United Technologies Corporation

Martin G Tabbita

James Preston Downs

Thomas A Auxier

Friedrich O Soechting

James Thompson Beals

Vincent C Nardone

Frederick W Steinbauer, Jr

Kenneth D Moore

A method for manufacturing a brush seal is provided including the steps of: (a) providing fiber; (b) providing a packing material; (c) providing a pair of backing plates; (d) arranging the fiber in a particular arrangement; (e) applying the packing material to selective areas of the arranged fiber; (f) cutting the fibers in bristle sections, wherein each of the bristle sections includes a plurality of bristles and one of the selective areas having applied packing material; (g) stacking the bristle sections, such that the selective areas of applied packing material are aligned between the backing plates; and (h) bonding the backing plates, the bristle sections, and the packing material together.

Method of manufacturing a brush seal

A hollow airfoil is provided which includes a body, a trench, and a plurality of cooling apertures disposed within the trench. The body extends chordwise between a leading edge and a trailing edge, and spanwise between an outer radial surface and an inner radial surface, and includes an external wall surrounding a cavity. The trench is disposed in the external wall along the leading edge, extends in a spanwise direction, and is aligned with a stagnation line extending along the leading edge.

Apparatus for cooling an airfoil for a gas turbine engine

A hollow airfoil is provided which includes a body having an external wall and an internal cavity. The external wall includes a suction side portion and a pressure side portion. The portions extend chordwise between a leading edge and a trailing edge and spanwise between an inner radial surface and an outer radial surface. A stagnation line extends along the leading edge. A plurality of cooling apertures, disposed spanwise along the leading edge. According to one aspect of the present invention, the apertures extend through the external wall along a helical path. According to another aspect of the present invention, the apertures are alternately directed towards the suction side portion and the pressure side portions of the airfoil.

Hollow airfoil for a gas turbine engine

Apparatus and method for cooling an airfoil for a gas turbine engine

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West Palm Beach, FL, United States of America

Martin G Tabbita