Abstract: An article is disclosed including a manifold, an article wall having at least one external aperture, and a post-impingement cavity disposed between the manifold and the article wall. The manifold includes an impingement plate defining a plenum having a plenum surface, and at least one impingement aperture. The at least one impingement aperture interfaces with the plenum at an intake aperture having a flow modification structure, which, together with the at least one impingement aperture, defines an exhaust aperture. The manifold exhausts a fluid from the plenum into the intake aperture, through the at least one impingement aperture, out the exhaust aperture, into the post-impingement cavity, and through the at least one external aperture.

Abstract: An article is disclosed including a manifold, an article wall having at least one external aperture, and a post-impingement cavity disposed between the manifold and the article wall. The manifold includes an impingement plate defining a plenum having a plenum surface, and at least one impingement aperture. The at least one impingement aperture interfaces with the plenum at an intake aperture having a flow modification structure, which, together with the at least one impingement aperture, defines an exhaust aperture. The manifold exhausts a fluid from the plenum into the intake aperture, through the at least one impingement aperture, out the exhaust aperture, into the post-impingement cavity, and through the at least one external aperture.

Abstract: The present application provides a combustion system for use with a cooling flow. The combustion system may include a head end, an aft end, a transition nozzle extending from the head end to the aft end, and an impingement sleeve surrounding the transition nozzle. The impingement sleeve may define a first cavity in communication with the head end for a first portion of the cooling flow and a second cavity in communication with the aft end for a second portion of the cooling flow. The transition nozzle may include a number of cooling holes thereon in communication with the second portion of the cooling flow.

Abstract: A turbomachine passage cleaning system includes a first airflow passage having a first inlet configured and disposed to fluidly connect to a compressor portion, a first outlet configured and disposed to fluidly connect to a turbine portion, and a first intermediate portion including a first strainer. A second airflow passage is fluidly coupled to the first airflow passage. The second airflow passage has a second intermediate portion having second strainer. A first valve is arranged in the first intermediate portion upstream from the first strainer, and a second valve is arranged in the second intermediate portion upstream from the second strainer. The first and second valves are selectively operated to control fluid flow into respective ones of the first and second airflow passages to filter air passing from a turbomachine compressor portion to a turbomachine turbine portion.

Abstract: Turbine components include at least one fluid flow passage at least one aperture disposed on a surface of the turbine component and fluidly connected to the at least one fluid flow passage. The at least one aperture includes a floor extending from the at least one fluid flow passage to the surface; and, a step disposed between an inner portion of the floor and an outer portion of the floor such that the inner portion of the floor and the outer portion of the floor do not comprise a single planar surface.

Abstract: A flow control system is provided. The flow control system includes at least one control valve coupled to at least one nozzle of a turbine engine, wherein the control valve is configured to regulate fluid flow in a first direction or a second direction. The first direction is when the fluid is channeled from a compressor to the nozzle and the second direction is when the fluid is channeled from the nozzle to an exhaust section of the turbine engine. A controller is coupled to the control valve and is configured to control the fluid flow in the first direction during operation of the turbine engine and to change the direction of the fluid flow from the first direction to the second direction to facilitate reconditioning of the turbine engine.

Abstract: A system includes a gas turbine engine, which includes a compressor configured to generate compressed air and a turbine. The turbine includes a stationary component and a conduit configured to convey the compressed air from the compressor to the stationary component in a forward direction. The gas turbine engine also includes a flow control device coupled to the conduit. The conduit is configured to convey a gas path air from the stationary component in a reverse direction opposite from the forward direction when the flow control device is in a startup mode. The gas turbine engine also includes a shaft coupled to the compressor and the turbine.

Abstract: An improved nozzle vane for a gas turbine engine, comprising a vane wall having inner and outer wall surfaces, the wall surfaces being spaced from one another to define a plurality of fluid passageways for a cooling medium; discreet cavities formed by interior wall members disposed between the inner and outer wall surfaces and within the fluid passageway for the cooling medium; a plurality of impingement cooling sleeves disposed in the discreet cavities defined by the inner and outer wall surfaces and by interior wall members; and a plurality of non-round, e.g., serrated, openings in each of the impingement cooling sleeves, with the openings being sufficient in size and number to accommodate the flow of a cooling media.

Abstract: Turbine systems are provided. In one embodiment, a turbine system includes a transition duct comprising an inlet, an outlet, and a duct passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The duct passage includes an upstream portion extending from the inlet and a downstream portion extending from the outlet. The turbine system further includes a rib extending from an outer surface of the duct passage, the rib dividing the upstream portion and the downstream portion.

Abstract: Turbine systems are provided. In one embodiment, a turbine system includes a transition duct comprising an inlet, an outlet, and a duct passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The duct passage includes an upstream portion extending from the inlet and a downstream portion extending from the outlet. The turbine system further includes a rib extending from an outer surface of the duct passage, the rib dividing the upstream portion and the downstream portion.

