Class / Patent application number | Description | Number of patent applications / Date published |
029889220 | Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles | 22 |
20080209728 | METHODS AND APPARATUS FOR ATTACHING SWIRLERS TO TURBINE ENGINE COMBUSTORS - A method facilitates assembling a combustor for a gas turbine engine, wherein the combustor includes a swirler assembly. The method comprises machining material to form a domeplate, positioning a sealplate including an overhanging portion against the domeplate, securing the sealplate in position relative to the domeplate with a welding process, and welding the swirler assembly to the domeplate. | 09-04-2008 |
20100064516 | Stator Ring Configuration - A stator ring for use in a compressor of a gas turbine engine and a method of assembling the stator ring are provided. The stator ring includes a first plurality of segments that includes a first segment including a first circumferential end formed with a first cut and a second circumferential end formed with a second cut that is complementary to the first cut, wherein the first plurality of segments are configured to be circumferentially-coupled together, and a second plurality of segments that includes a second segment including a first circumferential end with a third cut and a second circumferential end with a fourth cut that is complementary to the third cut, wherein the second plurality of segments are configured to be circumferentially-coupled together. | 03-18-2010 |
20100077612 | METHOD OF MANUFACTURING A FAIRING WITH AN INTEGRATED SEAL - A method of manufacturing an integrated seal on a component is disclosed, comprising the steps of supplying a component having an edge portion, forming a profile on the edge portion, supplying a seal, applying a bond preparation on a surface on the edge portion, applying a bonding material on the seal, mounting the seal to the edge portion, and curing the bond. A method of assembling a stator assembly is disclosed comprising the steps of providing a vane, providing a first fairing located near a first side of the vane, the first fairing having a first seal coupled to a first edge portion of the first fairing, providing a second fairing located near a second side of the vane, the second fairing having a second seal coupled to a second edge portion of the second fairing and engaging a portion of the first seal with a portion of the second seal. | 04-01-2010 |
20100126018 | METHOD OF MANUFACTURING A VANE WITH REDUCED STRESS - A method of manufacturing an airfoil assembly is described, the method comprising the steps of supplying an airfoil and a band, creating a support aperture in the band capable of receiving a portion of the airfoil, creating a slot in the band for reducing stress in the airfoil, and bonding the airfoil with the band. | 05-27-2010 |
20100313420 | THROUGH-HOLE MANUFACTURING METHOD FOR CYLINDRICAL BODY WALL AND CYLINDRICAL BODY STRUCTURE - There is provided a through-hole manufacturing method for a cylindrical body wall that enables the operation of forming a through-hole without leaving a machining burr on the wall of a cylindrical member to be easily and reliably carried out without depending on experts. A through-hole manufacturing method for a cylindrical body wall in which a machining burr is not formed on inner walls of through holes formed by a tool piercing the wall of a cylindrical body, the method including a hole forming step of forming one pair or a plurality of pairs of the through-holes in the cylindrical body wall by the tool piercing the cylindrical body from the outside orthogonally or substantially orthogonally to a cylindrical body axis of the cylindrical body; and a welding step of sealing the through-hole formed by the tool piercing the cylindrical body from the outer wall to the inner wall by welding using a welding jig made of a material having better heat conductivity than the cylindrical body, wherein the through-hole formed by the tool piercing the cylindrical body from the inner wall to the outer wall is left as a nozzle hole. | 12-16-2010 |
20110265328 | METHOD FOR MOUNTING AN INTEGRAL INNER RING OF A TURBOCOMPRESSOR STATOR - A method for mounting an integral inner ring ( | 11-03-2011 |
