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
  • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
• • 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
  • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
  • F02C7/055—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with intake grids, screens or guards
• • 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—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
  • B64D2033/022—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising bird or foreign object protections
• • 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—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
  • B64D2033/0233—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
• • 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—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
  • B64D2033/0253—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/32—Application in turbines in gas turbines
  • F05D2220/329—Application in turbines in gas turbines in helicopters
• • 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

Definitions

• This paper relates to an air intake for a helicopter engine equipped with an anti-icing grid providing significant bypass circulation in case of icing.
• the current air intakes are equipped with an anti-icing grid completely covering the air. air inlet opening in the turbine. This is particularly the case on the turbine Turbomeca TM-333 as shown in FIG 5A. With the latter, the possible icing forms on the outer surface 92a of the grid 92 rather than in the air inlet itself or the air supply passage. An inner portion 92b of the grid 92 is then provided to allow bypass circulation when the outer surface 92a of the grid 92 is frosted.
• the lips 90 of the air inlet on which the anti-icing grid 92 is mounted are generally machined in the mass, as in the case of the turbine TM-333, or made of composite and are therefore particularly cumbersome: considering the very constrained environment around the air inlet, it is then that the bypass section Se 'available when the outer surface 92a of the grid 92 is frosted is reduced which limits the air flow in case of icing.
• both mass-machined models and composite models raise assembly difficulties.
• the edges of the grid are glued on a profile which is in turn glued on the composite lips: in addition to the complexity of such an assembly, the implementation of the bonding of composite materials is this delicate day.
• the present disclosure relates to an air intake for a gas turbine helicopter engine having a compressor and an air compressor supply passage opening at its upstream end through said air inlet, this air inlet.
• a gas turbine helicopter engine having a compressor and an air compressor supply passage opening at its upstream end through said air inlet, this air inlet.
• the use of a thin sheet offering very good forming properties, makes it possible to produce complex and compact geometries, such a sheet allowing, in particular, very small radii of curvature.
• a thin sheet also makes it possible to use certain fastening techniques, such as welding, which would not be possible with other materials.
• the thin sheet provides the advantage of reduced mass, which reduces operating costs by reducing the fuel consumption of the engine.
• said thin metal sheet forming said at least one air inlet lip has a thickness of less than 1.5 mm, preferably less than 0.8 mm.
• the outer end of the at least one air intake lip is curved U outwards and the edge of the anti-icing grid engages in the U-shaped space thus defined .
• the forming properties of the sheet metal it is possible to define a very tight U-shaped space well adapted to the dimensions of the edge of the sheet. Grid.
• such a U-shaped space can be formed closer to the lip itself, which allows to release a large transverse space that can contribute to the increase of the contouement section.
• the edge of the anti-ice grill conforms to the walls of the U-shaped space defined by the inlet lip. This may allow in particular to crimp the border of the grid in this U-shaped space or to assemble by stamping.
• the edge of the anti-icing grid is provided with fastening tabs attached to said at least one air intake lip.
• fastening tabs attached to said at least one air intake lip.
• the edge of the anti-icing gate is provided with a continuous bead attached to said at least one air intake lip. This assembly solution allows attachment all along a section or the entire lip.
• the edge of the anti-icing gate is attached to said at least one air intake lip by welds. This attachment is reliable and durable.
• the edge of the anti-icing gate is fixed on said at least one air intake lip by solders, glue points, crimps or rivets.
• the attachment of the anti-icing gate to said at least one air intake lip is free of adhesive seal. The difficulty of implementing this technique is thus avoided.
• the grid border is a separate part of the body of the anti-icing grid, this grid border being fixed to the grid body.
• This solution makes it possible to easily adapt a fastening interface, specially designed to ensure the connection and be fixed on the air intake lip, on a grid anti-icing shaped for the sole purpose of preventing icing and offer a large section of contouement.
• the material of the border can be different from that of the body of the grid: for example, the border may be plastic when the body of the grid is metal.
• the grid border is attached to the body of the anti-icing grid by solders.
• the air intake lip is made in one piece on an angular sector greater than 90 °, preferably equal to 180 °.
• the two air inlet lips are formed by thin metal sheets.
• the air inlet is of the radial type.
• the air inlet is of the axial type.
• This disclosure also relates to a gas turbine helicopter engine having an air intake according to any one of the preceding embodiments.
• FIG 1 is a schematic overview of a helicopter engine.
• FIG 2 is a partial sectional view of an air inlet according to the invention.
• FIG 3 is a partial perspective view of the air inlet of the
• FIG. 1 A first figure.
• FIG 4 is an enlarged schematic view of the air inlet of FIG 2 illustrating the attachment of the anti-icing grid on the lips of the air inlet.
• FIG 5A is a view of an air inlet of the prior art.
• FIG 5B is a sketch schematically illustrating the bypass section gain offered by an air intake according to the invention vis-à-vis an air inlet of the prior art.
