| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415209400 | Vane fixed between radially separate surfaces | 13 |
| 20090028699 | STATIC GAS TURBINE COMPONENT AND METHOD FOR REPAIRING SUCH A COMPONENT - A static gas turbine component includes an inner and an outer annular support member and a plurality of circumferentially spaced radial struts arranged between the support members for transmitting structural loads. Each of a plurality of the struts includes a load carrying core rigidly fixed to both the inner and the outer support member forming a unitary carcass with the support members, an impact resistant shell surrounding the core, and an energy absorbing material arranged between the core and the shell. | 01-29-2009 |
| 20130287563 | TURBINE DIAPHRAGM CONSTRUCTION - An axial flow turbine diaphragm is constructed without welding or other metal fusion or melting techniques. Static blade units are attached to inner and outer diaphragm rings by radially inner platform portions that engage the radially inner ring, and radially outer platform portion s that engage the radially outer ring, the inner platform portions being elongate in the circumferential direction of the turbine diaphragm and the outer platform portions being elongate in a direction compatible with the stagger angle of the aerofoils. The outer circumference of the radially inner ring has a blade unit retaining feature of complementary shape and orientation to the inner platform portions of the static blade units, and the inner circumference of the radially outer ring is provided with a plurality of blade unit retaining features of complementary shape and orientation to corresponding outer platform portions of the static blade units. | 10-31-2013 |
| 20140241874 | WEAR LINER SPRING SEAL - A wear liner for a stator vane includes a shaped member, comprising a U-shaped portion that receives a foot of a stator vane. A first end of the wear liner is biased into contact with the stator vane. A spring seal extends from the U-shaped portion and into bias contact with an inner surface of the support structure to further prevent leakage between the stator foot and case support structure. | 08-28-2014 |
| 20140301841 | TURBOMACHINE COMPRESSOR GUIDE VANES ASSEMBLY - A sectorized turbomachine compressor guide vanes assembly includes assembled sectors forming two concentric shell rings, one outer and one inner, between which vanes are arranged with their leading and trailing edges near transverse faces of the shell rings, and of which an outer shell ring externally includes an attachment mechanism to an external casing that houses the sectors. The attachment mechanism is axially offset from the rear transverse face of the shell ring to be located, in projection, in alignment with the vanes between the leading and trailing edges thereof. | 10-09-2014 |
| 20150125291 | BRACKET FOR MOUNTING A STATOR GUIDE VANE ARRANGEMENT TO A STRUT IN A TURBINE ENGINE - A turbine engine assembly, with an axis, includes a vane arrangement segment, a mounting bracket and a strut. The vane arrangement segment includes a first platform segment, a second platform segment and a guide vane that extends radially between and is connected to the first and the second platform segments. The mounting bracket is connected to the vane arrangement segment. The strut extends radially through the first platform segment, the second platform segment and the guide vane, and is engaged with the mounting bracket. The mounting bracket attaches the vane arrangement segment to the strut. | 05-07-2015 |
| 20150300205 | SYSTEMS AND METHODS FOR ANTI-ROTATIONAL FEATURES - Systems and methods are disclosed for anti-rotation lugs. A stator for a gas turbine engine may comprise an outer shroud, an inner shroud, and a plurality of vanes located between the outer shroud and the inner shroud. A plurality of anti-rotation lugs may be coupled to the inner shroud. The anti-rotation lugs may be configured to contact a diffuser case in order to prevent rotation of the stator. The anti-rotation lugs may comprise a body and a tapered shoulder. The tapered shoulder may distribute stress concentrations in the anti-rotation lugs. | 10-22-2015 |
| 20150354381 | FLOW DISTRIBUTION BLADING COMPRISING AN IMPROVED SEALING PLATE - The invention concerns a fixed flow distribution blading ( | 12-10-2015 |
| 20160047259 | GAS TURBINE ENGINE STRESS ISOLATION SCALLOP - A nozzle segment for a gas turbine engine includes an arcuate outer vane platform segment. An arcuate inner vane platform segment spaced from the arcuate outer vane platform segment. A multiple of airfoils between the arcuate inner vane platform segment and the arcuate outer vane platform segment, the arcuate outer vane platform segment includes a scallop slot and a seal that seals the scallop slot. | 02-18-2016 |
| 20160069201 | Attachment Faces for Clamped Turbine Stator of a Gas Turbine Engine - An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face. | 03-10-2016 |
| 20160090862 | TRIPOD BUCKLE FOR SPLIT FAIRING OF A GAS TURBINE ENGINE - A fairing for a turbine engine strut includes: inner and outer bands; a vane extending between the bands; the fairing is split along a generally transverse plane passing through the bands and the vane, defining nose and tail pieces; wherein the vane is defined by spaced-apart sidewalls extending between a leading edge and a trailing edge, each sidewall split into forward and aft portions by the transverse plane; wherein each sidewall portion carries a radially-inwardly extending post, the posts positioned such that pairs of the posts lie adjacent to each other when the nose piece and tail piece are assembled, wherein each pair of adjacent posts includes at least two non-parallel faces; and a pair of slotted buckles, wherein each slotted buckle surrounds and clamps together a pair of the posts, wherein each pair of adjacent posts contacts a slot of the corresponding buckle in a tripod contact configuration. | 03-31-2016 |
| 20160123188 | STATOR SHROUD SYSTEMS - A shroud for a turbomachine stator includes a first portion and a second portion configured to sandwich around at least a portion of a stator vane assembly, a first pin hole defined in the first portion at an angle relative to an axial direction of the turbomachine, and a second pin hole defined in the second portion at the angle of the first portion, wherein the first pin hole is aligned and in communication with the second pin hole to accommodate a pin configured to be seated in the first and second pin holes. | 05-05-2016 |
| 20160201488 | VANE ASSEMBLY WITH TRAPPED SEGMENTED VANE STRUCTURES | 07-14-2016 |
| 20190145268 | ANNULUS FILLER | 05-16-2019 |
