| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415189000 | Removably secured or mounted in casing | 15 |
| 20080240912 | METHOD AND APPARATUS FOR ASSEMBLING TURBINE ENGINES - A method of assembling a stator assembly includes coupling at least one stator ring segment to a portion of a casing using at least one circumferential stator ring groove defined in the casing. The method also includes coupling at least one stator blade assembly to a portion of the stator ring segment such that at least one radial passage is at least partially defined by at least one of the stator blade assembly and the stator ring segment. The stator assembly includes at least one first radial passage defined within a portion of the stator ring segment. The assembly also includes at least one second radial passage coupled in flow communication with the first radial passage. The second radial passage is at least partially adjacent to at least one of a portion of the stator blade assembly and a portion of the stator ring segment. | 10-02-2008 |
| 20090324400 | STRUT FOR A GAS TURBINE ENGINE - The strut is for use in a gas turbine engine has body, typically having an airfoil shape, having a leading edge and a trailing edge. The leading edge has at least one gas inlet in direct fluid communication with at least one outlet located in the trailing edge through which gas may be redirected from the leading edge to the trailing edge through the strut for injection back into a wake region downstream of the strut. | 12-31-2009 |
| 20100054929 | TURBINE AIRFOIL CLOCKING - An assembly of airfoils in a compressor of a turbine engine that includes at least three axially stacked rows of airfoils: a middle airfoil row, a first upstream airfoil row, and a first downstream airfoil row. The middle airfoil row may be bordered on each side by the first upstream airfoil row, which comprises the first row of airfoils in the upstream direction from the middle airfoil row, and the first downstream airfoil row, which comprises the first row of airfoils in the downstream direction from the middle airfoil row. The first upstream airfoil row and the first downstream airfoil row may have substantially the same number of similarly shaped airfoils. The first upstream airfoil row and the first downstream airfoil row each may comprise a row of rotor blades, which rotate at substantially the same speed during operation. The middle airfoil row may comprise a row of stator blades, which remains substantially stationary during operation. At least 90% of the airfoils of the first upstream airfoil row and at least 90% of the airfoils of the first downstream airfoil row may comprise a clocking relationship of between 25% and 75% pitch. | 03-04-2010 |
| 20100061844 | LOAD PIN FOR COMPRESSOR SQUARE BASE STATOR AND METHOD OF USE - A load pin has an end portion, and a vane has a base with a cutout in the base, wherein the end portion of the load pin engages a wall portion of the cutout in the base of the vane, thereby inhibiting any movement of the vane in a particular direction. | 03-11-2010 |
| 20100166545 | STATOR ASSEMBLY FOR A GAS TURBINE ENGINE - A stator assembly for a gas turbine engine includes: (a) an outer shroud having a circumferential array of outer slots; (b) an inner shroud having a circumferential array of inner slots; (c) a plurality of airfoil-shaped vanes extending between the inner and outer shrouds, each vane having inner and outer ends which are received in the inner and outer slots; and (d) an annular, resilient retention ring spring which engages the inner ends of the vanes and urges them in a radially inward direction. | 07-01-2010 |
| 20110085899 | SHROUD ASSEMBLY WITH DISCOURAGER - A turbine shroud assembly is disclosed, the shroud assembly including an outer shroud, at least one inner shroud attached to the outer shroud, and at least one discourager enclosed within the inner shroud. The discourager prevents the hot gas or steam in the turbine from having a direct line of access to the outer shroud. In one embodiment, one inner shroud is provided for the shroud assembly, with one discourager enclosed within the inner shroud, the discourager positioned offset from the inner shroud so as to extend past the inner shroud and into an inner shroud of a neighboring shroud assembly. In another embodiment, a plurality of inner shrouds are provided, each inner shroud enclosing a discourager, the discouragers being adjacent to each other within the inner shrouds and positioned offset from the inner shrouds so as to cover a gap between the inner shrouds. | 04-14-2011 |
