An air seal (76) for a gas turbine engine platform (62) comprises a flow path platform, a seal retention ring (82), a finger seal (78). The seal retention ring (82) is situated radially adjacent the flow path platform (62). The finger seal (78) is retained by the seal retention ring (82) between the flow path platform (62) and the seal retention ring (82). The finger seal (78) comprises a first ply (96) with first keyhole slots (102), a second ply (98) with second keyhole slots (104) circumferentially offset relative to the first keyhole slots (102), and a foil layer (100). The foil layer (100) is disposed between the first and second plies (96, 98). The finger seal (78) has a series of cooling holes (94) in the outer circumferential segment (78B) to cool the outer diameter of the seal (76). In addition, leakage between the finger seal (78) and the flow path platform (62) cools the inner diameter of the seal (76).

Cooled finger seal

A seal assembly for a gas turbine engine (10) includes an engine static structure (30). First and second members fluidly separate cavities (52, 54, 56, 58) from one another. A seal assembly (46, 48) is captured by the engine structure (30). The seal assembly (46, 48) includes a carrier (70) and a seal (82) that engages the first member (88). The second member is captured by the carrier (70).

Gas turbine engine ring seal

A gas turbine engine component comprises a frame and a fairing. The frame comprises a monolithic ring-strut-ring structure. The fairing comprises a multi-segment ring-strut-ring structure that is assembled around the frame. A method of assembling the frame and fairing comprises positioning a plurality of shroud segments within a frame and joining the plurality of shroud segments to each other so that the fairing is trapped within the frame. In one embodiment, the fairing comprises a plurality of outer diameter shroud segments, a plurality of inner diameter shroud segments, a plurality of strut segments, and stiffening features connected to the plurality of strut segments to strengthen the fairing.

Multi-piece fairing for monolithic turbine exhaust case

A variable vane system for a gas turbine engine, comprising an actuator, a harmonic drive comprising a strain wave gearing mechanism comprising a fixed circular spline, a flex spline attached to an output shaft, and a wave generator attached to an input shaft driven by the actuator, the flex spline driven by the wave generator with respect to the circular spline, a drive gear driven by the output shaft along a first axis, and an actuator gear mounted to one of a multiple of variable vanes along a second axis transverse to the first axis, the actuator gear driven by the drive gear.

Off-axis electric actuation for variable vanes

A fairing sub-assembly 88 for a turbine frame comprises an inner ring 50, an outer ring 48 and a plurality of strut-shells. The inner ring is formed of a plurality of inner segments 82. The outer ring is formed of a plurality of outer segments 80. The plurality of strut-shells 84, 86 connecting the inner ring 48 and the outer ring 50. In another embodiment, the fairing sub-assembly comprises an inner band 45 joining the plurality of inner segments 82 and the plurality of strut-shells 86 to form outer slots, and an outer band 44 joining the plurality of outer segments 80 and the plurality of strut-shells 86 to form inner slots. A method of assembling a fairing 46 comprises inserting the aforementioned fairing sub-assembly 38 into an aft end of a turbine frame 42, inserting a plurality of forward strut-shells 84 into the outer and inner slots at a forward end of the turbine frame 42, and joining the forward strut-shells 84 to the fairing sub-assembly 88.

Bench aft sub-assembly for turbine exhaust case fairing

A seal assembly includes an annular base, a spring, a shoe, a first channel, a seal cover, and a seal. The spring includes a beam and is connected to the annular base. The shoe is disposed radially inward of the annular base and connected to the spring. The shoe includes an upstream portion, a downstream portion, and a lip connected to and extending radially outward from the upstream portion of the shoe. The spring extends from the annular base to the shoe. The first channel is positioned between the shoe and the beam of the spring. The seal is disposed between the seal cover and the shoe such that a downstream face of the seal is in contact with an upstream face of the shoe.

Floating non-contact seal vertical lip

A gas turbine engine assembly includes a second module interconnected with a first module along a joint such that a surface of a second radial wall faces a surface of a first radial wall, with a cavity defined in part by the first and second radial walls. A seal assembly includes a finger seal, and a seal support ring having a backing ring portion and a flow discourager arm. The backing ring is secured to one of the first radial wall and the second radial wall, and the flow discourager arm extends axially through the cavity into a recess formed in the other of the first and second radial walls. The finger seal includes a free end contacting an inner side of the flow discourager arm.

Gas turbine seal assembly and seal support

A gas turbine engine includes an engine casing structure and a retention block assembly. The engine casing structure includes a pocket which receives the retention block assembly. The retention block assembly includes a stop block and a pin that retains the stop block within the pocket. The stop block is loose relative to the pin.

Gas Turbine Engine Part Retention

A case assembly for a gas turbine engine is provided that includes an outer case with circumferentially spaced individual bosses that include a recess. A vane assembly is received in the outer case. An axial retention ring has uninstalled and installed conditions. The axial retention ring outside of the recess is in the uninstalled condition and received in the recess in the installed condition. An anti-rotation feature, such as a ring, is arranged between the bosses in a locking condition to prevent rotation of the axial retention ring between the installed and uninstalled conditions.

Conway Chuong

Papers

Floating non-contact seal vertical lip

Cooled finger seal

Gas turbine seal assembly and seal support

Gas Turbine Engine Part Retention

Axial retention feature for gas turbine engine vanes