53results about How to "Minimize leakage" patented technology

A thermal management system includes a cooling duct system that locates a ram air intake and an exhaust through a first aircraft surface above a second aircraft surface which locates a fan intake. During ground operations, an anti-re-ingestion door is open and a ram air door is closed such that the fan system may draw relatively cooler air from below the aircraft and exhaust the heated air above the aircraft to minimize re-ingestion of the heated exhaust. During flight operations, the anti-re-ingestion door is closed and the ram air door is open such that ram airflow communicates through the fan system prior to communication through the heat exchanger. Both the anti-re-ingestion door and the ram air door may also be operated in flight.

A fuel valve for use in regulating the pattern factor of a gas turbine has a highly accurate pressure balanced clevis valve assembly. The clevis valve is pivotally mounted inside the valve housing by a flexure pivot, and has a pair of legs at each side of a valve body that control flow through pairs of flow orifices. An armature mounts to the clevis valve, and when energized, an electromagnet inside the valve housing generates magnetic flux that moves the armature to pivot the clevis valve to open or closed the orifices. The clevis valve is inherently balanced and can meter fuel through multiple orifices simultaneously.

The present invention relates to a building block serving as a mold when carrying out civil engineering and construction works and forming an external appearance of a structure, a building structure and a method of bricking a wall using the same. The building block comprises first and second exterior walls facing each other and spacing from each other in back and forth directions, and a connecting portion connecting the first and second exterior walls to each other and having an upper portion provided with a first mounting groove for mounting a width-directional reinforcing bar. Here, concavo-convex coupling portions are formed at inner peripheries of the first and second exterior walls, for concavo-convexly coupling to each adjacent block, and here, leakage preventing recesses are respectively formed at outer peripheries of the first and second exterior walls.

A turbine shroud (30) of a gas turbine engine comprises a plurality of arcuate shroud segments (31) combined into an annular configuration, each shroud segment including a main body (32) defining an inner circumferential surface opposing the tips of the turbine rotor blades (11a) at a small clearance and an engagement feature including an axial wall (33a, 34a) having a prescribed circumferential length and a prescribed axial length, the turbine casing including an axial slot (51, 52) extending coaxially around the center line of the engine and configured to receive the axially extending wall of each shroud segment. A clearance defined between each circumferential end part (E) of the axial wall and an opposing inner circumferential surface of the turbine casing is greater than that defined between a circumferentially middle part (M) of the axial wall and an opposing inner circumferential surface of the turbine casing under a cool condition of the engine. A radial temperature gradient that develops in each shroud segment when the engine is warmed causes a deformation of the shroud segment such that the clearance can be made substantially uniform over the entire circumference of the shroud segment and the cooling air leakage can be minimized while minimizing thermal stress that may be caused by the thermal expansion of the shroud segment.