WO2022123100A1 - Protective device for aeroplane engines - Google Patents

Protective device for aeroplane engines Download PDF

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Publication number
WO2022123100A1
WO2022123100A1 PCT/ES2021/070878 ES2021070878W WO2022123100A1 WO 2022123100 A1 WO2022123100 A1 WO 2022123100A1 ES 2021070878 W ES2021070878 W ES 2021070878W WO 2022123100 A1 WO2022123100 A1 WO 2022123100A1
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WO
WIPO (PCT)
Prior art keywords
protective device
aircraft engines
turbine
rods
engine
Prior art date
Application number
PCT/ES2021/070878
Other languages
Spanish (es)
French (fr)
Inventor
Ubaldo CALDERÓN DEL BARRIO
Original Assignee
Calderon Del Barrio Ubaldo
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 Calderon Del Barrio Ubaldo filed Critical Calderon Del Barrio Ubaldo
Publication of WO2022123100A1 publication Critical patent/WO2022123100A1/en

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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
    • 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
    • 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
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • 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

Definitions

  • the invention refers to a protective device for aircraft engines that provides, to the function for which it is intended, advantages and characteristics, which are described in detail later.
  • the object of the present invention lies in a protective device that, specifically designed for its application in aircraft engines, has the purpose of preventing the entry of birds, or other foreign objects, into the turbine thereof, for which it is configured, essentially, from a metallic structure of rods in the form of a grid that can be coupled in front of the turbine and that, preferably, comprises a central reinforcing surface that is painted red and arranged inclined in a slightly oblique plane with respect to the frontal plane of the turbine .
  • the field of application of the present invention falls within the aeronautical industry sector, focusing particularly on the field of manufacturing apparatus, devices and protection systems.
  • the objective of the present invention is, therefore, to provide an alternative or supplementary solution that makes it possible to prevent said birds from entering the engines both in the vicinity of airports and during the entire flight path.
  • the protective device for aircraft engines that the invention proposes is configured as the ideal solution for the aforementioned objective, the characterizing details that make it possible and that conveniently distinguish it being collected in the final claims that accompany this description.
  • a protective device specifically designed to be incorporated into aircraft engines in order to prevent the entry of birds, or other foreign objects, into their turbine, which is essentially configured from a metallic structure of rods in the form of a mesh that can be attached in front of the engine turbine so that if a bird gets in the plane's path and is sucked in by the turbine, said structure will prevent its entry into the turbine.
  • said structure of rods preferably steel rods, comprises a central piece, also made of steel, which defines a flat surface that is inclined downwards, in an oblique plane with respect to the frontal plane of the turbine. , which, in addition to providing greater resistance to the structure, when a bird hits it will be thrown towards the bottom of the plane.
  • the rod structure is formed by a plurality of radial rods that define a cone-shaped body whose circular base fits into the circular mouth of the motor, the apex emerging frontally from it. of said cone with the central flat surface inclined downwards.
  • said inclined central surface which preferably also has a series of holes, is painted red, to make it more visible and, mainly, to prevent birds from approaching the aircraft.
  • Figure number 1 Shows a schematic perspective view of an embodiment of the protective device object of the invention, shown once incorporated into the engine of an aircraft, showing its configuration and layout; and figure number 2.- Shows a schematic side elevational view of the motor with the built-in protective device, especially showing the inclined arrangement of the central surface that the structure of the device has.
  • the protection device (1) of the invention applicable for its incorporation in an aircraft turbine engine (2) (3) in order to prevent the entry of birds, or other objects strangers, inside it, is configured, essentially, from a metallic structure of rods (4) in the form of a grid that can be coupled in front of the engine turbine (2) in such a way that it covers the mouth of the engine, preventing the passage towards the inside of birds or other objects that may be sucked into the turbine.
  • said structure of rods (4) also comprises a central reinforcement piece (5) that defines a flat surface that is inclined downwards, in an oblique plane with respect to the frontal plane of the engine turbine (2) in which the install the device (1), as shown in figure 2.
  • the structure of rods (4) is formed by a plurality of straight rods arranged radially in such a way that they define a body in the form of a truncated cone whose circular base (4a) fits into the circular mouth of the motor (2) and the cusp (4b) emerges frontally to it with the flat surface of the central piece (5) inclined downwards.
  • the front or external surface of the inclined central part (5) which is preferably a grid provided with holes, is preferably painted red.
  • the structure of rods (4) defines a circular base (4a) that includes a metal frame (6) that reinforces it and fixes it integrally, for example by welding or screwing, to the mouth of the motor ( 2), so that the assembly is strong enough to withstand the forces to which it will be subjected in flight.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Catching Or Destruction (AREA)

