An air-jet cooling device for a casing of a turbomachine, in particular a turbine casing, including a cooling air housing having a wall, and a tube having a first end mounted on the wall of the housing so as to put the tube into fluid communication with the housing, orifices being formed in a wall of the tube in order to eject the cooling air coming from the housing on the casing. The tube has a section at the first end with a gradual variation that defines a boss. The boss has a curved surface to be immersed in the cooling air so as to avoid a detachment of a boundary layer of the cooling air at an interface between the first end of the tube and the housing.

Disclosed is an outer air seal, having: an axial member, the axial member extending axially from an axial front end to an axial aft end, and extending radially from a radial inner surface to a radial outer surface; a radial flange extending radially from the radial outer surface of the axial member to a radial outer tip, and extending axially from an axial front surface to an axial aft surface; and a first kerf slot defined through the axial member from the axial front end to the axial aft end and from the radial inner surface to the radial outer surface, and through the radial flange from the axial front surface to the axial aft surface, wherein a radial top end of the first kerf slot is radially spaced apart from the radial outer tip of the radial flange.

A method of operating a gas turbine engine includes commanding an acceleration of the gas turbine engine and moving a variable pitch high pressure compressor vane toward an open position thereby reducing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal. An active clearance control system of a gas turbine engine includes an engine control system configured to command an acceleration of the gas turbine engine and move a variable pitch high pressure compressor vane toward an open position thereby slowing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal located radially outboard of the high pressure turbine rotor.

A method of operating a gas turbine engine includes commanding an acceleration of the gas turbine engine and moving a variable pitch high pressure compressor vane toward an open position thereby reducing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal. An active clearance control system of a gas turbine engine includes an engine control system configured to command an acceleration of the gas turbine engine and move a variable pitch high pressure compressor vane toward an open position thereby slowing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal located radially outboard of the high pressure turbine rotor.

A hanger for a turbine engine can include a first surface confronting a cooling airflow, a second surface facing a heated airflow, and a third surface radially outward of the first surface. The hanger can also include a cyclonic separator with a dirty air inlet and a clean air outlet, as well as a cooling air circuit extending through the cyclonic separator.

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 and formed in a circumferential direction in the casing, the cooling plate being contracted by cold air supplied thereto, an upper plate mounted radially outside the cooling plate in the groove and having a plurality of cold air holes formed therein, a cylinder extending radially from an inner peripheral surface of the upper plate and having a plurality of cooling holes formed on a side 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 and formed in a circumferential direction in the casing, the cooling plate being contracted by cold air supplied thereto, an upper plate mounted radially outside the cooling plate in the groove and having a plurality of cold air holes formed therein, a cylinder extending radially from an inner peripheral surface of the upper plate and having a plurality of cooling holes formed on a side thereof, and a ring segment mounted radially inside the cooling plate.

A method of modulating a cooling supply in a gas turbine engine includes providing the engine comprising a compressor section and a turbine section and including a cooling flow circuit, the cooling flow circuit supplying a cooling air flow from a compressor cavity in the compressor section to a blade ring cavity in the turbine section, wherein the cooling flow circuit includes a main line with a full capacity valve, measuring a first pressure in the blade ring cavity, measuring a second pressure in the compressor cavity, adjusting, by a control system, the opening of the full capacity valve to control the cooling air flow through the main line in order to maintain a target pressure ratio, wherein the pressure ratio defined as a ratio of the first pressure to the second pressure. The method is performed in an ambient temperature operating range of the engine.

A turbine includes a rotor surrounded by a stator, a first movable stage including a series of rotating vanes, a second movable stage including a second series of rotating vanes, a distributor including a series of stationary vanes, the vanes including platforms jointly delimiting a separation between a main space in which a hot flow circulates through the vanes, and a secondary space surrounding a hub of the rotor. The rotor includes an aperture through which air is blown towards the secondary space, this air being discharged towards the main space. Straightening fins are carried by the distributor in the secondary space for straightening the air flow in order to change its gyration.

A turbine includes a rotor surrounded by a stator, a first movable stage including a series of rotating vanes, a second movable stage including a second series of rotating vanes, a distributor including a series of stationary vanes, the vanes including platforms jointly delimiting a separation between a main space in which a hot flow circulates through the vanes, and a secondary space surrounding a hub of the rotor. The rotor includes an aperture through which air is blown towards the secondary space, this air being discharged towards the main space. Straightening fins are carried by the distributor in the secondary space for straightening the air flow in order to change its gyration.