• FIG. 1 schematically shows a gas turbine helicopter engine comprising a compressor stage 10 (for example a centrifugal compressor) receiving outside air through an annular air supply passage 12.
• a compressor stage 10 for example a centrifugal compressor
• the passage 12 opens with an annular outer opening 12a delimited by a metal casing 14 of the motor.
• the casing 14 also defines the walls of the passage 12.
• An annular combustion chamber 16, for example with an inverted flow, is provided with injectors (not shown) supplied with fuel and primary air flow from the compressor 10.
• the gases from combustion chamber 16 enter a turbine 18 for driving the compressor 10, connected thereto by a shaft 20, and a power turbine 22 (for example a single stage) connected by a shaft 23 to a gear train which provides mechanical power to an output shaft 24, the shafts 20 and 23 being coaxial.
• two lips 30, 32 define an air inlet 34 for the passage 12.
• the lips 30, 32 are formed by two respective annular thin sheets which at one end internal, are connected to the upstream end of the passage 12 on either side of the opening 12a along thereof.
• the metal sheets forming the lips 30, 32 are weldable metal, for example stainless steel, and have a thickness of the order of 0.6mm.
• each lip 30, 32 has a rim 30a, 32a curved U outwards which thus forms a U-shaped space 70.
• the lips 30, 32 may have tabs or a flange 30b, 32b, bent substantially at 90 °, allowing their attachment to the casing 14.
• the purpose of the grid 36 is to prevent frost formation in the air inlet 34 and the supply passage 12, any frost forming on the outer surface 36a of the grid 36.
• An annular bypass channel 38 is then provided to sufficiently feed the passage 12 of air despite icing of the outer surface 36a of the gate 36.
• the channel 38 is delimited on one side by an annular guide wall angled 39, or plenum, provided with ribs. rigidification 39a and secured to the casing 14.
• the wall 39 is located facing a lip of the air inlet, for example the lip 32, which delimits the other side of the channel 38.
• a second bypass channel 40 similar is also provided on the side of the other lip 30 (the plenum is however not shown so as not to weigh down the drawings).
• the bent edges of the anti-icing grid 36 define an internal bypass surface 36b on each side of the air inlet 34, facing the housing 14 and thus opening in the bypass channel 38 or 40, which allows the admission of a bypass air circulation when the outer surface 36a of the grid 36 is frosted.
• the bypass section Se defined transversely between the lip 30, 32 and the anti-icing grid 36, determines the maximum flow rate of this bypass circulation.
• each lip 30, 32 can be made in one piece over a large angular sector, typically greater than 90 °.
• the air inlet 34 comprises two upstream lips 30, each extending over 180 °, which are contiguous to each other to form the air inlet 34 over 360 °; similarly, the air inlet 34 also comprises two downstream lips 32 each extending over 180 °.
• the lips 30, 32 have in this embodiment a sectional substantially rectilinear profile between their edges 30a, 32a and their legs or flanges 30b, 32b. However, in other exemplary embodiments, this profile could be curved for one and / or for the other of the lips 30, 32.
• FIGS. 3 and 4 make it possible to better visualize the manner in which the grid 36 is assembled on the lips 30, 32.
• the lateral end edges 50 of the grid 36 are bent towards space U-shaped 70 of each lip 30, 32; a border 60 is mounted along each of these edges 50 to serve as a fixing interface between the grid 36 and the lips 30, 32.
• This edge 60 takes the form of a U-shaped section, made of the same metal as the lip 30 or 32, extending circumferentially all along the edge 50 of the grid 36 thus forming a groove 61 in which the edge of Lateral end 50 of the grid 36 is housed: it is fixed by solders 62.
• this edge 60 also has fixing lugs 63 which extend radially, in the extension of the inner edge of the groove 61, in the direction of the casing 14.
• the fastening tabs 63 extend along the outer wall of the lip 30, 32
• the fixing lugs 63 are then fixed against the wall of the lip 30, 32 by means of weld spots 64.
• the fastening lugs 63 have a length sufficient to descend along the lips 30, 32 to a level lower than that of the internal circumferential surface 36b of the anti-icing grid 36 so as to allow the passage of the tool at the time of assembly of the gate 36 on the lips 30, 32.
• the lips 30, 32 are themselves very compact and a very compact assembly of the grid 36 on the lips 30, 32 is possible. With a given external dimensions, it is thus possible to provide a significant bypass section.
• FIG 5B schematically illustrates the gain allowed by such an air inlet vis-à-vis a conventional air inlet of the prior art.
• an air inlet according to the invention is shown schematically in solid lines while an air inlet of the prior art is shown in dashed lines.
• the machined or composite lips 90 are thicker.
• the forming of the material is poorly easy so that the U-shaped space 91 formed by the rim of the lips 90 and in which the lateral end edge 93 of the grid 92 is housed has a radius of curvature R ' important, traditionally of the order of 5 to 10 mm.
• R ' the radius of curvature
• the lips 30, 32 are thinner and form a U-shaped space 70 having a much smaller radius of curvature R owing to the good forming properties of the sheets: thus obtain a radius of curvature R of the order of, or less than, 2 mm. Therefore, the lateral end edge 50 of the grid 36 can be mounted on the lips 30, 32 much closer to the walls of the lips 30, 32, that is to say much closer to the plane median of the air inlet.
• the bypass section Se between the lips 30, 32 and the grid 36 is larger than in the case of the prior air inlet.
• the air inlet lips extend along the annular opening 12a of the air supply passage over the entire periphery of the motor: the invention is however also applicable in the case where the outer opening of the air supply passage extends over only a portion of the periphery of the engine. Similarly, the invention is also applicable to the case of an axial outer opening of the air supply passage and not radial. In addition, the example of the helicopter has been used so far, but it goes without saying that this invention is transferable to any gas turbine provided with an air inlet equipped with a bypass gate.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)

