Disclosed is an air outlet of a nacelle for an aircraft turbojet engine, the nacelle forming a solid of revolution about a longitudinal axis, the air outlet having a straightening device having a plurality of flaps mounted circumferentially and protruding, each flap being mounted pivoting around a pivot axis, forming, with respect to the longitudinal axis, an angle of convergence in a radial plane, between a closed position, in which each flap extends along the pivot axis in the aerodynamic prolongation of the trailing edge in order to support a thrust phase and a deployed position, in which each flap extends in a deployed plane forming an angle of deployment with respect to the closed position about the pivot axis, so as to support a reverse thrust phase.

A gas turbine engine includes a rotor rotatable about a central axis. The gas turbine engine includes a turbine stage including a stationary portion and a rotating portion made up of a number of rotating blades and a plurality of stationary vanes arranged to define the stationary portion. Each stationary vane includes an inner rail having an inlet face, a suction side face, a pressure side face, and a platform. A vane portion extends along a radial line from the platform and defines one of a first stagger angle and a second stagger angle with respect to the central axis. The platform has an elliptical cross-section in a plane that includes the central axis.

Airfoils are provided having a body having a leading edge, a trailing edge, a first end surface, and a second end surface opposite the first end surface, wherein (i) a first true chord length is a line extending from a first leading edge point to a first trailing edge point and (ii) a second true chord length is a line extending from a second leading edge point to a second trailing edge point, a first button located on the first end surface of the airfoil body, the first button having a first diameter and a first attachment device extending from the first button to enable rotation of the airfoil body about an attachment device axis. The first diameter is at least 15% of the first true chord length or the attachment device axis is located 10% of the first true chord length from the leading edge point.

Aspects of the disclosure are directed to a seal comprising: a support ring, at least one beam coupled to the support ring, and a shoe coupled to the at least one beam, the shoe having an axial shoe face that includes a rounded edge that is configured to contact a support structure face of a support structure when the seal is subjected to a load that is equal to or greater than a first threshold.

A turbofan having a nacelle comprising a slider mobile in translation between an advanced and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one mobile in rotation on the slider between a stowed and a deployed position, where the blades are split into groups, where each group comprises a first blade, and a maneuvering system moving each blade and comprising a cam integral with the first blade of one of the groups and having a tooth, a groove receiving the tooth, a first transmission system transmitting the movement of the first blade bearing the cam to a first blade of each other group, and, for each group, a second transmission system transmitting the movement of the blade that bears the cam or is moved by the first transmission system to each of the other blades of the group.

A thrust reverser system is provided that includes a sleeve, a fixed cascade structure and a blocker door. The fixed cascade structure is within a cavity of the sleeve when the sleeve is in a sleeve stowed position. The blocker door is within the cavity of the sleeve when the sleeve is in the sleeve stowed position and the blocker door is in a blocker door stowed position. The blocker door projects in a radial inward direction away from the sleeve towards the centerline when the sleeve is in a sleeve deployed position and when the blocker door is in a blocker door deployed position. The blocker door includes a pivot attachment fixed at an end of the blocker door. The pivot attachment is configured to move in a forward direction from a first location to a second location.

An aircraft with a jet engine that has a radially outer engine cowling and an auxiliary gear appliance that has multiple auxiliary devices and that can be driven by a shaft that is in operative connection with an engine shaft that rotates about a central axis. The auxiliary gear appliance is arranged in the radial direction of the jet engine at least partially outside the outer engine cowling of the jet engine.

Wind funnel and gas combustion turbine systems are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a compression section of a gas turbine that is fueled by a hydrocarbon fuel source such as natural gas. Compressed air from the wind funnel enters the compression section of the gas turbine through one or more air inlets toward multiple rotating turbine blades in an air feed direction having a component normal to air impact surfaces of the turbine blades. In addition to the compressed air from the wind funnel, ambient air may be introduced into the compression section of the gas combustion turbine.

Wind funnel and gas combustion turbine systems are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a compression section of a gas combustion turbine that is fueled by a hydrocarbon fuel source such as natural gas. Compressed air from the wind funnel may enter the compression section at selected locations. The compression section may have a front relatively low compression section and a downstream relatively higher compression section, and the compressed air from the wind funnel may be selectively delivered to one or both of the lower and higher compression sections. In addition, ambient air may be introduced into the lower compression section. During periods when compressed air from the wind funnel is delivered to the downstream higher compression section, the front lower compression section may be decoupled from the downstream section.

Wind funnel and gas combustion turbine systems are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a compression section of a gas turbine that is fueled by a hydrocarbon fuel source such as natural gas. Compressed air from the wind funnel enters the compressor section of the gas turbine at relatively high density and force, and then flows to the combustion section of the gas turbine where oxygen from the wind-compressed air is used to combust the hydrocarbon fuel supplied to the gas turbine. The combustion section drives a power output generator having first and second generators that are selectively engageable and disengageable from each other. During periods when compressed air from the wind funnel is delivered to the compression section of the gas combustion turbine, the first and second generators may be drivingly engaged with each other by a generator coupling mechanism.