Abstract: A combustion turbine includes a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustion section. A diffuser section is downstream from the turbine section and has an outer wall, an inner wall, and at least one strut member extending therebetween. The outer wall has at least one first gas passageway therein, the inner wall has at least one second gas passageway therein, and the at least one strut member has at least one third gas passageway therein. The at least one first, second and third gas passageways deliver gas therethrough to assist attachment of a boundary layer to adjacent surfaces of the outer wall, the inner wall, and the at least one strut, respectively.

Abstract: A cover assembly disposed about a rotor in a gas turbine engine. The cover assembly comprises a first cover, a second cover, and securing structure. The first cover is disposed about the rotor and comprises a forward end and an opposed aft end. The first cover is associated with a case mounting structure that is fixed to an engine casing. The second cover is disposed about the rotor and comprises a forward end and an opposed aft end. At least a portion of the first cover is disposed radially outwardly from the second cover. The securing structure couples the first cover to the second cover and permits relative radial movement between the first and second covers.

Abstract: A cover assembly disposed about a rotor in a gas turbine engine. The cover assembly comprises a first cover, a second cover, and securing structure. The first cover is disposed about the rotor and comprises a forward end and an opposed aft end. The first cover is associated with a case mounting structure that is fixed to an engine casing. The second cover is disposed about the rotor and comprises a forward end and an opposed aft end. At least a portion of the first cover is disposed radially outwardly from the second cover. The securing structure couples the first cover to the second cover and permits relative radial movement between the first and second covers.

Abstract: A seal assembly (52, 54) for a gas turbine engine (10). The seal assembly (52, 54) includes a first seal member (40) including an abradable structure having at least first and second seal portions (58, 64) radially spaced from each other, and a second seal member (44) including first and second seal surfaces (56, 62) located in facing relationship to the first and second seal portions (58, 64), respectively. The first seal member (40) is formed of a honeycomb structure, and the first seal portion (58) of the first seal member (40) is a thin fin-like structure having a width in the axial direction of the turbine engine (10) that is less than the width of the second seal portion (64) in the axial direction.

Abstract: A combustion turbine includes a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustion section. A diffuser section is downstream from the turbine section and has an outer wall, an inner wall, and at least one strut member extending therebetween. The outer wall has at least one first gas passageway therein, the inner wall has at least one second gas passageway therein, and the at least one strut member has at least one third gas passageway therein. The at least one first, second and third gas passageways deliver gas therethrough to assist attachment of a boundary layer to adjacent surfaces of the outer wall, the inner wall, and the at least one strut, respectively.

Abstract: Aspects of the invention are directed to a system for improving engine performance by reducing vane tip clearances in the compressor section of a turbine engine. According to aspects of the invention, an abrasive material can be attached to a rotor disc. Thus, if a vane tip contacts the rotor disc during engine operation, the vane tip is worn away by the abrasive material. The system can reduce the risk of substantial component damage resulting from a vane tip rubbing event. The abrasive material can be provided in the form of an insert that can be removably attached to the rotor disc. Thus, the insert can be readily removed and replaced when necessary.

Abstract: The gas turbine engine includes a compressor section, a combustion section downstream from the compressor section and a turbine section downstream from the combustion section. The turbine section includes a rotor shaft, a plurality of turbine blades, and a plurality of discs coupling corresponding ones of the plurality of turbine blades to the rotor shaft. Each disc has a plurality of disc cooling fluid passages therein associated with cooling the turbine blades, and a respective thermal shape memory sleeve is in at least some of the disc cooling fluid passages. The thermal shape memory sleeve defines a sleeve throat opening that changes based upon a temperature to adjust a flow of cooling fluid therethrough. Part load efficiency may be increased by supplying only the needed cooling fluid to areas of the blades.

Abstract: Aspects of the invention are directed to a system for improving engine performance by reducing vane tip clearances in the compressor section of a turbine engine. According to aspects of the invention, an abrasive material can be attached to a rotor disc. Thus, if a vane tip contacts the rotor disc during engine operation, the vane tip is worn away by the abrasive material. The system can reduce the risk of substantial component damage resulting from a vane tip rubbing event. The abrasive material can be provided in the form of an insert that can be removably attached to the rotor disc. Thus, the insert can be readily removed and replaced when necessary.

Abstract: A biased, wear resistant seal assembly for sealing gas flow paths in a turbine system includes a planar shim having transverse legs at each end, a flattened leaf spring to urge the shim into sealing contact with the sealing surfaces of the turbine parts, and a shim protection material to avoid wear to the shim on the contact side. The shim protection material can include one or more metal fiber cloth layers secured to the shim, for example, by seam welding to a pair of rails or to the legs of the shim.

Abstract: A biased, wear resistant seal assembly for sealing gas flow paths in a turbine system includes a planar shim having transverse legs at each end, a flattened leaf spring to urge the shim into sealing contact with the sealing surfaces of the turbine parts, and a shim protection material to avoid wear to the shim on the contact side. The shim protection material can include one or more metal fiber cloth layers secured to the shim, for example, by seam welding to a pair of rails or to the legs of the shim.