EP1206383A1 - Dispositif de protection pour l'orifice d'entree d'air d'un reacteur d'avion - Google Patents

Dispositif de protection pour l'orifice d'entree d'air d'un reacteur d'avion

Info

Publication number
EP1206383A1
EP1206383A1 EP00952073A EP00952073A EP1206383A1 EP 1206383 A1 EP1206383 A1 EP 1206383A1 EP 00952073 A EP00952073 A EP 00952073A EP 00952073 A EP00952073 A EP 00952073A EP 1206383 A1 EP1206383 A1 EP 1206383A1
Authority
EP
European Patent Office
Prior art keywords
elements
engine according
aircraft engine
aircraft
engine
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.)
Withdrawn
Application number
EP00952073A
Other languages
German (de)
English (en)
Inventor
Richard Rudolph GÜTLICH
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.)
Cap International Nv
Original Assignee
Cap International Nv
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 Cap International Nv filed Critical Cap International Nv
Publication of EP1206383A1 publication Critical patent/EP1206383A1/fr
Withdrawn legal-status Critical Current

Links

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
    • F02C7/04—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
    • 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
    • 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—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
    • B64D2033/022—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising bird or foreign object protections

Definitions

  • the invention relates to an aircraft engine which on its front is provided with an air inlet through which the air flows into the engine during use, the engine comprising a device for protecting the air inlet against birds.
  • the object of the present invention is to provide a device which protects the engines against birds but on the other hand does not have the drawback of impairing the performance of the engines to an unacceptable degree.
  • the protection according to the present invention is characterized in that the engine according to the present invention comprises a device with elements which can move between a first, inactive position, in which the air inlet is substantially open, and a second, active position, in which elements form a protection in front of the inlet opening.
  • the advantage of this device compared to the known devices is that the protection may optionally be used or unused. If the protection is not required, for example because the aircraft is flying at a great height, the protection can be folded away.
  • the protective elements it is preferable for them to be attached at one end to a positioning device which is able to move the elements between the active and inactive positions. It has proved advantageous for the elements to be shaped in such a way that, by being rotated at their fixed end, they can be moved between the active and inactive positions.
  • the forks can be actuated by pins which are connected to an actuating body. In this way, a plurality of elements can be moved simultaneously and in a simple way.
  • the elements are shaped as substantially elongate, curved, aerodynamically shaped bars, which will be referred to in the present invention as whalebones.
  • the positioning device To make the device as robust as possible and to prevent components of this device entering the engine, for example as a result of an installation or construction fault, it is preferable for substantially all the components of the positioning device to be positively locked together. This means that the movement of most of the components is limited since they are enclosed by the shape of other components. It is preferable for the elements to be spring-mounted and/or themselves to be highly resilient. This makes it possible to prevent the impact of a collision from damaging the elements and also the positioning devices themselves excessively.
  • the device and/or the elements prefferably be provided with a detection device for detecting collision between an object and the guard device.
  • the elements, in the active position extend substantially radially with respect to the shaft of the engine.
  • the elements, in the inactive position it is preferable for the elements, in the inactive position, to extend substantially tangentially with respect to the shaft of the engine. It may be desirable for the elements, in the inactive position, also to extend substantially parallel to the circumference of the engine.
  • the actuating body extends substantially in a plane, which is at right angles to the shaft of the engine, parallel to the circumference of the said engine. This ensures that all the elements can be moved simultaneously by means of one actuating body. This limits the number of components required for the protective device.
  • the positioning device prefferably be situated substantially in the front edge of the engine.
  • the front edge means that part of the outer wall which adjoins the front side of the said engine.
  • the elements, in the inactive position it is advantageous for the elements, in the inactive position, to drop into a recess in the front edge. It may be expedient for the elements to be covered in the inactive position, in order to improve the aerodynamics still further.
  • the elements, in the active position to form a point extending forwards from the engine.
  • the birds will tend to graze past the protection, with the result that the forces on the elements are reduced.
  • This also has the advantage that it will be less easy for the birds to stick to the protection, with the result that there is less obstruction to the incoming flow of air. If the point is made to extend forwards from the front edge and substantially adjoin the outer wall of the engine, there is an increased likelihood of the bird sliding off the protection.
  • the positioning device can be controlled from the cabin of the aircraft by means of a communications system. Since it is safer, following a collision with a bird, for the protection where the collision has taken place not to be folded away, it is preferable for the device for detecting collisions to emit a signal to an indicator in the cabin of the aircraft.
  • Figure 1 shows an aircraft which is provided with engines having the protection
  • Figure 2 shows a front view of an engine from Figure 1
  • Figure 3 shows a partially cut-away side view of this engine
  • Figure 4 shows an enlarged view of the positioning device.
  • Figure 1 shows an aircraft 1 , which is provided with engines 2 according to the present invention.
  • the protection 4 extends across the entire air inlet, so that it is impossible for any birds 4 to fly into the engines during take-off and landing.
  • the protection can be folded away.
  • Figure 2 shows a front view of one of the engines 2, in which the protective device 4 is once again covering the entire inlet opening.
  • the shape and position of the whalebones is selected in such a way that a grate is formed which blocks birds of a defined minimum size.
  • the device 3 comprises curved whalebones 5 which extend substantially radially outwards in the drawing.
  • the whalebones 3 are of different lengths, so that they do not get in the way of one another in the centre. It can also be seen that whalebones 3 of equal lengths would unnecessarily block the flow of air in the centre, since the protection as in the embodiment shown is already sufficiently fine-meshed.
  • the embodiment shown is particularly suitable for engines which are circular in cross section.
  • engines with a different cross section it may be desirable to use a design specifically for that shape.
  • Figure 3 shows how the whalebones 3 are connected to the engine via the positioning devices 5, see also Figure 4.
  • the positoning device 5 is accommodated in a recess 6 in the front edge 7 of the engine. Since the whalebones, in the inactive position, are likewise accommodated in the recess 6, the geometry of the engine, and therefore its aerodynamic properties, are not affected. By rotating the whalebones about the axis of rotation R, they can be rotated out of their radial position shown into a substantially tangential position. If the recess 6 is closed successfully, the entire protective device has no adverse effect on the general aerodynamic properties of the engine 2. As shown in Figure 4, the whalebones 3 are mounted by means of a rotary element 8, in order to enable rotation from the substantially radial position shown in Figure 2 into a tangential position.
  • the whalebones are provided with a fork 9 which engages on a pin 10 which is attached to an actuating body 11.
  • the actuating body may, for example, be an annular body which coordinates the movement of all the whalebones, so that they can be moved simultaneously.
  • the spring element 12 is provided in order to absorb the impact of a collision with a bird, so that the load imposed on the whalebones 3 is reduced.
  • the positioning device 6 does not comprise any loose components and that all the components are positively locked together. This has the advantage that the device requires less maintenance and that components will not easily become detached in the event of assembly or construction faults.
  • the whalebones 3 are curved, in the folded-in position they substantially follow the contour of the outer wall of the engine 2, with the result that they can be accommodated in the recess 6.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Catching Or Destruction (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne un réacteur (2) d'avion muni sur sa partie frontale d'un orifice d'entrée d'air à travers lequel l'air pénètre dans le réacteur lors de son fonctionnement. Le réacteur comporte un dispositif (4) qui protège l'orifice d'entrée d'air et qui comporte des éléments qui peuvent être déplacés entre une première position inactive dans laquelle l'orifice d'entrée d'air est sensiblement ouverte et une seconde position active, dans laquelle les éléments (4) forment une protection devant l'orifice d'entrée d'air. D'autre part, les éléments peuvent être attachés à une extrémité à un dispositif de positionnement qui peut déplacer les éléments d'une position à l'autre.
EP00952073A 1999-08-13 2000-08-11 Dispositif de protection pour l'orifice d'entree d'air d'un reacteur d'avion Withdrawn EP1206383A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
NL1012824 1999-08-13
NL1012824A NL1012824C2 (nl) 1999-08-13 1999-08-13 Vliegtuigmotor voorzien van een inrichting voor het afschermen van een luchtinlaat van die vliegtuigmotor en een samenstel van een dergelijke motor en een vliegtuig.
PCT/NL2000/000563 WO2001012506A1 (fr) 1999-08-13 2000-08-11 Dispositif de protection pour l'orifice d'entree d'air d'un reacteur d'avion