Abstract

Disclosed is a protective device for aeroplane engines that prevents birds and other foreign objects from entering the engines. The device comprises a metal rod structure in the form of a grille that covers the opening of the engine air intake. Preferably, the structure comprises a central reinforcement piece that defines a flat surface sloping downwards with respect to the front plane of the intake opening. Preferably the structure is formed by a plurality of straight, radially disposed rods, defining a frustoconical body having a circular base that fits into the circular opening of the engine, the apex emerging from the front thereof with the flat surface of the central piece sloping downwards.

Description

DISPOSITIVO PROTECTOR PARA MOTORES DE AVIÓN PROTECTIVE DEVICE FOR AIRCRAFT ENGINES
MEMORIA DESCRIPTIVA DESCRIPTIVE MEMORY
OBJETO DE LA INVENCIÓN OBJECT OF THE INVENTION
La invención, tal como expresa el enunciado de la presente memoria descriptiva, se refiere a un dispositivo protector para motores de avión que aporta, a la función a que se destina, ventajas y características, que se describen en detalle más adelante. The invention, as expressed in the title of this specification, refers to a protective device for aircraft engines that provides, to the function for which it is intended, advantages and characteristics, which are described in detail later.
El objeto de la presente invención recae en un dispositivo protector que, específicamente diseñado para su aplicación en motores de avión, tiene como finalidad evitar la entrada de pájaros, u otros objetos extraños, en la turbina de los mismos, para lo cual se configura, esencialmente, a partir de una estructura metálica de varillas en forma de rejilla acoplable frente a la turbina y que, preferiblemente, comprende una superficie central de refuerzo que está pintada de rojo y dispuesta inclinada en un plano ligeramente oblicuo respecto del plano frontal de la turbina. The object of the present invention lies in a protective device that, specifically designed for its application in aircraft engines, has the purpose of preventing the entry of birds, or other foreign objects, into the turbine thereof, for which it is configured, essentially, from a metallic structure of rods in the form of a grid that can be coupled in front of the turbine and that, preferably, comprises a central reinforcing surface that is painted red and arranged inclined in a slightly oblique plane with respect to the frontal plane of the turbine .
CAMPO DE APLICACIÓN DE LA INVENCIÓN FIELD OF APPLICATION OF THE INVENTION
El campo de aplicación de la presente invención se enmarca dentro del sector de la industria aeronáutica, centrándose particularmente en el ámbito de la fabricación de aparatos, dispositivos y sistemas de protección. The field of application of the present invention falls within the aeronautical industry sector, focusing particularly on the field of manufacturing apparatus, devices and protection systems.
ANTECEDENTES DE LA INVENCIÓN BACKGROUND OF THE INVENTION
Es conocido que los pájaros suponen un problema en el ámbito de la aeronáutica, ya que si se interponen en la trayectoria de los aviones, normalmente en el despegue o aterrizaje, pero también en pleno vuelo, son succionados por la fuerza de la turbina de los motores, causando a menudo problemas que pueden llevar a riesgos importantes para dichos aviones. It is known that birds pose a problem in the field of aeronautics, since if they get in the way of aircraft, usually during takeoff or landing, but also in mid-flight, they are sucked in by the force of the engine turbine, often causing problems that can lead to significant risks for these planes.
Actualmente, para solventar este problema, únicamente se recurre a medios para evitar que las aves sobrevuelen las zonas cercanas a los aeropuertos, por ejemplo mediante la utilización de halcones o drones que controlan las poblaciones de aves cercanas. Currently, to solve this problem, only means are used to prevent birds from flying over areas near airports, for example through the use of falcons or drones that control nearby bird populations.
El objetivo de la presente invención es, pues, proporcionar una solución alternativa o suplementaria que permita evitar dicha entrada de pájaros en los motores tanto en las proximidades de los aeropuertos como durante todo el trayecto de vuelo. The objective of the present invention is, therefore, to provide an alternative or supplementary solution that makes it possible to prevent said birds from entering the engines both in the vicinity of airports and during the entire flight path.
Por otra parte, y como referencia al estado actual de la técnica, cabe señalar que, al menos por parte del solicitante, se desconoce la existencia de ningún otro dispositivo protector, ni ninguna otra invención de aplicación similar, que presente unas características técnicas y estructurales iguales o semejantes a las que presenta el que aquí se reivindica. On the other hand, and as a reference to the current state of the art, it should be noted that, at least by the applicant, the existence of any other protective device, or any other invention of similar application, that has technical and structural characteristics is unknown. equal or similar to those presented by the one claimed here.
