WO2015166113A1 - Sealing device for aircraft propeller engine - Google Patents

Sealing device for aircraft propeller engine Download PDF

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Publication number
WO2015166113A1
WO2015166113A1 PCT/ES2014/070372 ES2014070372W WO2015166113A1 WO 2015166113 A1 WO2015166113 A1 WO 2015166113A1 ES 2014070372 W ES2014070372 W ES 2014070372W WO 2015166113 A1 WO2015166113 A1 WO 2015166113A1
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WO
WIPO (PCT)
Prior art keywords
engine
propeller
ring
activating mechanism
aircraft
Prior art date
Application number
PCT/ES2014/070372
Other languages
Spanish (es)
French (fr)
Inventor
Arturo Turrillas Las Heras
Original Assignee
Wake Engineering, S.L.
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 Wake Engineering, S.L. filed Critical Wake Engineering, S.L.
Priority to PCT/ES2014/070372 priority Critical patent/WO2015166113A1/en
Publication of WO2015166113A1 publication Critical patent/WO2015166113A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C35/00—Flying-boats; Seaplanes

Definitions

  • the present invention is encompassed in the field of aircraft construction. Specifically with aircraft suitable for carrying out grounding maneuvers, that is, airplanes capable of hydroplaning and / or floating on the surface of the water.
  • Said invention relates to a sealing device for the propeller motor, which is actuated during the grounding maneuvers to prevent water from entering the engine compartment, as well as, propitiating the engine to stop, avoiding damage to the propeller. for possible impacts against water.
  • the invention is especially designed for aircraft of the UAV type (Unmanned Aerial Vehicles), airplanes and light aircraft, such as ultralight and general or sport aircraft, although their application can be extended to any type of aircraft suitable, either, for commercial or transportation purposes.
  • UAV Unmanned Aerial Vehicles
  • airplanes and light aircraft such as ultralight and general or sport aircraft, although their application can be extended to any type of aircraft suitable, either, for commercial or transportation purposes.
  • patent document WO 2012/175756 published on December 27, 2012, the which, discloses an aircraft landing device comprising at least one inflatable and folding chamber, at least one landing pad attached to the aircraft by means of the inflatable chamber, and at least one air intake connected to the chamber.
  • the air intake allows the entry of incident air into the chamber to inflate and deploy the chamber by extending the skate from a retracted skate position to an extended skate position, in which the device is ready for landing.
  • the present invention is charac ⁇ terizada established and in the independent claims, mien ⁇ after the dependent claims describe other characteristics of the same.
  • the present invention relates to a sealing device for a propeller aeronautical engine.
  • the device operates in a bounded space between a propeller and an engine fuselage, comprising an O-ring coupled to the end of an activating mechanism. Both the O-ring and the activating mechanism are arranged coaxially with respect to a motor rotor.
  • the activating mechanism moves the o-ring from a retracted seal position, in which the propeller-rotor assembly of the motor can freely rotate, towards an extended seal position, on which the O-ring rests against a plate of the cone of the propeller, causing the hermetic closing of the space between the propeller and the fuselage of the engine, as well as, the stop of the engine.
  • the present invention it is possible to prevent the entry of water into the engine compartment during the landing operations of the aircraft, as well as, subsequently, when said aircraft is floating on the surface of the water.
  • the engine stops, which prevents damage to the propeller caused by the impacts against water, the latter, generated during the landing operation.
  • Figure 1 represents a sectioned view of the aircraft engine including the sealing device, shown in a first position that allows the propeller-rotor assembly of the engine to be freely rotated.
  • Figure 2 represents a sectioned view of the aircraft engine including the sealing device of Figure 1, shown in a second position that closes the space between the propeller and the fuselage of the engine, as well as, promotes the arrest of the latter.
  • the present invention is a sealing device for an aeronautical propeller engine.
  • the device accio ⁇ na in a space (1) delimited between the propeller (2) and the fuselage (3) of the aircraft engine.
  • the embodiment shown in the figures could be an aircraft of the UAV type.
  • the device comprises an O-ring (5) coupled to the end of an activating mechanism (4).
  • the O-ring assembly (5) and activating mechanism (4) is arranged coaxially with respect to the motor shaft or rotor (6).
  • the activating mechanism (4) comprises a sleeve (4.1) in the form of a toroidal gutter, its side walls being parallel to the rotor (6) of the engine.
  • the jacket (4.1) be fixed to the inner wall of the fuselage (3) of the engine, acting as a frame of the activating mechanism (4).
  • the mechanism Tivador ac ⁇ (4) comprises a piston (4.2) with a head (4/21) which is fixed to the O - ring (5).
  • the piston (4.2) is also formed into a toroidal duct, external dimensions corresponding to the inter ⁇ nas dimensions of the toroidal channel forming shirt
  • the volume of the closed space (4.3) may vary depending on whether the piston (4.2) is moved in or out of the jacket (4.1).
  • compression rings (4.4) are arranged between side stop ⁇ des shirt (4.1) and the piston (4.2) to ensure the airtightness of the closed space (4.3).
  • the activating mechanism (4) be operated pneumatically or hydraulically. In both cases, through a connection (4.5), through which the working fluid (gas or liquid) enters the closed space (4.3), varying its volume.
  • the drive mechanism of the actuator (4) may be carried out so automa ⁇ tica, for example, linked to the activation of landing maneuvers of the aircraft.
  • the activating mechanism (4) is activated, which moves the O-ring (5) from the retracted joint position, where it was during the flight, to an extended seal position, seen in figure 2, in which the o-ring (5) is supported against the plate (2.11) of the cone (2.1) of the propeller (2), causing the tight seal of the space (1) and the engine stop.
  • the O - ring (5) remains obstructing the space (1), impi ⁇ diendo the water passage into the engine compartment to avoid damage to the latter.
  • the support of the O-ring (5) against the plate (2.11) causes the motor to stop, immobilizing the propeller (2) so that it does not suffer damage due to the impact against the water involved in the landing operations.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transmission Devices (AREA)
  • Gasket Seals (AREA)
  • Tires In General (AREA)

