A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.

Thrust vector control for a vehicle having a fluid drive, vehicle having thrust vector control and method of controlling thrust vector. Thrust vector control includes a thrust current region for a thrust current of a propulsion stream having a flow direction; a steering mechanism for the thrust current including at least one steering device arranged at least in a peripheral region of the thrust current region, and the at least one steering device includes a rotational body with a lateral surface and a rotational axis arranged transverse to the flow direction, and the rotational body being rotatable so that a first part of the lateral surface exposed to the thrust current rotates in a first rotational direction, whereby a Magnus effect is produced to deflect the thrust current. The first rotational direction is in a direction of the thrust current.

A gas turbine engine nozzle includes a flap movable relative to a structure. A seal assembly is supported by one of the structure and the flap and includes a seal hinged about an axis. The seal has a sealing profile engaging a seal land of the other of the structure and the flap. A biasing member is configured to urge the hinged seal toward the seal land. A method of sealing a nozzle flap includes supporting a seal relative to a structure along an axis. The seal is urged toward a nozzle flap. The seal rotates about the axis to maintain engagement between the seal and the nozzle flap in response to the urging step.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A rocket engine nozzle includes an aerospike having a plurality of adjustable airfoil vanes distributed around a central longitudinal axis of a rocket engine combustion chamber. The aerospike is integrated on an exit plane at an exit end of the combustion chamber. The adjustable airfoil vanes and an inner perimeter of the combustion chamber define a plurality of apertures which choke an exhaust exiting the combustion chamber and cause the exhaust to expand supersonically along the adjustable airfoil vanes, creating a supersonic jet. An actuator is configured to adjust a position of each of the adjustable airfoil vane relative to each other so as to direct the exhaust exiting the rocket engine combustion chamber as the exhaust expands supersonically over the airfoil vanes without causing a shockwave to be imparted on the supersonic jet that is created. Accordingly, performance of the rocket engine is improved over conventional systems.

The present disclosure provides systems, apparatuses, and methods relating to a fan apparatus including a lift fan mounted in a duct and a cover for the lift fan. In some examples, a fan apparatus has a louvered cover including louvers having different chord lengths and/or different projection distances relative to one another when the louvers are in an intermediate (transitional) position. In some examples, a fan apparatus includes a louver actuation assembly configured to move louvers of the fan apparatus rotationally and translationally between open and closed positions. In some examples, a fan apparatus includes a fluid-actuated sealing assembly configured to form a seal between a sealing member and a cover, such as a louvered cover.

A rocket engine nozzle includes an aerospike having a plurality of adjustable airfoil vanes distributed around a central longitudinal axis of a rocket engine combustion chamber. The aerospike is integrated on an exit plane at an exit end of the combustion chamber. The adjustable airfoil vanes and an inner perimeter of the combustion chamber define a plurality of apertures which choke an exhaust exiting the combustion chamber and cause the exhaust to expand supersonically along the adjustable airfoil vanes, creating a supersonic jet. An actuator is configured to adjust a position of each of the adjustable airfoil vane relative to each other so as to direct the exhaust exiting the rocket engine combustion chamber as the exhaust expands supersonically over the airfoil vanes without causing a shockwave to be imparted on the supersonic jet that is created. Accordingly, performance of the rocket engine is improved over conventional systems.

A multi-pulse rocket propulsion motor for use with vehicles, such as space vehicles like satellites, rockets, and the like. The propulsion motor is a modular system that is capable of providing a plurality of discrete, controllable propulsion pulses. The propulsion motor can be used for primary propulsion of the vehicle and/or as a maneuvering thruster of the vehicle. The propulsion motor includes a plurality of propellant housings each containing a combustible propellant grain, a discharge plenum defining a plenum volume in communication with the discharge of each propellant housing, and a nozzle downstream from and in fluid communication with the plenum volume.

A vertical take-off and landing aircraft is provided. The aircraft comprises a fuselage which has a nose end, a tail end, and a plurality of seats disposed in the interior. A pair of rear wings extend outwardly from opposing sides of the fuselage between a cockpit and the tail end, and a pair of front wings extend outwardly from opposing sides of the fuselage between the cockpit and the nose end. Each of the pair of rear wings and front wings includes an adjustably mounted turbine which comprises a statically mounted fan pod, a duct rotatably connected to the fan pod, and an adjustable nozzle rotatably connected to the duct. The nozzle can be adjusted to a variety of configurations ranging between a vertical position and a horizontal position via the duct. The adjustably mounted turbine enables the aircraft to adjust thrust through vectors ranging between horizontal and vertical.

A novel structural arrangement for the various components of an Ultra-Micro Gas Turbine Generator, based on a single part impeller element which comprises the compressor, the turbine and the electrical generator core in a single annular structure, produced as a single piece by an additive manufacturing process. The single annular structure has a hollow shell structure, with a supporting structure within in. The internal hollow space of the shell structure provides for a flow of cooling air from the outside through the internal space, for cooling the turbine region of the impeller. This air flow could be assisted by the use of internal blades, which can also serve as the supporting structure to increase the strength of the shell structure. The air flow can either be ejected at the center of the turbine, or can provide a high pressure supply for air bearings of the impeller element.