurs between the downstream edge of the fixed internal structure 4 of the nacelle and the primary gas ejection nozzle 5.
• the solution is provided by a fire-resistant seal 1 0, 1 1 which fills at least one angular sector of the space between the downstream edge of the fixed internal structure 4 of the nacelle and the primary nozzle gas ejection 5, as will be detailed below. after.
• FIG 2 there is shown the rear or downstream part of a nacelle equipped with the seal according to the invention.
• the rear part 1 of the nacelle comprises a primary nozzle for ejecting the combustion gases emitted by the body of the turbojet engine 8.
• the body of the turbojet engine 8 is mounted inside the fixed internal structure of the nacelle 4.
• the nacelle and the engine are suspended from the pylon 3 associated with the wing of an aircraft in part by the fasteners represented 6 and 7.
• the fireproof seal 1 0, 1 1 of the invention is responsible for preventing the passage of flames from the downstream zone 9, inside the fixed internal structure 4, to the outside.
• the seal 1 0, 1 1 of the invention consists of a plurality of baffles.
• each baffle is formed by a groove limited by two annular edges concentric to the axis A of the nacelle.
• a first planar groove is limited between two concentric annular edges, substantially perpendicular 12 and 13 to the plane of the first groove.
• a second planar groove is bounded between concentric annular edges, substantially perpendicular 14 and 15 to the plane of the first groove.
• the two groove planes are substantially perpendicular to the longitudinal axis A of the nacelle.
• the edges limiting the grooves of the seal 10, 11 are substantially aligned in the direction of the longitudinal axis A of the nacelle. Due to the cylindrical symmetry of the nacelle about the longitudinal axis A, the edges are substantially cylinders or cylinder arcs having a determined extension along the longitudinal axis A, while the substantially planar grooves affect the shape. at least partially of a flat ring.
• the fire seal is imitated over an angular sector greater than about 90 ° about the longitudinal axis.
• This situation is illustrated in Figure 1 in which the seal is distributed symmetrically in the upper sector on either side of the vertical plane separating the propulsion unit into two substantially symmetrical halves.
• the seal extends at least over the angular extension of the angular sector of the space 2 between the primary combustion gas ejection nozzle 5 and the downstream space of the fixed internal structure. nacelle 4 in which the risk of flames has been assessed.
• the baffles of the seal of the invention are divided into two separate parts of the seal.
• a first part 10 of the seal is attached to a specific part of the exhaust nozzle of the combustion gases 5 while a second part 1 1 of the seal is attached to a specific part downstream 9 of the fixed internal structure of nacelle 4.
• the turbojet engine 1 is configured in normal operation.
• the seal 10, 1 1 is in the "closed” state, in that the two parts are joined in sealing interaction.
• the edges 12, 13 of the groove of the first portion 10 of the seal are interdigitated with the edges 14 and 1 5 vis-à-vis the groove of the second part 1 1 of the seal.
• the second part 1 1 of the seal also comprises an integral part 16 which is fixed by a suitable means on the inner face of the downstream part 9 of the fixed internal structure of nacelle 4.
• the space between the edges of the first and second parts of the gasket is calibrated so that the fireproof function can be fulfilled being furthermore noted that a slight air passage between the two parts 1 0 and 1 1 contact seal in normal operation is tolerated.
• such a seal may be made of fire-resistant metal materials such as titanium or inconel.
• the materials and the dimensions of the edges and grooves constituting the baffles of the seal are determined so as to ensure a lack of contact between the edges and the bottoms of the grooves when the nacel is in operation and that vibratory regions are established between the two parts 10 and 1 1 of the seal.
• FIG. 3 shows a schematic sectional view of the rear part of the turbojet engine equipped with the gasket according to the invention, in a second relative position of the fixed internal nacelle structure and of the primary ejection nozzle. 5.
• the parts identical to those of FIGS. 1 and 2 bear the same reference number and are not necessarily described again.
• the fixed internal nacelle structure 4 is moved longitudinally towards the rear or downstream of the turbojet engine substantially along the arrow B aligned with the longitudinal axis A of the nacelle. .
• the seal 10, 1 1 is mechanically dissociated between its two parts, respectively the part 1 0 on the primary exhaust nozzle of the combustion gases and the part 1 1 on a downstream portion of the fixed structure of basket 1 1.
• the seal 10, 1 1 is therefore in an "open" state in that the two parts of the seal are disjoint and the seal removed.
• Figure 4 there is shown a schematic sectional view of the attachment of the seal according to the invention, the primary nozzle of combustion gas ejection 5 and the fixed internal structure nacelle.
• the view is partially a three-dimensional representation.
• the first part 10 of the seal is fixed by suitable means on a flange 20 which extends in the form of a disc ring disposed in a plane normal to the longitudinal axis A of the nacelle.
• the flange 20 is part of the primary combustion gas ejection nozzle 5 allowing the attachment of this nozzle to the body 8 of the trotrubber.
• the second part 10 of the seal is fixed by suitable means to a facing part which is downstream of the fixed nacelle structure 4.
• the seal of the invention can take various forms. Especially the number of baffles is not limited and more than two edges and a groove can be provided on each part of the seal.
• the shape of the edges and the groove can be variable while respecting the absence of contact on the one hand and the absence of interaction during the relative longitudinal translation of the fixed internal structure of nacelle 4 and the primary nozzle of ejection of combustion gases 5.
• any nacelle in which the fixed internal structure can slide for maintenance operations including to a nacelle in which the outer fairing does not form a single block with the fixed internal structure, and opens outwards in two halves each pivoting about a longitudinal axis.
• the gasket according to the invention is disposed between the pylon 3 and the primary exhaust nozzle 5 for the ejection of combustion gases.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Gasket Seals (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=47628352

Family Applications (1)

Country Status (8)

Families Citing this family (9)

Family Cites Families (8)

• 2012
  • 2012-01-05 FR FR1250111A patent/FR2985501B1/fr not_active Expired - Fee Related
• 2013
  • 2013-01-04 CA CA2858740A patent/CA2858740A1/fr not_active Abandoned
  • 2013-01-04 BR BR112014014261A patent/BR112014014261A2/pt not_active IP Right Cessation
  • 2013-01-04 RU RU2014131660A patent/RU2014131660A/ru not_active Application Discontinuation
  • 2013-01-04 WO PCT/FR2013/050015 patent/WO2013102739A1/fr active Application Filing
  • 2013-01-04 CN CN201380004834.3A patent/CN104093632A/zh active Pending
  • 2013-01-04 EP EP13701823.0A patent/EP2800693A1/fr not_active Withdrawn
• 2014
  • 2014-07-07 US US14/324,624 patent/US20140318149A1/en not_active Abandoned

Non-Patent Citations (1)

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