Abstract

The invention relates to a sealing device for an aircraft engine propeller, for use during the water landing of an aircraft. The device operates in a space between the propeller and the fuselage of the engine and comprises an O-ring coupled to an activating mechanism, the O-ring and the activating mechanism being arranged coaxially to the rotor of the engine. The activating mechanism moves the O-ring from a retracted position, in an opening in the fuselage of the engine, to an extended position, against a plate of the propeller cone, hermetically closing the space between the propeller and the fuselage of the engine, preventing water from entering the engine bay, and stopping the engine in order to protect the propeller from the impact against the water during the water landing of the aircraft.

Description

DISPOSI TIVO DE ESTANQUE IDAD PARA MOTOR AERONAUTICO DE IDAD PONDING DEVICE FOR AIRCRAFT ENGINE
HÉLICEPROPELLER
CAMPO TÉCNICO DE LA INVENCIÓN TECHNICAL FIELD OF THE INVENTION
La presente invención se engloba en el campo de la construcción de aeronaves. Específicamente con las aeronaves aptas para llevar a cabo maniobras de ameriza je, es decir, aeronaves con capacidad de hidroplanear y/o de flotar sobre la superficie del agua. The present invention is encompassed in the field of aircraft construction. Specifically with aircraft suitable for carrying out grounding maneuvers, that is, airplanes capable of hydroplaning and / or floating on the surface of the water.
Dicha invención trata de un dispositivo de es- tanqueidad para motor de hélice, el cual, es accionado durante las maniobras de amerizaje para evitar la entra da de agua al vano motor, así como, propiciar la parada del motor, evitando daños en la hélice por posibles impactos contra el agua. Said invention relates to a sealing device for the propeller motor, which is actuated during the grounding maneuvers to prevent water from entering the engine compartment, as well as, propitiating the engine to stop, avoiding damage to the propeller. for possible impacts against water.
La invención está concebida especialmente para aeronaves del tipo UAV (Vehículos Áereos No Tripulados) aeromodelos y aeronaves ligeras, tales como, ultralige- ros y avionetas de aviación general o deportiva, aunque su aplicación puede extenderse a cualquier tipo de aeronave adecuada, ya sea, con fines comerciales o transporte . The invention is especially designed for aircraft of the UAV type (Unmanned Aerial Vehicles), airplanes and light aircraft, such as ultralight and general or sport aircraft, although their application can be extended to any type of aircraft suitable, either, for commercial or transportation purposes.
ANTECEDENTES DE LA INVENCIÓN BACKGROUND OF THE INVENTION
Son conocidas diversas soluciones para dotar a las aeronaves de la posibilidad de amerizar sobre la superficie del agua. Various solutions are known to provide aircraft with the possibility to land on the surface of the water.
Por ejemplo, el documento de patente WO 2012/175756, publicado el 27 de diciembre de 2012, el cual, da a conocer un dispositivo de amerizaje para aeronave que comprende al menos una cámara inflable y plegable, al menos un patín de amerizaje acoplado a la aeronave por medio de la cámara inflable, y al menos una toma de aire conectada a la cámara. La toma de aire permite la entrada de aire incidente en la cámara para inflar y desplegar la cámara extendiendo el patín desde una posición de patín retraído hasta una posición de patín extendido, en la que el dispositivo está preparado para el amerizaje. For example, patent document WO 2012/175756, published on December 27, 2012, the which, discloses an aircraft landing device comprising at least one inflatable and folding chamber, at least one landing pad attached to the aircraft by means of the inflatable chamber, and at least one air intake connected to the chamber. The air intake allows the entry of incident air into the chamber to inflate and deploy the chamber by extending the skate from a retracted skate position to an extended skate position, in which the device is ready for landing.
