Class / Patent application number | Description | Number of patent applications / Date published |
029890010 | Rocket or jet device making | 15 |
20090100678 | ROCKET ENGINE NOZZLE AND METHOD OF FABRICATING A ROCKET ENGINE NOZZLE USING PRESSURE BRAZING - A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket. | 04-23-2009 |
20090188109 | Friction stir welded bladder fuel tank - A method of fabricating a rolling bladder propellant tank assembly includes providing a pair of half-domes comprising a nanophase metallic material and a bladder formed of a ductile metallic material. A bladder support ring extends from at least one of the pair of half-domes. The pair of half-domes are positioned together to form a cavity therein with a portion of the bladder trapped between the pair of half-domes adjacent to the bladder support ring, wherein the bladder is positioned within the cavity. A seal is formed between the pair of half-domes and the bladder by friction stir welding. A friction stir welding pin used to form the seal is aligned with the bladder support ring during the friction stir welding operation. | 07-30-2009 |
20090217525 | Stereolithographic rocket motor manufacturing method - A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, | 09-03-2009 |
20090313825 | GAS TURBINE ENGINE EXHAUST COMPONENT AND MANUFACTURING METHOD OF SAME - A gas turbine exhaust component, such as an exhaust nozzle, is provided that includes circumferential ribs arranged along a longitudinal axis. Longitudinal strakes are supported by the circumferential ribs and arranged about the longitudinal axis. Fastening elements are used to secure the longitudinal strakes to one another to provide a desired exhaust component contour. In one example, fastening elements are used to secure the longitudinal strakes to the circumferential ribs using a bracket. The longitudinal strakes are preformed into the desired exhaust component contour, using low cost forming methods. The longitudinal strakes are formed to fit the circumferential ribs and provide the desired exhaust component contour. The longitudinal strakes are secured to one another to maintain the desired exhaust component contour. The longitudinal strakes may be provided by a low cost steel, in one example. | 12-24-2009 |
20100058586 | METHOD OF MANUFACTURING A WALL STRUCTURE AND A MACHINING TOOL - A method of manufacturing a wall structure includes producing at least one elongated web in a workpiece by feeding a machining tool along the workpiece, wherein the machining tool simultaneously machines a first side surface of the web, a second side surface of the web and a top surface of the web. | 03-11-2010 |
20100229389 | COMBUSTION CHAMBER COMPRISING A COOLING UNIT AND METHOD FOR PRODUCING SAID COMBUSTION CHAMBER - A method for producing a combustion chamber includes providing a combustion chamber wall; forming a plurality of milled recesses in the combustion chamber wall, along a longitudinal axis and in an area of the longitudinal axis transverse to the longitudinal axis; and forming a cooling channel having a substantially rectangular cross section and opposite web walls inside the combustion chamber wall along the longitudinal axis and configured to receive a flow a cooling medium along the longitudinal axis, wherein the plurality of milled recesses form depressions in the web walls. | 09-16-2010 |
20110030215 | METHOD FOR DETERMINING SENSOR LOCATIONS - A method for determining sensor locations in a gas turbine engine is provided. The said method includes providing a turbine rear frame including a radially inner surface, a radially outer surface and a plurality of circumferentially-spaced struts extending between the inner and outer surfaces, wherein a strut sector is defined between each pair of circumferentially-adjacent struts, providing a plurality of fuel nozzles that are each aligned with a strut sector, selecting one of the plurality of fuel nozzles as a primary index nozzle and positioning each of a plurality of sensors relative to one of the plurality of nozzles using a corresponding positioning angle such that each of the plurality of sensors coincides with a gas flow temperature distribution profile between each pair of circumferentially-spaced nozzles. | 02-10-2011 |
20110271528 | METHOD OF REPAIRING A GAS TURBINE ENGINE COMBUSTOR - A method of repairing an annular sheet metal combustor liner of a gas turbine engine includes cutting circumferentially around combustor liner bands bounding an effusion patch extending circumferentially around the liner, the effusion patch having effusion cooling holes and being bounded on either side by at least one effusionless band free from effusion cooling holes, to thereby remove a portion of the combustor liner having the effusion patch. A replacement liner portion including an effusion patch is provided and welded to the liner assembly, the weld extending circumferentially around the cut band to provide a welded effusionless band. The welded effusionless bands is cooled during engine use using one of film cooling of an inner surface of the welded effusionless band and impingement cooling of an outer surface of the welded effusionless band. | 11-10-2011 |
20120285016 | Stereolithographic Rocket Motor Manufacturing Method - A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, | 11-15-2012 |
20130312263 | METHOD FOR MANUFACTURING AN AIR INTAKE STRUCTURE FOR A TURBOJET ENGINE NACELLE - A method for manufacturing an air-intake structure for a turbojet-engine nacelle includes two component parts, i.e. one air-intake lip structure and one outer cowl for the air-intake structure. In particular, the method includes the following steps: separately manufacturing the component parts such that each integrates one overlapping portion with a part to which is to be attached. The overlapping portion is configured such that an outer surface of the outer overlapping portion provides continuity with an outer surface of the outer cowl associated with the inner overlapping portion. To secure the overlapping portions, glue or a fastener may be used. | 11-28-2013 |
20150059177 | METHOD FOR REMOVING AN END CAP OF A COMBUSTOR CAP ASSEMBLY - A method for removing an end cap assembly from a combustor cap assembly includes inserting a push rod through an opening in a back plate portion of the cap assembly. One end of the push rod is engaged with a radial support feature of the end cap assembly and a substantially linear force is applied to the push rod. The force is distributed to the radial support feature, thereby preventing damage to a cap plate portion of the end cap assembly. | 03-05-2015 |
20160003479 | PROCESS OF ASSEMBLING FUEL NOZZLE END COVER - A process of assembling a fuel nozzle end cover includes machining a base material of the fuel nozzle end cover, then positioning one or more ring inserts in contact with the base material, then welding the ring insert(s) to the base material to define one or more ledge features within the fuel nozzle end cover. The ring insert(s) have a net shape or near-net shape. | 01-07-2016 |
20160024948 | METHODS FOR MANUFACTURING A TURBINE NOZZLE WITH SINGLE CRYSTAL ALLOY NOZZLE SEGMENTS - Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall. | 01-28-2016 |
20160108759 | DEVICE AND METHOD FOR MOUNTING OR DISMANTLING, REPLACEMENT AND MAINTENANCE OF A CAN-COMBUSTOR - The present invention concerning of a device for mounting or dismantling, replacement and maintenance of a can-combustor of a gas turbine engine including an assembly tool or assembly tool with additional frame having at least one lifting beam, at least one linear driver, wheels, at least one eccentric rolling hook for fixation of the gas turbine housing, optionally spacers for building the interface to the can-combustor, adapters, lifting points for the main crane. The eccentric rolling hook is connected to the gas turbine housing by giving in axial or quasi-axial direction a force for mounting or dismantling the can-combustor from the gas turbine housing. | 04-21-2016 |
20160194093 | SYSTEM AND METHOD OF SECURING A COMPONENT IN POSITION FOR MACHINING USING A FIXTURE ASSEMBLY | 07-07-2016 |