Abstract: Exhaust frequency mitigation apparatus, exhaust diffusers, and turbomachines are provided. An exhaust frequency mitigation apparatus includes a main body extending along an axial centerline from a base to a tip. the base defines a first diameter and the tip defining a second diameter. the main body converges from the first diameter to the second diameter with respect to the axial centerline. The base is configured to extend from an inner shell of a turbomachine exhaust diffuser. The exhaust frequency mitigation apparatus further includes at least one rib extending from a root coupled to the main body to a free end.

Abstract: Exhaust frequency mitigation apparatus, exhaust diffusers, and turbomachines are provided. An exhaust frequency mitigation apparatus includes a main body extending along an axial centerline from a base to a tip. the base defines a first diameter and the tip defining a second diameter. the main body converges from the first diameter to the second diameter with respect to the axial centerline. The base is configured to extend from an inner shell of a turbomachine exhaust diffuser. The exhaust frequency mitigation apparatus further includes at least one rib extending from a root coupled to the main body to a free end.

Abstract: A system includes a probe disposed through one or more walls of a turbomachine. The probe includes a sensing component configured to sense a parameter of the turbomachine. The probe also includes a body coupled to the sensing component, an inlet configured to receive a cooling inflow, a shell that defines a cooling passage, and an outlet. The sensing component is disposed on a warm side of the one or more walls. The inlet and the outlet are disposed on a cool side of the one or more walls. The cooling passage directs the cooling inflow toward the sensing component and toward the outlet. The outlet is configured to receive an outflow from the cooling passage, wherein the outflow includes at least a portion of the cooling inflow.

Abstract: A turbine or turbine system includes a compressor, a combustor, a turbine section, a diffuser with a parting line between two components, and a seal along the parting line. The seal includes a protrusion, a recess, and a flexible portion between the protrusion and the recess. The flexible portion has a bent cross-section perpendicular to the parting line. An outer surface of the bent cross-section contacts an inner surface of the recess. An inner surface of the bent cross-section contacts an outer surface of the protrusion. Sealing a parting line between two parts of a diffuser in a gas turbine system includes disposing a flexible portion between a protrusion and a recess of the two parts, contacting an outer surface of the bent cross-section with an inner surface of the recess, contacting an inner surface of the bent cross-section with an outer surface of the protrusion, and pressurizing the diffuser.

Abstract: A system includes a probe disposed through one or more walls of a turbomachine. The probe includes a sensing component configured to sense a parameter of the turbomachine. The probe also includes a body coupled to the sensing component, an inlet configured to receive a cooling inflow, a shell that defines a cooling passage, and an outlet. The sensing component is disposed on a warm side of the one or more walls. The inlet and the outlet are disposed on a cool side of the one or more walls. The cooling passage directs the cooling inflow toward the sensing component and toward the outlet. The outlet is configured to receive an outflow from the cooling passage, wherein the outflow includes at least a portion of the cooling inflow.

Abstract: A system includes a probe. The probe includes a sensing component configured to sense a parameter of a turbomachine. The probe also includes an inlet configured to receive a cooling inflow. The probe also includes a cooling passage configured to receive the cooling inflow from the inlet. The cooling passage is disposed along at least a portion of the probe, and the cooling inflow absorbs heat from the probe. The probe also includes an outlet coupled to the cooling passage and configured to receive an outflow from the cooling passage. The outflow includes at least a portion of the cooling inflow. The system also includes an ejector coupled to the outlet.

Abstract: An inner casing assembly for a turbine including: an annular inner casing including cooling passages, wherein each passage extends through a wall of the inner casing from a source of cooling fluid to an outer surface of the wall of the inner casing, and struts extending outward from the outer surface of the inner casing wherein the cooling passages are arranged on the inner casing such that a pair of the cooling passages is on opposite sides of each of the struts, and the cooling passages in each pair are equidistant to the corresponding strut.

