Abstract: A shrouded fan assembly for use with a gas turbine engine includes a central hub and a plurality of variable-pitch fan blades coupled to and extending radially outward from the central hub. Each variable-pitch fan blade includes a radially outer tip is rotatable about a longitudinal axis extending therethrough. A shroud is coupled to each radially outer tip.

Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.

Abstract: A gas turbine engine includes a first shaft defining an axis of rotation and a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft. A speed change mechanism is driven by the second shaft. A fan includes a fan rotor driven by the speed change mechanism such that the fan and the first shaft rotate at a slower speed than the second shaft. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

Abstract: A gas turbine engine includes a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A bypass ratio is greater than about 11.0.

Abstract: A gas turbine engine includes a fan section including a fan that is rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0.

Abstract: A propeller arrangement has a first propeller assembly providing a row of first propellers, and a second propeller assembly, rearward of the first propeller assembly, providing a row of second propellers. The first and second propellers are radially extendable and retractable. The propeller arrangement further has a control system for controlling the extension and retraction of the first and second propellers. The control system is arranged such that when the propellers of one of the first and second propeller assemblies extend, the propellers of the other of the first and second assemblies retract.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an axis and a speed reduction device in communication with the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A fan blade tip speed of the fan is less than 1400 fps.

Abstract: A fan structure comprises a first impeller and a second impeller, wherein the first impeller is composed of a first annular substrate, a plurality of first ribs and a plurality of first blades. The first ribs and the first blades are formed on the first annular substrate, each of the first ribs comprises an engaging hole, and a first accommodating space is formed between each of the adjacent first blades. The second impeller is composed of a hub, a second annular substrate, a plurality of second ribs, a plurality of second blades and at least one engaging member formed on the second ribs. The second ribs and the second blades are formed on the second annular substrate, and a second accommodating space is formed between each of the adjacent second blades. The first blades and the second blades are arranged in a staggered relationship.

Abstract: An HMSWT is disclosed which is constructed of successive cage type turbine assemblies. The multiple turbine assemblies are preferably induced into a reverse rotational movement from one another in a coupling effect. A first turbine assembly is propelled and forced into a rotational movement propelled by the oncoming wind which in turn induces a second, inner turbine assembly to rotate in an opposite and reverse direction. This coupling effect enables the rotational movement of two or more turbines with the same oncoming wind and airflow. The particular design of these multiple blades not only enhance the propelling force of the wind by increasing rotational movement, but simultaneously redirects the same airflow inward increasing the velocity of the airflow and propelling it onto the inner turbine assembly.

Abstract: A conical fan assembly, having a generally conical support member having an exterior surface and a vertical major axis, and a plurality of generally crescent-shaped fan blades extending from the exterior surface of the support member, wherein the plurality of fan blades define a helix configured to urge a fluid to flow in a spiral flow pattern up and around the support member.

Abstract: A fan rotor has a hub, and a plurality of axial flow fan blades extending radially outwardly of the hub. A radial compressor impeller is positioned radially inwardly of the fan blades. The radial compressor impeller has an upstream inlet which extends generally in an axial direction defined by an axis of rotation of the hub. The radial flow compressor impeller has an outlet that extends radially outwardly of the inlet, and into a supply passage for supplying air to a core engine. An engine is also disclosed.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an axis and a speed reduction device in communication with the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A fan blade tip speed of the fan is less than 1400 fps.

Abstract: A turbomachine comprises a flow duct with coaxially arranged radially inner and outer endwalls, first and second sets of axially spaced rotor stages arranged between the inner and outer endwalls, and a plurality of variable endwall segments arranged along the inner endwall. The first set of rotor stages rotates in a first direction, and the second set rotates in a second direction. The first and second sets alternate in axial series along the flow duct, such that axially adjacent rotor stages rotate in different directions. The variable endwall segments are radially positionable, in order to regulate loading on the first and second sets of rotor stages by changing a cross-sectional flow area between the inner and outer endwalls.

Abstract: A turboprop having at least one propeller formed by a set of variable pitch blades. Each blade is swivel-mounted on a rotary support and carries a gearwheel meshing with an actuator annulus rotating on the rotary support and coupled to a control annulus via an epicyclic mechanism.

Abstract: The present disclosure relates to a wind turbine (10) including: a rotor (18) including a rotatable hub (20) and a plurality of rotor blades (22), each of the plurality of rotor blades (22) being attached to the hub (20); and at least one airfoil body (120) including an aerodynamic profile (156) and an airfoil body root portion (122); wherein the aerodynamic profile (156) is configured for increasing aerodynamic lift of at least an inner portion of a rotor blade (22); and the at least one airfoil body (120) is attached to the hub (20) at the airfoil body root portion (122). In addition thereto, the present disclosure relates to an aerodynamic assembly (118) for a wind turbine (10) and a method of assembling a wind turbine (10).