La presente solución tiene el inconveniente que, durante la maniobra de amerizaje, así como, posterior¬ mente cuando la aeronave se encuentra flotando en la superficie del agua, a través del espacio existente entre la hélice y el fuselaje o carena del motor, pene¬ tra agua hacia el vano motor causando daños en éste último . Otro problema existente es que, durante la ma¬ niobra de amerizaje, la hélice puede recibir impactos con el agua que pueden producir daños en la misma, por encontrarse aun en movimiento. Por tal razón, se requiere diseñar, de forma sencilla y económica, un dispositivo de estanqueidad para motor de hélice que permita dar solución a los problemas anteriormente comentados. DESCRIPCIÓN DE LA INVENCIÓN This solution has the drawback that, during the maneuver splashdown and, subsequent ¬ when the aircraft is floating on the water surface, through the space between the propeller and the fuselage or hull engine, penis ¬ It brings water to the engine compartment causing damage to the latter. Another problem is that during the ma ¬ niobra splashdown, the propeller can receive impacts with the water can damage it, because they were still moving. For this reason, it is required to design, in a simple and economical way, a sealing device for a propeller motor that allows to solve the problems mentioned above. DESCRIPTION OF THE INVENTION
La presente invención queda establecida y carac¬ terizada en las reivindicaciones independientes, mien¬ tras que las reivindicaciones dependientes describen otras características de la misma. A la vista de lo anteriormente enunciado, la presente invención se refiere a un dispositivo de estan- queidad para motor aeronáutico de hélice. The present invention is charac ¬ terizada established and in the independent claims, mien ¬ after the dependent claims describe other characteristics of the same. In view of the foregoing, the present invention relates to a sealing device for a propeller aeronautical engine.
El dispositivo acciona en un espacio delimitado entre una hélice y un fuselaje del motor, comprendiendo una junta tórica acoplada al extremo de un mecanismo activador. Tanto la junta tórica como el mecanismo activador están dispuestos de forma coaxial con respecto a un rotor del motor. The device operates in a bounded space between a propeller and an engine fuselage, comprising an O-ring coupled to the end of an activating mechanism. Both the O-ring and the activating mechanism are arranged coaxially with respect to a motor rotor.
Donde, una vez accionado el mecanismo activador, éste traslada la junta tórica desde una posición de junta retraída, en la que puede girar libremente el conjunto hélice-rotor del motor, hacia una posición de junta extendida, en la que la junta tórica se apoya contra un plato del cono de la hélice, propiciando el cierre hermético del espacio existente entre la hélice y el fuselaje del motor, así como, la parada del motor. Where, once the activating mechanism is activated, it moves the o-ring from a retracted seal position, in which the propeller-rotor assembly of the motor can freely rotate, towards an extended seal position, on which the O-ring rests against a plate of the cone of the propeller, causing the hermetic closing of the space between the propeller and the fuselage of the engine, as well as, the stop of the engine.
Como puede verse, con la presente invención, se logra evitar la entrada de agua al vano motor durante las maniobras de amerizaje de la aeronave, así como, posteriormente, cuando dicha aeronave se encuentra flotando sobre la superficie del agua. Al mismo tiempo, se produce la parada del motor, lo que evita daños en la hélice causados por los impactos contra el agua, éstos últimos, generados durante la maniobra de amerizaje. As can be seen, with the present invention, it is possible to prevent the entry of water into the engine compartment during the landing operations of the aircraft, as well as, subsequently, when said aircraft is floating on the surface of the water. At the same time, the engine stops, which prevents damage to the propeller caused by the impacts against water, the latter, generated during the landing operation.
BREVE DESCRIPCIÓN DE LAS FIGURAS BRIEF DESCRIPTION OF THE FIGURES
Se complementa la presente memoria descriptiva, juego de figuras, ilustrativas del ejemplo prefe rente, y nunca limitativas de la invención. The present specification, set of figures, illustrative of the prefe example is complemented rent, and never limit the invention.
