The present disclosure is directed generally to firewall seals for sealing pass-through members extending through a firewall, such as a firewall of a turbine engine. In one example aspect, the firewall seal includes quick-connect features that facilitate more efficient assembly and disassembly of the firewall seal to and from the pass-through member. Particularly, the firewall seal may define a slit extending through at least a portion of the seal that allows for the pass-through member to be slid through the slit and positioned in place. A retainer formed of an elastomeric material may include a metal spring plate that springs the seal back into place after the pass-through member is positioned within the seal. Moreover, a spherical bearing of the firewall seal may include features for receiving a static or dynamic pass-through member therethrough and for allowing the pass-through member to translate and rotate.

A rotor assembly for a gas turbine engine is disclosed. The assembly includes: a composite fan blade, the fan blade including a root; a metallic rotor including a slot for receiving the root; the root being at least partially coated with a metal to form a metal-coated portion; the metal-coated portion of the root being at least partially covered with an intermediate material; and the root, metal-coated portion and intermediate material being received in the slot and bonded to the rotor.

A silicone bond coat composition having a viscosity of less than 1,600 centistokes is applied to substantially all external surfaces of the article and then cured. A liquid silicone elastomer outer coat composition comprising a high viscosity first liquid silicone elastomer formulation and a low viscosity second liquid silicone elastomer formulation is then applied and cured to provide a protected article having a complex shape. Optimal coatings result from a careful balancing of component viscosities. In an embodiment, the first formulation has a viscosity greater than 300,000 centistokes, and the second formulation has a viscosity less than 6,000 centistokes, and the liquid silicone elastomer outer coat composition comprises from about 60 to about 40 percent by weight of the first formulation and from about 40 to about 60 percent by weight of the second liquid silicone elastomer formulation.

A vacuum pump and a damper for the vacuum pump are provided so as to increase vibration isolation in a twisting direction with a simple structure and prevent rupture of an O-ring and an elastic member by regulating a misalignment of flanges facing each other. Provided are a first flange and a second flange, each having a central opening, the flanges being shaped like rings opposed to each other; an O-ring and an intermediate ring that are disposed between the first flange and the second flange; O-rings disposed between the first flange and the intermediate flange and between the intermediate ring and the second flange; a plurality of elastic members that are disposed between the first flange and the second flange and are spread in the circumferential direction of central openings; and airtightness keeping means including positioning pins inserted into positioning holes sequentially provided on the first flange, the intermediate ring, and the second flange.

A polymer airfoil assembly is disclosed and includes at least one cooling passage for circulating coolant to remove heat from the polymer airfoil portion.

An improved stator assembly for use in a gas-turbine engine is disclosed. The stator assembly may comprise a vane, an inner diameter (ID) ring, an outer diameter (OD) ring, a vane disposed between the ID ring and the OD ring, a potting component coupling the vane to at least one of the OD ring or the ID ring, and a potting embedded component disposed within the potting component. The potting embedded component may prevent disbond of the potting component during operation of the gas-turbine engine.

A stator assembly, in accordance with various embodiments, is disclosed herein. The stator assembly comprises either a first bumper or a first tab. The first bumper or the first tab extends circumferentially outward from a mating portion of the vane towards a slot in a ring. The ring may be an outer diameter (OD) ring or an inner diameter (ID) ring. The mating portion of the vane may be coupled to the ring by a potting component. The potting component may prevent direct contact between the vane and the ring.

Isolation seals for gas turbine engines are described. The isolation seals include an elastomer body configured to be attached to a first case structure at a first end and a second case structure at a second end and a seal shield configured to be attached to the first case structure, the seal shield having a shielding member configured to define a protected space between the shielding member and the elastomer body.

The invention relates to an anti-icing turbomachine blade (26), in particular for a low-pressure compressor or an intermediate-pressure compressor of a turbomachine. The blade (26) has a leading edge (28) formed by an ice-phobic surface (40) and two hydrophobic surfaces (42; 44) which extend the ice-phobic surface (40) on the pressure side (32) and the suction side (34) to allow water droplets escaping from the leading edge (28) to flow.

A gas turbine engine assembly comprises a casing defining a gas path, the casing including a shroud having an annular body having a surface defining a portion of gas path, the shroud having slots configured for receiving inserted vanes. The slots are delimited substantially about their perimeter by respective flanges, the flanges radially offset from the shroud gas path surface so as to be disposed outside of said gas path, the flanges defined by opposed flange surfaces. Vanes received in the slots. Grommets engage the vanes at the slots. Inserts extend between the shroud and the grommets, the inserts having slots configured for engaging both of the opposed flanges, the inserts extending in a radial direction from at least the respective flange to an adjacent said shroud gas path surface to substantially matchingly mate with an inner surface the adjacent shroud gas path surface.