WO2013045783A1 - Ensemble de lèvre pour nacelle de turboréacteur à dégivrage électrique - Google Patents
Ensemble de lèvre pour nacelle de turboréacteur à dégivrage électrique Download PDFInfo
- Publication number
- WO2013045783A1 WO2013045783A1 PCT/FR2012/052006 FR2012052006W WO2013045783A1 WO 2013045783 A1 WO2013045783 A1 WO 2013045783A1 FR 2012052006 W FR2012052006 W FR 2012052006W WO 2013045783 A1 WO2013045783 A1 WO 2013045783A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- conductor
- heating element
- assembly according
- lip assembly
- turbojet engine
- Prior art date
Links
- 239000004020 conductor Substances 0.000 claims abstract description 37
- 230000007935 neutral effect Effects 0.000 claims abstract description 20
- 238000005485 electric heating Methods 0.000 claims abstract description 11
- 238000010438 heat treatment Methods 0.000 claims description 25
- 238000010257 thawing Methods 0.000 claims description 5
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 claims description 2
- 230000001939 inductive effect Effects 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 206010042255 Struck by lightning Diseases 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 150000002500 ions Chemical class 0.000 description 1
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
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
-
- 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
-
- 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
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B3/00—Ohmic-resistance heating
- H05B3/20—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater
-
- 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
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B2203/00—Aspects relating to Ohmic resistive heating covered by group H05B3/00
- H05B2203/002—Heaters using a particular layout for the resistive material or resistive elements
- H05B2203/003—Heaters using a particular layout for the resistive material or resistive elements using serpentine layout
Definitions
- the present invention relates to a heating element for an electric deicing device equipping a turbojet engine nacelle.
- An aircraft is propelled by one or more propulsion units each comprising a turbojet engine housed in a substantially tubular nacelle.
- Each propulsion unit is attached to the aircraft by a mast generally located under a wing or at the fuselage of the aircraft.
- a nacelle generally has a substantially tubular structure surrounding the turbojet engine and comprises, an air inlet upstream of the engine, a median section intended to surround a fan of said turbojet engine and a downstream section surrounding the combustion chamber of the turbojet engine and which can be equipped with thrust reversal means.
- the air intake comprises, on the one hand, an inlet lip adapted to allow optimal capture to the turbojet of the air necessary to supply the blower and the internal compressors of the turbojet engine, and other on the other hand, a downstream structure to which the lip is attached and intended to properly channel the air towards the fan blades.
- the assembly is attached upstream of a fan casing belonging to the middle section of the assembly.
- ice may form on the nacelle, particularly at the outer surface of the air intake lip.
- the presence of ice or frost changes the aerodynamic properties of the air intake and disturbs the flow of air to the blower.
- a solution for de-icing or deglazing the outer surface is to prevent ice from forming on this outer surface by keeping the surface concerned at a sufficient temperature.
- an electric defrosting device uses sets of heating resistors, also called heating mats, located at the air intake lip near the outer surface and electrically powered by a generally three-phase power supply. .
- a disadvantage of such systems is that they are located in an area of the nacelle particularly exposed to the most direct effects of lightning. This leads to induced currents in the device and heating mats that are particularly high. These induced currents propagate through the power harnesses of the system and can severely damage system equipment.
- the present invention aims to overcome these drawbacks and relates for this purpose to a lip assembly of a turbojet engine nacelle equipped with at least one electrical deicing system comprising at least one resistive heating element powered electrically via minus one supply conductor, each supply conductor being associated with a neutral conductor or "earth" arranged in a clustered manner adjacent the corresponding supply conductor.
- each supply conductor is associated with a neutral conductor and is grouped together, the phase and neutral conductors are always side by side and thus the surface of the loops formed by the different conductors is minimized and extremely reduced.
- the induced electric currents are therefore greatly reduced and it is possible to simplify and size accordingly the anti-lightning components.
- the electric heating element is supplied with alternating current, preferably three-phase.
- each phase is bifilaire comprising a phase conductor and a neutral conductor or "earth".
- the electrical wires may be twisted or not.
- the electric heating element has at least one side and the supply and neutral conductors are arranged on the same side.
- the heating element is a carpet or heating tape.
- the heating element comprises at least one resistive coil disposed between a supply conductor and its associated neutral conductor.
- the resistive coil is disposed in at least two serpentine tracks.
- the two tracks are substantially parallel.
- the coil extends substantially along a length of the heating element.
- the present invention also relates to a turbojet engine nacelle, characterized in that it comprises an air intake lip assembly according to the invention.