La figura 1 representa una vista seccionada en corte del motor de la aeronave incluyendo el dispositivo de estanqueidad, mostrado en una primera posición que permite girar libremente el conjunto hélice-rotor del motor . Figure 1 represents a sectioned view of the aircraft engine including the sealing device, shown in a first position that allows the propeller-rotor assembly of the engine to be freely rotated.
La figura 2 representa una vista seccionada en corte del motor de la aeronave incluyendo el dispositivo de estanqueidad de la figura 1, mostrado en una segunda posición que cierra el espacio existente entre la hélice y el fuselaje del motor, asi como, propicia la detención de éste último. Figure 2 represents a sectioned view of the aircraft engine including the sealing device of Figure 1, shown in a second position that closes the space between the propeller and the fuselage of the engine, as well as, promotes the arrest of the latter.
EXPOSICIÓN DE TALLADA DE LA REALIZACIÓN PREFERENTE DE LA INVENCIÓN EXHIBITION OF CARVED PREFERRED EMBODIMENTS OF THE INVENTION
La presente invención es un dispositivo de es- tanqueidad para un motor aeronáutico de hélice. The present invention is a sealing device for an aeronautical propeller engine.
Como muestran las figuras, el dispositivo accio¬ na en un espacio (1) delimitado entre la hélice (2) y el fuselaje (3) del motor de la aeronave. La realización mostrada en las figuras, por ejemplo, podría tratarse de una aeronave del tipo UAV. As the figures show, the device accio ¬ na in a space (1) delimited between the propeller (2) and the fuselage (3) of the aircraft engine. The embodiment shown in the figures, for example, could be an aircraft of the UAV type.
El dispositivo comprende una junta tórica (5) acoplada al extremo de un mecanismo activador (4) . El conjunto de junta tórica (5) y mecanismo activador (4) está dispuesto de forma coaxial con respecto al eje o rotor (6) del motor. The device comprises an O-ring (5) coupled to the end of an activating mechanism (4). The O-ring assembly (5) and activating mechanism (4) is arranged coaxially with respect to the motor shaft or rotor (6).
Preferiblemente, el mecanismo activador (4) com- prende una camisa (4.1) con forma de canaleta toroidal, siendo sus paredes laterales paralelas al rotor (6) del motor . Preferably, the activating mechanism (4) comprises a sleeve (4.1) in the form of a toroidal gutter, its side walls being parallel to the rotor (6) of the engine.
Asi mismo, se prefiere que la camisa (4.1) esté fijada a la pared interior del fuselaje (3) del motor, actuando como bastidor del mecanismo activador (4) . Por ejemplo, muy próximo a la boca (3.1) del fuselaje (3), de tal forma que, en una posición de junta retraída, vista en la figura 1, el extremo libre de la junta tórica (5) quede al menos alineado con el borde de dicha boca (3.1), granizando que, en dicha posición de junta retraída, la junta tórica (5) no impida el giro libre del conjunto hélice-rotor (2,6) del motor. Por otro lado, se prefiere que el mecanismo ac¬ tivador (4) comprenda un pistón (4.2), con una cabeza (4.21) a la cual está fijada la junta tórica (5) . Likewise, it is preferred that the jacket (4.1) be fixed to the inner wall of the fuselage (3) of the engine, acting as a frame of the activating mechanism (4). For example, very close to the mouth (3.1) of the fuselage (3), so that, in a retracted joint position, seen in Figure 1, the free end of the O-ring (5) is at least aligned with the edge of said mouth (3.1), granulating that, in said retracted joint position, the O-ring (5) does not prevent free rotation of the propeller-rotor assembly (2,6) of the motor. Furthermore, it is preferred that the mechanism Tivador ac ¬ (4) comprises a piston (4.2) with a head (4/21) which is fixed to the O - ring (5).
Preferentemente, el pistón (4.2) también está conformado en forma de canaleta toroidal, de dimensiones externas que se corresponden con las dimensiones inter¬ nas de la canaleta toroidal que conforma la camisa Preferably, the piston (4.2) is also formed into a toroidal duct, external dimensions corresponding to the inter ¬ nas dimensions of the toroidal channel forming shirt
