Abstract: An air supply device for an aircraft engine turbine, in which device the air is conveyed to at least one aircraft engine turbine after being conveyed through at least one connecting sleeve from a low pressure distributor to a space defined by at least one upstream side and one downstream side, the upstream side having at least one opening and each pierced opening receiving one end of one of the connecting sleeves, wherein the upstream side and the downstream side are secured by at least one fastener. A retaining plate is used for each fastener in order to position a securing element of the fastener, the retaining plate having a supporting surface that blocks each connecting sleeve axially in one direction.

Abstract: A cooling device for the casing of a jet engine, includes a cooling tube and a supporting device, the supporting device including an attachment plate and an attachment clamp, the attachment clamp including a clamp body surrounding the cooling tube and an attachment element attached to the attachment plate, wherein the attachment plate includes: an opening; and an attachment tab secured to the main wall of the attachment plate and arranged on at one portion of the periphery of the opening, the attachment clamp passing through the opening, and the attachment element of the attachment clamp being attached to the attachment tab.

Abstract: An interface device between first and second turbomachine elements is provided. The interface device includes an annular air inlet structure including opposite first and second parts, designed to come into contact with the first and second turbomachine elements respectively, in which the first part is configured to be in swivel contact with the first element; and an elastic return device that can be placed around the air inlet structure and designed to come into contact with at least the first turbomachine element.

Abstract: A cooling device for the casing of a jet engine, includes a cooling tube and a supporting device, the supporting device including an attachment plate and an attachment clamp, the attachment clamp including a clamp body surrounding the cooling tube and an attachment element attached to the attachment plate, wherein the attachment plate includes: an opening; and an attachment tab secured to the main wall of the attachment plate and arranged on at one portion of the periphery of the opening, the attachment clamp passing through the opening, and the attachment element of the attachment clamp being attached to the attachment tab.

Abstract: An air supply device for an aircraft engine turbine, in which device the air is conveyed to at least one aircraft engine turbine after being conveyed through at least one connecting sleeve from a low pressure distributor to a space defined by at least one upstream side and one downstream side, the upstream side having at least one opening and each pierced opening receiving one end of one of the connecting sleeves, wherein the upstream side and the downstream side are secured by at least one fastener. A retaining plate is used for each fastener in order to position a securing element of the fastener, the retaining plate having a supporting surface that blocks each connecting sleeve axially in one direction.

Abstract: The main purpose of the invention is an interface device (1) between first (2) and second (3) turbomachine elements, characterised in that it comprises an annular air inlet structure (4) comprising opposite first (5) and second (6) parts, designed to come into contact with first (2) and second (3) turbomachine elements respectively, the first part (5) being configured to be in swivel contact with the first element (2), and an elastic return device (7) that can be placed around the air inlet structure (4) and designed to come into contact with at least the first turbomachine element (2).