Abstract: A counter-rotatable low pressure turbine includes counter-rotatable outer and inner drum rotors. The outer drum rotor is connected to a sole shaft for transmitting torque and power out of the low pressure turbine. Low pressure outer drum turbine blade rows extend radially inwardly from an outer shell of the outer drum rotor. Low pressure inner drum turbine blade rows extend radially outwardly from the low pressure inner drum rotor. The outer drum turbine blade rows are interdigitated with the inner drum turbine blade rows. The drum rotors are geared together through an epicyclic gearbox for transmitting all the torque and power produced by the drum rotors to the shaft. The gearbox may be located aft of the drum rotors. A differential thrust bearing is disposed between the drum rotors. A single stage fan section of an engine is connected to the turbine by the shaft.

Abstract: A small twin spool gas turbine engine with a hollow inner rotor shaft having solid shaft ends and an outer rotor shaft having a cylindrical portion on the compressor end that forms a forward bearing support surface and a turbine rotor disk on the turbine end that forms a aft bearing support surface. The inner rotor shaft includes solid shaft ends that project out from the cylindrical portion of the outer shaft on one end and out from the turbine rotor disk on the other end. An inner bearing housing is secured on the solid shaft ends of the inner rotor shaft. A threaded nut on the inner rotor shafts ends provide a compressive load to the inner bearing housings which results in a tension preload to the inner rotor shaft solid ends so that the bearing assemblies for the forward and aft ends of the twin spools do not become lose from the engine operation.

Abstract: An aircraft having counter-rotating, ring-type wing rotors that are driven by engines located at the wing tips is disclosed. The aircraft incorporates large span, high aspect ratio wings that are configured in a joined-tip design to improve the structural characteristics of the wings. One of the wings counter-rotates inside the other wing to enable vertical take-off and landing. The wings may comprise elliptical shapes, each having upper and lower sections that are separated from each other.

Abstract: A variable axis turbine may include multiple nested rotatable rotor assemblies. The turbine may be self-starting in slow fluid conditions while simultaneously self-limiting in fast fluid conditions. The turbine may provide omni-directional energy recovery and be self-balancing. The nested rotatable rotor assemblies may be configured to rotate independently of each other, but along the same rotational axis. Each outer nested rotor blade set may direct fluid onto the inner rotor blade sets in an aerodynamically beneficial manner. Each rotor blade set may be interconnected with a rotating generator hub that encloses a rotating generator element that rotates along with a corresponding rotor blade set for electric power generation. The blades may be “smart blades” that are sufficiently flexible to be self-configuring during rotation and soft enough to partially absorb sound. The blades may have a variable hardness and a two or more dimensional twist.

Abstract: A shaft oil purge system comprises an entrance seal, an exit seal and a buffer air flow. The entrance seal comprises a circumferential carbon seal running on an inner shaft and another carbon seal running on an outer shaft. The exit seal comprises a labyrinth seal positioned on the inner shaft and towards the exit end of the annulus between the shafts. An abradable material filled groove positioned radially outward from the exit seal allows the inner shaft to rub without compromising the integrity of the outer shaft. The buffer air flow enters the annulus from a cavity at the entrance seal, purges oil from the annulus and improves the efficiency of the seals.

Abstract: A wind power installation comprising at least two rotors which are arranged one behind the other and of which the first rotor which is arranged in front of the second rotor is of a smaller diameter than the second rotor.

Abstract: A multi-directional air circulation device for use in a living space. The multi-directional air circulation device comprises a first housing having i) a first wall portion defining a first interior space, ii) a first air outlet, and iii) a first air directing grill adjacent to the first air outlet. At least a second housing rotatable with respect to the first housing. The second housing having i) a second a wall portion defining a second interior space, ii) a second air outlet and, and iii) a second air directing grill adjacent to the second air outlet. At least one air generator is placed in the housings and used to generate at least one air stream which is then discharged from said device as at least two independently directed air exhaust streams through the first and second air outlets into said living space.

Abstract: A fan assembly includes a vertical axis wind turbine (VAWT) which is coupled to an air extraction or air supply fan. The VAWT is located above and is coupled coaxially to the fan. The fan assembly also includes an auxiliary turbine to provide start-up torque to initiate rotation of the VAWT. The VAWT is typically a Darrieus-type turbine and the auxiliary turbine is typically a Savonius-type turbine. In the preferred embodiments, the fan assembly includes a rotational speed governor to avoid damage to the turbine and/or fan in high winds.

