WO2018015022A1 - Actionneur hydraulique de commande de vol comprenant un dispositif à double joint d'étanchéité et à fuite définie - Google Patents

Actionneur hydraulique de commande de vol comprenant un dispositif à double joint d'étanchéité et à fuite définie Download PDF

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Publication number
WO2018015022A1
WO2018015022A1 PCT/EP2017/000893 EP2017000893W WO2018015022A1 WO 2018015022 A1 WO2018015022 A1 WO 2018015022A1 EP 2017000893 W EP2017000893 W EP 2017000893W WO 2018015022 A1 WO2018015022 A1 WO 2018015022A1
Authority
WO
WIPO (PCT)
Prior art keywords
piston ring
piston
hydraulic
leakage
secondary seal
Prior art date
Application number
PCT/EP2017/000893
Other languages
German (de)
English (en)
Inventor
Jürgen KLETT
Philipp Kegel
Albert Petretti
Michael Koros
Original Assignee
Liebherr-Aerospace Lindenberg Gmbh
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 Liebherr-Aerospace Lindenberg Gmbh filed Critical Liebherr-Aerospace Lindenberg Gmbh
Publication of WO2018015022A1 publication Critical patent/WO2018015022A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/24—Transmitting means
    • B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
    • B64C13/36—Transmitting means without power amplification or where power amplification is irrelevant fluid
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/24—Transmitting means
    • B64C13/38—Transmitting means with power amplification
    • B64C13/40—Transmitting means with power amplification using fluid pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
    • F15B15/08—Characterised by the construction of the motor unit
    • F15B15/14—Characterised by the construction of the motor unit of the straight-cylinder type
    • F15B15/1423—Component parts; Constructional details
    • F15B15/1447—Pistons; Piston to piston rod assemblies
    • F15B15/1452—Piston sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B19/00—Testing; Calibrating; Fault detection or monitoring; Simulation or modelling of fluid-pressure systems or apparatus not otherwise provided for
    • F15B19/005—Fault detection or monitoring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/002—Sealings comprising at least two sealings in succession
    • F16J15/004—Sealings comprising at least two sealings in succession forming of recuperation chamber for the leaking fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
    • F16J15/3492—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member with monitoring or measuring means associated with the seal
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J9/00—Piston-rings, e.g. non-metallic piston-rings, seats therefor; Ring sealings of similar construction
    • F16J9/12—Details
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M13/00—Testing of machine parts
    • G01M13/005—Sealing rings
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M3/00—Investigating fluid-tightness of structures
    • G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
    • G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors

Definitions

  • the invention relates to a hydraulic Flugêtaktuator with a piston-cylinder device with a piston and a cylinder and a double sealing device with at least one primary seal and at least one piston ring as a secondary seal, wherein the primary seal and the piston ring between the piston and the cylinder are provided.
  • the object of the invention is to provide an improved hydraulic Flugêtaktuator in which the targeted installation of a defined and at least short-term tolerable leakage of a secondary seal or secondary seal failure of a primary seal or primary seal is made visible without the reliability of the device to endanger.
  • the object of the invention is to provide a flight control actuator which requires less intensive maintenance and which can be checked more easily for any leaks.
  • a hydraulic Flug horrinaktuator comprising a piston-cylinder device with a piston and a cylinder and a double-sealing device with at least one primary seal and at least one piston ring as a secondary seal.
  • the primary seal and the piston ring are in this case provided between the piston and the cylinder, wherein at least one throttle point in the region of the secondary seal is provided for introducing a defined leakage at the secondary seal.
  • the throttle in the Area of the secondary seal can be designed in any way and serves to reduce the sealing effect of the secondary seal defines.
  • the restriction may be part of the secondary seal and / or be separate therefrom and adjacent to the secondary seal.
  • the reduction of the sealing effect may be so low that, in a case where the primary seal fails, the flight control actuator may function solely by sealing through the secondary seal and with a defined defined leakage at the secondary seal. If a leakage at the flight control actuator is detected during maintenance or diagnostic work, which corresponds to the defined leakage, this is a sign of the wear of the primary seal.
  • the throttle point comprises at least one groove provided on the end face on the secondary seal, and / or at least one groove provided on the outer diameter of the secondary seal, and / or a throttle provided on the piston.
  • the throttle body is designed as a groove, there is the advantage that it can be produced particularly easily in the context of the production of the corresponding seal or the piston ring without additional work steps.
  • the throttle point additionally or alternatively is designed as a throttle or recess provided on the piston, this can be, for example, a groove running on a piston outer surface, which groove is correspondingly incorporated in the piston structure. It is also conceivable to provide a passage on the piston with a corresponding throttling action.
  • the throttle point comprises at least two end-side grooves on the secondary seal, which are arranged in particular offset by 180 ° in the circumferential direction of the secondary seal.
  • the seal can be circular or hollow cylindrical, whereby a related circumferential direction is clearly specified.
  • the grooves are provided on both sides or on one side of the secondary seal.
  • the grooves are designed to generate turbulent flows.
  • the person skilled in the art dimensioned the grooves in such a way that turbulent flows are generated in the respective pressure regimes of the flight control actuator at the throttle points or at the grooves.
  • the throttle points or grooves can be sized accordingly large or small.
  • the piston ring is designed as a double piston ring and has a stepped overlap between the two sections of the double piston ring. Due to the corresponding overlap, the leakage at the double piston ring can be further reduced.
  • the invention also relates to a piston ring for a hydraulic Flugêtaktuator according to one of claims 1 to 8, wherein the piston ring comprises at least one frontally provided thereon groove, and / or at least one provided on the outer diameter of the piston ring groove, in particular at least two end-side grooves on the piston ring are provided, which are arranged offset by 180 ° in the circumferential direction of the piston ring, wherein further in particular the two grooves together have a constant cross-section errors constant cross-section, further more particularly the grooves are provided on both sides or on one side of the on the piston ring, and wherein Furthermore, in particular, the grooves for generating turbulent flows are formed.
  • the invention is also directed to a method for testing the tightness of a hydraulic flight control actuator according to any one of claims 1 to 8, comprising at least one piston ring according to claim 9, wherein a differential pressure is applied to the piston; an occurring leakage is measured; the measured leakage is compared with a stored target leakage; and wherein an impermissible leakage is detected when the measured leakage is above the desired leakage.
  • Figures 3a and 3b views of the secondary seal with throttling points
  • FIG. 4a a sectional view of a partial region of a device according to the invention
  • FIG. 4b top view of a piston ring according to the invention.
  • Figure 1 shows the leakage behavior of the device according to the invention in its time course (abscissa).
  • the leakage quantity and the critical leakage are indicated on the ordinate, at the crossing of which a critical state of the flight control actuator or the corresponding seal occurs.
  • the leakage is determined in corresponding measurement intervals, for example by pressure measurement at the appropriate Flugêtaktuator.
  • the measured leakage is indicated as measurable leakage in its time course. If leakage occurs at the primary seal 1, the measured leakage value rises to a level which is predetermined by the defined mean leakage of the secondary seal 2.
  • the second case is shown in the central region of FIG. 1 and is present when there is a fault or defect at the primary seal 1, in which case the secondary seal 2 is active and the leakage defined thereon occurs. This corresponds to level 1. If this level or leakage level is detected, this is an indication to carry out a maintenance action.
  • the third case is shown in the right-hand area of FIG. 1 and is present when both seals 1, 2 are defective.
  • the corresponding Flugêtaktuator is then no longer fully operational, which can lead to the loss of the corresponding hydraulic system.
  • a prerequisite for a correspondingly defined leakage is a piston ring 2 which permits virtually no or as little as possible leakage at the opening 24 of the ring 2 or at its slot 24 (see FIGS. 2 and 4b).
  • This can be realized by a double ring 2 ', which is arranged so that the two slots 24 of the two double-ring parts 22, 23 are offset from each other.
  • a double ring 2 ' can in this case comprise two, in particular identical, circumferentially offset and axially spaced-apart piston rings 2.
  • the opening or the slot 24 may be designed so that changes in length, which may occur due, for example, due to tolerances or temperature changes, do not affect the tightness of the piston ring 2.
  • This can be realized by a stepped overlap of the double ring 2 ', which prevents a flow of hydraulic fluid in the radial and / or axial direction even with changes in length.
  • grooves 11, 21 may be provided on the secondary seal 2 at the end or otherwise, which are characterized by their size determine the flow.
  • two grooves 11, 21 can be provided per side and offset by 180 °, which together provide a constant cross section, which remains independent of any concentricity errors of the piston also constant or approximately constant. Otherwise, concentricity errors can otherwise lead to a groove 11, 21 which lies in a region in which the distance between the piston and cylinder is reduced due to the concentricity error, being deformed more strongly and thus for example has a smaller cross-section or a cross-section with a smaller cross-sectional area ,
  • the grooves 21 can be mounted on both sides to allow a flow in both directions, or they can also be mounted only on one side to allow only one-way flow.
  • the grooves 21 can be designed so that turbulent flows occur during the flow of hydraulic fluid and thereby the flow over the entire temperature range of the hydraulic fluid remains as constant as possible.
  • a differential pressure can be applied to the piston or in the piston-cylinder device.
  • the throttle body 21 and thus the defined leakage can also be realized by a throttle in the piston itself or on the piston itself.
  • FIG. 3 b shows an enlarged view of a groove 11, which is provided on an end region of a secondary seal 2. Also conceivable are grooves 11, 21, which are arranged on the lateral surfaces of the optionally hollow cylindrical secondary seal 2. It can also be seen in FIG. 3b that a circumferential groove 12 running in the circumferential direction can be provided on the secondary seal 2. This can separate or partially separate the secondary seal 2 into two subregions, or alternatively can be present only within the structure of the integrally manufactured secondary seal 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • Fluid Mechanics (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Actuator (AREA)
  • Sealing Devices (AREA)