EXPLICACIÓN DE LA INVENCIÓN EXPLANATION OF THE INVENTION
El dispositivo protector para motores de avión que la invención propone se configura como la solución idónea al objetivo anteriormente señalado, estando los detalles caracterizadores que lo hacen posible y que lo distinguen convenientemente recogidos en las reivindicaciones finales que acompañan a la presente descripción. The protective device for aircraft engines that the invention proposes is configured as the ideal solution for the aforementioned objective, the characterizing details that make it possible and that conveniently distinguish it being collected in the final claims that accompany this description.
Concretamente, lo que la invención propone, como se ha apuntado anteriormente, es un dispositivo protector específicamente diseñado para su incorporación en motores de avión con la finalidad de evitar la entrada de pájaros, u otros objetos extraños, en la turbina de los mismos, el cual se configura, esencialmente, a partir de una estructura metálica de varillas en forma de rejilla acoplable frente a la turbina del motor de manera que si algún pájaro se sitúa en la trayectoria del avión y es succionado por la turbina, dicha estructura impedirá su entrada hacia el interior de la misma. Specifically, what the invention proposes, as has been pointed out above, is a protective device specifically designed to be incorporated into aircraft engines in order to prevent the entry of birds, or other foreign objects, into their turbine, which is essentially configured from a metallic structure of rods in the form of a mesh that can be attached in front of the engine turbine so that if a bird gets in the plane's path and is sucked in by the turbine, said structure will prevent its entry into the turbine.
Además, en la realización preferida, dicha estructura de varillas, preferentemente de varillas de acero, comprende una pieza central, también metálica de acero, que define una superficie plana que queda inclinada hacia abajo, en un plano oblicuo respecto del plano frontal de la turbina, la cual, además de proporcionar una mayor resistencia a la estructura, al impactar un pájaro sobre la misma se verá despedido hacia la parte inferior del avión. In addition, in the preferred embodiment, said structure of rods, preferably steel rods, comprises a central piece, also made of steel, which defines a flat surface that is inclined downwards, in an oblique plane with respect to the frontal plane of the turbine. , which, in addition to providing greater resistance to the structure, when a bird hits it will be thrown towards the bottom of the plane.
Por su parte, en el modo de realización preferido, la estructura de varillas está formada por una pluralidad de varillas radiales que define un cuerpo en forma de ronco de cono cuya base circular encaja en la boca circular del motor emergiendo frontalmente de la misma la cúspide de dicho cono con la superficie plana central inclinada hacia abajo. For its part, in the preferred embodiment, the rod structure is formed by a plurality of radial rods that define a cone-shaped body whose circular base fits into the circular mouth of the motor, the apex emerging frontally from it. of said cone with the central flat surface inclined downwards.
Por último, cabe señalar que, preferentemente, dicha superficie central inclinada, que preferentemente también presenta una serie de orificios, está pintada de rojo, para hacerla más visible y, principalmente, para evitar que las aves se acerquen al avión. Finally, it should be noted that, preferably, said inclined central surface, which preferably also has a series of holes, is painted red, to make it more visible and, mainly, to prevent birds from approaching the aircraft.
DESCRIPCIÓN DE LOS DIBUJOS DESCRIPTION OF THE DRAWINGS
Para complementar la descripción que se está realizando y con objeto de ayudar a una mejor comprensión de las características de la invención, se acompaña a la presente memoria descriptiva, como parte integrante de la misma, un plano en el que con carácter ilustrativo y no limitativo se ha representado lo siguiente: To complement the description that is being made and in order to To help a better understanding of the characteristics of the invention, a drawing is attached to this specification, as an integral part thereof, in which the following has been represented by way of illustration and not limitation:
