An impeller for a centrifugal turbomachine includes: a hub having a small-diameter portion positioned at a first end portion in an axial direction and a large-diameter portion positioned at a second end portion in the axial direction, the large-diameter portion having a greater diameter than the small-diameter portion; and a blade having a first edge positioned at an axial-directional position of the small-diameter portion and a second edge positioned at an axial-directional position of the large-diameter portion, the blade being disposed on an outer peripheral surface of the hub. The impeller is configured such that, when a first radial-directional cross section is a cross section of the impeller at an axial-directional position passing a tip of the first edge, at least a part of the first radial-directional cross section in a blade-height range of 50% or more is inclined downstream in a rotational direction of the impeller with respect to a radial direction.

A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.

A rotor blade includes an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.

Turbine (1) comprising a casing, an outer metal shroud (9), an inner metal shroud (5) and an annular distributor (2) having a plurality of CMC ring sectors (20), each sector comprising a mast (6), an inner platform (24), an outer platform (26) and at least one blade (28) having a hollow profile that defines an inner housing (280), the inner and outer platforms each having an opening (245, 265) communicating with said inner housing, and the mast (6) passing through said openings and the inner housing and being secured to said casing and connected to said annular sector. Each blade comprises at least one first radial shoulder (72) projecting axially towards the inside of the blade, and each mast comprises at least one second shoulder (71) projecting axially towards the outside of the mast (6) configured to radially cooperate with a first shoulder (72) and radially press the blade (28) against the mast (6).

Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a housing with a solid propellant positioned within the housing, and an injector ring positioned at a proximal end of the housing. The injector ring can include a plurality of angled injector units each including a first injector and a second injector angled towards an impingement point. A first fluid stream of a liquid propellant dispensed from the first injector can collide with a second fluid stream of the liquid propellant dispensed from the second injector to atomize the liquid propellant and form a spray fan formation. At least one of the first injector and the second injector can be positioned at an injection angle relative to the sidewall to create a swirl flow of the atomized injector fluid

A turbine housing can include a bearing housing end and a treatment unit end; a volute wall that defines a volute; a wall that defines at least a portion of a turbine wheel space that defines a turbine wheel space axis and a turbine wheel space diameter, where the wall extends to an axial peak to define an extended space with an extended space outlet having an extended space outlet dimension; and an outlet wall that defines an outlet space with a treatment unit end outlet having an outlet dimension, where the extended space is disposed at least in part axially between the turbine wheel space and the outlet space to increase axial velocity uniformity at the treatment unit end outlet.

A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake comprising an inner wall facing the axis X and an outer wall for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall to allow the hot air flow to escape after heating the inner cavity, the ventilation orifice comprising an upstream edge, the circumferential profile of which is discontinuous in order to generate turbulences, and a downstream edge, the radial profile of which is aerodynamic in order to limit the formation of pressure fluctuations.

A center plug includes an inner skin, the inner skin extending along an axial centerline; an outer skin positioned radially outside the inner skin; a forward bulkhead connected to and extending radially outward from the inner skin; an aft bulkhead connected to and extending radially outward from the inner skin; and an acoustic panel, the acoustic panel including a first sheet having a first plurality of perforated walls and a first plurality of non-perforated walls, a second sheet having a second plurality of perforated walls and a second plurality of non-perforated walls, the first sheet being sandwiched together with the second sheet to form an N-shaped structure having a combined plurality of perforated walls and a combined plurality of non-perforated walls.

A gas turbine engine may include a fan, a plurality of inlet pre-swirl features disposed upstream of a fan, and an outlet guide vane assembly disposed downstream of the fan. The outlet guide vane assembly includes a plurality of outlet guide vanes that may define an outlet guide vane solidity profile, wherein the outlet guide vane solidity profile is achieves a minimum solidity at a radial position between an inner boundary and seventy percent of an outlet guide vane span. The fan includes a plurality of fan blades that may define a fan solidity profile, wherein the fan solidity profile maintains a solidity of greater than 1.1 between a radial position at seventy percent of the fan blade span and an outer boundary.