Matches 1 - 32 out of 32


Match Document Document Title
US20110211946 WELDED NOZZLE ASSEMBLY FOR A STEAM TURBINE AND ASSEMBLY FIXTURES  
A nozzle blade and nozzle ring assembly includes a nozzle blade having radially inner and outer sidewalls with an airfoil portion extending therebetween; the inner and outer sidewalls walls formed...
US20140301836 VANE ASSEMBLY AND METHOD OF MAKING THE SAME  
A vane assembly for a gas turbine engine comprises at least one vane, a first platform and a second platform. The at least one vane has a first end and an opposite second end with the first end of...
US20150125291 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...
US20080152488 Cantilevered nozzle with crowned flange to improve outer band low cycle fatigue  
A flange for supporting arcuate components comprising at least one arcuate rail, each arcuate rail having an inner radius, a first taper location, a first taper region, a second taper location, a...
US20080131276 Thermally decoupled mixer  
The present invention provides a mixer assembly including a mixer and a plurality of scoops attached around a circumference of the mixer element via a combination of sliding brackets and fixed...
US20140241874 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...
US20090162194 Annular component  
A stator vane assembly for a compressor has a support structure which carries and is bounded by an annular stator vane structure. The stator vane structure comprises a central bore and a sleeve...
US20050100442 Method of soldering a compressor nozzle ring of a gas turbine  
Titanium-based metal parts (1, 3) are soldered by using as a filler metal (7) an aluminium alloy containing magnesium and virtually no silicon. Application to the bonding of blades (3) to the...
US20130287563 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...
US20080138201 FLOW-GUIDING DEVICE AND FAN ASSEMBLY  
A flow-guiding device, connected between two fans disposed in series and rotating in the same rotation direction, includes a main frame and a plurality of flow-guiding pieces. The flow-guiding...
US20100111682 CRENELATED TURBINE NOZZLE  
A turbine nozzle includes a row of vanes extending radially between annular outer and inner bands. The outer band includes a pair of radial flanges defining an annular seal groove therebetween....
US20090028699 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...
US20140301841 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...
US20100254804 STATOR VANE ASSEMBLY  
A stator vane assembly comprising: an inner vane support (44); an outer vane support; and a plurality of vanes (50) extending radially between the inner vane support (44) and the outer vane...
US20150027131 Axial Compressor, Gas Turbine with Axial Compressor, and its Remodeling Method  
An axial compressor includes: a rotor as a rotational shaft; a plurality of rotor blades mounted on the rotor; a compressor casing that covers the rotor and the rotor blades; a plurality of stator...
US20170037871 TURBOMACHINE FAN FRAME COMPRISING IMPROVED ATTACHMENT MEANS  
A turbomachine fan frame including a central hub, a plurality of radial vanes installed on the hub and distributed around the hub, each vane including an inner radial end root at which the vane is...
US20160327141 STATOR ASSEMBLY OF HYDROKINETIC TORQUE CONVERTER, AND METHOD FOR MAKING THE SAME  
A stator of a hydrokinetic torque converter comprises a stator hub having an axis, a stator belt coaxial to the axis and a plurality of stator blades extending radially outwardly between the...
US20160290169 TURBINE FRAME AND AIRFOIL FOR TURBINE FRAME  
A turbine frame for a turbine engine having an axial centerline, the turbine frame comprising an inner hub, an outer hub encircling the inner hub, a plurality of struts extending between the inner...
US20160258307 FLOATING PANEL FOR A GAS POWERED TURBINE  
A foil assembly for a gas powered turbine includes a plurality of floating wall sectors arranged circumferentially about an axis defined by a flowpath. Each of the floating wall sectors includes a...
US20160201488 VANE ASSEMBLY WITH TRAPPED SEGMENTED VANE STRUCTURES  
A vane assembly includes inner and outer rings, a plurality of segmented vane structures circumferentially-spaced around a central axis and between the inner and outer rings, and at least one...
US20160130960 Mixed Stator for an Axial Turbine Engine Compressor  
The present application relates to a stator for a low-pressure compressor of an axial turbine engine. The stator includes an annular row of stator vanes with connection vanes, and support vanes...
US20160123188 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...
US20160108746 VANE ASSEMBLY INCLUDING TWO- AND THREE-DIMENSIONAL ARRANGEMENTS OF CONTINUOUS FIBERS  
A vane assembly includes a plurality of airfoils that extend from a first end to a second, opposed end. A first platform is at the first end and is joined to the plurality of airfoils. A second...
US20160090862 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...
US20160084096 CLAMPED VANE ARC SEGMENT HAVING LOAD-TRANSMITTING FEATURES  
A vane arc segment includes a radially inner and outer platforms and an airfoil mechanically clamped between the platforms. The airfoil has an airfoil section that extends radially between...
US20160076390 MOUNTING AND SEALING ARRANGEMENT FOR A GUIDE VANE OF A GAS TURBINE  
The invention relates to a mounting and sealing arrangement for a guide vane of a gas turbine, which includes a vane carrier for carrying said vanes in a ring-like arrangement, whereby the vanes...
US20160069201 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...
US20160047259 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...
US20160024949 MID-TURBINE FRAME AND GAS TURBINE ENGINE INCLUDING SAME  
A mid-turbine frame for a gas turbine engine ducts gases between a high pressure turbine and a low pressure turbine. The mid-turbine frame may include an outer flowpath ring, an inner flowpath...
US20150354381 FLOW DISTRIBUTION BLADING COMPRISING AN IMPROVED SEALING PLATE  
The invention concerns a fixed flow distribution blading (10) in a turbomachine, comprising two coaxial annular platforms that are internal (12) and external respectively, linked to each other by...
US20150330237 Casing arrangement for a gas turbine  
The present invention relates to a gas turbine casing arrangement having a gas turbine casing element (10), a guide-vane ring with an outer ring (20), and a coated ring (30), which lies radially...
US20150300205 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...

Matches 1 - 32 out of 32