(4.1); de tal forma que, una vez insertada una dentro de la otra, las paredes laterales del pistón (4.2) se deslicen, de forma ajustada, entre las paredes laterales de la camisa (4.1), definiéndose entre ellas un espacio cerrado (4.3) variable. En otras palabras, el volumen del espacio cerrado (4.3) puede variar según sea movido el pistón (4.2) hacia dentro o hacia fuera de la camisa (4.1) .  (4.1); such that, once inserted into each other, the side walls of the piston (4.2) slide, tightly, between the side walls of the jacket (4.1), defining a closed space (4.3) between them . In other words, the volume of the closed space (4.3) may vary depending on whether the piston (4.2) is moved in or out of the jacket (4.1).
Adicionalmente, se prefiere que entre las pare¬ des laterales de la camisa (4.1) y del pistón (4.2) estén dispuestos unos aros de compresión (4.4) que garanticen la hermeticidad del espacio cerrado (4.3) . Con vistas a aligerar el peso de la aeronave, se prefiere que el mecanismo activador (4) sea accionado neumáticamente o hidráulicamente. En ambos casos, a través de una conexión (4.5), por donde penetra el fluido de trabajo (gas o liquido) al espacio cerrado (4.3), haciendo variar su volumen. Additionally, it is preferred that between side stop ¬ des shirt (4.1) and the piston (4.2) are arranged compression rings (4.4) to ensure the airtightness of the closed space (4.3). With a view to lightening the weight of the aircraft, it is preferred that the activating mechanism (4) be operated pneumatically or hydraulically. In both cases, through a connection (4.5), through which the working fluid (gas or liquid) enters the closed space (4.3), varying its volume.
Sin embargo, cualquier otro sistema de accióna¬ miento mecánico o eléctrico conocido, o combinación de ellos, pudiera preverse, siempre que logre accionar la junta tórica (5) cuando se requiera. However, any other system actuates mechanical or electrical ¬ known, or combination thereof lie, could be envisaged, provided that achieves actuate the O - ring (5) when required.
Por otro lado, el accionamiento del mecanismo activador (4) podría ser llevado a cabo de forma automᬠtica, por ejemplo, vinculado a la activación de las maniobras de amerizaje de la aeronave. Furthermore, the drive mechanism of the actuator (4) may be carried out so automa ¬ tica, for example, linked to the activation of landing maneuvers of the aircraft.
En cualquier caso, cuando las maniobras de ame- rizaje sean llevadas a cabo, el mecanismo activador (4) es accionado, el cual, traslada la junta tórica (5) desde la posición de junta retraída, donde se encontraba durante el vuelo, hacia una posición de junta extendida, vista en la figura 2, en la que la junta tórica (5) se apoya contra el plato (2.11) del cono (2.1) de la hélice (2), propiciando el cierre hermético del espacio (1) y la parada del motor. In any case, when the maneuvering maneuvers are carried out, the activating mechanism (4) is activated, which moves the O-ring (5) from the retracted joint position, where it was during the flight, to an extended seal position, seen in figure 2, in which the o-ring (5) is supported against the plate (2.11) of the cone (2.1) of the propeller (2), causing the tight seal of the space (1) and the engine stop.
De esta forma, durante la maniobra de amerizaje, así como, posteriormente mientras la aeronave se encuen¬ tre flotando sobre la superficie del agua, la junta tórica (5) permanece obstruyendo el espacio (1), impi¬ diendo el paso del agua hacia el vano motor para evitar daños a éste último. Paralelamente, el apoyo de la junta tórica (5) contra el plato (2.11) hace que el motor se detenga, inmovilizando la hélice (2) para que ésta no sufra daños por el impacto contra el agua que presuponen las maniobras de amerizaje. Thus, during the maneuver splashdown and then while the aircraft encuen ¬ tre floating on the water surface, the O - ring (5) remains obstructing the space (1), impi ¬ diendo the water passage into the engine compartment to avoid damage to the latter. In parallel, the support of the O-ring (5) against the plate (2.11) causes the motor to stop, immobilizing the propeller (2) so that it does not suffer damage due to the impact against the water involved in the landing operations.

