22500 results about "Fan blade" patented technology

A turbofan includes a row of fan blades extending from a supporting disk inside an annular casing. Each blade includes an airfoil having opposite pressure and suction sides extending radially in span between a root and tip and axially in chord between leading and trailing edges. Adjacent airfoils define corresponding flow passages therebetween for pressurizing air. Each airfoil includes stagger increasing between the root and tip, and the flow passage has a mouth between the airfoil leading edge and the suction side of an adjacent airfoil and converges to a throat aft from the mouth. The row includes no more than twenty fan blades having low tip solidity for increasing the width of the passage throat.

A vertical takeoff and landing (VTOL) aircraft design particularly suitable as a full-sized aircraft or remote controlled (RC) model aircraft is disclosed. The invention employs lightweight, high strength materials to reduce the power requirements of the propulsion plant. A preferred system of the invention comprises one internal combustion engine able to spit shaft power to four fan units. The fan units further employ counter rotating fan blades for stability. Separate horizontal and vertical tilting mechanisms delivered to the fan units are additionally disclosed. A variation in design is further included wherein electric motors provide the necessary shaft power.

A vertical takeoff and landing (VTOL) aircraft design particularly suitable as a full-sized aircraft or remote controlled (RC) model aircraft is disclosed. The invention employs lightweight, high strength materials to reduce the power requirements of the propulsion plant. A preferred system of the invention comprises one internal combustion engine able to spit shaft power to four fan units. The fan units further employ counter rotating fan blades for stability. Separate horizontal and vertical tilting mechanisms delivered to the fan units are additionally disclosed. A variation in design is further included wherein electric motors provide the necessary shaft power.

A fan blade comprises an airfoil having a generally elliptical top surface and a generally elliptical bottom surface. The fan blade has a lower radius of curvature toward its leading edge as compared to a higher radius of curvature toward its trailing edge. When mounted to a rotating hub member, elliptical fan blades may provide air movement at significant efficiencies.

The invention relates to an air channel module and an air channel structure with the air channel module and an air conditioner. The air channel module comprises an air channel main body and a connecting assembly, wherein the air channel main body comprises an air field area in which an airflow air channel is formed, and the airflow air channel is provided with two opposite air outlets; the connecting assembly is arranged on the air channel main body; and a plurality of air channel modules can be connected with each other by virtue of respective connecting assemblies so as to form the air channel structure with a plurality of air field areas. According to the air channel module, different number of air channel modules can form different air channel structures so as to install different number of fan blades, so that the air channel module can be applied to series of products with different heat transfer periods, and the different air channel structures do not need to be independently designed and manufactured according to the products with the different heat transfer periods, so that the design and production cost is effectively reduced, and the production cycle is shortened.

A cooling fan for an engine in a vehicle. Ordinarily, a fan rotates within a shroud, which surrounds the fan. Leakage can occur between the tips of the fan blades and the shroud, wherein fan exhaust moves forward, and then passes through the fan again. The invention reduces leakage by placing a surface downstream of the fan. The surface employs the Coanda Effect, to urge fan exhaust to continue in the downstream direction, and not move forward as leakage air.

A winglet includes a vertical member and a mounting member. The mounting member is configured to facilitate the mounting of the winglet to the tip of a fan blade. The vertical member is configured to extend perpendicularly relative the tip of a fan blade. Adding winglets to fan blades may improve the aerodynamics of the fan blades, and thereby increase efficiencies of a fan.

An exemplary embodiment of a FLADE counter-rotating fan aircraft gas turbine engine includes at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to one of axially spaced-apart first and second counter-rotatable fans. A core engine located downstream and axially aft of the first and second counter-rotatable fans is circumscribed by a fan bypass duct downstream and axially aft of the first and second counter-rotatable fans. The row of FLADE fan blades radially extend across a FLADE duct circumscribed about the first and second counter-rotatable fans and the fan bypass duct. A second low pressure turbine is drivingly connected to the first counter-rotatable fan and a first low pressure turbine is drivingly connected to the second counter-rotatable fan.