Abstract: A propeller propulsion unit comprising a prime mover, propellers, and rotating force transmission for transmitting the rotating force of the prime mover to the propellers, wherein a counter propeller is fixed to a main shaft and a forward propeller is mounted to be rotatable on the main shaft, and these propellers are rotated in the directions reverse to each other by a belt transmission mechanism having forward and reverse running belts, whereby a lightweight moving body susceptible to an effect by a torque reaction can be steered stably.

Abstract: A generator of aerodynamic force by rotational movement, by means of a device which, starting from a rotational movement, induces a field of velocities in the surrounding fluid, which produces a difference in pressure on a surface, which in turn results in an aerodynamic force. The rotor element (1) is set in rotation at high speed by a motor (3). The rotational movement of the rotor element causes the fluid in which the device is immersed to assume a rotational movement, the velocity of the fluid layer that is in contact with the cylinder being equal to the velocity of a point at the surface of the cylinder. The planar element (2) separates the fluid into two regions. The fluid in the region below the surface is motionless, whereas the fluid above the surface is in motion. Since the higher the velocity of the fluid the lower its pressure, the fluid in the region below the surface exerts a higher pressure than that exerted by the fluid in the region below the surface.

Abstract: A flying apparatus has a body; power means; and lifting force generating units, the lifting force generating units being arranged parallel to a plane of symmetry of the body and turnable in a vertical plane, each of the lifting force generating units is formed as a rotor including a plurality of aerodynamic blades arranged uniformly on a disk and at equal distances from an axis of rotation so as to be turnable.

Abstract: A fan assembly includes a circular first array of first fan blades; a first primary ring member supportively connecting inner extremities of the first blades about a fan axis, respective end extremities of at least a majority of the first blades defining inside and outside diameters of the array, the first blades being oriented for producing a primary axial fluid flow between the inside and outside diameters in response to rotation of the first ring member, the first ring member extending between the inside and outside diameters. A second primary ring member connects outer extremities of the first blades, the first blades in combination with the first ring member defining a generally circular opening about the fan axis.

Abstract: Apparatus and method for harnessing fluid energy from a fluid current and converting it into mechanical energy. The invention comprises a big wheel and a little wheel where the little wheel rotates about on axis parallel to but offset from an axis about which the big wheel rotates. The little wheel rotates within the big wheel. Flexible sails are fastened between masts of the big wheel and masts of the little wheel so that when the wheels rotate each sail is unfurled and extended during one phase of operation and said sail is folded upon itself during another phase of operation. When extended or stretched open, the sail derives power from the fluid current. When the sail is folded, it offers a reduced resistance to the fluid current into which said sail is moving.

Abstract: The invention concerns a connector, in an aircraft engine, for mounting a ring to a turbine rotor which the ring surrounds. The ring carries propeller blades, and the connector transmits both thrust and torque loads between the ring and the rotor, without significant deformation. However, the connector does deform in order to accommodate differential thermal growth between the ring and the rotor.

Abstract: A system for obtaining and regulating energy from the air or sea and river currents includes a cyclone converter formed by three concentric rotating bodies, either on shafts or cylindrical rails or the like. Fixed rollers or other electromagnetic systems permit the rotation of the group around an imaginary or actual geometrical shaft. The outside body is self-orientating with its main components and deflectors on rotating components or a base sliding rail. The intermediate concentric body or turbine is formed by rings and vanes and a system of rollers or electro-magnetic supports which are inside or outside the turbine. The inside body or diffuser rotates concentrically in a reverse direction to the turbine and has vanes of opposite complementary angles.

Abstract: A tethered wind-driven floating power plant which includes a support body carrying at least one rotor assembly, a current generator coupled to the rotor and alignment assembly for aligning the rotor to face into the wind, a ground anchor and at least one captivating stay connecting the floating power plant to the anchor. The support body is hollow and gas-filled to carry its own weight as well as the weight of the rotor assembly, current generator and alignment assembly. The support body is connected to the captivating stay through a joint connection having three degrees of freedom. The rotors are gimbal-mounted, at a variable relative position with respect to the support body but in fixed positions relative to one another.

Abstract: A rotor arrangement for an aircraft comprising two coaxially counter-rotatable rotators, each rotor being journaled freely rotatable about an imaginary axis of rotation common to both rotors on or through a fuselage part or a support member, each fuselage part or support member being either rigidly connected to or journaled on the fuselage, each rotor together with the other respective rotor or with the component part of the support member or fuselage part supporting the first mentioned rotor constituting an integral part of an electromotor by forming the counteracting parts of the electromotor ("rotor" and "stator") which rotate relative to one another by securing a plurality of poles of the electromotor to the respective rotor and by arranging on the other counter-rotating rotor or on the component part of the support member or fuselage part supporting the first mentioned rotor the corresponding poles of the electromotor facing toward the poles of the respective rotor such that a reciprocal field effect exi