Abstract: A turbine or turbine system includes a compressor, a combustor, a turbine section, a diffuser with a parting line between two components, and a seal along the parting line. The seal includes a protrusion, a recess, and a flexible portion between the protrusion and the recess. The flexible portion has a bent cross-section perpendicular to the parting line. An outer surface of the bent cross-section contacts an inner surface of the recess. An inner surface of the bent cross-section contacts an outer surface of the protrusion. Sealing a parting line between two parts of a diffuser in a gas turbine system includes disposing a flexible portion between a protrusion and a recess of the two parts, contacting an outer surface of the bent cross-section with an inner surface of the recess, contacting an inner surface of the bent cross-section with an outer surface of the protrusion, and pressurizing the diffuser.

Abstract: A system includes a probe. The probe includes a sensing component configured to sense a parameter of a turbomachine. The probe also includes an inlet configured to receive a cooling inflow. The probe also includes a cooling passage configured to receive the cooling inflow from the inlet. The cooling passage is disposed along at least a portion of the probe, and the cooling inflow absorbs heat from the probe. The probe also includes an outlet coupled to the cooling passage and configured to receive an outflow from the cooling passage. The outflow includes at least a portion of the cooling inflow. The system also includes an ejector coupled to the outlet.

Abstract: An inner casing assembly for a turbine including: an annular inner casing including cooling passages, wherein each passage extends through a wall of the inner casing from a source of cooling fluid to an outer surface of the wall of the inner casing, and struts extending outward from the outer surface of the inner casing wherein the cooling passages are arranged on the inner casing such that a pair of the cooling passages is on opposite sides of each of the struts, and the cooling passages in each pair are equidistant to the corresponding strut.

Abstract: A system is provided including a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an outer structure having an outer casing, an outer exhaust wall disposed along the exhaust flow path, and an outer cavity disposed between the outer exhaust wall and the outer casing. The turbine exhaust section further includes an inner structure having an inner exhaust wall disposed along the exhaust flow path, a bearing cavity disposed between the inner casing and a bearing housing. In addition, the turbine exhaust section includes a strut extending between the outer structure and the inner structure. The strut includes a first flow passage configured to flow a fluid from the bearing cavity to the outer cavity. The flow of fluid is thermally insulated from the strut.

Abstract: A seal for a turbine system includes a rotor, a bowl region and a stator assembly having a tip strip disposed proximate the rotor. Also included is a packing head disposed proximate the tip strip. Further included is a flex seal having a first end portion fixedly secured to at least one of the tip strip and the packing head, with a second end portion slidably engaged with at least one of the tip strip and the packing head.

Abstract: Apparatus for sealing and purging a bearing region includes a bearing housing having at least one hole that allows a flow of air to flow through the at least one hole, and at least one bearing seal that allows the flow of air to flow through the at least one bearing seal, thereby creating a pressure difference across the bearing seal. The apparatus also includes an air directional device having at least a portion of the flow of air to flow adjacent to the air directional device, and a pair of components having a gap between the pair of components that allows the at least a portion of the flow of air to flow through the gap, thereby purging the gap.

Abstract: A pressure containing casing for a turbine engine. The pressure containing casing may include a first extraction cavity, a second extraction cavity, an interface between the first extraction cavity and the second extraction cavity, and a wing seal positioned within the interface.

Abstract: Apparatus for sealing and purging a bearing region includes a bearing housing having at least one hole that allows a flow of air to flow through the at least one hole, and at least one bearing seal that allows the flow of air to flow through the at least one bearing seal, thereby creating a pressure difference across the bearing seal. The apparatus also includes an air directional device having at least a portion of the flow of air to flow adjacent to the air directional device, and a pair of components having a gap between the pair of components that allows the at least a portion of the flow of air to flow through the gap, thereby purging the gap.

Abstract: The present application provides a pressure containing casing. The pressure containing casing may include a first extraction cavity, a second extraction cavity, an interface between the first extraction cavity and the second extraction cavity, and a wing seal positioned within the interface.

Abstract: The present application thus provides for a turbine component cooling system. The component cooling system may include a turbine component, an airflow passing adjacent to the turbine component, and a seal positioned adjacent to the turbine component. The seal may include a number of apertures so as to allow the airflow to pass therethrough.