Abstract: A passive flow modulation device according to an embodiment includes: a temperature sensitive element disposed within a first area; a piston coupled to the temperature sensitive element, the piston extending through a wall to a second area, wherein the first area is at a higher temperature than the second area; and a valve arrangement disposed in the second area and actuated by a distal end portion of the piston, the valve arrangement tangentially injecting a supply of cooling air through an angled orifice from the second area into the first area in response an increase in temperature in the first area.

Abstract: A thermal actuator is provided and includes an expansion material disposed and configured to move a movable element from a first movable element position toward a second movable element position in accordance with an expansion condition of the expansion material. The expansion material includes an inorganic salt mixture or a metal oxide mixture.

Abstract: A system includes a gas turbine engine that includes a combustor section having one or more combustors configured to generate combustion products, a turbine section having one or more turbine stages between an upstream end and a downstream end, an exhaust section disposed downstream from the downstream end of the turbine section, and a fluid supply system coupled to the exhaust section. The one or more turbine stages are driven by the combustion products. The exhaust section has an exhaust passage configured to receive the combustion products as an exhaust gas. The fluid supply system is configured to route a cooling gas to the exhaust section. The cooling gas has a temperature lower than the exhaust gas. The cooling gas includes an extracted exhaust gas, a gas separated from the extracted exhaust gas, carbon dioxide, carbon monoxide, nitrogen oxides, or a combination thereof.

Abstract: A system according to various embodiments includes: a cooling network within a turbine component, the cooling network including at least one passageway fluidly connected with a surface of the turbine component; a cooling fluid source for providing a cooling fluid to the cooling network; and a temperature-actuated flow modulating device fluidly connected with the cooling fluid source and the cooling network, the temperature-actuated flow modulating device configured to: detect an ambient air temperature proximate the turbine component; and control a flow of the cooling fluid to the cooling network based upon the detected ambient air temperature.

Abstract: A hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface of the substrate defines at least one interior space. At least a portion of the outer surface of the substrate includes a recess formed therein. The recess includes a bottom surface and a groove extending at least partially along the bottom surface of the recess. A cover is disposed within the recess and covers at least a portion of the groove. The groove is configured to channel a cooling fluid therethrough to cool the cover.

Abstract: A hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface defines an interior space. The outer surface defines a pressure side surface and a suction side surface. The pressure and suction side surfaces are joined together at a leading edge and at a trailing edge. A first cooling passage is formed in the suction side surface of the substrate. It is coupled in flow communication to the interior space. A second cooling passage, separate from the first cooling passage, is formed in the pressure side surface. The second cooling passage is coupled in flow communication to the interior space. A cover is disposed over at least a portion of the first and second cooling passages. The interior space channels a cooling fluid to the first and second cooling passages, which channel the cooling fluid therethrough to remove heat from the component.

Abstract: A cooling system for a hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface defines at least one interior space. A passage is formed in the substrate between the outer surface and the inner surface. An access passage is formed in the substrate and extends from the outer surface to the inner space. The access passage is formed at a first acute angle to the passage and includes a particle collection chamber. The access passage is configured to channel a cooling fluid to the passage. Furthermore, the passage is configured to channel the cooling fluid therethrough to cool the substrate.

Abstract: A method for providing micro-channels in a hot gas path component includes forming a first micro-channel in an exterior surface of a substrate of the hot gas path component. A second micro-channel is formed in the exterior surface of the hot gas path component such that it is separated from the first micro-channel by a surface gap having a first width. The method also includes disposing a braze sheet onto the exterior surface of the hot gas path component such that the braze sheet covers at least of portion of the first and second micro-channels, and heating the braze sheet to bond it to at least a portion of the exterior surface of the hot gas path component.

Abstract: A thermal valve is disclosed. The thermal valve may provide one or more flows of cooling fluid to a hot cavity within a cooling circuit of a gas turbine engine. The thermal valve may include a temperature sensitive element and a valve assembly in communication with the temperature sensitive element. The valve assembly may include at least one inlet in fluid communication with at least one cooling fluid source, at least one outlet in fluid communication with the hot cavity, and at least one valve in communication with the temperature sensitive element. The at least one valve may be disposed between the at least one inlet and the at least one outlet. The temperature sensitive element may be configured to move the at least one valve between a closed position and an open position.

Abstract: A component for a turbine engine includes a substrate that includes a first surface, and an insert coupled to the substrate proximate the substrate first surface. The component also includes a channel. The channel is defined by a first channel wall formed in the substrate and a second channel wall formed by at least one coating disposed on the substrate first surface. The component further includes an inlet opening defined in flow communication with the channel. The inlet opening is defined by a first inlet wall formed in the substrate and a second inlet wall defined by the insert.

Abstract: A thermally actuated assembly for a gas turbine assembly for a gas turbine system includes a heat transfer component having a first portion and a second portion, wherein the first portion is disposed within a first cavity having a first temperature and the second portion is disposed in a second cavity having a second temperature, wherein the heat transfer component extends through a cavity wall, wherein the first temperature is greater than the second temperature. Also included is a temperature sensitive element disposed within the second cavity and in operable communication with the heat transfer component. Further included is a flow manipulating device disposed within the second cavity and configured to displace in response to a temperature change in the first cavity.