| 20110250058 | Turbine Nozzle Apparatus and Associated Method of Manufacture - A turbine nozzle is constructed from a plurality of associated circumferential turbine nozzle segments each of which incorporates at least one pre-formed annular-segment passage bounded at a first azimuthal boundary by a first portion of a first bounding nozzle vane, and at a second azimuthal boundary by a second portion of a second bounding nozzle vane, with the at least one pre-formed annular-segment passage therebetween, wherein when assembled in the turbine nozzle, a first portion of a first bounding nozzle vane of one circumferential turbine nozzle segment is joined to a second portion of a second bounding nozzle vane of another adjacent circumferential turbine nozzle segment so as to form therebetween a nozzle vane of the turbine nozzle, wherein the minimum through-flow area of the associated at least one pre-formed annular-segment passage is substantially unaffected by the assembly of the circumferential turbine nozzle segments to form the turbine nozzle. | 10-13-2011 |
| 20120134791 | GAS TURBINE NOZZLE ATTACHMENT SCHEME AND REMOVAL/INSTALLATION METHOD - A turbine nozzle attachment assembly includes an outer turbine component (a shroud or a turbine shell) formed with a circumferential groove open in a forward-facing axial direction; a nozzle segment including a vane extending between inner and outer bands, the outer band provided with an upstanding annular hook formed with a hook element extending in an aft-facing axial direction and received in the circumferential groove. The upstanding annular hook and hook element are formed with a circumferentially-oriented slot. An anti-rotation block is located in the circumferentially-oriented slot, and an anti-tipping plate having a circumferential width greater than a corresponding circumferential width of the circumferentially-oriented slot substantially covers a forward face of the anti-rotation block. The anti-rotation block and the anti-tipping plate are fastened directly to the outer turbine component. | 05-31-2012 |
| 20120189438 | GAS TURBINE ENGINE STATOR VANE ASSEMBLY - A method of assembling gas turbine engine front architecture includes positioning inner and outer fairings relative to one another. Multiple vanes are arranged circumferentially between the inner and outer fairings. A liquid sealant is applied around a perimeter of the vanes to seal between the vanes and at least one of the fairings. | 07-26-2012 |
| 20130022453 | ALIGNMENT MEMBER FOR STEAM TURBINE NOZZLE ASSEMBLY - An alignment member for a turbine diaphragm segment is disclosed. The alignment member is configured to span radially across a portion of the turbine diaphragm segment and an adjacent turbine casing segment. The alignment member can include: a main body having a first aperture for aligning with a first corresponding aperture in one of the turbine diaphragm segment or the turbine casing segment; and a flange extending from the main body, the flange including a second aperture for aligning with a portion of the other of the turbine diaphragm segment or the turbine casing segment, the alignment member for adjusting a position of the turbine diaphragm segment relative to the adjacent turbine casing segment. | 01-24-2013 |
| 20130039749 | METHODS AND APPARATUS TO FACILITATE TURBINE CASING ASSEMBLY - A turbine assembly is provided. The turbine assembly includes an inner turbine casing and an outer turbine casing radially outward from the inner turbine casing, the outer turbine casing including an aperture extending therethrough and a support assembly extending through the aperture, the support assembly externally adjustable outside of the outer turbine casing to adjust the inner turbine casing relative to the outer turbine casing. | 02-14-2013 |
| 20140003926 | COMPRESSOR FOR A GAS TURBINE AND METHOD FOR REPAIRING AND/OR CHANGING THE GEOMETRY OF AND/OR SERVICING SAID COMPRESSOR | 01-02-2014 |
| 20140093363 | LINER AND METHOD OF ASSEMBLY - An assembly includes a plurality of vanes, a forward liner segment, and an aft liner segment. The forward liner segment and the aft liner segment are mounted to the plurality of vanes and each segment comprises an arc of less than 360° in length. | 04-03-2014 |
| 415190000 | Axially arranged securing or mounting means | 2 |
| 20100135777 | SPLIT FAIRING FOR A GAS TURBINE ENGINE - A fairing for a structural strut in a gas turbine engine includes: (a) an inner band; (b) an outer band; (c) a hollow, airfoil-shaped vane extending between the inner and outer bands; (d) wherein the fairing is split along a generally transverse plane passing through the inner band, outer band and vane, so as to define a nose piece and a tail piece; and (e) complementary structures carried by the nose piece and the tail piece adapted to secure the nose piece and the tail piece to each other. | 06-03-2010 |
| 20140140832 | Quick Engine Change Assembly for Outlet Guide Vanes - A quick engine change assembly, comprises a first circular frame member, a plurality of doublet supports spaced about the first circular frame member, the doublet supports being contoured along the axial direction, a flow surface defined between the plurality of doublet supports and, a plurality of cradles, each of the cradles including the doublet supports, the doublet supports from a lower portion of the cradle to the flow surface. | 05-22-2014 |
