Abstract: An internally air cooled turbine blade for a gas turbine engine of the type including a trailing edge section, leading edge section and mid chord section wherein each section includes a straight through radial passage communicating cooling air from the root to the tip of the blade, and the radial passages (feed channels) on the pressure side and suction side supply the cooling air to the film cooling holes in the airfoil surface and the radial passage (feed chamber) in the mid chord section replenishes the feed channels with cooling air through replenishment cooling holes interconnecting the feed channels and feed chamber. The rotation of the blade imparts a centrifugal pumping action to the air within the feed chamber for maximizing the cooling effectiveness of the cooling air. The air discharging at the tip cools the tip of the blade and provides tip aerodynamic sealing and the leading edge and trailing edge are similarly fed cooling air.
August 24, 1988
Date of Patent:
February 24, 1998
United Technologies Corporation
Robert R. Sellers, Friedrich O. Soechting, Frank W. Huber, Thomas A. Auxier
Abstract: The present invention provides a mixing impeller including a plurality of blades circumferentially mounted to a frame around the mixing impeller with adjacent blades being opened from one another. The blades are secured to the frame in a manner such that at least part of each blade extends outwardly of the frame to guide discharge of fluid passing through the impeller away from the frame and substantially eliminate any turbulence that the frame might otherwise create. In addition, the frame has a rearwardly inwardly tapering configuration with each of the blades having the same inward rearward taper as that of the frame. This combination of features substantially reduces turbulance of the outward flow of liquid from the impeller relative to conventional impeller designs.
Abstract: The invention relates to our energy conversion system for converting the kinetic energy possessed by the wind into mechanical energy. The objective is to produce a controlled, tornado like, turbulence around a turbine. This is accomplished by using a deflector to channel the air over a main body made up of five rotating wings which in turn deflect the air into small turbine rotatably connected to the wings.
Abstract: The invention concerns a system for reducing the resisting torque which must be overcome in changing pitch of aircraft propeller blades. The resisting torque includes gas twisting moment and centrifugal twisting moment. The invention includes a bearing system which derives a torque from radial motion of the blade, the radial motion being induced by centrifugal force. The derived torque opposes the resisting torque. The derived torque can also be used to not only oppose, but also overcome, the resisting torques. Such overcoming can be desirable because the resisting torques can drive the propeller blades into a flat pitch position if the pitch change mechanism fails.
Abstract: The present invention refers to a rotor for a fluid-kinetic machine comprising a rotatably supported hub, the support being provided with axial bearing means, an outer ring which is indirectly supported on said hub, and rotor blades which are arranged in an area between said hub and said outer ring. In order to provide a possibility of utilizing the influence of the gyroscopic effects, which occur during operation of the rotor, for the purpose of stabilizing the rotor, it is suggested in accordance with the invention that the outer ring should be composed of a plurality of arcuate sections in the circumferential direction and should be arranged essentially in the plane of rotation of the axial bearing means, and that the arcuate sections of the outer ring should be under the action of flexible tension elements which embrace said arcuate sections at least partly and which are secured to a carrier ring.
Abstract: A blade-to-blade vibration damper for a turbine rotor blade is disclosed. Each blade has airfoil, platform and root portions. A plurality of blades are circumferentially spaced about a rotor disk. An inclined recess extends into the platform portion of each blade from a first surface thereof, and toward its root portion. A U-shaped wire-form damping member has its in-turned marginal end portions slidably received in each recess. When the rotor disk is rotated at a sufficient angular speed, the damping members move outwardly by the centrifugal force acting thereon to engage the opposing surface of the platform portion of the adjacent blade. When so engaged, the members damp vibrations of such blades and seal the space between the opposing platform surfaces.
Abstract: A power takeoff for an unducted fan gas turbine engine having first and second counterrotating coaxial rotors coupled respectively to first and second propellers. The rotors and propellers are oriented for rotation about a longitudinal axis of the engine. A gear is coupled to each of the rotors for rotation therewith and arranged to provide rotational motion about an axis transverse to the engine axis. A shaft is coupled to the gear for rotation about the transverse axis. Each of the propellers includes a plurality of propeller blades, each of the blades is rotatable about a corresponding blade axis, and a control is coupled to the blades for varying the pitch thereof whereby power is selectively distributed between the propellers and the power takeoff. The power takeoff may include a propeller coupled to the shaft for developing thrust substantially transverse to the engine axis and/or a pump, compressor, or generator to supply fluids or electric power to other apparatus.
Abstract: An abradable coating is described for interaction with a abrasive gas turbine engine component to provide sealing. The abradable coating comprises yttria stabilized zirconia with intentional porosity which is applied by plasma spraying to a MCrAlY bond coat which in turn rest on a superalloy substrate. The coating system is applied by plasma spraying. The coating system is adapted to interact with an abrasive coated abrasive treated gas turbine engine component.
December 16, 1988
Date of Patent:
June 26, 1990
United Technologies Corporation
Raymond W. Vine, Donald A. Robbins, Donald G. Nordstrom, Mark B. Goodstein
Abstract: A self-locking pitch change actuator is configured to fit within an annular hub (34). A ring gear (40) is driven circumferentially by a tangentially oriented ballscrew (42) and traveler (44). The ballscrew (42) is driven by a hydraulic motor (50) controlled responsive to an electric pitch change motor (74). A pitchlock (62) is positioned by the collective actions of the ballscrew (42) and pitch change motor (74), with any movement relative to a preselected null position driving the hydraulic motor beta control valve (60) into an operative position.