La figura número 1 .- Muestra una vista esquemática en perspectiva de un ejemplo de realización del dispositivo protector objeto de la invención, representado una vez incorporado al motor de un avión, apreciándose la configuración y disposición del mismo; y la figura número 2.- Muestra una vista esquemática en alzado lateral del motor con el dispositivo protector incorporado, apreciándose especialmente la disposición inclinada de la superficie central con que cuenta la estructura del dispositivo. Figure number 1.- Shows a schematic perspective view of an embodiment of the protective device object of the invention, shown once incorporated into the engine of an aircraft, showing its configuration and layout; and figure number 2.- Shows a schematic side elevational view of the motor with the built-in protective device, especially showing the inclined arrangement of the central surface that the structure of the device has.
REALIZACIÓN PREFERENTE DE LA INVENCIÓN PREFERRED EMBODIMENT OF THE INVENTION
A la vista de las mencionadas figuras, y de acuerdo con la numeración adoptada, se puede observar en ellas un ejemplo de realización no limitativa del dispositivo protector para motores de avión de la invención, el cual comprende lo que se describe en detalle a continuación. In view of the aforementioned figures, and in accordance with the adopted numbering, a non-limiting example of embodiment of the protective device for aircraft engines of the invention can be seen, which includes what is described in detail below.
Así, tal como se observa en dichas figuras, el dispositivo (1) de protección de la invención, aplicable para su incorporación en un motor (2) de turbina de avión (3) con la finalidad evitar la entrada de pájaros, u otros objetos extraños, en el interior del mismo, se configura, esencialmente, a partir de una estructura metálica de varillas (4) en forma de rejilla acopladle frente a la turbina del motor (2) de manera que cubre la boca del mismo impidiendo el paso hacia el interior de los pájaros u otros objetos que puedan verse succionados por la turbina. Preferentemente, dicha estructura de varillas (4) comprende además una pieza central (5) de refuerzo que define una superficie plana que queda inclinada hacia abajo, en un plano oblicuo respecto del plano frontal de la turbina del motor (2) en el que se instala el dispositivo (1), tal como se aprecia en la figura 2. Thus, as can be seen in said figures, the protection device (1) of the invention, applicable for its incorporation in an aircraft turbine engine (2) (3) in order to prevent the entry of birds, or other objects strangers, inside it, is configured, essentially, from a metallic structure of rods (4) in the form of a grid that can be coupled in front of the engine turbine (2) in such a way that it covers the mouth of the engine, preventing the passage towards the inside of birds or other objects that may be sucked into the turbine. Preferably, said structure of rods (4) also comprises a central reinforcement piece (5) that defines a flat surface that is inclined downwards, in an oblique plane with respect to the frontal plane of the engine turbine (2) in which the install the device (1), as shown in figure 2.
Preferentemente, la estructura de varillas (4) está formada por una pluralidad de varillas rectas dispuestas radialmente de tal modo que definen un cuerpo en forma de tronco de cono cuya base circular (4a) encaja en la boca circular del motor (2) y la cúspide (4b) emerge frontalmente a la misma con la superficie plana de la pieza central (5) inclinada hacia abajo. Preferably, the structure of rods (4) is formed by a plurality of straight rods arranged radially in such a way that they define a body in the form of a truncated cone whose circular base (4a) fits into the circular mouth of the motor (2) and the cusp (4b) emerges frontally to it with the flat surface of the central piece (5) inclined downwards.
Preferentemente, la superficie anterior o externa de la pieza central (5) inclinada, que preferentemente es una rejilla dotada de orificios, está pintada, de preferencia, de color rojo. Preferably, the front or external surface of the inclined central part (5), which is preferably a grid provided with holes, is preferably painted red.
Preferentemente también, en todo caso, la estructura de varillas (4) define una base circular (4a) que comprende un cerco metálico (6) que la refuerza y la fija solidariamente, por ejemplo mediante soldadura o atornillado, a la embocadura del motor (2), de modo que el conjunto sea suficientemente resistente como para soportar las fuerzas a que se verá sometido en situación de vuelo. Also preferably, in any case, the structure of rods (4) defines a circular base (4a) that includes a metal frame (6) that reinforces it and fixes it integrally, for example by welding or screwing, to the mouth of the motor ( 2), so that the assembly is strong enough to withstand the forces to which it will be subjected in flight.
Descrita suficientemente la naturaleza de la presente invención, así como la manera de ponerla en práctica, no se considera necesario hacer más extensa su explicación para que cualquier experto en la materia comprenda su alcance y las ventajas que de ella se derivan. Having sufficiently described the nature of the present invention, as well as the way of putting it into practice, it is not considered necessary to make its explanation more extensive so that any person skilled in the art understands its scope and the advantages derived from it.