An aft FLADE gas turbine engine includes a fan section drivenly connected to a low pressure turbine section, a core engine located between the fan section and the low pressure turbine section, a fan bypass duct circumscribing the core engine and in fluid communication with the fan section, and a mixer downstream of the low pressure turbine section and in fluid communication with the fan bypass duct, and an aft FLADE turbine downstream of the mixer. At least one row of aft FLADE fan blades disposed radially outwardly of and connected to the aft FLADE turbine and radially extending across a FLADE duct circumscribing the fan bypass duct. The aft FLADE turbine may be a free turbine or connected to and rotatable with the low pressure turbine section. A power extraction apparatus may be disposed within the engine and drivenly connected to the aft FLADE turbine.

A cooling fan for an engine in a vehicle. Ordinarily, a fan rotates within a shroud, which surrounds the fan. Leakage can occur between the tips of the fan blades and the shroud, wherein fan exhaust moves forward, and then passes through the fan again. The invention reduces leakage by placing a surface downstream of the fan. The surface employs the Coanda Effect, to urge fan exhaust to continue in the downstream direction, and not move forward as leakage air.

The composite turbomachine blade of the present invention comprises a preform made of yarns or fibers woven in three dimensions and a binder maintaining the relative disposition between the yarns of the preform. Said preform is made up of warp yarns and of weft yarns, the direction of the warp yarns forming the longitudinal direction of the preform. In characteristic manner, said preform comprises at least a first portion made using a first weave forming the airfoil of the blade, and a second portion made using a second weave forming the root of the blade, and the first and second portions are united by a transition zone in which the first weave is progressively modified to end up with the second weave, thereby obtaining a reduction at least in the thickness of the blade between the second portion and the first portion. The invention is applicable to making a fan blade for a turbojet.

A circulatory device comprising a large diameter fan having reinforced fan blades with a tapered airfoil shape is disclosed. The fan blades may be formed using an extrusion method of fabrication, wherein each fan blade may comprise a reinforced trailing edge with a downwardly extending flange. The benefit of forming each fan blade with a reinforced trailing edge of the present invention results in improved structural characteristics such that the trailing edge of each fan blade may be fabricated longer so as to improve aerodynamic performance. Also, the reinforced trailing edge resists tearing that may occur during extrusion by adding the bent flanged region to at least one distal end of the trailing edge. For example, the bent portion of the trailing edge tends to rigidly orient the extruded material in a stabilized position more readily during formation. Also, the bent portion provides added strength by providing supporting forces in two dimensions that relatively parallel and perpendicular to its length so as to neutralize the adverse effects of pressure forces acting on the trailing edge of the fan blade during extrusion.

A multiple bypass turbofan engine includes axially spaced-apart first and second stage fans of the engine fan connected in driving engagement to a low pressure shaft. A fan bypass duct circumscribes the second stage fan. A first bypass inlet to the fan bypass duct is disposed axially between the first and second stage fans and a second bypass inlet is axially disposed between the second stage fan and an annular core engine inlet. A fan shroud divides the second stage fan blades into radially inner and outer fan hub and tip sections, respectively. The tip sections are radially disposed in a fan tip duct. An axially translatable deflector is positioned to close the fan tip duct when it opens the first bypass inlet and open the fan tip duct when it closes the first bypass inlet.

A fan blade includes an airfoil having opposite pressure and suction sides extending in span between a root and tip, and extending in chord between opposite leading and trailing edges. From root toward tip, the airfoil includes increasing stagger and decreasing camber, and increasing chord length to barrel the airfoil along both the leading and trailing edges. The airfoil further includes forward aerodynamic sweep at the tip, and non-forward aerodynamic sweep between the maximum barrel and the root.

A method for reducing vortex promotion of a rotor blade used in high core PR fans comprises shifting a curvature distribution of a blade section immediately adjacent to the hub such that a major turning of the suction side of the section is located near a trailing edge of the blade.

A wash apparatus includes a harness assembly comprising a coupling device a coupling device for connecting one or more fluid supply lines to one or more fluid delivery lines; one or more fluid delivery lines removably attached at one end to the coupling device's first portion and positioned for delivering washing fluid directly into the gas turbine engine core as the engine is cranked; one or more fluid supply lines removably attached to the coupling device's second portion for supplying washing fluid to the harness assembly and remaining in a static position relative to the rotating fluid delivery lines; one or more harness rings attached to the one or more fluid delivery lines for spacing, stabilizing, and positioning the fluid delivery lines relative to the fan blades; and a connector for removably attaching the harness assembly directly onto the fan hub.