Abstract: A seal assembly in a gas turbine engine is presented. The seal assembly is arranged at a forward side of an inner compressor exit diffusor. The seal assembly is arranged between an outlet guide vane assembly and the forward side of the inner compressor exit diffusor to reduce cooling air leakage therebetween or is arranged between adjacent outlet guide vane assemblies to reduce cooling air leakage therebetween. The seal assembly includes a plurality of seal segments. The seal assembly includes at least one seal, such as a brush seal.

Abstract: A non-contact seal assembly for sealing a gap between relatively rotatable components in a gas turbine engine is presented. The non-contact seal assembly includes a primary seal having a radially movable seal shoe, a mid-plate, an aft secondary seal radially movable along with the seal shoe, a forward secondary seal and a U-shaped seal carrier for holding the components together using pins. The seal shoe includes a plurality of seal shoe segments. The aft secondary seal includes a plurality of aft secondary seal segments. Each aft secondary seal segment is attached to each seal shoe segment. Each aft secondary seal segment includes at least a notch at outer radial side to receive the pin for accommodating radial movement of the seal shoe segment.

Abstract: A non-contact seal assembly for sealing a circumferential gap between a first machine component and a second machine component which is rotatable relative to the first machine component about a longitudinal axis is provided. The non-contact seal assembly includes a seal carrier, a primary seal that includes a plurality of shoes, a mid plate, a secondary seal, and a front plate. The secondary seal may comprise a plurality of sealing segments. The non-contact seal also includes a plurality of damping elements to damp vibrations of the primary seal during operation.

Abstract: A non-contact seal assembly for sealing a gap between relatively rotatable components in a gas turbine engine is presented. The non-contact seal assembly includes a primary seal having a radially movable seal shoe, a mid-plate, an aft secondary seal radially movable along with the seal shoe, a forward secondary seal and a U-shaped seal carrier for holding the components together using pins. The seal shoe includes a plurality of seal shoe segments. The aft secondary seal includes a plurality of aft secondary seal segments. Each aft secondary seal segment is attached to each seal shoe segment. Each aft secondary seal segment includes at least a notch at outer radial side to receive the pin for accommodating radial movement of the seal shoe segment.

Abstract: A seal assembly in a gas turbine engine is presented. The seal assembly is arranged at a forward side of an inner compressor exit diffusor. The seal assembly is arranged between an outlet guide vane assembly and the forward side of the inner compressor exit diffusor to reduce cooling air leakage therebetween or is arranged between adjacent outlet guide vane assemblies to reduce cooling air leakage therebetween. The seal assembly includes a plurality of seal segments. The seal assembly includes at least one seal, such as a brush seal.

Abstract: A mid-frame section of a gas turbine engine having a radial clearance adjustability and a method for adjusting a radial clearance to a rotor in a mid-frame section of a gas turbine engine are presented. The mid-frame section includes a radial clearance adjusting assembly arranged at a compressor exit diffusor. The radial clearance adjusting assembly is configured to adjust the radial clearance to the rotor such that the rotor is concentric with respect to components of the mid-frame section, such as the compressor exit diffusor and shaft cover. The radial clearance adjusting assembly provides radial clearance adjustability in the mid-frame section at multiple locations, such as at forward end and aft end of the compressor exit diffusor. The radial clearance adjusting assembly improves efficiency of the gas turbine and reduces service and operating cost of the gas turbine engine.

Abstract: A seal assembly for sealing a circumferential gap between a first machine component and a second machine component which is rotatable relative to the first machine component about a longitudinal axis. The seal assembly includes a seal carrier, a primary seal, a mid plate, at least one secondary seal, and a front plate. The at least one secondary seal includes at least one sealing element. The at least one sealing element and the mid plate each have one of at least one pin or at least one hole that collectively prevent rotation for the at least one sealing element within the seal assembly.