A guide vane arrangement configured for use in a turbo pump, wherein the guide vane arrangement includes a first guide vane and a second guide vane, wherein the second guide vane is arranged adjacent to the first guide vane such that a flow channel is defined between a leading surface of the first guide vane and a trailing surface of the second guide vane. The trailing surface of the second guide vane comprises a trailing portion which is arranged adjacent to a trailing edge of the second guide vane and which is arranged at a first angle with respect to a virtual plane defined by a trailing edge of the first guide vane and the trailing edge of the second guide vane, a leading portion which is arranged adjacent to a leading edge of the second guide vane and which is arranged at a second angle with respect to the virtual plane defined by the trailing edge of the first guide vane and the trailing edge of the second guide vane, the second angle being larger than the first angle, and an intermediate portion which is arranged between the trailing portion and the leading portion and which is arranged at a third angle with respect to the virtual plane defined by the trailing edge of the first guide vane and the trailing edge of the second guide vane, the third angle being smaller than the first angle.

A gas turbine engine including: an exhaust diffuser including an inner tube and an outer tube that form therebetween an annular exhaust passage; a bearing chamber formed radially inside the inner tube for accommodating a bearing that supports a rotor of a turbine; a plurality of hollow struts extending across the exhaust passage; an oil introduction passage extending through one of the struts for introducing oil to be supplied to the bearing chamber; an oil drain passage extending through one of the struts for draining the oil from an exhaust oil inlet opened on a bottom surface of the bearing chamber; and an oil discharge passage for discharging a portion of the oil having passed through the oil introduction passage toward the oil drain inlet.

A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.

A nozzle guide vane for a gas turbine engine having a combined side wall thickness value which varies within a cavity region so as to provide a point with a maximum value of combined side wall thickness, which is advantageous for capturing debris travelling through the engine core.

A counter-rotating fan, comprising an impeller assembly and an air guide structure. The impeller assembly comprises a first stage impeller and a second stage impeller, of which the rotation directions are opposite. The pressure surfaces of first blades of the first stage impeller are configured to be opposite the suction surfaces of second blades of the second stage impeller, and from the blade root to the blade tip, each of the first blades and the second blades bends toward its own rotation direction. The air guide structure comprises a flow guide cover. The flow guide cover is provided at the center position of the air intake side of the first stage impeller, and the air intake side surface of the flow guide cover at least partially forms a flow guide surface, the flow guide surface extending along the axis of the first stage impeller in the direction away from the counter-rotating fan.

A curved contour of the lateral surface of a blade arrangement includes in at least one meridian section on mutually opposite sides of a blade airfoil an intersection point that is closer to the blade airfoil front edge, and an intersection point that is closer to the blade airfoil rear edge, and a best-fit line of least square distances from the curved contour. The curved contour includes first and/or the second contour section which meet specified conditions.

A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. Another internal channel in body receives the upstream supply pressure and provides a downstream supply pressure. At least one axial rib separates an internal area adjacent to the trailing edge into a plurality of individual cavities. At least one pressure regulating feature is located at an entrance to at least one individual cavity entrance to control downstream supply pressure to the trailing edge. Exits formed in the trailing edge communicate with an exit pressure. The rib and pressure regulating features cooperate such that the downstream supply pressure mimics the exit pressure along the radial span.

A turbomachine turbine blade, includes a platform, a vane, a cooling cavity supplying a plurality of cooling outlets provided along the trailing edge, two radially adjacent cooling outlets defining therebetween a rib. At least one cooling hole is formed in the thickness of at least one rib and/or in the thickness of a portion of the trailing edge fillet located in the axial extension of at least one rib, so as to ensure fluid communication for a cooling flow between the inside and the outside of the blade for cooling the at least one rib.

A humidification and air cleaning apparatus is provided, in which a first sweep angle and a second sweep angle are formed at diffuser blades, and an included angle is formed between the first sweep angle and the second sweep angle, such that a phase difference is formed in air passing through the diffuser blades, and thus, air flow noise may be reduced.

A multi-material vane includes an airfoil extending longitudinally between a leading edge and a trailing edge. The airfoil extends spanwise between an inner end and an outer end. The airfoil extends laterally between a first side and a second side. The airfoil includes a base section, a first side section, a second side section and a sheath. The base section extends along the span line between the inner end and the outer end. The base section is laterally between the first side section and the second side section. The first side section is connected to the base section and partially forms the first side of the airfoil. The second side section is connected to the base section and partially forms the second side of the airfoil. The sheath at least partially forming an edge of the airfoil. The edge is the leading edge or the trailing edge of the airfoil.