- Figure 1 is a schematic representation of a set of heating elements arranged on the periphery of an air inlet lip and supplied by a star-shaped three-phase network according to the prior art.
- Figure 2 is a schematic representation of a set of heating elements arranged on the periphery of an air inlet lip and fed by a three-phase network mounted according to the invention.
- FIG. 3 is a schematic representation of a heating element according to the invention equipping an assembly as represented in FIG. 2.
- a defrosting system assembly 1 equipping an air intake lip assembly with a nacel of the rboreactor comprises a greater amount of light, here s ix, deg rou pes 2 of electric heating elements 4 regularly arranged on the periphery of the air inlet, each group 2 of electric heating elements 4 itself comprising a plurality of electrical elem en t ions ch a uffa nts 4 d isposed radially (here six heating elements 4 per group 2).
- the defrosting assembly 1 is powered by a three-phase power source 5 comprising a conductor of a first phase P1
- the power supply also includes a neutral connector N ⁇ ⁇ ⁇ ).
- Each group 2 and heating element 4 of said group is connected to a phase connection P 1, P 2 or P 3, and to the neutral conductor N, on the other hand.
- FIG. 1 shows a star assembly of the deicing system 1 according to the prior art.
- the power supply passes through the heating elements 4, the phase conductor P1, P2, P3 entering on one side of said element 4 and emerging at the neutral N by an opposite side.
- the neutral conductors are interconnected and form a floating neutral.
- FIG. 2 shows a circuit diagram according to the invention of a deicing system 10.
- the assembly of FIG. 2 differs from the star assembly according to the prior art in that for each heating element 4, the phase conductor P1, P2, P3 is grouped on the same side and close to the neutral conductor N.
- the supply inlets and outlets of the heating elements are two-wire comprising a phase conductor P1, P2, P3 and a neutral conductor N.
- the inductive loops that can be formed are, on the one hand, less numerous and, on the other hand, offer a reduced surface area.
- FIG. 3 illustrates a heating element 4 advantageously equipping the deicing system 100.
- the heating element 4 is substantially in the form of a carpet, or a rectangular strip within which a heating resistive element 7 forming a coil circulates.
- the resistive heating element no longer forms a coil passing through the heating element 4 which has an element conductor P1, P2, P3 and a neutral conductor N on opposite sides, but has a coil which is arranged to form two substantially parallel tracks along the heating element 4.
- the optimization of the wiring of the coil in addition to the optimization of the wiring of the defrosting system previously presented makes it possible to reduce and especially not to size the size of the anti-lightning protection components that are present in the various electrical components of the nacelle and the aircraft.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Resistance Heating (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201280047097.0A CN103826971A (zh) | 2011-09-28 | 2012-09-07 | 用于电除冰的涡轮喷气发动机机舱的唇缘组件 |
BR112014006236A BR112014006236A2 (pt) | 2011-09-28 | 2012-09-07 | montagem de aba de uma nacela de motor turbo equipada com pelo menos um sistema de degelo elétrico e nacela de motor turbo |
RU2014115889/11A RU2014115889A (ru) | 2011-09-28 | 2012-09-07 | Узел кромки для гондолы турбореактивного двигателя с электрической противообледенительной защитой |
EP12767046.1A EP2760741B1 (fr) | 2011-09-28 | 2012-09-07 | Ensemble de lèvre pour nacelle de turboréacteur à dégivrage électrique |
CA2847806A CA2847806A1 (fr) | 2011-09-28 | 2012-09-07 | Ensemble de levre pour nacelle de turboreacteur a degivrage electrique |
US14/227,628 US8975560B2 (en) | 2011-09-28 | 2014-03-27 | Lip unit for an electrically deiced turbojet engine nacelle |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1158678A FR2980458B1 (fr) | 2011-09-28 | 2011-09-28 | Ensemble de levre pour nacelle de turboreacteur a degivrage electrique |