Claims

REIVINDICACIONES
1. -Dispositivo de estanqueidad para motor aeronáuti¬ co de hélice, que acciona en un espacio (1) delimitado entre una hélice (2) y un fuselaje (3) del motor, carac- terizado por comprender una junta tórica (5) acoplada al extremo de un mecanismo activador (4), la junta tórica (5) y el mecanismo activador (4) están dispuestos de forma coaxial con respecto a un rotor (6) del motor, el mecanismo activador (4) traslada la junta tórica (5) desde una posición de junta retraída, en la que puede girar libremente el conjunto hélice-rotor (2,6), hacia una posición de junta extendida, en la que la junta tórica (5) se apoya contra un plato (2.11) del cono (2.1) de la hélice (2), propiciando el cierre hermético del espacio (1) y la parada del motor. 1. -Device sealing motor aeronáuti ¬ co propeller which drives in a space (1) delimited between a propeller (2) and a fuselage (3) engine, charac- terized by comprising an O - ring (5) coupled At the end of an activating mechanism (4), the O-ring (5) and the activating mechanism (4) are arranged coaxially with respect to a motor rotor (6), the activating mechanism (4) moves the O-ring ( 5) from a retracted joint position, in which the propeller-rotor assembly (2.6) can freely rotate, towards an extended joint position, in which the O-ring (5) rests against a plate (2.11) of the cone (2.1) of the propeller (2), promoting the hermetic closing of the space (1) and the engine stop.
2. -Dispositivo según la reivindicación 1, en el que el mecanismo activador (4) comprende una camisa (4.1), con forma de canaleta toroidal, fijada a la pared inte- rior del fuselaje (3) del motor. 2. Device according to claim 1, wherein the activating mechanism (4) comprises a jacket (4.1), in the form of a toroidal channel, fixed to the inner wall of the fuselage (3) of the engine.
3. -Dispositivo según la reivindicación 2, en el que el mecanismo activador (4) comprende un pistón (4.2), con forma de canaleta toroidal, que desliza, de forma ajustada, entre las paredes laterales de la camisa 3. Device according to claim 2, wherein the activating mechanism (4) comprises a piston (4.2), in the form of a toroidal channel, which slides, tightly, between the side walls of the jacket
(4.1), definiendo un espacio cerrado (4.3) variable.  (4.1), defining a closed space (4.3) variable.
4. - Dispositivo según la reivindicación 3, en el que la junta tórica (5) está fijada al exterior de una cabeza (4.21) del pistón (4.2) . 4. - Device according to claim 3, wherein the o-ring (5) is fixed to the outside of a piston head (4.21) (4.2).
5. -Dispositivo según la reivindicación 3, en el que entre las paredes laterales de la camisa (4.1) y del pistón (4.2) están dispuestos unos aros de compresión (4.4) que garantizan la hermeticidad del espacio cerrado (4.3) . 5. Device according to claim 3, wherein between the side walls of the jacket (4.1) and the piston (4.2) compression rings are arranged (4.4) that guarantee the tightness of the enclosed space (4.3).
6. -Dispositivo según cualquiera de las reivindica- ciones anteriores, en el que el mecanismo activador (4) es accionado neumáticamente. 6. -Device according to any of the preceding claims, wherein the activating mechanism (4) is pneumatically actuated.
7. -Dispositivo según cualquiera de las reivindica¬ ciones de la 1 a la 5, en el que el mecanismo activador (4) es accionado hidráulicamente. 7. -Device according to any of claims ¬ tions 1 to 5, wherein the trigger mechanism (4) is hydraulically driven.
PCT/ES2014/070372 2014-04-29 2014-04-29 Sealing device for aircraft propeller engine WO2015166113A1 (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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US5462410A (en) * 1994-11-10 1995-10-31 United Technologies Corporation Damper and seal for propeller quill shaft
WO2000066428A1 (en) * 1999-05-05 2000-11-09 United Technologies Corporation Pressure relief device for a propeller hub

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CN112249320A (en) * 2020-11-04 2021-01-22 重庆工程职业技术学院 Low-cost unmanned aerial vehicle on water

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