The present disclosure is directed to an aircraft power generation system including a reverse Brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. The reverse Brayton cycle system includes a compressor, a driveshaft, a turbine, and a first exchanger. The driveshaft is rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine are in serial flow arrangement. The gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.

The present disclosure is directed to an aircraft power generation system including a reverse Brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. The reverse Brayton cycle system includes a compressor, a driveshaft, a turbine, and a first exchanger. The driveshaft is rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine are in serial flow arrangement. The gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.

A system for modulating airflow into a bore defined by a rotor of a gas turbine engine defining an axial direction, a circumferential direction, and a radial direction is provided. The system includes a movable member positioned forward of a first stage of rotor blades of the rotor. The movable member is movable between at least a first position and a second position to modulate airflow into the bore via a plurality of opening in fluid communication with the bore.

The invention concerns a cooling device (21) extending circumferentially around a turbo machine housing, such as a turbine housing, having at least one cooling module (30a, 30b, 30c) comprising a tube holder (31, 32) having at least one plate, preferably a radially inner plate (31) and a radially outer plate (32) fixed to each other, the tube holder (31, 32) defining at least two axially spaced housings (34a), each housing (34a) receiving a tube (23) and a sleeve (38) mounted around each tube (23), each tube (23) extending circumferentially around the housing, each cooling module (30a, 30b, 30c) having first fastening means capable of firmly holding its tube holder (31, 32) with respect to the housing, the fixing means comprising at least one spacer (41) having a radially inner end intended to bear against the housing and a radially outer end bearing on the single or on one of the sheets of the tube support (31, 32).

The invention concerns a cooling device (21) extending circumferentially around a turbo machine housing, such as a turbine housing, having at least one cooling module (30a, 30b, 30c) comprising a tube holder (31, 32) having at least one plate, preferably a radially inner plate (31) and a radially outer plate (32) fixed to each other, the tube holder (31, 32) defining at least two axially spaced housings (34a), each housing (34a) receiving a tube (23) and a sleeve (38) mounted around each tube (23), each tube (23) extending circumferentially around the housing, each cooling module (30a, 30b, 30c) having first fastening means capable of firmly holding its tube holder (31, 32) with respect to the housing, the fixing means comprising at least one spacer (41) having a radially inner end intended to bear against the housing and a radially outer end bearing on the single or on one of the sheets of the tube support (31, 32).

An induction heater is employed with a gas turbine engine in order to heat a static component of the gas turbine engine. The heating of the static component is performed such that the clearance space between the static component and a rotating component remains constant during steady state conditions and transient conditions.

An induction heater is employed with a gas turbine engine in order to heat a static component of the gas turbine engine. The heating of the static component is performed such that the clearance space between the static component and a rotating component remains constant during steady state conditions and transient conditions.

An apparatus for controlling tip clearance between a turbine casing and a turbine blade is provided. The apparatus for controlling tip clearance includes a casing surrounding the turbine blade, a cooling plate installed in a groove, formed in a circumferential direction in the casing, and contracted by cold air supplied thereto, the cooling plate having at least one fin formed on an outer peripheral surface thereof, and a ring segment mounted radially inside the cooling plate.

An apparatus for controlling tip clearance between a turbine casing and a turbine blade is provided. The apparatus for controlling tip clearance includes a casing surrounding the turbine blade, a cooling plate installed in a groove, formed in a circumferential direction in the casing, and contracted by cold air supplied thereto, the cooling plate having at least one fin formed on an outer peripheral surface thereof, and a ring segment mounted radially inside the cooling plate.

A heatshield for a gas turbine engine includes a main body having a leading edge, a trailing edge, lateral edges, a first surface and a second surface, the first surface being exposed to a hot working gas in use passing through the gas turbine engine. The main body having an array of cooling channels for conveying a coolant flow, where each cooling channel of the array of cooling channels having a surface. At least one cooling channel of the array of cooling channels includes at least one flow disturbing feature extending from the surface and into the cooling channel.