Safran Aircraft Engines

Matthieu Simon

Patrick Jean Laurent Sultana

Léandre Ostino

Sébastien Serge Francis Congratel

Lucien Henri Jacques Quennehen

Clément Jean Pierre Duffau

Julian Nicolas Girardeau

Jean-Luc Bacha

Joao Antonio Amorim

Ulysse Jacques Bernard Danteny

Kenny Beauboit

Paul Danre

Loic Ansart

The present invention relates to a turbine rotor () comprising a rotor disc (), provided at its periphery with a plurality of axial cells () for receiving a bilobed root () of a blade (), each cell () comprising a radially inner cavity () and a radially outer cavity (). This rotor is characterised in that it comprises a ring () for axially retaining the blade roots and an annular flange (), the ring () comprising a radially inner portion provided with notches () and being arranged against the upstream face () of the disc (), so that each of its notches () is located opposite a cell () of the disc (), the flange () being secured against the upstream face of the ring (), forming a space (E) with said disc (), and comprising at least one air-intake opening () which opens into said space (E), and in that each blade () comprises a groove () for receiving the outer circumferential edge () of said ring ().

Turbine rotor comprising a blade stop ring configured to aid the cooling of the blade roots

The present invention relates to a nozzle guide vane for a turbine, having an axis of revolution and comprising:

Turbine nozzle guide vane comprising an annular sealing element

A turbine has a first rotor and a second rotor configured to pivot about a longitudinal axis (X) according to two opposite directions of rotation. The first rotor has a radially outer drum from which blades extend radially inwards. The first rotor and the second rotor are surrounded by a stator annular part. The stator annular part delimits, with the drum, at least one upstream annular cavity and one downstream annular cavity separated from each other by sealing means.

Turbine with pressurised cavities

A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.

Blade for a turbine engine, associated turbine engine distributor and turbine engine

A hollow turbomachine turbine blade including rising cavities communicating with a squealer tip of the blade through standard dust removal holes intended to remove dust and through inclined cooling bores intended to cool a barrier of the squealer tip by leading to a pressure side face of the blade, at least one rising cavity including a tip with no dust removal hole and an inclined cooling bore formed in its lateral wall and intended to cool the squealer tip barrier is enlarged to have a diameter at least equal to the standard diameter of a dust removal hole and thus also serve as a dust removal hole, so that the air flow extracted for cooling the blade is reduced, at least one of the cavities positioned facing the tip of one of the rising cavities having an increased volume corresponding to at least a volume deducted from the tip of the rising cavity.

Hollow turbine blade with reduced cooling air extraction

A turbine ring assembly including both a plurality of ring sectors together forming a turbine ring and also a ring support structure including an upstream annular flange and a downstream annular flange, each ring sector having a first horizontal sealing tongue, an upstream vertical sealing tongue, and a first downstream vertical sealing tongue. Each ring sector also includes a second horizontal sealing tongue over the first horizontal sealing tongue in the radial direction of the ring. A first angled sealing element is housed both in a vertical groove present in the upstream tab and in a second horizontal groove, and a second angled sealing element is received both in a first horizontal groove and in a first vertical groove present in the downstream tab.

Growing community of inventors

Moissy-Cramayel, France

Matthieu Simon