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US20130160426 ROCKET ENGINE INJECTOR ASSEMBLY WITH CRYOGENIC CAVITY INSULATION  
An injector assembly for a rocket engine includes a thermal insulating layer adjacent to an oxidizer cavity.
US20140318140 PREMIXER ASSEMBLY AND MECHANISM FOR ALTERING NATURAL FREQUENCY OF A GAS TURBINE COMBUSTOR  
A system and method are provided for altering the natural frequency of a dome plate portion of a premixer assembly of a gas turbine combustor. The plate assembly has a dome plate with a central...
US20150241067 FASTENED JOINT FOR A TANGENTIAL ON BOARD INJECTOR  
A combustor assembly for a gas turbine engine includes a combustor shell, a TOBI, a case, and a joint for securing the combustor shell, TOBI and case together. The joint has a combustor flange...
US20090217525 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...
US20130129495 HYDROELECTRIC TURBINE NOZZLES AND THEIR RELATIONSHIPS  
Hydroelectric turbines in confined spaces depend heavily on nozzles and relationships involving nozzles and related turbine components in order to obtain maximal efficiencies for a wide range of...
US20120097144 EXPLOSIVE DECOMPRESSION PROPULSION SYSTEM  
A projectile propulsion system includes a launch tube, multiphase material, and a membrane. The launch tube has an interior cavity, the multiphase material disposed therein. The launch tube also...
US20110215193 HYBRID TORQUE BOX FOR A THRUST REVERSER  
A hybrid torque box comprising a plurality of composite tubes and metal fittings attached together in alternating succession and configured to attach a thrust reverser to an engine fan case of an...
US20120210695 BELTED TOROID PRESSURE VESSEL AND METHOD FOR MAKING THE SAME  
A toroid pressure vessel includes a toroid body having an inner shell and an outer shell. The toroid body includes a toroid outer perimeter. The outer shell extends along the toroid outer...
US20150204273 ROCKET STAGE AND METHOD OF IMPROVING AN EXISTING ROCKET STAGE  
The present invention relates to an improved rocket stage and a method of improving an existing rocket stage. In an embodiment, the improved rocket stage is where one can take existing rocket...
US20110293411 HONEYCOMB CORE STRUCTURE FOR USE IN A STRUCTURAL PANEL FOR A JET ENGINE NACELLE  
The invention relates to a honeycomb core structure (202) for use in a structural panel for a jet engine nacelle, comprising at least one block with a honeycomb core (A, B) having a central part...
US20120285016 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...
US20140096510 SLOTTED MULTI-NOZZLE GRID WITH INTEGRATED COOLING CHANNELS  
An apparatus includes a slotted multi-nozzle grid with a plate having multiple elongated slotlettes through the plate. Each of at least some of the slotlettes has a convergent input, a divergent...
US20090235666 CRACK RESISTANT COMBUSTOR  
A combustion chamber louver assembly includes an aft louver having a forward panel 24 that extends axially from a louver leading edge 26 to a corner 28, and a forward louver joined to the forward...
US20100011742 Rocket Motor Containing Multiple Pellet Cells  
A rocket motor may include a case, a plurality of pellet cells disposed within the case, an igniter disposed to ignite at least one of the pellet cells, and a nozzle coupled to the case. Each...
US20140061331 DISCHARGE SYSTEM OF A SEPARATED TWIN-FLOW TURBOJET FOR AN AIRCRAFT, CORRESPONDING TURBOJET AND ASSOCIATED DESIGN METHOD  
A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, is disclosed. The system includes a main nozzle delimited by an annular cowl with a slot of...
US20090260340 Combustor of a Turbine, a Method of Retro-Fitting a Combustor of a Turbine and a Method of Building a Combustor of a Turbine  
A combustor of a turbine, a method of retro-fitting a combustor of a turbine and a method of building a combustor of a turbine are each provided. The combustor includes a combustion chamber along...
US20120063894 TURBINE NOZZLE ASSEMBLIES AND METHODS FOR REPAIRING TURBINE NOZZLE ASSEMBLIES  
A method is provided for repairing a turbine nozzle assembly with an insert and a support structure. The method includes positioning the insert on the support structure of the turbine nozzle...
US20090007812 PARACHUTE ROCKET, IN PARTICULAR A PARACHUTE SIGNALING ROCKET AND/OR A PARACHUTE FLARE ROCKET, AND METHOD FOR THEIR PRODUCTION  
Parachute signaling rockets in which the parachute (18) is connected to the effect charge (14) in the form a plug connection (16). This plug connection (16) can be made automatically, so that...
US20110030215 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...
US20110289926 EXTRUDED FLUID MANIFOLD FOR GAS TURBOMACHINE COMBUSTOR CASING  
A turbomachine includes a compressor, a turbine, and a combustor operatively coupled to the compressor and the turbine. The combustor includes a combustor casing having a flange, an outer surface...
US20100024428 Rocket Apparatus and/or Method  
A rocket motor for one or more of limited re-use or single use, including a rocket motor housing, the motor housing adapted to contain propellant; an aft closure with a nozzle, the aft closure...
US20090235640 Pellet Loaded Attitude Control Rocket Motor  
There is disclosed a solid fuel rocket motor which may include a case and a nozzle coupled to the case. A plurality of fuel pellets may be disposed within the case. An igniter may be disposed to...
US20140352797 AIRCRAFT JET ENGINE  
In various embodiments, a jet engine, as described herein, may include a fan case, a fan cowl, and an air inlet. Further, in various embodiments, at least one of the fan case and the fan cowl may...
US20090313825 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...