Priority Applications (9)

Applications Claiming Priority (2)

Publications (1)

Family

ID=47178073

Family Applications (1)

Country Status (11)

Cited By (1)

Families Citing this family (4)

Citations (4)

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• 2012
  • 2012-07-30 FR FR1257385A patent/FR2993862B1/fr active Active
• 2013
  • 2013-07-26 IN IN616DEN2015 patent/IN2015DN00616A/en unknown
  • 2013-07-26 US US14/417,225 patent/US10071813B2/en active Active
  • 2013-07-26 EP EP13756606.3A patent/EP2879955B1/fr active Active
  • 2013-07-26 WO PCT/FR2013/051809 patent/WO2014020267A1/fr not_active Ceased
  • 2013-07-26 CN CN201380039984.8A patent/CN104507810B/zh active Active
  • 2013-07-26 JP JP2015524828A patent/JP6295252B2/ja not_active Expired - Fee Related
  • 2013-07-26 KR KR1020157002008A patent/KR102180839B1/ko not_active Expired - Fee Related
  • 2013-07-26 RU RU2015106685A patent/RU2638055C2/ru active
  • 2013-07-26 CA CA2879517A patent/CA2879517C/fr not_active Expired - Fee Related
  • 2013-07-26 PL PL13756606T patent/PL2879955T3/pl unknown

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