Abstract: A liner support system for an exhaust liner in an aircraft engine. The liner support system includes a plurality of posts that space the exhaust liner from the exhaust duct, the plurality of posts spacing the exhaust liner from the exhaust duct further supporting the exhaust liner. Each post includes an interface region adjacent to the back side of the exhaust liner sealed to the back side of the exhaust liner, a shank extending to a low pressure region, and a hollow passageway internal to the shank, providing fluid communication between the interface region and the low pressure region. The low pressure region results in pressure against the liner, pulling the liner adjacent the post interface region against the post while preventing fluid leakage between the exhaust liner and the interface region. The posts create a pattern of alternating pressures in the liner allowing for elimination of hangers.

Abstract: A liner support system for an exhaust liner in an aircraft engine. The liner support system includes a plurality of posts that space the exhaust liner from the exhaust duct, the plurality of posts spacing the exhaust liner from the exhaust duct further supporting the exhaust liner. Each post includes an interface region adjacent to the back side of the exhaust liner sealed to the back side of the exhaust liner, a shank extending to a low pressure region, and a hollow passageway internal to the shank, providing fluid communication between the interface region and the low pressure region. The low pressure region results in pressure against the liner, pulling the liner adjacent the post interface region against the post while preventing fluid leakage between the exhaust liner and the interface region. The posts create a pattern of alternating pressures in the liner allowing for elimination of hangers.

Abstract: The mechanical damper is fabricated from a relatively thin metal spring stock and formed in cross-section to an E-shape that is arcuately bent into a ring that fits into the cavity defined between the inner diameter of the inner shroud and the outer diameter of the segmented back rings of the honeycomb sealing structure of the stator for the compressor of a gas turbine engine. The E-shaped damper is segmented and provides damping of the compressor stator of a gas turbine engine and is particularly adapted for stators that are formed from integrally cast stator vanes and shrouds.

Abstract: A spacer band for maintaining uniform spacing between adjacent compressor liner segments comprising two segments having a plurality of locking fingers extending from the band for engaging the casing at both ends of the liner segments and in the middle of the segments. The spacer band is located in a vertical channel located along an edge of each liner segment. The vertical channel is defined by a plurality of vertical flanges and a horizontal flange located on the edge of each liner segment. The horizontal flange has notches for receiving said locking fingers.

Abstract: An axial-flow compressor in which rotor blade clearance, in an area where the stator case surrounding a rotor blade stage is unsupported, is controlled by the cross-sectional area of a ring surrounding the stator case and by a gap between the inner surface of the ring and the outer surface of the stator case established at the time of compressor build.