A turbine blade that includes an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may further include a rib configuration that partitions the chamber into radially extending flow passages, and a blade outer shell that defines an outer surface of the airfoil. The rib configuration is a non-integral component to the blade outer shell.

A turbine blade comprising an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may further include: a rib configuration that partitions the chamber into radially extending flow passages that include a first flow passage and a second flow passage; and a crossover passage that fluidly connects an inlet formed in the first flow passage to an outlet formed in the second flow passage. The crossover passage may include a canted configuration relative to the second flow passage.

The present disclosure provides a centrifugal fan blade, an air treatment device and a fan; the centrifugal fan blade includes a hub and a plurality of fan blades; the plurality of fan blades are distributed around the periphery of the hub; each fan blade includes a first blade and a second blade; moreover, the first blade is in a backward blade form; and the second blade is in a forward blade form. The centrifugal fan blade can improve the flowing of the airflow and improve the air output efficiency.

An axial fan includes a hub and blades. The hub has a rotating shaft, and is configured to be driven to rotate. The blades are provided to the hub, and each have a front edge portion and a rear edge portion. In a state in which the blades rotate to generate an airflow, the front edge portion is placed most upstream in the airflow, and the rear edge portion is placed most downstream in the airflow. In a shape of the blades rotated and projected onto a meridian plane that covers shapes of the blades and a shape of the rotating shaft, the front edge portion has an outline represented by a front-edge projected portion having a first recess portion formed in a recessed shape that recedes upstream in the airflow, the rear edge portion has an outline represented by a rear-edge projected portion having a second recess portion formed in a recessed shape that recedes upstream in the airflow, and the first recess portion has at least a portion that is formed further radially inside than is the second recess portion.

An airfoil for a gas turbine engine, which has an airfoil body extending in a spanwise direction and in a chordwise direction, a platform located at an inner end and/or an outer end of the airfoil body, and a fillet at a junction between the airfoil body and the platform. The fillet has a radius distribution at a given chordwise location, the radius distribution varying from the platform to the airfoil body in the spanwise direction. The radius distribution defines a local minimum, the radius of the fillet at the given chordwise location increasing from the local minimum along the spanwise direction toward both of the airfoil and the platform. A local maximum of the radius distribution is offset from the local minimum along the spanwise direction, the radius decreasing from the local maximum along the spanwise direction toward both of the airfoil and the platform.

A guide vane for arrangement in a gas duct of a turbomachine, including a guide vane blade and an outer platform which, relative to a longitudinal axis of the turbomachine, is arranged radially on an outside on the guide vane blade. The outer platform delimits the gas duct with an inner wall surface radially to the outside. The inner wall surface has a curved profile with an inflection point when viewed in an axial section, the inner wall surface having a concave curvature in a first axial section which is upstream from the inflection point with respect to a flow through the gas duct, and a convex curvature in a second axial section which is arranged downstream from the inflection point with respect to the flow through the gas duct.

A fan blade for an airplane turbojet, the blade including an airfoil extending axially between a leading edge and a trailing edge and including a plurality of airfoil sections stacked radially between a root section and a tip section. All of the airfoil sections situated between the root section and an airfoil section situated at a radial height corresponding to 30% of a total radial height of the airfoil possess a skeleton curve having a point of inflection.

A blade includes an airfoil portion including a pressure surface and a suction surface each extending between a leading edge and a trailing edge along a spanwise direction, and at least one communication hole extending m the airfoil portion and having a first and a second opening end opening to the pressure and suction surface, respectively. The first opening end is located on a first cross-section perpendicular to the spanwise direction at a first position in the spanwise direction, the second opening end is located on a second cross-section perpendicular to the spanwise direction at a second position in the spanwise direction, and a dimensionless blade chord length position of the first opening end with respect to the leading edge on the first cross-section is larger than a dimensionless blade chord length position of the second opening end with respect to the leading edge on the second cross-section.

A distributor valve comprising a second element configured to be displaced relative to a first element, so as to form an overall passage opening of variable fuel passage section corresponding to the intersection of a first passage opening and a second passage opening. The head portion of the second passage opening comprises a first inclination having a first average slope, the intermediate portion of the second passage opening comprises a second inclination having a second average slope strictly greater than said first average slope, and the foot portion of the second passage opening comprises a third inclination having a third average slope, strictly less than said second average slope.

A heat exchanger system for a propulsion system inlet duct includes a heat exchanger assembly that is disposed within an inlet duct assembly. The heat exchanger includes a heat exchanger with a front facing area that is greater than an area of the inlet duct that is transverse to a longitudinal length of the inlet duct.