Alain Jacques Emile Guibert

Bio: Alain Jacques Emile Guibert is an academic researcher. The author has contributed to research in topics: Turbine & Ring (chemistry). The author has an hindex of 2, co-authored 3 publications receiving 75 citations.

Turbine ring for a gas turbine engine

Abstract: A turbine ring has an annular metallic carrier which is mounted within the inside of the turbine casing and within the carrier there is provided a ceramic abradable ring. A cooling air circuit is provided to regulate the temperature of only the annular carrier such that the latter always exerts a centripetal compression force on the ring under all operational conditions of the gas turbine to clamp the abradable ring.

Tip-sealing shroud for a gas turbine

Abstract: L'invention concerne un anneau de turbine. A turbine ring. Cet anneau comprend un support annulaire, metallique (6) qui est monte a l'interieur du carter (1), a l'interieur duquel est monte un anneau (5) en materiau ceramique abradable; This ring comprises an annular support, metal (6) which is mounted within the housing (1), inside which is mounted a ring (5) made of abradable ceramic material; selon la presente invention, des moyens, tels qu'un circuit d'air de refroidissement (7-11-9a-9b-12-13) sont prevus pour regler seulement la temperature du support annulaire (6) de facon que celui-ci exerce toujours une compression axipete appropriee sur l'anneau (5), a tous les regimes de fonctionnement de la turbine, c'est-a-dire que le support annulaire (6) se comporte comme une frette pour l'anneau (5). according to the present invention, means such as a cooling air circuit (7-11-9a-9b-12-13) are provided only for adjusting the temperature of the annular support (6) so that it always exercises appropriate axipete compression on the ring (5) at all operating speeds of the turbine, that is to say that the annular support (6) behaves like a hoop to the ring (5) .

Anneau de turbine pour une turbomachine à gaz

Abstract: L'invention concerne un anneau de turbine. Cet anneau comprend un support annulaire, metallique (6) qui est monte a l'interieur du carter (1), a l'interieur duquel est monte un anneau (5) en materiau ceramique abradable; selon la presente invention, des moyens, tels qu'un circuit d'air de refroidissement (7-11-9a-9b-12-13) sont prevus pour regler seulement la temperature du support annulaire (6) de facon que celui-ci exerce toujours une compression axipete appropriee sur l'anneau (5), a tous les regimes de fonctionnement de la turbine, c'est-a-dire que le support annulaire (6) se comporte comme une frette pour l'anneau (5).

Ceramic matrix composite component for a gas turbine engine

Abstract: A ceramic matrix composite (CMC) component for a combustion turbine engine ( 10 ). A blade shroud assembly ( 30 ) may be formed to include a CMC member ( 32 ) supported from a metal support member ( 32 ). The CMC member includes arcuate portions ( 50, 52 ) shaped to surround extending portions ( 46, 48 ) of the support member to insulate the metal support member from hot combustion gas ( 16 ). The use of a low thermal conductivity CMC material allows the metal support member to be in direct contact with the CMC material. The gap ( 42 ) between the CMC member and the support member is kept purposefully small to limit the stress developed in the CMC member when it is deflected against the support member by the force of a rubbing blade tip ( 14 ). Changes in the gap dimension resulting from differential thermal growth may be regulated by selecting an angle (A) of a tapered slot ( 76 ) defined by the arcuate portion.

Rotor seal segment

Abstract: A ceramic seal segment (30) for a shroud ring (21) of a rotor (15) of a gas turbine engine (10), the ceramic seal segment (30) positioned radially adjacent the rotor (15) and characterised by being a hollow section that defines an inlet (44) and an outlet (64, 66) for the passage of coolant therethrough.

Passive clearance control

Abstract: The clearance between the tips of the rotor blades and the segmented shroud of a gas turbine engine is controlled by a passive clearance control that includes a support ring made from a low thermal expansion material supporting a retainer for the blade outer air seal that is slidable relative thereto so that the segments expand circumferentially and move radially to match the rate of change slope of the rotor during expansion and contraction for all engine operations. A leaf spring between the support ring and outer air seal biases the outer air seal in the radial direction and maintains the desired radial position during steady state operation of the gas turbine engine.

Abradable coating applied with cold spray technique

Abstract: A cold spray process (20) for applying an abradable coating (16) to a substrate material (12). A bond coat layer (14) and/or an abradable coating material layer (16) are applied to a substrate (12) by directing particles of the material toward the substrate surface at a velocity sufficiently high to cause the particles to deform and to adhere to the surface. Particles of the bond coat material may first be directed toward the substrate surface at a velocity sufficiently high to clean the surface (24) but not sufficiently high to cause the particles to deform and to adhere to the surface.

Network cooled coated wall

Abstract: A turbine wall includes a metal substrate having front and back surfaces. A thermal barrier coating is bonded atop the front surface. A network of flow channels is laminated between the substrate and the coating for carrying an air coolant therebetween for cooling the thermal barrier coating.