Abstract

L'invention concerne un actionneur hydraulique de commande de vol comprenant un dispositif à piston et cylindre pourvu d'un piston et d'un cylindre, et comprenant également un dispositif à double joint d'étanchéité pourvu d'au moins un joint primaire (1) et d'au moins un segment de piston (2) faisant office de joint d'étanchéité secondaire (2), le joint d'étanchéité primaire (1) et le segment de piston (2) étant situés entre le piston et le cylindre. L'invention est caractérisée en ce que, pour l'introduction d'une fuite définie sur le joint d'étanchéité secondaire (2), au moins un point d'étranglement (21) est présent dans la zone du joint d'étanchéité secondaire (2).
PCT/EP2017/000893 2016-07-19 2017-07-19 Actionneur hydraulique de commande de vol comprenant un dispositif à double joint d'étanchéité et à fuite définie WO2018015022A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016008818.4 2016-07-19
DE102016008818.4A DE102016008818A1 (de) 2016-07-19 2016-07-19 Hydraulischer Flugsteueraktuator mit Doppeldichtungsvorrichtung und definierter Leckage

Publications (1)

Publication Number Publication Date
WO2018015022A1 true WO2018015022A1 (fr) 2018-01-25

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ID=59523062

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2017/000893 WO2018015022A1 (fr) 2016-07-19 2017-07-19 Actionneur hydraulique de commande de vol comprenant un dispositif à double joint d'étanchéité et à fuite définie

Country Status (2)

Country Link
DE (1) DE102016008818A1 (fr)
WO (1) WO2018015022A1 (fr)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2084683A (en) * 1934-01-11 1937-06-22 Westinghouse Air Brake Co Piston ring testing device
US4089534A (en) * 1973-12-29 1978-05-16 Polypac B.A.L. Limited Packing assemblies
US4207800A (en) * 1978-11-02 1980-06-17 Homuth Kenneth C Single directional sealing piston ring
DE4133188A1 (de) * 1990-10-08 1992-04-09 Zahnradfabrik Friedrichshafen Dichtungsanordnung
DE102010020490A1 (de) * 2010-05-14 2011-11-17 Man Diesel & Turbo, Filial Af Man Diesel & Turbo Se, Tyskland Verfahren zur Optimierung der Funktion eines Kolbenringpakets sowie hierfür geeignetes Kolbenringpaket
EP2557337A1 (fr) * 2011-08-09 2013-02-13 MTU Aero Engines GmbH Elément de construction
US20130113165A1 (en) * 2011-03-23 2013-05-09 Kayaba Industry Co., Ltd. Piston bearing structure for fluid pressure cylinder
EP2933623A1 (fr) * 2014-04-16 2015-10-21 Bell Helicopter Textron Inc. Dispositif de surveillance de fuite de joint d'actionneur de giravion

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4065852A (en) * 1976-07-16 1978-01-03 Miller Fluid Power Corporation Nuclear cylinder seal construction
DE3244209C2 (de) * 1982-11-30 1985-05-02 Kaco Gmbh + Co, 7100 Heilbronn Dichtung zum Abdichten gegen hydraulische Medien, vorzugsweise Dichtabstreifelement
DE19955270A1 (de) * 1999-11-17 2001-05-23 Roemheld A Gmbh & Co Kg System zur Überwachung von Hydraulikzylindern
DE202006002727U1 (de) * 2006-02-21 2006-04-20 Festo Ag & Co Pneumatisches Antriebssystem

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2084683A (en) * 1934-01-11 1937-06-22 Westinghouse Air Brake Co Piston ring testing device
US4089534A (en) * 1973-12-29 1978-05-16 Polypac B.A.L. Limited Packing assemblies
US4207800A (en) * 1978-11-02 1980-06-17 Homuth Kenneth C Single directional sealing piston ring
DE4133188A1 (de) * 1990-10-08 1992-04-09 Zahnradfabrik Friedrichshafen Dichtungsanordnung
DE102010020490A1 (de) * 2010-05-14 2011-11-17 Man Diesel & Turbo, Filial Af Man Diesel & Turbo Se, Tyskland Verfahren zur Optimierung der Funktion eines Kolbenringpakets sowie hierfür geeignetes Kolbenringpaket
US20130113165A1 (en) * 2011-03-23 2013-05-09 Kayaba Industry Co., Ltd. Piston bearing structure for fluid pressure cylinder
EP2557337A1 (fr) * 2011-08-09 2013-02-13 MTU Aero Engines GmbH Elément de construction
EP2933623A1 (fr) * 2014-04-16 2015-10-21 Bell Helicopter Textron Inc. Dispositif de surveillance de fuite de joint d'actionneur de giravion

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Publication number Publication date
DE102016008818A1 (de) 2018-01-25

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