FR11/58678 | 2011-09-28 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/227,628 Continuation US8975560B2 (en) | 2011-09-28 | 2014-03-27 | Lip unit for an electrically deiced turbojet engine nacelle |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2013045783A1 true WO2013045783A1 (fr) | 2013-04-04 |
Family
ID=46968275
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/052006 WO2013045783A1 (fr) | 2011-09-28 | 2012-09-07 | Ensemble de lèvre pour nacelle de turboréacteur à dégivrage électrique |
Country Status (8)
Country | Link |
---|---|
US (1) | US8975560B2 (fr) |
EP (1) | EP2760741B1 (fr) |
CN (1) | CN103826971A (fr) |
BR (1) | BR112014006236A2 (fr) |
CA (1) | CA2847806A1 (fr) |
FR (1) | FR2980458B1 (fr) |
RU (1) | RU2014115889A (fr) |
WO (1) | WO2013045783A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2021087454A1 (fr) * | 2019-11-01 | 2021-05-06 | Watlow Electric Manufacturing Company | Dispositif de chauffage à moyenne tension triphasé |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10399684B2 (en) * | 2014-10-29 | 2019-09-03 | The Boeing Company | Induction heating coils with uniform heating |
JP6549855B2 (ja) * | 2015-02-17 | 2019-07-24 | 三菱航空機株式会社 | 航空機の風防 |
US10486821B2 (en) | 2015-07-07 | 2019-11-26 | The Boeing Company | Jet engine anti-icing and noise-attenuating air inlets |
CN108688824B (zh) * | 2017-04-10 | 2020-07-14 | 清华大学 | 发动机进气口除冰系统、内燃发动机及航空器 |
CN113955124B (zh) * | 2021-11-05 | 2024-02-13 | 天津航空机电有限公司 | 一种嵌入式进气道唇口防冰加热组件及制作方法 |
FR3130755A1 (fr) * | 2021-12-20 | 2023-06-23 | Airbus Operations | Dispositif de chauffage à matelas chauffant pour un système de protection contre le givre d’un aéronef. |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4688757A (en) | 1986-08-11 | 1987-08-25 | Dresser Industries, Inc. | Soft seat Y pattern globe valve |
EP1495963A2 (fr) | 2003-07-08 | 2005-01-12 | Rohr, Inc. | Procédé et dispositif pour l'atténuation du bruit et pour la protection contre le givre d'un bord d'entrée d'air d'une nacelle de réacteur |
EP1715159A1 (fr) * | 2005-04-22 | 2006-10-25 | Rohr, Inc. | Nacelle de moteur d'avion munie d'une ouverture d'accès au système de dégivrage |
WO2006136748A2 (fr) * | 2005-06-22 | 2006-12-28 | Airbus France | Systeme d'anti-givrage et de degivrage de nacelle de moteur d'aeronef a tapis resistif |
GB2432409A (en) * | 2005-11-18 | 2007-05-23 | Goodrich Corp | Radar altering structure |
US20080179448A1 (en) * | 2006-02-24 | 2008-07-31 | Rohr, Inc. | Acoustic nacelle inlet lip having composite construction and an integral electric ice protection heater disposed therein |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2699303A (en) * | 1947-10-24 | 1955-01-11 | Rotol Ltd | Means for electrically heating the spinners of airscrews |
FR2887519B1 (fr) * | 2005-06-22 | 2008-10-10 | Airbus France Sas | Systeme d'anti-givrage et de degivrage de nacelle de moteur d'aeronef a tapis resistif |
FR2898868B1 (fr) * | 2006-03-24 | 2008-12-12 | Aircelle Sa | Structure pour levre d'entree d'air de nacelle a degivrage electrique |
US7922120B2 (en) * | 2006-11-15 | 2011-04-12 | Honeywell International Inc. | Wing ice protection heater element network |
FR2908738B1 (fr) * | 2006-11-16 | 2009-12-04 | Airbus France | Bord d'attaque d'aeronef. |
US7922121B2 (en) * | 2007-10-15 | 2011-04-12 | Rosemount Aerospace Inc. | Power distribution architecture for an ice protection system |
-
2011
- 2011-09-28 FR FR1158678A patent/FR2980458B1/fr active Active
-
2012
- 2012-09-07 WO PCT/FR2012/052006 patent/WO2013045783A1/fr active Application Filing
- 2012-09-07 CN CN201280047097.0A patent/CN103826971A/zh active Pending
- 2012-09-07 RU RU2014115889/11A patent/RU2014115889A/ru not_active Application Discontinuation
- 2012-09-07 CA CA2847806A patent/CA2847806A1/fr not_active Abandoned
- 2012-09-07 BR BR112014006236A patent/BR112014006236A2/pt not_active IP Right Cessation
- 2012-09-07 EP EP12767046.1A patent/EP2760741B1/fr active Active
-
2014
- 2014-03-27 US US14/227,628 patent/US8975560B2/en active Active
