Abstract: A sealing system for a rotary machine is provided. The sealing system includes a pair of circumferentially-adjacent rotary components and an axial seal. Each of the rotary components includes a platform including a first side channel and an opposite second side channel, a shank extending radially inwardly from the platform, and a dovetail region extending radially inwardly from the shank. The axial seal is sized and shaped to be received in the first side channel of a first of the rotary components and the second side channel of a second of the rotary components, such that the axial seal sealingly interfaces with the first and second channels.

Abstract: A cooling system for a turbine engine is provided. The turbine engine includes a compressor, a compressor discharge chamber (CDC), a combustor assembly, and a turbine coupled in a serial flow relationship such that a first portion of air from the CDC is channeled to the combustor assembly. The turbine is coupled to the compressor via a rotor. The cooling system includes an air duct configured to channel a second portion of air from the CDC to a mid-rotor region of the rotor, and a fluid supply system coupled to the air duct at a coupling. The fluid supply system is configured to channel a flow of fluid to the coupling. The coupling is configured to cool the second portion of CDC air via absorption of heat by the fluid from the second portion of CDC air.

Abstract: A gas turbine casing with an internal heat exchange system. The gas turbine extends between an inlet section and an exhaust section and defines a downstream direction from the inlet section to the exhaust section. The casing includes a forward end, an aft end downstream of the forward end, a first exterior surface facing radially outward, a second exterior surface facing radially inward, and an internal body at least partially defined between the first exterior surface and the second exterior surface. The heat exchange system includes an inlet and an outlet formed in an exterior surface of the casing proximate the aft end, a supply bore extending upstream from the inlet through the interior body of the casing, and a return bore extending downstream to the outlet through the interior body of the casing.

Abstract: A bearing housing configured to enclose a bearing assembly rotatable supporting a shaft coupled to a rotating assembly of a turbine engine, may include a housing base and a housing cover each including a flange for coupling the housing base to the housing cover. The housing cover may include an inner shell and an outer shell radially spaced outward of the inner shell to provide a cavity therebetween. The bearing housing may include a plurality of outlets arranged along an outer surface of the inner shell and configured to spray the pressurized cooling fluid to an inner surface of the housing cover defining the cavity. At least one of the outlets may be configured to spray the pressurized cooling fluid to a region of the inner surface of the housing cover that is adjacent to the flange of the housing cover.

Abstract: A sealing system for a rotary machine is provided. The sealing system includes a pair of circumferentially-adjacent rotary components and an axial seal. Each of the rotary components includes a platform including a first side channel and an opposite second side channel, a shank extending radially inwardly from the platform, and a dovetail region extending radially inwardly from the shank. The axial seal is sized and shaped to be received in the first side channel of a first of the rotary components and the second side channel of a second of the rotary components, such that the axial seal sealingly interfaces with the first and second channels.

Abstract: The turbomachine comprises a stationary component, a rotary component, rotatingly supported in the stationary component, and a sealing arrangement between the rotary component and the stationary component. A cooling arrangement is further provided, which is configured and designed for delivering a cooling fluid to the sealing arrangement and removing heat therefrom.

Abstract: A cooling system for a turbine engine is provided. The turbine engine includes a compressor, a compressor discharge chamber (CDC), a combustor assembly, and a turbine coupled in a serial flow relationship such that a first portion of air from the CDC is channeled to the combustor assembly. The turbine is coupled to the compressor via a rotor. The cooling system includes an air duct configured to channel a second portion of air from the CDC to a mid-rotor region of the rotor, and a fluid supply system coupled to the air duct at a coupling. The fluid supply system is configured to channel a flow of fluid to the coupling. The coupling is configured to cool the second portion of CDC air via absorption of heat by the fluid from the second portion of CDC air.

Abstract: A gas turbine casing with an internal heat exchange system. The gas turbine extends between an inlet section and an exhaust section and defines a downstream direction from the inlet section to the exhaust section. The casing includes a forward end, an aft end downstream of the forward end, a first exterior surface facing radially outward, a second exterior surface facing radially inward, and an internal body at least partially defined between the first exterior surface and the second exterior surface. The heat exchange system includes an inlet and an outlet formed in an exterior surface of the casing proximate the aft end, a supply bore extending upstream from the inlet through the interior body of the casing, and a return bore extending downstream to the outlet through the interior body of the casing.

Abstract: A bearing housing configured to enclose a bearing assembly rotatable supporting a shaft coupled to a rotating assembly of a turbine engine, may include a housing base and a housing cover each including a flange for coupling the housing base to the housing cover. The housing cover may include an inner shell and an outer shell radially spaced outward of the inner shell to provide a cavity therebetween. The bearing housing may include a plurality of outlets arranged along an outer surface of the inner shell and configured to spray the pressurized cooling fluid to an inner surface of the housing cover defining the cavity. At least one of the outlets may be configured to spray the pressurized cooling fluid to a region of the inner surface of the housing cover that is adjacent to the flange of the housing cover.

Abstract: The gas turbine engine (3) comprises a compressor section (9) configured for compressing combustion air, a combustor section (15) and a turbine section (21). The turbine section (21) comprises a turbine rotor (41) with a bladed wheel (43) rotating around a turbine rotation axis (A-A), an exhaust gas diffuser (65), and a casing (52) having an inner surface and an outer surface. The casing (52) further comprises a plurality of cooling fins (75) located on the outer surface thereof.

Abstract: A centrifugal compressor including: a casing; at least one impeller supported for rotation in the casing and provided with a hub, a shroud and an impeller eye; an impeller-eye sealing arrangement, for sealing the impeller in the region of said impeller eye. The centrifugal compressor further includes at least one cooling-medium portlocated at the impeller-eye sealing arrangement, arranged for delivering a cooling medium around the impeller eye.

Abstract: The turbomachine comprises a stationary component, a rotary component, rotatingly supported in the stationary component, and a sealing arrangement between the rotary component and the stationary component. A cooling arrangement is further provided, which is configured and designed for delivering a cooling fluid to the sealing arrangement and removing heat therefrom.

Abstract: A centrifugal compressor including: a casing; at least one impeller supported for rotation in the casing and provided with a hub, a shroud and an impeller eye; an impeller-eye sealing arrangement, for sealing the impeller in the region of said impeller eye. The centrifugal compressor further includes at least one cooling-medium portlocated at the impeller-eye sealing arrangement, arranged for delivering a cooling medium around the impeller eye.