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: 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: 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 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 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 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: 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: 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: A turbine engine for an aircraft which includes, in general, at least one assembly made up of a first part wherein a second part is attached with an attachment device including a milled head applied to the first part and a body engaging with the second part in order to clamp the parts. The recess of the head of such an attachment device requires a boss on the first part, which is complex and expensive to produce using conventional techniques. Such a boss can be replaced with a removable seat having an opening through which the body passes and forming a recess for the head, a bearing surface for the head, and abutment device applied to the first part in order to prevent a movement of the seat towards the second part.

Abstract: A turbine engine for an aircraft which includes, in general, at least one assembly made up of a first part wherein a second part is attached with an attachment device including a milled head applied to the first part and a body engaging with the second part in order to clamp the parts. The recess of the head of such an attachment device requires a boss on the first part, which is complex and expensive to produce using conventional techniques. Such a boss can be replaced with a removable seat having an opening through which the body passes and forming a recess for the head, a bearing surface for the head, and abutment device applied to the first part in order to prevent a movement of the seat towards the second part.