Patent application number | Description | Published |
20090169384 | METHODS AND SYSTEM FOR BALANCING TURBINE ROTOR ASSEMBLIES - A balancing system and method for reducing imbalance in a rotatable member of a machine is provided. The system includes a plurality of vibration sensors positioned about a stationary portion of the machine, a controller assembly communitively coupled to the plurality of vibration sensors, and a balancing assembly coupled to the rotatable member, said balancing assembly configured to wirelessly communicate with said controller assembly, said balancing assembly configured to modify the weight distribution of the rotatable member in response to a command wirelessly transmitted from the controller assembly. The controller assembly is configured to receive data from the plurality of vibration sensors and determine an imbalance in the rotatable member using the received data. | 07-02-2009 |
20100080697 | INTEGRATED GUIDE VANE ASSEMBLY - An integrated outlet guide vane assembly for turbomachinery typically includes at least one outlet guide vane and at least one bifurcation having a leading edge and a trailing edge. The turbomachinery has a central axis of rotation and a defined direction of rotation about the axis. The guide vane comprises an airfoil having a leading edge and a trailing edge and has a non-zero angle of lean in the direction of rotation and a non-zero sweep angle relative to a line perpendicular to the central axis. The leading edge of the bifurcation has a non-zero angle of lean in the direction of rotation and a non-zero sweep angle relative to a line perpendicular to the central axis. The trailing edge of the vane is faired into the leading edge of the bifurcation. | 04-01-2010 |
20110008156 | COMPOSITE TURBINE NOZZLE - A composite nozzle segment includes one or more airfoils extending radially between arcuate radially outer and inner band segments having band plies curved about a centerline axis, an outer chordal seal line on an outer aft flange of the outer band segment, and thickened areas in corners of the outer aft flange along pressure and suction side edges of the outer band segment. The thickened areas may be thickest at the pressure and suction side edges and thinnest near a middle of the outer band segment. The thickened areas taper off from an aft end of the thickened area towards a forward flange of the outer band segment. Insert plies may be disposed between some of the band plies within the thickened areas may be grouped together in a discrete group or be interspersed with some of the band plies. The insert plies may have triangular shapes. | 01-13-2011 |
20110008163 | COMPOSITE ARTICLE AND SUPPORT FRAME ASSEMBLY - A support frame includes a rail engaging a hook of a composite article having plys. The rail included a rail contact surface generally conformal to and contacting a hook contact surface of the hook. The rail and hook contact surfaces being substantially normal to the plys beneath the hook contact surface. One embodiment of the article is a composite nozzle segment including one or more airfoils extending radially between arcuate radially outer and inner band segments having plys curved about a centerline axis and the rail engages a hook of the radially inner band segment. The hook and the rail may be straight or arcuate. The frame includes a central body extending axially aftwardly from the rail to an aft frame flange. A frame pin may be mounted on the frame, engage the inner band segment or one of the airfoils, and may extend into a cavity in the airfoil. | 01-13-2011 |
20130164140 | AIRFOILS INCLUDING COMPLIANT TIP - An airfoil, a fan assembly and an engine include at least one airfoil including a root portion, a body portion and a tip portion. The body portion is configured extending radially outward from the root portion and the tip portion is configured extending radially outward from the root portion and the body portion. The airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil including a compliant tip at the tip portion. The compliant tip extending along at least a portion of the tip portion in a chord-wise direction and a span-wise direction. The compliant tip is configured to provide wave propagation along the tip portion such that critical strain proximate the tip portion and the trailing edge is reduced during a foreign object impact. | 06-27-2013 |
20130302168 | Embedded Actuators in Composite Airfoils - An airfoil having active actuators and at least one morphing area allowing shape change of the airfoil and further allowing for optimization of the airfoil shape at more than one operating condition. | 11-14-2013 |
20130327262 | METHODS AND SYSTEMS FOR STITCHING COMPOSITE MATERIALS - A composite material includes a composite body having a composite surface, and a reinforcing element extending through the composite body in a first plurality of stitches and a second plurality of stitches. The first plurality of stitches are aligned relative to the composite surface substantially similarly to each other. The second plurality of stitches are aligned relative to the composite surface substantially dissimilarly to each other. | 12-12-2013 |
20140112796 | COMPOSITE BLADE WITH UNI-TAPE AIRFOIL SPARS - A gas turbine engine composite blade includes an airfoil having pressure and suction sides extending outwardly in a spanwise direction from a blade root along a span to a blade tip. A core section of the blade including composite quasi-isotropic plies extends spanwise outwardly through the blade. One or more spars including a stack of uni-tape plies having predominately a 0 degree fiber orientation with respect to the span and extending spanwise outwardly through the root and a portion of the airfoil towards the tip. Spars may include pressure and suction side spars sandwiching a chordwise extending portion of the core section in the airfoil and which be located near or along the pressure and suction sides respectively. Chordwise extending portion may be centered about a maximum thickness location of the airfoil. Spars may have height, width, and thickness that avoids flexural airfoil modes. | 04-24-2014 |