Safran Aircraft Engines

Snecma

Catherine Pikovsky

Antoine Jean-Philippe Beaujard

Serge Rene Morreale

Christophe Marcel Lucien Perdrigeon

Tewfik Boudebiza

Cédric Zaccardi

Cedric Zaccardi

Benoit Guillaume Farvacque

Paul Ghislain Albert Levisse

Serge René Morreale

Alexandre Bernard Marie Boisson

Pierre Jean-Baptiste Metge

Dominik Igel

Bastien Pierre Verdier

Mathieu Jean Pierre Trohel

Alexandre Corsaut

Thomas Gabriel Elie Gatteau

Aude Simonet

Boris Lemattre

Mathieu Jean Trohel

An aircraft turbine engine having a primary air flow path with a low-pressure and a high-pressure compressors, a secondary air flow path with vanes and decks between vanes, each of the decks being located between the inner radial ends or between the outer radial ends of two adjacent vanes, each deck having a wall partially delimiting the secondary path. A pressurized air circuit draws air between the low-pressure compressor and the high-pressure compressor or in the high-pressure compressor and supplies at least one turbine engine component located near a main axis of the turbine engine. The pressurized air circuit includes a heat exchanger between the pressurized-air stream and the air stream flowing in the secondary path. The heat exchanger is formed by at least one deck through which the pressurized air flows, the wall of the deck performing the heat transfer between the pressurized air and the air stream flowing in the secondary path.

Turbine engine comprising a heat exchanger consisting of at least one deck between vanes

A turbine arrangement comprising a journal having a flange carrying a disc that is attached to the flange with bolts, wherein it includes a stationary circular trough surrounding the flange for collecting oil capable of passing radially between the disc and the flange carrying this disc.

Turbine arrangement incorporating an oil recovery circumferential trough

The present invention relates to a bypass air/fluid heat exchanger () for a turbofan engine. According to the invention, this exchanger () comprises: &#x2014;an annular outer shroud () with two walls, an inner wall () and an outer wall (), &#x2014;an annular inner shroud () concentric with the outer shroud (), &#x2014;a series of OGV guide vanes () which connect said outer shroud to said inner shroud, &#x2014;and a circulation circuit () for circulating said fluid, the two shrouds delimiting a bypass air flow path, the fluid circulation circuit () is formed in the body of the outer shroud () and in the body of at least one of the OGV guide vanes (), this circulation circuit () opening at the two respective ends thereof into an inlet opening () and into an outlet opening (), formed through said outer wall () of the outer shroud, and the two shrouds (), the OGV guide vanes () and the circulation circuit () of said fluid are integral.

Bypass air/fluid heat exchanger, method for manufacturing same and turbofan engine provided with such exchanger

An aircraft turbine engine having a primary air flow path with low-pressure and high-pressure compressors, a secondary air flow path which is located around the primary path and runs coaxially thereto, the turbine engine including vanes distributed about a main axis of the turbine engine. A pressurized air circuit draws air between the low-pressure compressor and the high-pressure compressor or in the high-pressure compressor and supplies at least one component located close to a main axis of the turbine engine. The pressurized air circuit includes a heat exchanger between the stream of pressurized air and the stream of air flowing in the secondary path, the heat exchanger being arranged in at least one of the straightening vanes, where a heat exchanger pipe is arranged, the pipe having a pressurized-air inlet and a pressurized-air outlet that are located at the same radial end of the vane.

Turbine engine comprising a heat exchanger in the secondary path

A turbomachine blade including a body that extends mainly in a plane defined by a main axis and a longitudinal direction, which is defined by a lower surface wall, an upper surface wall, a leading edge located at a first longitudinal end of the body and a trailing edge located at a second longitudinal end of the body, wherein the body of the blade includes a plurality of first pipes that extend mainly along the direction of the main axis, for circulation of a gas flow, and a plurality of second pipes that extend mainly along the longitudinal direction, for circulation of a second gas flow.

Turbomachine comprising a heat exchanger in the secondary path

Double flow turbojet including an intermediate flow path dedicated to supplying with air via radial arms an exhaust casing of this turbojet

A turbine engine of an aircraft includes: a primary air flow duct; a secondary air flow duct which is located around the primary duct, the secondary duct including a stator including a plurality of blades distributed around a main axis of the turbine engine and inter-blade platforms located between radially internal ends or between radially external ends of two adjacent blades, each platform including a wall partially delimiting the secondary duct; and a fluid circuit which includes a heat exchanger formed by at least one of the platforms. The platform includes a line that has an inlet port of the fluid and a fluid outlet port. The fluid circuit includes a distributor associated with each port of the at least one platform with the rest of the fluid circuit and of which each distributor is axially offset with respect to the platform along the main axis.

Turbine engine including a heat exchanger formed in a platform

A turbine engine comprises a rotor shaft and a roller bearing supporting the shaft in rotation along an axis. The bearing comprises an inner ring, an outer ring, and rolling elements engaged between the inner and outer rings. The inner ring has a first axial end annular portion that is more exposed to heat during operation than a second axial end annular portion thereof. The turbine engine further comprises an oil injection device configured to supply the rolling elements with oil for lubrication of the latter. In order to homogenise the temperature of the inner ring, the latter comprises through-holes formed in the first axial end annular portion and distributed around the axis in order to allow for a circulation of oil coming from the oil injection device through the first axial end annular portion, thereby providing additional cooling to the first end annular portion.

Turbine engine comprising means for axially homogenising the temperature of an inner ring of a roller bearing

An annular cap for collecting lubricating oil for turbomachine equipment is configured to extend around the equipment and to rotate about an axis. The cap includes through-orifices through which the oil can pass radially under the effect of spinning. The cap further includes means of deflecting the oil leaving the orifices in a direction substantially transverse to the axis and substantially tangential to the cap.

Lubricating-oil collection cap for turbomachine equipment

The invention relates to a turbine engine module comprising a rotating device () having a cover (), said cover () comprising radial through ports () for the passage of the oil escaping by centrifugation and means () for guiding the oil leaving said ports () radially outwards, and a casing () defining at least one portion of a lubrication enclosure of said device (), said casing () comprising at least one gutter (), arranged to recover the oil, characterized in that the gutter () comprises an annular bottom wall () having at least one discharge port, and in that the casing () comprises at least one other port located on the outside of the gutter (), said at least one other port and said at least one discharge port being connected to common discharge means.

Turbine engine module comprising a casing around a device with a cover for recovering lubricating oil

A device for lubricating a turbomachine rolling bearing includes a rolling bearing mounted between an internal component and an external component. The bearing has rolling elements mounted between an outer ring secured to the external component and an inner ring secured to the internal component. The internal component includes at least one first duct for the passage of oil for supplying the internal ring of the bearing with oil, wherein the internal component is a stator component and at least one first duct is connected to an oil supply source configured to deliver the oil at a pressure high enough that this oil can be conveyed as far as the rolling elements of the bearing.

Device and method for lubricating a turbomachine rolling bearing

A turbomachine assembly including first and second bodies, in which one of the bodies is rotating relative to the other body around the axis of rotation of the turbomachine, is provided. A tight zone is formed between the bodies and includes a sealing gasket. A flowing fluid, in particular lubricant oil, is able to circulate inside the first and second bodies and to be driven toward the one rotating body from the other body. The one rotating body includes a device for guiding the rotation, in the direction of rotation of the one rotating body, of the flow of fluid inside the one rotating body so as to drive the flowing fluid away from the tight zone.

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Moissy-Cramayel, France

Catherine Pikovsky