Aerojet Rocketdyne | Date: 2015-10-29
An internal combustion engine including a pilot subchamber, a pilot fuel injector having a tip in communication with the pilot subchamber, an ignition element positioned to ignite fuel within the pilot subchamber, and a main fuel injector spaced apart from the pilot fuel injector. The engine includes a common rail in fluid communication with the main fuel injector and with the pilot fuel injector. The internal combustion engine may be a reciprocating engine. A method of combusting fuel in an internal combustion engine is also provided.
Aerojet Rocketdyne | Date: 2016-01-07
Feedback from a solenoid is achieved by adding at least one variable resistance in parallel with the solenoid current feedback circuit for position detection. The resistance has current flowing therethrough when a switching device actuated by the solenoid is in one position or transitions from one position to at least one other position. A feedback current may be measured in the current feedback circuit and the position of the switching device in response to actuation thereof by the solenoid may be determined from the measured feedback current.
Aerojet Rocketdyne | Date: 2015-12-08
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.
Aerojet Rocketdyne | Date: 2015-04-08
A propellant includes a binder system that has a polybutadiene component, a polytetrahydrofuran component, and an anti-oxidant component. In an example, the propellant includes a solid oxidizer, a solid fuel, and a binder system that holds the solid oxidizer and the solid fuel together. The binder system includes a polybutadiene component, a hydrocarbon diluent component of a higher level of saturation than the polybutadiene component, and an anti-oxidant component.
Aerojet Rocketdyne | Date: 2015-06-25
A heat management system of a gas turbine engine for cooling oil and heating fuel, includes an oil circuit having parallel connected first and second branches. The first branch includes a fuel/oil heat exchanger and a first fixed restrictor in series and the second branch includes an air cooled oil cooler and a second fixed restrictor. The first and second fixed restrictors limit respective oil flows through the first and second branch differently, in response to viscosity changes of the oil caused by temperature changes of the oil during engine operation to modify oil distribution between the first and second branches.