Aerojet Rocketdyne

Azusa, CA, United States

Aerojet Rocketdyne

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: 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: 2017-06-14

A combustor (16) for a gas turbine engine (10) comprises a single skin liner (20a, 20b) defining a combustion chamber (22). The single skin liner (20a, 20b) has an inner surface facing the combustion chamber (22) and an outer surface (36) exposed to a coolant flow discharged in a plenum (17) extending from the outer surface (36) of the single skin liner (20a, 20b) to the engine casing (26). Cooling holes (30) extend through the single skin liner (20a, 20b). Open flow guiding channels (37) are provided on the outer surface (36) of the single skin liner (20a, 20b), the open flow guiding channels (37) being uncovered and aligned with the flow of air over the outer surface (36) of the single skin liner (20a, 20b).


Methods and systems for diagnosing a condition of an engine based on lubrication fluid analysis are disclosed. One embodiment of the methods comprises: receiving input data (128) representative of a respective geometric parameter and a respective chemical composition for a plurality of particles (124) filtered from a sample of fluid (126) obtained from the engine; generating data representative of a mass of material of a chemical composition category in one or more of the particles (124); comparing the mass of material of the chemical composition category with reference data (134); and generating output data (130) representative of a diagnosis of the condition of the engine.


Patent
Aerojet Rocketdyne | Date: 2017-06-21

An exhaust mixer (32) for a gas turbine engine (10) has a lobe cross-over offset (O). The proposed geometric feature leads to improved exhaust performance and potential weight reduction.


A method of determining a radius of a cutting end of a tool for a turning machine using a touch probe is provided. One of the cutting end and the touch probe is movable relative to a reference frame having a first axis and a second axis and having a reference point trackable in the reference frame. The method comprises establishing a first contact point and recording a first coordinate of the reference point on the first axis; establishing a second contact point and recording a second coordinate of the reference point on the second axis; establishing a third contact point and recording a third coordinate of the reference point on the first axis and a fourth coordinate of the reference point on the second axis upon contact; and determining a radius of the cutting end based on the first, second, third and fourth coordinates.


Patent
Aerojet Rocketdyne | Date: 2017-06-28

A compressor rotor (12) for a gas turbine engine (10) is described which includes sets of blades (28, 30) having different airfoil thickness distributions, each including a frequency modifier (50, 52) forming a thickness differential relative to a baseline blade thickness. The frequency modifiers (50, 52) provide different natural vibration frequencies for each of the blades (28, 30), and facilitate modifying natural vibration frequency separation between adjacent blades (28, 30) of the compressor rotor (12).


Patent
Aerojet Rocketdyne | Date: 2017-01-25

A munition includes a composite case, a blast cone housed by the composite case, a grenade aft of the blast cone and housed by the composite case, a first attenuator forward of the blast cone, and a second attenuator aft of the blast cone and forward of the grenade.


Patent
Aerojet Rocketdyne | Date: 2017-03-27

A contact seal assembly for a shaft of a gas turbine engine includes a seal runner adapted to be connected to the shaft and rotatable relative to a carbon ring. The seal runner includes concentric inner and outer annular portions radially spaced apart to define at least one internal fluid passage between the inner and outer annular portions of the seal runner.

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