Azusa, CA, United States
Azusa, CA, United States

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Patent
Aerojet Rocketdyne | Date: 2017-01-25

A method for positioning a rotary part on a machining fixture adapted to hold the rotary part for a machining operation is described. The machining fixture has a center axis and a diaphragm with engaging segments affixed thereto and extending away therefrom. The method includes mounting the rotary part on the machining fixture concentrically about the center axis and adjacent to the engaging segments, and then applying an axial force in a direction substantially parallel to the center axis against the diaphragm. This elastically deforms the diaphragm and radially displaces the contact members of the engaging segments into frictional engagement with a circumferential surface of the rotary part.


Patent
Aerojet Rocketdyne | Date: 2016-12-22

A method of supporting a part with particulate shape retaining media, the method including placing the part on a bed of the particulate shape retaining media, fluidizing the particulate shape retaining media until the part penetrates therein, and vibrating the bed of particulate shape retaining media to compact the particulate shape retaining media around the part. The part may be a green part to be debound in a powder injection molding process. Fluidization may be performed through vibrations at a different frequency than the compaction.


Patent
Aerojet Rocketdyne | Date: 2016-12-15

A turbine blade for a gas turbine engine comprises a platform, a blade root, an airfoil portion defining pressure and suction sides, and a shroud provided at a tip of the airfoil portion opposite to the blade root. The shroud includes a body having a radially outer face opposite to the airfoil portion, upstream and downstream generally parallel fins extending outwardly from the outer face, and two ribs extending outwardly from the outer face. Each of the fins has an end disposed toward the pressure side and another end disposed toward the suction side. The ribs extend from and connecting the upstream fin to the downstream fin at locations other than the ends of the upstream and downstream fins. The ribs converge toward the downstream fin at an angle of between about 10 and about 45 degrees. A shroud for a blade is also presented.


Patent
Aerojet Rocketdyne | Date: 2016-07-07

A system includes a combustion chamber that has a throat, and a regulator for changing area cross-sectional area of the throat. The regulator includes a first piston in fluid connection with the combustor, and a second piston that is moveable with the first piston. The second piston at least partially defining the throat.


Patent
Aerojet Rocketdyne | Date: 2016-07-07

A nacelle exhaust nozzle having a deployable noise-reducing component is described. The noise-reducing component includes an annular perforated sleeve coinciding with the inner nacelle loft line and circumscribing a mixed exhaust gas flow exiting the nacelle. The annular perforated sleeve is radially spaced apart from of a displaceable wall of an inflatable envelope that is displaceable between a deployed position, wherein noise-reduction is active, and a retracted position, wherein noise-reduction is inactive. When the inflatable envelope is pressurized, portions of the displaceable wall project through openings in the perforated sleeve and into the exhaust gas flow to form a rough surface at the loft line which causes a reduction in noise level. The portions of the displaceable wall that project through the openings in the perforated sleeve when the inflatable enveloped is pressurized include a plurality of dimples formed on the inner wall and forming the rough surface.


Patent
Aerojet Rocketdyne | Date: 2016-07-06

A gas turbine engine and a method of tuning a rotor in the gas turbine engine wherein the rotor includes an array of blades extending from a rotor hub each having an airfoil mounted to a blade platform. The method includes adding or removing material from bladed rotor projections to alter the mass of the rotor and change the frequency of the respective airfoil.


Patent
Aerojet Rocketdyne | Date: 2017-04-05

A circuit (400, 700, 800) comprising: a first power source (402) supplying first current to a load (470) during a first Period of Time (PoT); a second power source (416) supplying a second current to the load during a second POT; a Unidirectional Current Valve (UCV) in series with the first power source; a current detector (420, 702, 802) in series with the UCV (422); and a switch (424) in parallel with a series combination of the current detector and UCV to bypass the UCV during the second PoT. The current detector determines whether the second period of time has commenced and whether the switch has closed.


Patent
Aerojet Rocketdyne | Date: 2017-05-17

There are described herein methods and systems for estimating a system parameter in a closed loop scheme using a sensor model associated with a sensor performing a measurement of the system parameter. Past and current measurements of the parameter are used to provide an initial estimate of the system parameter (606) and sensor dynamics are used to refine the estimated parameter (606).


Patent
Aerojet Rocketdyne | Date: 2017-01-12

An engine mounting arrangement is provided for supporting a gas turbine engine. The mounting arrangement comprises a module adaptor mounted to an overhead or a ground based carrier for rotation about a substantially horizontal axis. The module adaptor extends horizontally from a base to an axially-opposed distal end having a first mounting interface configured for attachment to a module of the engine. The module adaptor holds the engine by the module to which it is attached and with the other engine modules projecting in a cantilever fashion from the supported module.


Patent
Aerojet Rocketdyne | Date: 2016-12-28

A monopropellant includes 30-70% by weight of an oxidizer including hydroxylammonium nitrate, 5-50% by weight of a fuel, and a burn rate modifier in a non-zero amount of up to 3% by weight. The burn rate modifier can be selected from vanadium salts, iron salts, and combinations thereof. The monopropellant is a stable liquid between -20C and 100C at ambient pressure.

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