Claims

R E I V I N D I C A C I O N E S
1.- Dispositivo protector para motores de avión que, aplicable para su incorporación en un motor (2) de turbina de avión (3) con la finalidad evitar la entrada de pájaros, u otros objetos extraños, en el interior del mismo, está caracterizado por comprender una estructura metálica de varillas (4) en forma de rejilla acoplable frente a la turbina del motor (2) de modo que cubre la boca del mismo e impide el paso hacia el interior de los pájaros u otros objetos que puedan verse succionados por la turbina. 1.- Protective device for aircraft engines that, applicable for incorporation into an aircraft turbine engine (2) (3) in order to prevent the entry of birds, or other foreign objects, inside it, is characterized for comprising a metal structure of rods (4) in the form of a mesh that can be attached to the engine turbine (2) so that it covers its mouth and prevents birds or other objects that may be sucked in from entering. the turbine.
2.- Dispositivo protector para motores de avión, según la reivindicación 1 , caracterizado porque la estructura de varillas (4) comprende una pieza central (5) de refuerzo que define una superficie plana que queda inclinada hacia abajo, en un plano oblicuo respecto del plano frontal de la turbina del motor (2) en que se instala el dispositivo (1). 2. Protective device for aircraft engines, according to claim 1, characterized in that the rod structure (4) comprises a central piece (5) of reinforcement that defines a flat surface that is inclined downwards, in an oblique plane with respect to the front plane of the engine turbine (2) in which the device (1) is installed.
3.- Dispositivo protector para motores de avión, según las reivindicaciones 1 ó 2, caracterizado porque la estructura de varillas (4) está formada por una pluralidad de varillas rectas dispuestas radialmente de modo que definen un cuerpo en forma de tronco de cono cuya base circular (4a) encaja en la boca circular del motor (2) y la cúspide (4b) emerge frontalmente a la misma con la superficie plana de la pieza central (5) inclinada hacia abajo. 3. Protective device for aircraft engines, according to claims 1 or 2, characterized in that the rod structure (4) is formed by a plurality of straight rods arranged radially so as to define a body in the form of a truncated cone whose base circular (4a) fits in the circular mouth of the motor (2) and the cusp (4b) emerges frontally to it with the flat surface of the central piece (5) inclined downwards.
4.- Dispositivo protector para motores de avión, según la reivindicación 2 ó 3, caracterizado porque la pieza central (5) inclinada es una rejilla dotada de múltiples orificios. 4. Protective device for aircraft engines, according to claim 2 or 3, characterized in that the inclined central part (5) is a grid provided with multiple holes.
