Abstract: A fire resistance device intended to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling equipping this turbomachine, the connecting cowling being intended to connect an upstream ring delimiting an inter-flow compartment, to an arm that extends radially across a secondary flow of the turbomachine. The device includes two contacting lips extending along different lines, of which a first lip with a C-shaped section is integrated within a contact structure, and a second lip including at its end a protruding blocking portion protecting the contact structure.

Abstract: A fire resistance device designed to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling with which the turbomachine is equipped, the connecting cowling being designed to connect an upstream ring, delimiting an inter-flow compartment, to an arm that extends radially across a secondary flow of the turbomachine. The device can be produced as a single piece and includes two contact lips which extend along different lines, the first lip having a C-shaped cross-section.

Abstract: An air-sealing device intended to be inserted between an aircraft dual-flow turbine engine casing element and a nacelle element, the sealing device including an attachment tab at the end of which is located a sealing portion having an outer surface intended to be contacted by the casing element and the nacelle element, and an inner surface defining a cavity. The inner surface defines at least one protuberance extending inside the cavity.

Abstract: A rotary piezoelectric motor (1), in particular for a timepiece, including a rotor (3) configured to rotate and actuate a mechanical device, and a stator (2) configured to rotate the rotor (3), the stator (2) including a piezoelectric actuator provided with a resonator (29) arranged to perform an oscillatory motion, and a fixed element (4). The resonator in a movable element (5) arranged at a distance from the fixed element (4) and connected to the fixed element (4), the piezoelectric actuator being configured to move the movable element (5) against the rotor (3) to make it rotate, the movement of the movable element (5) making the rotor (3) rotate in a first direction.

Abstract: The piezoelectric balance spring (3) is provided for a circuit (10) for self-regulating an oscillation frequency of an oscillating mechanical system (2, 3), or an energy recovery circuit or a motor circuit for actuating the movement or for the automatic maintenance thereof. The piezoelectric balance spring (3) comprises at least one piezoelectric layer (7, 7?, 17, 17?, 27, 27?) disposed on a top face (20) or bottom face of a certain number of coils of the spring in a plane, and at least two pairs of electrodes (8a, 8b, 8c, 8d), whereby the electrodes of each pair are disposed on two opposing faces of the same piezoelectric layer or respectively two piezoelectric layers so as to apply a reverse bias voltage on each pair of electrodes.

Abstract: An airtight seal configured to be mounted on a first turbomachine member, such as a door of a bleed valve, and to bear against a second member of the turbomachine, such as a hub of an intermediate casing, the airtight seal including a retaining device for mounting the seal on the first member; a sealing lip ensuring airtightness through contact and intended to bear against the second member; an anti-return device for the sealing lip reinforcing the rigidity of the airtight seal at the base of the sealing lip.

Abstract: A discharge grille of an intermediate casing of a turbomachine includes a peripheral edge and a seal mounted on the peripheral edge via an attachment system, the seal ensuring the sealing between a first turbomachine member and a second member of the turbomachine, and surrounding the discharge grille of the intermediate casing, the seal having a U-shaped cross section and includes a base plate configured to bear against the first member, a sealing lip configured to bear against the second member through deformation of the sealing lip to ensure air tightness and fire proofing through contact.

Abstract: An outer shroud of an intermediate casing for a dual flow turbine engine for an aircraft, the shroud including: an annular downstream portion provided with a shroud opening passing through an annular downstream edge of the shroud; a connecting member (50) attached to the annular downstream portion, and intended to attach an arm that passes through a secondary flow path; an air-sealing and fire-resistance device including: a portion including: a pad arranged in a hollow annular area of the annular downstream edge of the shroud; a blade protruding from the pad and clamped between a circumferential end and the radially outer end of the arm, a leaf spring (pressing the pad into the hollow annular area.

Abstract: An horological movement includes an analogue time display, a geartrain, a barrel and an electromechanical oscillator, which is formed of a resonator, including a balance and a piezoelectric balance-spring, and a mechanical escapement, and further includes an electronic control circuit connected to an electrical energy source and arranged to be able to control the application of an electrical voltage on at least one electrode of the piezoelectric balance-spring so as to generate driving electrical pulses for the oscillator. The horological movement is configured such that the barrel is capable, in a first main state, of maintaining alone a functional oscillation of the oscillator with a first amplitude, while in a second main state, the electronic control circuit powers the piezoelectric balance-spring to maintain, partially or fully, the oscillation of the resonator with a second amplitude greater than the first amplitude for any spatial orientation, the second amplitude being preferably constant.

