Abstract: An annular nacelle for a turbine engine of an aircraft has a variable contour annular air inlet. The variable contour annular inlet includes annular outer and inner surface-defining radially-spaced structures on the forward portion of the nacelle, an annular member disposed between the annular outer and inner structures and coupled to the annular outer structure for sliding movement along the interiors of the annular outer and inner structures, and a plurality of actuating mechanisms coupled between the nacelle body and the annular member. The actuating mechanisms are operable for moving the annular member between forward and rearward positions.

Abstract: An assembly for mounting a plurality of circumferentially spaced and radially extending airfoils. In a preferred embodiment the assembly comprises a plurality of arcuate mounting fairings each including a central boss having at least one radially extending recess disposed in a radially inner surface thereof which contains an elastomeric boot for receiving an end of one of the plurality of airfoils. The mounting fairing further includes integral first and second flanges extending circumferentially outwardly from opposite sides of the boss portion which overlap complementary second and first flanges, respectively, of adjacent mounting fairings. Fastening means connect the first and second flanges of adjacent mounting fairings to form a continuous annular shroud.

Abstract: A turbine airfoil, such as a turbine blade or nozzle vane, is disclosed for use in a high temperature environment. The airfoil comprises a center post and at least one side piece. The side piece is attached to the center post so that, at room temperature, a clearance between the center post and the side piece permits limited relative movement between the post and side piece. This clearance space, however, is dimensioned so that at the operating temperature of the turbine, thermal expansion of the center post and/or side piece substantially eliminates the clearance as well as the limited movement between the center post and side piece.

Abstract: A two part metering adapter ring, for providing bleed air from the compressor of an aircraft engine, having a plurality of metering air flow passages. The adapter ring is secured to the outer casing stator support member and has a movable seal engaging a member on the inner casing stator support member. A pair of spring members hold the seal in contact with the seal engaging member on the inner casing stator support member.