Abstract: A system includes a gas turbine engine, which includes a compressor configured to generate compressed air and a turbine. The turbine includes a stationary component and a conduit configured to convey the compressed air from the compressor to the stationary component in a forward direction. The gas turbine engine also includes a flow control device coupled to the conduit. The conduit is configured to convey a gas path air from the stationary component in a reverse direction opposite from the forward direction when the flow control device is in a startup mode. The gas turbine engine also includes a shaft coupled to the compressor and the turbine.

Abstract: According to one aspect of the invention, a turbine includes a first sidewall, an airfoil positioned between the first sidewall and a second sidewall and a first passage in the airfoil proximate a high temperature region, the first passage configured to receive a cooling fluid, wherein the high temperature region is near an interface of the first sidewall and a trailing edge of the airfoil. The turbine further includes a first diffuser in fluid communication with the first passage, the first diffuser configured to direct the cooling fluid to form a film on a surface of the first sidewall.

Abstract: A flow control system is provided. The flow control system includes at least one control valve coupled to at least one nozzle of a turbine engine, wherein the control valve is configured to regulate fluid flow in a first direction or a second direction. The first direction is when the fluid is channeled from a compressor to the nozzle and the second direction is when the fluid is channeled from the nozzle to an exhaust section of the turbine engine. A controller is coupled to the control valve and is configured to control the fluid flow in the first direction during operation of the turbine engine and to change the direction of the fluid flow from the first direction to the second direction to facilitate reconditioning of the turbine engine.

Abstract: The present application provides a combustion system for use with a cooling flow. The combustion system may include a head end, an aft end, a transition nozzle extending from the head end to the aft end, and an impingement sleeve surrounding the transition nozzle. The impingement sleeve may define a first cavity in communication with the head end for a first portion of the cooling flow and a second cavity in communication with the aft end for a second portion of the cooling flow. The transition nozzle may include a number of cooling holes thereon in communication with the second portion of the cooling flow.

Abstract: A turbomachine passage cleaning system includes a first airflow passage having a first inlet configured and disposed to fluidly connect to a compressor portion, a first outlet configured and disposed to fluidly connect to a turbine portion, and a first intermediate portion including a first strainer. A second airflow passage is fluidly coupled to the first airflow passage. The second airflow passage has a second intermediate portion having second strainer. A first valve is arranged in the first intermediate portion upstream from the first strainer, and a second valve is arranged in the second intermediate portion upstream from the second strainer. The first and second valves are selectively operated to control fluid flow into respective ones of the first and second airflow passages to filter air passing from a turbomachine compressor portion to a turbomachine turbine portion.

Abstract: An improved nozzle vane for a gas turbine engine, comprising a vane wall having inner and outer wall surfaces, the wall surfaces being spaced from one another to define a plurality of fluid passageways for a cooling medium; discreet cavities formed by interior wall members disposed between the inner and outer wall surfaces and within the fluid passageway for the cooling medium; a plurality of impingement cooling sleeves disposed in the discreet cavities defined by the inner and outer wall surfaces and by interior wall members; and a plurality of non-round, e.g., serrated, openings in each of the impingement cooling sleeves, with the openings being sufficient in size and number to accommodate the flow of a cooling media.

Abstract: An apparatus for removing heat from a turbine includes a stator having a cavity and a first plenum and a second plenum inside the cavity. The second plenum is connected to the first plenum and surrounds the first plenum inside the cavity. A refrigerant flows through the first plenum and the second plenum to remove heat from the stator. A method for cooling a turbine includes forming a cavity in a component to be cooled, installing a first plenum inside the cavity, and installing a second plenum inside the cavity. The method further includes connecting the second plenum to the first plenum, surrounding the first plenum with the second plenum inside the cavity, and flowing a refrigerant through the first plenum and the second plenum to cool the component.

Abstract: According to one aspect of the invention, a turbine includes a first sidewall, an airfoil positioned between the first sidewall and a second sidewall and a first passage in the airfoil proximate a high temperature region, the first passage configured to receive a cooling fluid, wherein the high temperature region is near an interface of the first sidewall and a trailing edge of the airfoil.

Abstract: An apparatus for removing heat from a turbine includes a stator having a cavity and a first plenum and a second plenum inside the cavity. The second plenum is connected to the first plenum and surrounds the first plenum inside the cavity. A refrigerant flows through the first plenum and the second plenum to remove heat from the stator. A method for cooling a turbine includes forming a cavity in a component to be cooled, installing a first plenum inside the cavity, and installing a second plenum inside the cavity. The method further includes connecting the second plenum to the first plenum, surrounding the first plenum with the second plenum inside the cavity, and flowing a refrigerant through the first plenum and the second plenum to cool the component.