| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415209200 | Having means for mounting diaphragm or plural vane holder to casing | 18 |
| 20130089417 | WEAR PREVENTION SYSTEM FOR SECURING COMPRESSOR AIRFOILS WITHIN A TURBINE ENGINE - A wear prevention system for securing compressor airfoils within a turbine engine while reducing wear of related components is disclosed. The wear prevention system may include a compressor diaphragm spring positioned in an airfoil receiving channel between a radially outer surface of a diaphragm base and a radially inner surface of the airfoil receiving channel. The spring may bias the diaphragm base and airfoil attached thereto radially inward against upstream and downstream arms formed from upstream and downstream recesses extending axially from the airfoil receiving channel in the compressor case. The compressor diaphragm spring may dampen vibration and increase service life of the diaphragm base. | 04-11-2013 |
| 20090155068 | RADIAL LOADING ELEMENT FOR TURBINE VANE - A vane assembly for a gas turbine engine comprising a number of radial loading elements disposed between lugs of the vane ring and the vane support, such as to generate a radial load force against the vane ring. The radial load force prevents unwanted relative movement between the vane ring and the vane support during operation of the gas turbine engine. | 06-18-2009 |
| 20090092487 | Systems and Methods Involving Multiple Torque Paths for Gas Turbine Engines - Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative spool assembly for a gas turbine engine, which incorporates a compressor, a turbine and a gear assembly, includes: a shaft operative to be driven by the turbine; a first spool segment operative to couple the shaft to the compressor; and a second spool segment operative to couple the shaft to the gear assembly. The first spool segment and the second spool segment are not coupled to each other. | 04-09-2009 |
| 20090169376 | Turbine Nozzle Segment and Method for Repairing a Turbine Nozzle Segment - A turbine nozzle segment includes a first band, an airfoil extending from the first band and a support attached to the first band. The support may have a plurality of circumferentially spaced apart tabs. | 07-02-2009 |
| 20080286098 | Wear minimization system for a compressor diaphragm - Aspects of the invention relate to a system for reducing relative movement between the outer shroud of a compressor diaphragm and the compressor shell of a turbine engine, thereby minimizing the wear and prolonging the life of such parts. Embodiments of the invention include a system for applying a preload on the outer shroud of a compressor diaphragm. The preload can be applied in the axial and/or radial directions. The preload can be applied at or proximate the joint between two shell segments, which is typically the location of the largest relative movement. In one embodiment, the preload can be achieved by providing one or more load applying members that operatively engage the outer shroud. A load applying member according to aspects of the invention includes a first portion, a second portion, and a biasing member operatively positioned therebetween. The biasing member can be a plurality of spring washers. | 11-20-2008 |
| 20090311095 | Centrifugal Pump with Segmented Diffuser - A centrifugal pump with a volute and at least one stage with an associated impeller and removable diffuser assembly comprises: multiple diffuser segments, each diffuser segment comprising a central passage from an inner curvilinear surface to an outer curvilinear surface and a curvilinear leading engagement surface between a leading end of its curvilinear inner surface and its curvilinear outer surface; multiple curvilinear volute mounting surfaces within the volute, each curvilinear mounting surface receiving a corresponding diffuser segment to mount the diffuser segments in a generally annular pattern about the impeller to form the removable diffuser assembly, with the curvilinear inner surface of each diffuser segment proximate an outer periphery of the impeller and the curvilinear leading engagement surface of each diffuser segment engaging a trailing portion of the curvilinear outer surface of an adjacent one of the diffuser segments; and a volute connecting passage within the volute for coupling the central passages of each diffuser segment to a pump outlet. | 12-17-2009 |
| 20080292457 | Device for Suspending Guide Blades | 11-27-2008 |
| 20080286097 | Support bar with adjustable shim design for turbine diaphragms - A support arrangement for a diaphragm segment in a turbine casing that includes: 1) a support bar joined to a diaphragm segment; 2) a turbine casing comprising a vertical wall and a horizontal shoulder, wherein a portion of the horizontal shoulder underlies the support bar; 3) a cut out area defined by the vertical wall and an outer edge of the support bar; and 4) a shim interposed between the horizontal shoulder and the support bar. The cut out area may be a size that allows the shim to pass through. | 11-20-2008 |
| 20110250063 | SUPPORT BAR FOR STEAM TURBINE NOZZLE ASSEMBLY - A support bar for a steam turbine nozzle assembly is disclosed. In one embodiment, the support bar includes a hook-shaped portion for engaging a lip portion of a steam turbine diaphragm, wherein the steam turbine support bar is configured to non-affixedly join a steam turbine casing to the steam turbine diaphragm. | 10-13-2011 |