Abstract: An axial fan construction wherein individual blade assemblies are secured within apertures in the fan hub. Fasteners extend between a retaining member and a blade base, with each blade base including a shoulder overlying a bearing surface on the hub and with resilient members positioned between the blade base shoulders and hub bearing surfaces. A spacer maintains the blade base shoulders and retaining members a preselected distance apart to allow prestressing of the fasteners while limiting the compressive force applied to the resilient member. The blade base shoulders and hub bearing surfaces are configured to cooperate with the resilient member to impart a centering force on the blade base relative to a hub aperture when the resilient member is compressed between the blade shoulder and hub bearing surface.
Abstract: a propulsion and steering apparatus generally for a boat having a unitized construction comprising an engine, propeller, rudder and protective cage for the propeller, all mounted on a rotatable pylon adapted to be secured to the transom or other portions of the boat. A rudder is attached to the pylon and projects into the water to facilitate steering of the boat if the engine should die or be at idle speed. An ice break can be substituted for the rudder for use of the vehicle on snow and frozen water such as for ice fishing and rescue work. If desired, the apparatus can be mounted forwardly of the transom on transversely extending beams in the boat to provide a large open area that will be kept available for fishermen and equipment in the rear of the boat. The entire propulsion means is adaptable to be hinged to the mounting so it may be laid down to present a low profile for moving under bridges, storing in garages and while being transported on the highways.
Abstract: A diffuser vane assembly for a centrifugal compressor includes movable vanes which are inserted or retracted from the diffuser passage through slots in one of the diffuser walls. The vane assembly is axially movable by an internally threaded drum and gear arrangement. A hand crank external to the compressor is effective to rotate the drum and thereby axially move the plate and attached vanes within the diffuser passage.
Abstract: In a wind power plant having wind surfaces which are moved by air currents and coupled to a generator and are guided in longitudinal frames so as to be staggered one behind the other and are pivotally connected to lateral pulling devices and supported by endless lateral circulation rails, wherein the plant is mounted on a rotatable support plate, an arrangement and construction are provided in which, simultaneously, the wind surfaces are approximately perpendicular in the upper run of the pulling device and horizontal in the lower run and a number of wind surfaces at both ends of the longitudinal frame are in the reverse position. An additional horizontal guide strut may be disposed in the top region of each wind surface, the outwardly projecting ends of which guide strut engage an outer guide bar which, having a larger diameter, is secured to the longitudinal frame at a specific distance from the inner guide groove.
Abstract: An impeller comprises a central hub part, and a plurality of vanes extending from the central hb part, the plurality of vanes including two first neighboring vanes having a predetermined construction and at least one second vane located between the first vanes and having a construction which is different from the construction of the first vanes.
July 13, 1989
Date of Patent:
June 5, 1990
Robert Bosch GmbH
Bruno Kesel, Gerhard Zink, Karin Winter
Abstract: A control system for providing individual blade control inputs to a four-bladed helicopter rotor. Limited authority series actuators located in a non-rotating portion of the helicopter are driven by a computer which receives inputs from individual blade sensors and aircraft stabilization sensors, summed with cockpit control inputs, and the resultant motions transmitted to the rotor blades through a conventional swashplate which drives four blades of the rotor and a translatable differential sleeve and summing linkage which drives only two blades. The differential sleeve is adapted for axially raising or lowering the swashplate. The combined motion of swashplate and differential sleeve is shown mathematically to result in individual blade control in pitch. Computer individual blade commands are converted from the rotating reference frame to cyclic, collective and differential blade pitch commands in the fixed reference frame through a coordinate transformation matrix.
Abstract: A submersible pump (10) consists of a pump unit (12) driven by a motor (11) and a suction inlet bowl (13) which draws in and filters fluid and provides the same to the pump unit (12) upon activation of the motor (11). The suction inlet bowl (13) includes a generally cylindrical upper portion (31) adapted to attach to the pump unit (12) and a generally cylindrical base (14) adapted to be attached to the motor (11). A fluid inlet portion (20) is located between the upper portion (31) and the base (14) and is recessed radially inwardly of the outer periphery of the base (12) and upper portion (31). The fluid inlet portion (20) includes a plurality of generally vertical slots (27) through which the fluid may pass and be filtered thereby.
Abstract: Combination trip and throttle valve steam controls for a steam turbine include manual controls to actuate the trip mechanism and shut the turbine down and a trip/reset, with a single control to regulate the steam delivered to the turbine and to reset the trip mechanism to provide simplified and reliable controls.
Abstract: There is provided a self-actuating, variable pitch propeller having a plurality of blades. All of the blades are automatically movable between a first, relatively lower pitch position and a second, relatively higher pitch position, substantially simultaneously and equally in response to achieving a predetermined combination of propeller rotational speed and hydrodynamic loading on the propeller blades. The blades are releasably locked to prevent the pivoting of each blade when in the locked position. The locking means are released by actuating means activated by the combined effects of centrifugal force and hydrodynamic loading.
Abstract: An electric motor driven blade pitch varying system for the fan blades of an unducted fan type aircraft gas turbine engine utilizes permanent magnet alternating current motors located in the oil sump region of the engine. An alternator driven by the engine generates unregulated variable frequency, variable amplitude power which is rectified and placed on a DC bus. Controlled inverters convert the DC power on the bus to appropriate AC power for the motors. The system incorporates redundancy without significant weight penalty by providing alternators and motors dividing into two independent operating sections on common shafts. Separate electronic circuits are provided to supply power for each sectionalized motor or to rectify power from each alternator section. A common power bus may be used to couple the multiple motors and alternators. The common bus may alternatively receive power from tbe aircraft 400 Hz system or from on-board batteries.