Abstract: A horological movement includes an analogue time display, a gear train, a barrel driving the analogue display via the gear train, and an oscillator formed of a resonator, including a balance and a piezoelectric spring, and a mechanical escapement coupling the balance to the gear train. This horological movement further includes an electric energy source which is associated with the electronic control circuit, which is arranged to be able to control the application of an electrical supply voltage to the piezoelectric spring so as to excite the oscillator to obtain a functional oscillation of the resonator and then to maintain this functional oscillation. The mechanical escapement is configured so as to be an escapement for counting the alternations of the functional oscillation, so as to pace the running of the horological movement, without the resonator being able to receive from the barrel via this mechanical escapement enough mechanical energy to maintain the functional oscillation.

Abstract: A fire resistance device is intended to be interposed between an upstream end of an aircraft turbine engine mounting structure and a cowling of the turbine engine delimiting an inter-flow compartment.

Abstract: A discharge grille of an intermediate casing of a turbomachine includes a peripheral edge and a seal mounted on the peripheral edge via an attachment system, the seal ensuring the sealing between a first turbomachine member and a second member of the turbomachine, and surrounding the discharge grille of the intermediate casing, the seal having a U-shaped cross section and includes a base plate configured to bear against the first member, a sealing lip configured to bear against the second member through deformation of the sealing lip to ensure air tightness and fire proofing through contact.

Abstract: A fire resistance device intended to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling equipping this turbomachine, the connecting cowling being intended to connect an upstream ring delimiting an inter-flow compartment, to an arm that extends radially across a secondary flow of the turbomachine. The device includes two contacting lips extending along different lines, of which a first lip with a C-shaped section is integrated within a contact structure, and a second lip including at its end a protruding blocking portion protecting the contact structure.

Abstract: An airtight seal configured to be mounted on a first turbomachine member, such as a door of a bleed valve, and to bear against a second member of the turbomachine, such as a hub of an intermediate casing, the airtight seal including a retaining device for mounting the seal on the first member; a sealing lip ensuring airtightness through contact and intended to bear against the second member; an anti-return device for the sealing lip reinforcing the rigidity of the airtight seal at the base of the sealing lip.

Abstract: An air-sealing device intended to be inserted between an aircraft dual-flow turbine engine casing element and a nacelle element, the sealing device including an attachment tab at the end of which is located a sealing portion having an outer surface intended to be contacted by the casing element and the nacelle element, and an inner surface defining a cavity. The inner surface defines at least one protuberance extending inside the cavity.

Abstract: An air-fire seal designed to be attached to a first tubular member of a turbomachine, such as a bleed duct, and to rest against a second member of the turbomachine, such as an intermediate casing hub, includes an attachment base having an annular shape around a reference axis (Y); a first annular fire-stop lip extending from the attachment base over a first length (L1); and a second annular air-sealing lip extending from the attachment base over a second length (L2) lower than the first length and facing the first lip.

Abstract: A fire resistance device designed to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling with which the turbomachine is equipped, the connecting cowling being designed to connect an upstream ring, delimiting an inter-flow compartment, to an arm that extends radially across a secondary flow of the turbomachine. The device can be produced as a single piece and includes two contact lips which extend along different lines, the first lip having a C-shaped cross-section.

Abstract: An outer shroud of an intermediate casing for a dual flow turbine engine for an aircraft, the shroud including: an annular downstream portion provided with a shroud opening passing through an annular downstream edge of the shroud; a connecting member (50) attached to the annular downstream portion, and intended to attach an arm that passes through a secondary flow path; an air-sealing and fire-resistance device including: a portion including: a pad arranged in a hollow annular area of the annular downstream edge of the shroud; a blade protruding from the pad and clamped between a circumferential end and the radially outer end of the arm, a leaf spring (pressing the pad into the hollow annular area.

Abstract: An air-fire seal designed to be attached to a first tubular member of a turbomachine, such as a bleed duct, and to rest against a second member of the turbomachine, such as an intermediate casing hub, includes an attachment base having an annular shape around a reference axis (Y); a first annular fire-stop lip extending from the attachment base over a first length (L1); and a second annular air-sealing lip extending from the attachment base over a second length (L2) lower than the first length and facing the first lip.

Abstract: An air-fire seal designed to be attached to a first tubular member of a turbomachine, such as a bleed duct, and to rest against a second member of the turbomachine, such as an intermediate casing hub, includes an attachment base having an annular shape around a reference axis (Y); a first annular fire-stop lip extending from the attachment base over a first length (L1); and a second annular air-sealing lip extending from the attachment base over a second length (L2) lower than the first length and facing the first lip.