US20090120056 Microthruster, in particular for use as a position adjustment thruster, thruster and method for producing a microthruster  
Microthruster includes a combustion chamber comprising a substrate material, a fuel inlet, and a gas outlet. A first resistance heater is arranged in the combustion chamber. A catalyst is...
US20110271528 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...
US20090188109 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...
US20120006001 SOLID PROPELLANT ROCKET MOTORS EMPLOYING TUNGSTEN ALLOY BURST DISCS AND METHODS FOR THE MANUFACTURE THEREOF  
Embodiments of a solid propellant rocket motor are provided. In one embodiment, the solid propellant rocket motor includes a pressure vessel having a cavity therein, a solid propellant disposed...
US20150059177 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...
US20130312263 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...
US20140318139 PREMIXER ASSEMBLY FOR GAS TURBINE COMBUSTOR  
A novel and improved combustion liner for use in a gas turbine engine is provided in which the premixer assembly is removably fastened to the combustion liner. Apparatus and method for removably...
US20080092514 Tip Turbine Engine Composite Tailcone  
A non-metallic tailcone (202) in a tip turbine engine includes a tapered wall structure disposed (208) about a central axis. The non-metallic tailcone is fastened to a structural frame (44) in the...
US20150252753 ANTIVORTEX DEVICE AND METHOD OF ASSEMBLING THEREOF  
An antivortex device for use in suppressing formation of a vortex created by fluid flowing through multiple outlet ports defined in a sump is provided. The antivortex device includes a plurality...
US20130283806 COMBUSTOR AND A METHOD FOR REPAIRING THE COMBUSTOR  
A combustor generally includes a liner that at least partially defines a combustion chamber within the combustor. The liner may generally include a hole that extends through the liner and that at...
US20090243176 Systems and Methods for Positioning Fairing Sheaths of Gas Turbine Engines  
Systems and methods for positioning fairing sheaths are provided. In this regard, a representative method includes using vacuum pressure to assist in moving opposing portions of a fairing sheath...
US20120304655 TURBOMACHINE COMBUSTOR ASSEMBLY INCLUDING A LINER STOP  
A turbomachine combustor assembly includes a combustor housing and a combustor body. The combustor body defines a combustor liner having a first end portion that extends to a second end portion...
US20130031888 Systems, Methods, and Apparatus for Providing a Multi-Fuel Hybrid Rocket Motor  
Certain embodiments of the invention may include systems, methods, and apparatus for providing a multi-fuel hybrid rocket motor. According to an example embodiment of the invention, a method is...
US20100326045 MULTIPLE-USE ROCKET ENGINES AND ASSOCIATED SYSTEMS AND METHODS  
Multiple-use rocket engines and associated systems and methods are disclosed. A method in accordance with a particular embodiment includes launching a two-stage vehicle have a first stage and a...
US20080276596 Engine Wall Structure and a Method of Producing an Engine Wall Structure  
An engine wall structure includes an inner wall to which hot gas is admitted during engine operation, an outer wall, which is colder than the inner wall during engine operation, and at least two...
US20120117941 FLIGHT VEHICLES INCLUDING ELECTRICALLY-INTERCONNECTIVE SUPPORT STRUCTURES AND METHODS FOR THE MANUFACTURE THEREOF  
Embodiments of a flight vehicle are provided, as are embodiments of a method for manufacturing a flight vehicle. In one embodiment, the flight vehicle includes a solid-propellant rocket motor,...
US20110100019 APPARATUS AND METHODS FOR FUEL NOZZLE FREQUENCY ADJUSTMENT  
A combustion liner cap assembly includes a cylindrical outer sleeve. The cylindrical outer sleeve includes a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around...
US20110265448 JET NOZZLE MIXER  
An external jet nozzle mixer includes identically formed lobes. The external mixer works with the internal mixer further to mix the engine internal bypass flow with the internal jet engine core...
US20130112776 NOZZLE ARRANGEMENT AND METHOD OF MAKING THE SAME  
A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a...
US20100205933 Regeneratively cooled porous media jacket  
The fluid and heat transfer theory for regenerative cooling of a rocket combustion chamber with a porous media coolant jacket is presented. This model is used to design a regeneratively cooled...
US20110192137 Method for Manufacturing a Regeneratively Cooled Nozzle Extension of a Rocket Combustion Chamber and Nozzle Extension  
A method for manufacturing a regeneratively cooled nozzle extension of a rocket combustion chamber, the nozzle extension including a first wall and a second wall arranged coaxially to each other...
US20100058586 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...
US20120210720 COMBUSTOR ASSEMBLY FOR USE IN A TURBINE ENGINE AND METHODS OF FABRICATING SAME  
A combustor assembly that includes a casing that includes a plenum, a combustor liner positioned within the plenum and defining a combustion chamber there within, and a transition piece that...
US20120137912 CONTROLLABLE DIGITAL SOLID STATE CLUSTER THRUSTERS FOR ROCKET PROPULSION AND GAS GENERATION  
A thruster stack assembly and method for manufacturing the same is provided. The thruster stack assembly includes a plurality of grain elements having a common core region (e.g., a channel or...
US20060238573 Monolithic fluid ejection device and method for fabricating the same  
A method for fabricating a monolithic fluid ejection device. The method includes providing a substrate with a signal transmitting circuit and a heating element. A protective layer is formed to...
US20130019587 THRUSTER DEVICES AND METHODS OF MAKING THRUSTER DEVICES FOR USE WITH THRUST VECTOR CONTROL SYSTEMS  
Thruster devices for use with a lateral thrust module and/or a flight body are adapted to achieve short action times with relatively slow burning propellant materials. Such thruster devices...
Matches 1 - 50 out of 65 1 2 >