A system for circumferentially distributing debris in a gas turbine engine includes a component that defines a component cooling channel that has an opening and is configured to receive a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris distribution surface positioned radially between the casing and the opening.

A system for circumferentially distributing debris in a gas turbine engine includes a component that defines a component cooling channel that has an opening and is configured to receive a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris distribution surface positioned radially between the casing and the opening.

A core for a fan containment includes an intermediate core segment and a plenum for fluid passage defined through the intermediate core segment. The intermediate core segment has an axial inlet side, an axial outlet side opposed to the axial inlet side, a radially inner side, and a radially outer side opposed to the radially inner side. The radially outer side is configured to be operatively connected to a cylindrical outer case and the radially inner side is configured to be operatively connected to at least one arcuate panel to form a liner assembly. The plenum extends through the intermediate core segment proximate the radially outer side for fluid passage between the axial inlet side and the axial outlet side.

A core for a fan containment includes an intermediate core segment and a plenum for fluid passage defined through the intermediate core segment. The intermediate core segment has an axial inlet side, an axial outlet side opposed to the axial inlet side, a radially inner side, and a radially outer side opposed to the radially inner side. The radially outer side is configured to be operatively connected to a cylindrical outer case and the radially inner side is configured to be operatively connected to at least one arcuate panel to form a liner assembly. The plenum extends through the intermediate core segment proximate the radially outer side for fluid passage between the axial inlet side and the axial outlet side.

A sector for the assembly of a stage of a turbine comprises a central and a peripheral portion; a plurality of blades attached between the central and the peripheral portions; a first and a second side opposite to each other, the first side is configured to join with the second side of another sector, the first side is provided with a first connecting portion and the second side is provided with a second connecting portion configured to mate with a first connecting portion of a first side of another sector.

A sector for the assembly of a stage of a turbine comprises a central and a peripheral portion; a plurality of blades attached between the central and the peripheral portions; a first and a second side opposite to each other, the first side is configured to join with the second side of another sector, the first side is provided with a first connecting portion and the second side is provided with a second connecting portion configured to mate with a first connecting portion of a first side of another sector.

This stationary turbine blade comprises: a stationary blade main body extending in the radial direction intersecting the flow direction of steam; a hydrophilic region which is formed on the surface of the stationary blade main body and which has a higher hydrophilicity than the other parts and has the radial dimension gradually increasing toward the downstream side in the flow direction; and a collecting portion which is provided on the downstream side of the hydrophilic region and which collects a liquid film flowing along the hydrophilic region.

A method and apparatus for the operation of a gas turbine unit with an evaporative intake air cooling system in the intake air pathway, wherein the return water flow of the evaporative intake air cooling system is used for the cooling of components of the gas turbine unit and/or of a generator coupled to the gas turbine unit and/or of another element coupled to the gas turbine unit, and a gas turbine unit adapted to be operated using this method.

A method and apparatus for the operation of a gas turbine unit with an evaporative intake air cooling system in the intake air pathway, wherein the return water flow of the evaporative intake air cooling system is used for the cooling of components of the gas turbine unit and/or of a generator coupled to the gas turbine unit and/or of another element coupled to the gas turbine unit, and a gas turbine unit adapted to be operated using this method.

A particle separator associated with a compressor section of a gas turbine engine includes a duct that defines a fluid flow path from a diffuser to a deswirl section. The duct includes a curved portion between an outlet of the diffuser and an inlet of the deswirl section. The curved portion is configured to have at least one low velocity region and a high velocity region. The particle separator includes at least one cluster of inlet passages defined at the at least one low velocity region. The particle separator includes a scavenge plenum coupled to the duct and in fluid communication with the at least one cluster of inlet passages. At least one outlet slot is defined through the duct downstream of the at least one cluster of inlet passages in the high velocity region and is in fluid communication with the scavenge plenum.