The present disclosure concerns removal of entrained contaminant particles in a coolant airflow for a gas turbine engine. Example embodiments include a coolant airflow assembly for a gas turbine engine, comprising: a coolant feed passage connected between a supply of coolant air and an inlet of a component to be cooled, the coolant feed passage defining a coolant airflow path and comprising first and second opposing internal faces (305, 306), the inlet of the component connected to the coolant airflow path through one of the first and second internal faces (305, 306) of the coolant feed passage; and a particulate filter for removing entrained particles from the coolant airflow path, comprising: a first filter panel extending from the first face into the coolant airflow path upstream of the inlet of the component; and a second filter panel extending from the second face into the coolant airflow path upstream of the first filter panel.

An airfoil includes a cooling passage circuit that has a first plenum, a skincore passage, a first connector passage, a second plenum, and a second connector passage. The first plenum is in a first platform and extends adjacent a first side, a trailing end, and a second side of and airfoil section. The skincore passage is embedded in the first side of the airfoil section and extends longitudinally. The first connector passage is longitudinally spaced from an internal core cavity in the airfoil section so as to extend around the cavity. The first connector passage connects the first plenum with the skincore passage. The second plenum is in the second platform and extends adjacent the first side, the trailing end, and the second side of the airfoil section. The second connector passage connects the skincore passage with the second plenum.

An airfoil includes a cooling passage network is embedded in an airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an entrance region adjacent the first end of the airfoil section, a plenum region between the entrance region and the second end of the airfoil section, and an exit region adjacent the plenum region. The entrance region includes a plurality of flow guides that divide the entrance region into a plurality of channels that open into the plenum region. The plenum region includes a plurality of pedestals that have a shape that is different from the flow guides.

An airfoil includes an airfoil section that has a ceramic airfoil wall that defines a suction side and a pressure side. There is an interior cavity in the airfoil section. A rib spans across the interior cavity and connects the suction side and the pressure side. The rib has a thermal conductance element that is configured to conduct heat away from the suction side and the pressure side.

An airfoil include an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes a first arm by which the rib is solely connected to the first side wall, and second and third arms by which the rib is solely connected to the second side wall.

There are provided a seal fin, a seal structure, and a turbo machine that can achieve a high leak-suppressing effect and can reduce leak loss of the turbo machine. The disclosure suppresses leak of a fluid from a gap between a first structure being in a static state and a second structure rotating around an axis line and is formed on the first structure so as to extend toward the second structure while keeping a clearance between a tip face thereof on an extending direction and the second structure. The first structure and the second structure face each other in a radius direction with the gap inbetween. A plurality of hollows opening at a tip on the extending direction are arranged along a circumference direction in parallel with each other on a front face facing an upstream side of a flow direction of the fluid.

The present invention relates to a reinforcing structure for a casing accommodating an impeller. A double-suction centrifugal pump includes: a rotational shaft (1); an impeller (2) secured to the rotational shaft (1); a casing (3) that accommodates the impeller (2) therein; and legs (5) secured to the casing (3). The casing (3) includes a suction volute (20) that communicates with a suction port (6), the casing (3) includes an upper casing (3a) and a lower casing (3b) fastened to each other, at least one rib (28A, 28B, 28C) is provided on each of both side surfaces of the lower casing (3b) constituting the suction volute (20), the rib (28A, 28B, 28C) extends in a radial direction of the rotational shaft (1) when viewed from an axial direction of the rotational shaft (1), and the rib (28A, 28B, 28C) is separated from the legs (5).

A turbine vane assembly adapted for use with a gas turbine engine includes an airfoil and a spar. The airfoil is formed to define a cavity that extends into the airfoil. The spar is located in the cavity to define a cooling passage that extends around the spar between the spar and the airfoil. The turbine vane assembly includes cooling features to aid heat transfer of the turbine vane assembly during operation in the gas turbine engine.

A turbine vane includes a platform, an airfoil, and a cooling arrangement. The platform has a first surface and a second surface. The first surface and the second surface each axially between a first platform end and a second platform end and each circumferentially extend between a first platform side and a second platform side. The airfoil is connected to the platform and defines a passage outlet that extends through the second surface. The cooling arrangement includes a third wall that is connected to the second surface of the platform. The third wall defines a first outlet and a second outlet.

An example airfoil vane according to the present disclosure includes an airfoil section including an outer wall that defines an internal cavity, and an insert situated in the internal cavity. A space is defined between the insert and the airfoil outer wall, the insert including an insert wall. A plurality of standoff features extend from the insert wall into the space and contact the airfoil outer wall at a contact area, whereby the standoff features are configured to block airflow in the space at the contact area and redirect the airflow to gaps between the standoff features. A gas turbine engine with the example airfoil vane and a method of assembling an airfoil vane are also disclosed.