Abstract: Various embodiments include a heat transfer device, a turbomachine casing and a related storage medium. In some cases, the device includes: a body having an outer surface and an inner cavity within the outer surface; at least one aperture extending through the body, the at least one aperture positioned to direct fluid from the inner cavity through the body to the outer surface; a first lip proximate a first end of the body, and a second lip proximate a second end of the body, the first lip and the second lip each extending radially outward from the outer surface relative to a direction of flow of the fluid through the inner cavity; and a plug coupled with the body, the plug for obstructing an end of the inner cavity, the plug positioned to redirect flow of the fluid from a first direction to a second, distinct direction.

Abstract: A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a combustor assembly fluidically connected to each of the compressor portion and the turbine portion. A turbine casing includes a body having an outer surface and an inner surface. A clearance control system includes a plurality of fluidically connected fluid channels extending through the turbine casing. The plurality of fluidically connected fluid channels includes a first fluid channel configured to direct a fluid flow in a first axial direction, a circumferential fluid channel configured to direct the fluid flow in a circumferential direction, and a second fluid channel configured to direct the fluid flow in a second axial direction substantially opposite the first axial direction. The first fluid channel includes a first outlet passing through the inner surface, and the second fluid channel including a second outlet passing through the inner surface.

Abstract: Various embodiments include a heat transfer device, a turbomachine casing and a related storage medium. In some cases, the device includes: a body having an outer surface and an inner cavity within the outer surface; at least one aperture extending through the body, the at least one aperture positioned to direct fluid from the inner cavity through the body to the outer surface; a first lip proximate a first end of the body, and a second lip proximate a second end of the body, the first lip and the second lip each extending radially outward from the outer surface relative to a direction of flow of the fluid through the inner cavity; and a plug coupled with the body, the plug for obstructing an end of the inner cavity, the plug positioned to redirect flow of the fluid from a first direction to a second, distinct direction.

Abstract: A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a combustor assembly fluidically connected to each of the compressor portion and the turbine portion. A turbine casing includes a body having an outer surface and an inner surface. A clearance control system includes a plurality of fluidically connected fluid channels extending through the turbine casing. The plurality of fluidically connected fluid channels includes a first fluid channel configured to direct a fluid flow in a first axial direction, a circumferential fluid channel configured to direct the fluid flow in a circumferential direction, and a second fluid channel configured to direct the fluid flow in a second axial direction substantially opposite the first axial direction. The first fluid channel includes a first outlet passing through the inner surface, and the second fluid channel including a second outlet passing through the inner surface.

Abstract: Systems and devices configured for active thermal control of turbine components are disclosed. In one embodiment, a thermal control system for a turbine includes: a thermal source shaped to connect to a turbine; a set of sensors disposed about the turbine and configured to obtain operational data from the turbine; and a computing device communicatively connected to the thermal source and the set of sensors, the computing device configured to regulate a thermal input of the thermal source to the turbine based on the operational data obtained by the set of sensors.

Abstract: Systems and devices configured for active thermal control of turbine components are disclosed. In one embodiment, a thermal control system for a turbine includes: a thermal source shaped to connect to a turbine; a set of sensors disposed about the turbine and configured to obtain operational data from the turbine; and a computing device communicatively connected to the thermal source and the set of sensors, the computing device configured to regulate a thermal input of the thermal source to the turbine based on the operational data obtained by the set of sensors.