20120023746 | METHODS AND APPARATUS FOR FABRICATING A TURBINE NOZZLE ASSEMBLY - A method for fabricating a nozzle segment for use within a turbine nozzle assembly. The method comprises providing a nozzle segment including an outer band, an inner band, and at least one vane extending there between, wherein at least one of the inner band and the outer band is formed with a transition piece groove defined therein, positioning an inspection tool in contact with the nozzle assembly such that the inspection tool is aligned relative to the nozzle segment using at least one datum, and verifying an alignment of each transition piece groove using the inspection tool. | 02-02-2012 |
20120110849 | METHOD FOR ASSEMBLING RADIALLY LOADED VANE ASSEMBLY OF GAS TURBINE ENGINE - A method for assembling a vane ring with a vane support of a vane assembly in a gas turbine engine is described, and includes flexing each of the radial loading elements into the resiliently flexed state simultaneously by sliding the radial loading elements against corresponding lead-in tapers. This can be achieved, for example, using a guide tool which includes a plurality of segments bearing the lead-in tapers and which is previously assembled to the vane support. | 05-10-2012 |
20130014389 | ASSEMBLY FIXTURE WITH WEDGE CLAMPS FOR STATOR VANE ASSEMBLY - A fixture for assembling a stator vane assembly of a gas turbine engine includes a base which defines a multiple of locators to position each of a multiple of vanes relative to an outer fairing and an inner fairing. A first tangential wedge clamp is receivable in a first aperture located within the base for each of the multiple of vanes. A second tangential wedge clamp is receivable in a second aperture located within the base for each of the multiple of vanes. | 01-17-2013 |
20130074338 | PRE-COMPRESSED SEAL INCLUDING REMOVABLE PRE-COMPRESSION MEMBER - A seal is provided that includes a resilient, arc-shaped body having a pair of sealing portions movable between a pre-compressed state and a compressed state. A removable pre-compression member slidingly engages the seal body along at least a portion of its length to hold the sealing portions in the pre-compressed state. In an embodiment, the seal body includes a pair of first retaining features and the pre-compression member includes a retaining portion having a pair of second retaining features that engage the pair of first retaining features to hold the sealing portions in the pre-compressed state. A strap portion extends from and between each retaining portion to allow the pre-compression member to flex during assembly of the seal to accommodate the radius of the seal body. | 03-28-2013 |
20130199041 | METHOD FOR MANUFACTURING MICRO GAS TURBINE - The invention relates to a method for manufacturing an inexpensive micro gas turbine | 08-08-2013 |
20140082940 | METHOD AND FIXTURE FOR AIRFOIL ARRAY ASSEMBLY - An example method of assembling a turbomachine airfoil array includes, among other things, securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed. The method includes mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area, holding a replacement airfoil using the positioning saddle, applying a curable material at an interface between the replacement airfoil and the inner and outer fairing, and curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing. | 03-27-2014 |
20140130354 | METHOD FOR MANUFACTURING TURBINE NOZZLE HAVING NON-LINEAR COOLING CONDUIT - A method for manufacturing a turbine nozzle having a non-linear cooling conduit is disclosed. In one embodiment, a method includes: providing a turbine nozzle. The turbine nozzle includes: an airfoil, a cavity, having an inner surface, located within the airfoil, at least one endwall adjacent the airfoil, and a fillet region connecting the airfoil and the endwall. The fillet region also includes an outer surface. The method also includes: forming a non-linear cooling conduit within the fillet region and adjacent the outer surface of the fillet region of the turbine nozzle. The forming of the non-linear cooling conduit includes curved drilling through a portion of the outer surface of the fillet region of the turbine nozzle. | 05-15-2014 |
20150052750 | METHOD AND TOOLING FOR ASSEMBLING A GUIDE VANE STAGE - A method and tooling for assembling a guide vane stage that includes an inner shroud and an outer shroud that are coaxial and interconnected by radial airfoils, the method including holding plates pressed against an outer surface of the inner shroud so that the plates cover gaps formed between openings in the inner shroud and the airfoils at least in part and in a manner that is leaktight, and applying a sealing resin to the inner surface of the inner shroud so that the resin fills the gaps and so that radially inner ends of the airfoils are embedded in the resin. | 02-26-2015 |