Publications (1)

Publication Number Publication Date
EP1206383A1 true EP1206383A1 (fr) 2002-05-22

Family

ID=19769734

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00952073A Withdrawn EP1206383A1 (fr) 1999-08-13 2000-08-11 Dispositif de protection pour l'orifice d'entree d'air d'un reacteur d'avion

Country Status (4)

Country Link
EP (1) EP1206383A1 (fr)
AU (1) AU6483400A (fr)
NL (1) NL1012824C2 (fr)
WO (1) WO2001012506A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002029224A1 (fr) * 2000-10-05 2002-04-11 Calyx Limited Protection d'entree d'air pour moteur
US7871455B1 (en) 2009-06-19 2011-01-18 Vintage Capital Group, Llc Jet engine protection system
RU187080U1 (ru) * 2018-05-03 2019-02-18 Публичное акционерное общество "Авиационная холдинговая компания "Сухой" Защитное устройство воздухозаборника

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2704136A (en) * 1951-06-05 1955-03-15 Armstrong Siddeley Motors Ltd Retractable debris guard
US2709499A (en) * 1952-03-12 1955-05-31 Bristol Aeroplane Co Ltd Air-intakes, more particularly for aircraft
GB1272938A (en) * 1968-09-26 1972-05-03 Rolls Royce Improvements in or relating to retractable guards for air intakes of gas turbine engines
FR2344445A1 (fr) * 1976-03-16 1977-10-14 Linderoth Hans Deflecteur de protection pour moteur a reaction
US4726183A (en) * 1986-01-24 1988-02-23 Innerspace Corporation Self retracting screens for turbomachinery

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO0112506A1 *

Also Published As

Publication number Publication date
NL1012824C2 (nl) 2001-02-14
WO2001012506A1 (fr) 2001-02-22
AU6483400A (en) 2001-03-13

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