Abstract: A method of manufacturing a component and a method of thermal management are provided. The methods include forming at least one portion of the component, printing a cooling member of the component and attaching the at least one portion to the cooling member of the component. The cooling member includes at least one cooling feature. The at least one cooling feature includes at least one cooling channel adjacent to a surface of the component, wherein printing allows for near-net shape geometry of the cooling member with the at least one cooling channel being located within a range of about 127 (0.005 inches) to about 762 micrometers (0.030 inches) from the surface of the component. The method of thermal management also includes transporting a fluid through at least one fluid pathway defined by the at least one cooling channel within the component to cool the component.

Abstract: A thermal actuator is provided and includes an expansion material disposed and configured to move a movable element from a first movable element position toward a second movable element position in accordance with an expansion condition of the expansion material. The expansion material includes an inorganic salt mixture or a metal oxide mixture.

Abstract: Embodiments of the disclosure include systems and methods for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity or a stator cavity. According to one embodiment, there is disclosed a turbine assembly. The turbine assembly may include a rotor assembly, a stator assembly positioned adjacent to the rotor assembly, and a wheel space cavity formed between the rotor assembly and the stator assembly. At least one fixed purge air orifice may be associated with the stator assembly. The fixed purge air orifice may be configured to provide a flow of purge air to the wheel space cavity. Moreover, at least one adjustable cooling air orifice may be associated with the stator assembly. The at least one adjustable cooling air orifice may be configured to provide a flow of cooling air to the wheel space cavity.

Abstract: A system includes a gas turbine engine that includes a combustor section having one or more combustors configured to generate combustion products, a turbine section having one or more turbine stages between an upstream end and a downstream end, an exhaust section disposed downstream from the downstream end of the turbine section, and a fluid supply system coupled to the exhaust section. The one or more turbine stages are driven by the combustion products. The exhaust section has an exhaust passage configured to receive the combustion products as an exhaust gas. The fluid supply system is configured to route a cooling gas to the exhaust section. The cooling gas has a temperature lower than the exhaust gas. The cooling gas includes an extracted exhaust gas, a gas separated from the extracted exhaust gas, carbon dioxide, carbon monoxide, nitrogen oxides, or a combination thereof.

Abstract: A pressure and temperature actuation system is provided having a high-temperature low-pressure zone, a low-temperature high-pressure zone, a boundary, a pressure actuated mechanism, and a temperature mechanism. A gas located in the high-temperature low-pressure zone has a greater gas temperature than the gas located in the low-temperature high-pressure zone. The gas located in the low-temperature high-pressure zone has a greater gas pressure than the gas located in the high-temperature low-pressure zone. The boundary separates the high-temperature low-pressure zone from the low-temperature high pressure zone. The pressure actuated mechanism is located within the boundary and is configured for opening at a specified gas pressure in either the high-temperature low-pressure zone or the low-temperature high-pressure zone.

Abstract: A thermally actuated assembly for a gas turbine assembly for a gas turbine system includes a heat transfer component having a first portion and a second portion, wherein the first portion is disposed within a first cavity having a first temperature and the second portion is disposed in a second cavity having a second temperature, wherein the heat transfer component extends through a cavity wall, wherein the first temperature is greater than the second temperature. Also included is a temperature sensitive element disposed within the second cavity and in operable communication with the heat transfer component. Further included is a flow manipulating device disposed within the second cavity and configured to displace in response to a temperature change in the first cavity.

Abstract: A test device for a compressor has a valve and ducting connected to the valve. A flow nozzle connected to the ducting has a corresponding coefficient of flow. A pressure sensor connected to the flow nozzle measures a pressure of a working fluid, and a flow rate of the working fluid is calculated using the pressure and the coefficient of flow. A method for testing a compressor includes operating the compressor at a first power level, measuring a flow rate of a working fluid at the first power level, adjusting a pressure of the working fluid to equal a first predetermined pressure, and measuring operating parameters of the compressor at the first power level. The method also includes adjusting the pressure of the working fluid to equal a second predetermined pressure and measuring operating parameters of the compressor at the first power level with the pressure of the working fluid at the second predetermined pressure.

Abstract: A pressure and temperature actuation system is provided having a high-temperature low-pressure zone, a low-temperature high-pressure zone, a boundary, a pressure actuated mechanism, and a temperature mechanism. A gas located in the high-temperature low-pressure zone has a greater gas temperature than the gas located in the low-temperature high-pressure zone. The gas located in the low-temperature high-pressure zone has a greater gas pressure than the gas located in the high-temperature low-pressure zone. The boundary separates the high-temperature low-pressure zone from the low-temperature high pressure zone. The pressure actuated mechanism is located within the boundary and is configured for opening at a specified gas pressure in either the high-temperature low-pressure zone or the low-temperature high-pressure zone.

Abstract: A test device for a compressor has a valve and ducting connected to the valve. A flow nozzle connected to the ducting has a corresponding coefficient of flow. A pressure sensor connected to the flow nozzle measures a pressure of a working fluid, and a flow rate of the working fluid is calculated using the pressure and the coefficient of flow. A method for testing a compressor includes operating the compressor at a first power level, measuring a flow rate of a working fluid at the first power level, adjusting a pressure of the working fluid to equal a first predetermined pressure, and measuring operating parameters of the compressor at the first power level. The method also includes adjusting the pressure of the working fluid to equal a second predetermined pressure and measuring operating parameters of the compressor at the first power level with the pressure of the working fluid at the second predetermined pressure.