20150107110 | WELDING METHOD AND SYSTEM - A welding method including the steps of: providing, in a first position, a weld target assembly having a welding region and a weld tab located adjacent the welding region, the weld tab changeable from a first physical configuration to a second physical configuration when subject to a first type of weld operation; performing a first weld process on the welding region and weld tab; moving the assembly from the first to a second position; providing safeguard apparatus for cooperating with the weld tab to: prevent the assembly from moving to the second position when the first weld procedure did not include the first type of weld operation; and permit the assembly be moved to the second position when the first weld procedure included the first type of weld operation. The assembly includes a sub-assembly having a foot member and blade portion welded together, thereby ultimately forming an output guide vane. | 04-23-2015 |
20150308278 | Integral Bent Housing for an Axial Turbomachine Compressor - The present application relates to a method for producing a housing for an axial turbomachine compressor having a metal sheet with annular rows of stator blades which are welded to the metal sheet. The method includes the steps of: (a) providing or producing a planar metal sheet with a step of machining in order to form blade stumps; (b) welding stator blades by means of friction to one of the planar faces of the metal sheet, the blades being arranged so as to form parallel straight rows of blades; (c) bending the metal sheet about a bending axis perpendicular to each row of blades, so as to form a half-tube with annular half-rows of blades which are axially spaced apart, and producing annular grooves by means of rolling; (d) welding annular flanges and axial flanges; (e) application of annular layers of abradable material. | 10-29-2015 |
20150375259 | METHOD AND APPARATUS FOR MANUFACTURING PRE-COATED HONEYCOMB SEGMENTS FOR TURBOMACHINES - A method of manufacturing a pre-coated honeycomb segment includes forming a honeycomb segment having a first surface and a second, opposing surface, and providing a coating material on the honeycomb segment. The coating does not extend to the first surface and the second, opposing surface. The method further includes positioning the first surface at a first fixture and forming a coating on the honeycomb segment. | 12-31-2015 |
20160084094 | METHOD AND FIXTURE FOR AIRFOIL ARRAY ASSEMBLY - An example method of assembling a turbomachine airfoil array includes, among other things, securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed. The method includes mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area, holding a replacement airfoil using the positioning saddle, applying a curable material at an interface between the replacement airfoil and the inner and outer fairing, and curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing. | 03-24-2016 |
20160090869 | METHOD OF INSTALLING A DIFFUSER IN AN AIR CYCLE MACHINE - A method of installing a diffuser in an air cycle machine includes placing a first housing on a shaft, placing a seal plate on the shaft, and placing a diffuser on the shaft. Next, the diffuser and the seal plate are aligned with an alignment tool. The alignment tool has a first annular surface to align with a radially outer surface of the seal plate and a second annular surface to align with an annular flange on the diffuser. Finally, the diffuser is fastened to the seal plate and the alignment tool is removed from the diffuser and the seal plate. | 03-31-2016 |
20160175921 | FORGED FUEL INJECTOR STEM | 06-23-2016 |
20160199950 | METHOD FOR ASSEMBLING TWO BLADES OF A TURBOMACHINE NOZZLE | 07-14-2016 |
20160376926 | MANIPULATION OF TURBOMACHINE COMBUSTORS - Embodiments of the present disclosure relate to the manipulation of turbomachine combustors. An apparatus according to the present disclsoure can include: a bracket body including an operative head configured to removably attach a turbomachine combustor; a rotatable joint rotatably coupled to the bracket body through a gear bearing, wherein the gear bearing is configured to rotate the bracket body relative to the rotatable joint; and a suspended member rotatably coupled to the rotatable joint at a first end, and coupled to a suspension joint at a second end, wherein the rotatable joint rotates the gear bearing and the bracket body relative to the suspended member to center the gear bearing about a predetermined axis of rotation. | 12-29-2016 |