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4688757A (en) | 1986-08-11 | 1987-08-25 | Dresser Industries, Inc. | Soft seat Y pattern globe valve |
EP1495963A2 (fr) | 2003-07-08 | 2005-01-12 | Rohr, Inc. | Procédé et dispositif pour l'atténuation du bruit et pour la protection contre le givre d'un bord d'entrée d'air d'une nacelle de réacteur |
EP1715159A1 (fr) * | 2005-04-22 | 2006-10-25 | Rohr, Inc. | Nacelle de moteur d'avion munie d'une ouverture d'accès au système de dégivrage |
WO2006136748A2 (fr) * | 2005-06-22 | 2006-12-28 | Airbus France | Systeme d'anti-givrage et de degivrage de nacelle de moteur d'aeronef a tapis resistif |
GB2432409A (en) * | 2005-11-18 | 2007-05-23 | Goodrich Corp | Radar altering structure |
US20080179448A1 (en) * | 2006-02-24 | 2008-07-31 | Rohr, Inc. | Acoustic nacelle inlet lip having composite construction and an integral electric ice protection heater disposed therein |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2021087454A1 (fr) * | 2019-11-01 | 2021-05-06 | Watlow Electric Manufacturing Company | Dispositif de chauffage à moyenne tension triphasé |
Also Published As
Publication number | Publication date |
---|---|
US8975560B2 (en) | 2015-03-10 |
CA2847806A1 (fr) | 2013-04-04 |
CN103826971A (zh) | 2014-05-28 |
BR112014006236A2 (pt) | 2017-04-04 |
FR2980458B1 (fr) | 2013-08-30 |
FR2980458A1 (fr) | 2013-03-29 |
EP2760741B1 (fr) | 2016-11-16 |
EP2760741A1 (fr) | 2014-08-06 |
US20140209592A1 (en) | 2014-07-31 |
RU2014115889A (ru) | 2015-11-10 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2760741B1 (fr) | Ensemble de lèvre pour nacelle de turboréacteur à dégivrage électrique | |
EP1893484B1 (fr) | Systeme d'anti-givrage et de degivrage de nacelle de moteur d'aeronef a tapis resistif | |
EP2262684B1 (fr) | Levre d'une entree d'air d'une nacelle de turboreacteur | |
EP2406132B1 (fr) | Dispositif de dégivrage, notamment pour nacelle d'aéronef | |
FR2887519A1 (fr) | Systeme d'anti-givrage et de degivrage de nacelle de moteur d'aeronef a tapis resistif | |
EP2352672B1 (fr) | Procédé de contrôle d'un système de dégivrage électrique | |
EP2941382B1 (fr) | Dispositif de dégivrage électrique pour élément de nacelle pour turboréacteur | |
FR2999533A1 (fr) | Procede et dispositif de degivrage a air chaud des bords d'attaque d'un aeronef a reaction | |
WO2014167329A1 (fr) | Antigivrage d'entrée de turbine à gaz utilisant l'énergie électrique | |
FR3004165A1 (fr) | Element d'aeronef necessitant un traitement contre le givre | |
FR2887518A1 (fr) | Nacelle de moteur d'aeronef a dispositif de degivrage perfectionne et attenuation acoustique optimisee | |
FR2992291A1 (fr) | Ensemble electrique chauffant pour dispositif de degivrage | |
BE1023498B1 (fr) | Bec anti givre de compresseur basse pression de turbomachine axiale | |
CN107565247B (zh) | 供电接头、制造供电接头的方法、电防冰系统、飞机电防冰翼面以及组装方法 | |
FR3038342A1 (fr) | Element profile de turbomachine presentant un systeme d'antigivrage et/ou de degivrage, et procedes de fabrication | |
FR2887520A1 (fr) | Systeme de degivrage a reseaux d'elements resistifs segregues | |
WO2023187292A1 (fr) | Unite integree de transfert de puissance tournant d'une chaine electrique de degivrage des pales d'helice et du cone avant d'une turbomachine | |
BE1024761A1 (fr) | Aube degivrante de compresseur de turbomachine axiale |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 12767046 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 2847806 Country of ref document: CA |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
REEP | Request for entry into the european phase |
Ref document number: 2012767046 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2012767046 Country of ref document: EP |
|
ENP | Entry into the national phase |
Ref document number: 2014115889 Country of ref document: RU Kind code of ref document: A |
|
REG | Reference to national code |
Ref country code: BR Ref legal event code: B01A Ref document number: 112014006236 Country of ref document: BR |
|
ENP | Entry into the national phase |
Ref document number: 112014006236 Country of ref document: BR Kind code of ref document: A2 Effective date: 20140317 |