ELLIOTT COMPANY Patent applications |
Patent application number | Title | Published |
20140322001 | TURBOMACHINERY STATIONARY VANE ARRANGEMENT FOR DISK AND BLADE EXCITATION REDUCTION AND PHASE CANCELLATION - A turbomachine includes a plurality of rotating blades adjacent to a plurality of stationary vanes attached to a stationary casing. Stationary vanes are spaced apart circumferentially with equal spacing around an inner perimeter of the casing. Optionally, stationary vanes are offset radially and/or circumferentially. Stationary vanes may alternate with leading and/or trailing edges at different distances from the rotating blades. In one embodiment, stationary vanes have tapered leading and/or trailing edge angles to homogenize flow and reduce stator wake excitation, flow excitation, and acoustic excitation due to interaction with spinning modes of acoustic pressure pulsations at rotating blade passing frequency. Tapered trailing edges are arranged such that they are inclined at mutually opposing angles to reduce rotor blade and/or disk excitation by: a) homogenizing the successive wakes within the flow stream, and b) reducing the effect of vortices shed-off the stationary vanes on acoustic modes of the gas within the casing. | 10-30-2014 |
20140000831 | DEPOSITED CORE CAST DIAFRAM PROCESS | 01-02-2014 |
20130309087 | ASSEMBLY AND METHOD OF ATTACHING STUB SHAFT TO DRUM OF AXIAL COMPRESSOR ROTOR SHAFT - An assembly and method for an axial compressor includes an axial shaft extending between an inlet casing and a discharge casing along the longitudinal length of a compressor housing. The axial shaft assembly includes a first stub shaft, a second stub shaft, and a hollow shaft drum having a longitudinal axis. The first stub shaft and the second stub shaft are coupled to opposing ends of the shaft drum along its longitudinal axis. A plurality of keys is disposed in a radial arrangement near the outer circumference of the first and second stub shafts and the shaft drum. A plurality of pins engage the plurality of keys, whereby the pins prevent the shaft drum from rotating axially relative to the first stub shaft and the second stub shaft and prevent the shaft drum from axially and radially separating from the stub shafts. | 11-21-2013 |
20130263659 | PASSIVE DYNAMIC INERTIAL ROTOR BALANCE SYSTEM FOR TURBOMACHINERY - A passive dynamic inertial rotor balance system including a plurality of balancing members fitted onto a rotor shaft at locations of predicted maximum shaft modal deflection. Each of the balancing members has at least one chamber and located within the at least one chamber is a plurality of movable weights and a viscous fluid. As the shaft accelerates toward an unbalance point, the weights move within the at least one chamber to a location which is opposite from the unbalance point. The viscous fluid provides damping for the movable weights to prevent excess movement within the chamber and to provide lubrication thereof. A system for self-correcting an unbalance of a turbomachinery rotor during rotation of the rotor and a method for balancing a rotor in a turbomachinery is also provided. | 10-10-2013 |
20130094957 | BRUSH RING SEAL - A brush ring seal device for installation within a packing case of a turbine includes: a brush seal carrier having a substantially ring-shaped body portion having a front face, a rear face, an inner circumferential groove, and an outer circumferential groove; a brush seal mounted within the inner circumferential groove of the brush seal carrier; and a ring-shaped spring mounted within the outer circumferential groove of the brush seal carrier. The rear face of the brush seal carrier is coated with an anti-friction coating, thereby allowing movement of the brush ring seal device within the packing case. | 04-18-2013 |
20100272561 | Boltless Multi-part Diaphragm for Use with a Centrifugal Compressor - A diaphragm assembly of a centrifugal compressor includes a return channel wall having a generally ring-like shape; a vane assembly having a plurality of vanes formed integrally with at least one ring-shaped track having a rail structure extending therefrom; and a diaphragm wall having a generally ring-like shape and at least one groove extending around a circumference thereof. The vane assembly is fixedly coupled to the return channel, thereby forming a return channel assembly. The return channel assembly is coupled to the diaphragm wall by sliding the rail structure into the at least one groove of the diaphragm wall. | 10-28-2010 |