5.- Dispositivo protector para motores de avión, según cualquiera de las reivindicaciones 2 a 4, caracterizado porque la superficie anterior o extema de la pieza central (5) inclinada está preferentemente pintada de color rojo. 5. Protective device for aircraft engines, according to any of claims 2 to 4, characterized in that the anterior or external surface of the inclined central piece (5) is preferably painted red.
6.- Dispositivo protector para motores de avión, según cualquiera de las reivindicaciones 1 a 3, caracterizado porque la estructura de varillas (4) define una base circular (4a) que comprende un cerco metálico (6) que la refuerza y la fija solidariamente a la embocadura del motor (2). 6. Protective device for aircraft engines, according to any of claims 1 to 3, characterized in that the structure of rods (4) defines a circular base (4a) that comprises a metal frame (6) that reinforces and fixes it integrally to the motor mouth (2).
PCT/ES2021/070878 2020-12-10 2021-12-10 Protective device for aeroplane engines WO2022123100A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ES202032665U ES1262674Y (en) 2020-12-10 2020-12-10 PROTECTIVE DEVICE FOR AIRCRAFT ENGINES
ESU202032665 2020-12-10

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WO2022123100A1 true WO2022123100A1 (en) 2022-06-16

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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3196598A (en) * 1962-10-31 1965-07-27 Walter T Olson Inlet deflector for jet engines
US4149689A (en) * 1976-08-18 1979-04-17 Mcdonald John Protective screen for jet-engine intake
US5411224A (en) * 1993-04-08 1995-05-02 Dearman; Raymond M. Guard for jet engine
JPH11301595A (en) * 1998-04-22 1999-11-02 Kazuo Ariyoshi Cover protector of jet engine for airplane
CN201367945Y (en) * 2009-03-16 2009-12-23 左学禹 Jet engine protecting cover
US20100270427A1 (en) * 2009-04-27 2010-10-28 Barrientos Ernesto D Bird collision prevention device for an aircraft
US20130000271A1 (en) * 2011-06-29 2013-01-03 Farr Sonei Engine shield
KR20140049996A (en) * 2014-04-01 2014-04-28 최일호 Airplane engine a guard net

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3196598A (en) * 1962-10-31 1965-07-27 Walter T Olson Inlet deflector for jet engines
US4149689A (en) * 1976-08-18 1979-04-17 Mcdonald John Protective screen for jet-engine intake
US5411224A (en) * 1993-04-08 1995-05-02 Dearman; Raymond M. Guard for jet engine
JPH11301595A (en) * 1998-04-22 1999-11-02 Kazuo Ariyoshi Cover protector of jet engine for airplane
CN201367945Y (en) * 2009-03-16 2009-12-23 左学禹 Jet engine protecting cover
US20100270427A1 (en) * 2009-04-27 2010-10-28 Barrientos Ernesto D Bird collision prevention device for an aircraft
US20130000271A1 (en) * 2011-06-29 2013-01-03 Farr Sonei Engine shield
KR20140049996A (en) * 2014-04-01 2014-04-28 최일호 Airplane engine a guard net

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ES1262674Y (en) 2021-06-04

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