| 20110164971 | NOZZLE STAGE FOR A TURBOMACHINE COMPRESSOR - The invention relates to a nozzle stage for a turbomachine compressor, the stage comprising two coaxial shrouds, a radially inner shroud and a radially outer shroud, and radial vanes extending between the shrouds and being connected via their ends to the shrouds, together with a support for abradable material that is mounted by crimping onto the upstream and downstream edges of the inner shroud, the inner shroud presenting openings in which the radially inner ends of the vanes are inserted and fastened. The radially inner ends of the vanes are plane and do not have any projecting tenons. | 07-07-2011 |
| 20110150644 | DIAPHRAGM SHELL STRUCTURES FOR TURBINE ENGINES - A shell structure for a turbine engine that includes a plurality of diaphragms, wherein each diaphragm comprises: an annularly formed support structure that positions and secures a row of circumferentially spaced stator blades, and wherein the plurality of diaphragms are configured and axially stacked such that each diaphragm abuts the diaphragm that is positioned directly upstream from it and the diaphragm that is positioned directly downstream from it such that a first shell structure is formed; a second shell structure disposed outboard of the first shell structure; and an intermediate chamber defined between an outboard face of the first shell structure and an inboard face of the second shell structure; wherein: a downstream end and an upstream end of the first shell structure define the axial length of the first shell structure; one or more downstream radial ports are defined at the approximate axial position of the downstream end of the first shell structure, each downstream radial port fluidly connecting the intermediate chamber to the main flow path of the turbine engine; and between the axial position of the downstream axial ports and the axial position of the upstream end of the first shell structure, the first shell structure is configured such that the intermediate chamber is substantially sealed from the main flow path. | 06-23-2011 |
| 20110097206 | ANNULAR FLANGE FOR FASTENING A ROTOR OR STATOR ELEMENT - A radial annular flange of a rotor or stator element of a turbomachine including, at an inner/outer periphery, alternating solid portions and hollow portions, the solid portions including orifices for passing fastener bolts. The flange in the bottom of at least one hollow portion has a radius relative to the axis of the turbomachine that is less/greater than the radius of a circle that is tangential to the outsides/insides of the orifices for passing bolts through the solid portions. | 04-28-2011 |
| 20110116919 | SUPPORT BAR FOR TURBINE DIAPHRAGM THAT FACILITATES REDUCED MAINTENANCE CYCLE TIME AND COST - A support bar for a turbine diaphragm that facilitates reduced maintenance cycle time and cost is provided. In one aspect, the support bar is secured to the turbine diaphragm vertically rather than horizontally, allowing access to remove a lower diaphragm half without having to remove the rotor for maintenance. | 05-19-2011 |
| 20110305566 | ADJUSTABLE SUPPORT APPARATUS FOR STEAM TURBINE NOZZLE ASSEMBLY - An adjustable support apparatus for a steam turbine nozzle assembly is disclosed. In one embodiment, a steam turbine apparatus includes: a diaphragm segment having a horizontal joint surface and an angled ledge below the horizontal joint surface, the angled ledge configured to receive a complementary angled portion of a wedge member. | 12-15-2011 |
| 20100290902 | REPAIR OF INDUSTRIAL GAS TURBINE NOZZLE DIAPHRAGM PACKING - A technique for refurbishing nozzle diaphragm sections of a gas turbine replaces an eroded section of the nozzle diaphragm with a replacement part designed to engage a slot machined in the nozzle diaphragm. The replacement part is formed of a material with capable of sustained exposure to higher temperature than the original eroded section, and with a similar coefficient of expansion as the material used for manufacture the original nozzle diaphragm. The combination of the nozzle diaphragm and the replacement part conform to the original manufacturer's dimensional specifications for the nozzle diaphragm. | 11-18-2010 |
| 20120128482 | OUTER SHELL SECTOR FOR A BLADED RING FOR AN AIRCRAFT TURBOMACHINE STATOR, INCLUDING VIBRATION DAMPING SHIMS - An assembly forming an outer shell sector, for a bladed ring sector configured to be used on a compressor or turbine stator in an aircraft turbomachine, including a plurality of elementary sectors and vibration damping shims each of them being inserted between two elementary sectors associated with it. A profile of each vibration damping shim is approximately the same as a profile of the elementary sectors. | 05-24-2012 |
| 20120128481 | ANTI-WEAR DEVICE FOR THE BLADES OF A TURBINE DISTRIBUTOR IN AN AERONAUTICAL TURBINE ENGINE - A blade sector of a turbine distributor to be carried by a turbine casing of an aeronautical turbine engine, including a front connection mechanism and a rear connection mechanism, wherein the front connection mechanism is adapted so as to bear against a holder carried by the turbine casing. The sector further includes an anti-wear device formed by a piece of a metal material surrounding the front end of the front connection mechanism and provided between the front connection mechanism and the holder to ensure a sliding contact between the two parts. The anti-wear device is axially maintained in position on the blade sector using an attachment mechanism engaging with the front connection mechanism. | 05-24-2012 |
| 20120282088 | INNER RING FOR FORMING A GUIDE BLADE RING, AND GUIDE BLADE RING AND TURBOMACHINE - An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring. | 11-08-2012 |