20100172745 | CENTRIFUGAL COMPRESSOR HAVING ADJUSTABLE INLET GUIDE VANES - An apparatus for adjustment of inlet guide vanes of a compressor includes a ring having a plurality of slots spaced around a circumference thereof; a plurality of lever arm assemblies each having a pin that includes a body with a first end and a second end and a lever arm extending perpendicularly from the second end of the body of the pin; a plurality of vanes each coupled to an end of one of the plurality of lever arms by a shaft; and a rack and pinion drive mechanism. The pin of each of the lever arm assemblies is configured to be positioned within each of the plurality of slots such that the first end of the pin extends into the slot. The rack and pinion drive mechanism includes a pinion coupled to the shaft of one of the plurality of vanes, thereby creating a drive vane; and a driven rack operationally coupled to the pinion. The drive vane is configured to rotate the ring via the rack and pinion drive mechanism, thereby adjusting an angular position of the plurality of vanes. | 07-08-2010 |
20100037462 | METHOD OF POSITIONING A BEARING ASSEMBLY AND CENTERING SUPPORT STRUCTURE THEREFOR - The bearing assembly is intended for application with rotor shafts in turbomachinery. The bearing assembly includes an annular bearing in which the shaft is disposed and a support structure for supporting the bearing. The bearing support is mounted about and radially supports the bearing. The bearing support at least in part defines a squeeze film annulus of the bearing assembly. A plurality of centering elements is associated with the bearing and bearing support and act to center the bearing within the squeeze film annulus. The centering elements are provided at radially spaced locations around the bearing. The centering elements may also be cylinder springs provided at uniformly spaced locations around the bearing. The centering elements may additionally be load cell springs provided at uniformly spaced locations around the bearing. In an alternative embodiment, a singular annular wave spring may be provided in place of the plurality of centering elements. | 02-18-2010 |
20090180858 | Method to Prevent Brinelling Wear of Slot and Pin Assembly - A method to prevent brinelling wear of a slot and pin assembly of an adjustable inlet guide vane mechanism includes: providing a compressor having the adjustable inlet guide vane mechanism including a control ring with a plurality of tapered slots positioned around a circumference of the control ring; providing a plurality of tapered pin/lever arm assemblies each comprising a tapered pin having a tapered body with a first threaded end and a second end, a lever arm extending perpendicularly from the second end of the tapered body of the tapered pin and a vane coupled to an end of the lever arm; positioning the tapered pin of the tapered pin/lever arm assembly within each of the plurality of tapered slots such that the first threaded end of the tapered body of the tapered pin extends through the tapered slot; positioning a washer and spring over the first threaded end of the tapered pin of each of the tapered pin/lever arm assemblies; and securing the tapered pin of each of the tapered pin/lever arm assemblies within each of the tapered slots by coupling a nut to the first threaded end of the tapered pin of each of the tapered pin/lever arm assemblies. The tapered body of the tapered pin of each of the tapered pin/lever arm assemblies and each of the plurality of tapered slots are shaped to ensure contact between the tapered body of the tapered pin and the tapered slot thereby preventing brinelling wear. | 07-16-2009 |
20090068006 | Tilted Cone Diffuser for Use with an Exhaust System of a Turbine - An exhaust system for a turbine includes an annular diffuser and a collector. The annular diffuser is positioned adjacent to a final stage of the turbine and includes a hub portion surrounding a turbine shaft and an outer cone having a substantially frusto-conical shape that is radially symmetrical about a central longitudinal axis thereof that is tilted relative to the turbine shaft. The collector has an inlet extending from the annular diffuser and an outlet. The collector is configured to include a turn that causes the collector to turn exhaust gases approximately 90° from the longitudinal axis of the turbine shaft. The outer cone of the annular diffuser is tilted in a direction of the turn of the collector. | 03-12-2009 |
20080246204 | Positioning Device for the Fabrication of Compressor Impellers - Disclosed is a multi-axis workpiece manipulator or positioning device ( | 10-09-2008 |