United Technologies Corporation

Andrew S Foose

Mark W Costa

Charles W Brown

Douglas A Welch

Nathan D Korn

Jennifer L Grudnoski

Jan B Kowza

Wendy P Lopardi

Charles Brown

A gas turbine engine vane has first and second members. The first member has a first surface section forming a suction side of an airfoil of the vane. The second surface section forms leading and trailing portions of a pressure side of the airfoil. The third surface section forms a recess between the leading and trailing portions. The second member is secured to the first member and has a first surface section forming an intermediate portion of the pressure side a leading protrusion of the second member may be captured by a recess below a lip of the first member.

Gas turbine engine vane

A liner assembly for a fan case includes a noise attenuation layer covered by a face sheet. The face sheet includes openings to the underlying noise attenuation layer. The face sheet and noise attenuation layer include acoustically transparent joints. The noise attenuation layer includes a first side joined to a second side at a seam by an adhesive strip. The adhesive strip bonds the first side to the second side without filling any chambers. The face sheet includes a joint filled with an adhesive providing the desired uninterrupted surface within the fan case. Openings are formed through the joint and the adhesive to communicate with the underlying noise attenuation layer. The joint and seam become essentially transparent acoustically to improve noise attenuation performance.

Zero acoustic splice fan case liner

The invention is a penetration resistant turbine engine fan casing (12) for containing separated fragments of a fan blade (16). The casing includes a penetration susceptible support case (14), a penetrable covering (32) circumscribing an impact zone (I) of the support case and an optional, but highly recommended collapsible support covering (34) circumscribing the case but axially offset from the impact zone. A containment covering (36) circumscribes both the penetrable covering (32) and the support covering (34). In a preferred embodiment, the coverings are aromatic polyamide fiber fabrics and the support covering is a collapsible cellular array. In operation, a detached fragment of a fan blade penetrates through the case (14) and the penetrable covering (32), and is plastically deformed by the penetrable covering to reduce the fragment's potential for damaging the containment covering (36). The containment covering intercepts the deformed fragment, confining it to a predetermined radial envelope bounded by the inner surface (58) of a nacelle (52). The impact forces arising from a separated blade fragment cause the containment fabric to collapse the cellular array (32) and momentarily detension the containment fabric to maximize its penetration resistance.

Penetration resistant fan casing for a turbine engine

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Vernon, CT, United States of America

Andrew S Foose