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.

A turbine assembly in a turbine section of an aircraft engine includes a rotor with blades having blade tips, and a turbine housing radially surrounding the blades. A distance between an inner surface of the housing and the blade tips defines a tip clearance gap. A passive cooling system for optimizing the tip clearance gap includes a cooling airflow passage located radially outward from, and in heat-transfer with, the turbine housing. The cooling airflow passage has an inlet opening located upstream of the rotor and an exit opening located downstream of the rotor. The inlet opening provides air flow into the cooling airflow passage. The exit opening provides air flow communication between the cooling airflow passage and a main gaspath of the turbine section. A flow of cooling air through the cooling airflow passage is induced, to cool the housing.

A turbine assembly in a turbine section of an aircraft engine includes a rotor with blades having blade tips, and a turbine housing radially surrounding the blades. A distance between an inner surface of the housing and the blade tips defines a tip clearance gap. A passive cooling system for optimizing the tip clearance gap includes a cooling airflow passage located radially outward from, and in heat-transfer with, the turbine housing. The cooling airflow passage has an inlet opening located upstream of the rotor and an exit opening located downstream of the rotor. The inlet opening provides air flow into the cooling airflow passage. The exit opening provides air flow communication between the cooling airflow passage and a main gaspath of the turbine section. A flow of cooling air through the cooling airflow passage is induced, to cool the housing.

There is provided a system and a method for controlling a tip clearance between a turbine casing and turbine blade tips of an aircraft engine. At least one operational parameter of the aircraft engine is obtained. Based on the at least one operational parameter, a current value of the tip clearance and a target value of the tip clearance are determined. A limiting factor to be applied to the target value of the tip clearance is computed. The limiting factor is applied to the target value of the tip clearance to obtain a tip clearance demand for the aircraft engine. A tip clearance control apparatus of the aircraft engine is controlled based on a difference between the current value of the tip clearance and the tip clearance demand.

There is provided a system and a method for controlling a tip clearance between a turbine casing and turbine blade tips of an aircraft engine. At least one operational parameter of the aircraft engine is obtained. Based on the at least one operational parameter, a current value of the tip clearance and a target value of the tip clearance are determined. A limiting factor to be applied to the target value of the tip clearance is computed. The limiting factor is applied to the target value of the tip clearance to obtain a tip clearance demand for the aircraft engine. A tip clearance control apparatus of the aircraft engine is controlled based on a difference between the current value of the tip clearance and the tip clearance demand.

A cooling device (11) for a turbine of a turbomachine extending along an axis includes at least one radially inner metal sheet (14) and one radially outer metal sheet (15) that are joined to one another and delimit, between them, cooling air circulation channels (17) extending circumferentially from a connection region (16). Each channel (17) includes at least one air inlet and air ejection orifices (19), that are designed to be oriented toward a region to be cooled. The cooling device also includes at least one cooling duct (21) intended for the circulation of cooling air, the duct (21) located radially outside said metal sheets (14, 15) and close to or in contact with the metal sheets so as to cool said metal sheets using the cooling air circulating in the duct (21), the cooling duct (21) extending axially and arranged toward the circumferential end regions of the channels (17).

A cooling device (11) for a turbine of a turbomachine extending along an axis includes at least one radially inner metal sheet (14) and one radially outer metal sheet (15) that are joined to one another and delimit, between them, cooling air circulation channels (17) extending circumferentially from a connection region (16). Each channel (17) includes at least one air inlet and air ejection orifices (19), that are designed to be oriented toward a region to be cooled. The cooling device also includes at least one cooling duct (21) intended for the circulation of cooling air, the duct (21) located radially outside said metal sheets (14, 15) and close to or in contact with the metal sheets so as to cool said metal sheets using the cooling air circulating in the duct (21), the cooling duct (21) extending axially and arranged toward the circumferential end regions of the channels (17).

An electroformed heat exchanger suitable for use between rotating blades and seals in a stationary casing of a turbine engine. The heat exchanger comprising a non-electroformed carrier plate having a radial outer surface and a radial outer surface, an electroformed duct provided along the radial outer surface, an electroformed rail provided on the radial inner surface, and an electroformed stiffener formed by a portion of the electroformed duct and the electroformed rail.

A device (26) for cooling an annular outer turbine casing (17) includes at least one circumferentially extending tube (27) having an air inlet intended for conveying cooling air, the tube having a radially inner wall provided with cooling air discharge openings and a radially outer wall arranged radially opposite each other, an air inlet manifold (28), the inlet of the tube opening into the manifold, the tube (27) including at least one intermediate wall extending over a circumferential portion of the tube from the air inlet, the intermediate wall being located radially between the radially inner wall and the radially outer wall, the radially inner wall and the intermediate wall forming a first air conveying duct, the radially outer wall and the intermediate wall forming a second air conveying duct extending circumferentially beyond the first air conveying duct, relative to the air inlet.

A valve assembly for an active clearance control (ACC) system in a gas turbine engine. The assembly comprises a first valve disc positioned within a first outlet duct, a second valve disc positioned within the second outlet duct, and a shaft coupled to the first and second valve discs such that rotation of the shaft rotates both the first and second valve discs within the first and second outlet ducts, respectively. A flow control member in the second outlet duct surrounds the second valve disc, and is configured to restrict fluid flow passing through the second outlet duct to a greater extent than the fluid flow passing through the first outlet duct for a given degree of rotation of the first and second valve discs. A corresponding ACC system, gas turbine and method is also provided.