Abstract: Systems and methods for augmenting power output when operating a load having relatively brief periods of high energy demand and high heat generation. A system comprises a gas turbine engine including a coolant injection assembly, an electrical generator coupled to the gas turbine engine, a high-energy operating load coupled to the electrical generator, and a cooling system adapted to provide cooling to the high-energy operating load. The cooling system is coupled and adapted to provide coolant to the coolant injection assembly of the gas turbine engine. A method comprises coupling the cooling system to the coolant injection assembly at the inlet of the gas turbine engine, selectively diverting at least a portion of the coolant of the cooling system to the coolant injection assembly, and spraying the diverted coolant into air entering the gas turbine engine.

Abstract: The part load method controls delivery of diluent fluid, fuel fluid, and oxidant fluid in thermodynamic cycles using diluent, to increase the Turbine Inlet Temperature (TIT) and thermal efficiency in part load operation above that obtained by relevant art part load operation of Brayton cycles, fogged Brayton cycles, or cycles operating with some steam delivery, or with maximum steam delivery. The part load method may control the TIT at the design level by controlling one or both of liquid and/or gaseous fluid water over a range from full load to less than 45% load. This extends operation to lower operating loads while providing higher efficiencies and lower operating costs using water, steam and/or CO2 as diluents, than in simple cycle operation.

Abstract: A system to provide a two piece robust fluid injector. According to various embodiments, the fluid injector is a fuel injector for a combustion engine. The injector includes two coaxially formed annuluses. One annulus is formed in a face plate and the second annulus or hole is defined by a tube extending through the face plate. The tube extends through the face plate in a portion of a through bore which also is used to define the second annulus. The second annulus is formed using a throughbore through which the tube extends. This allows the second annulus to always be formed inherently and precisely substantially coaxial with the first annulus. Moreover, the second annulus can be formed with a much greater tolerance than if other independent components needed to be added.

Abstract: A stream of hydrocarbon fuel is catalytically decomposed to produce hydrogen and lower molecular weight fuel fragments, which may separated by molecular size. The hydrogen and low molecular weight fuel fragments are introduced along with a stream of nondecomposed hydrocarbon fuel into the combustor of a high speed propulsion unit. The method results in a wider combustor operating range, with higher combustion rates and increased flame stability, achieved through more rapid diffusional mixing. The process effectively extends the operating limits of gas turbines, and especially ramjet and scramjet combustors.

Abstract: A scramjet engine for powering an aircraft at supersonic velocities is disclosed. The scramjet engine includes supersonic compressed airflow in a combustor along with a fuel for providing combustion. A monopropellant is also supplied adjacent to the airflow and fuel. The monopropellant is effective for expanding in the combustor for mixing the airflow and the fuel for the combustion of the airflow and fuel for generating combustion gases. In a preferred embodiment of the invention, the monopropellant is hydrazine and is effective for obtaining a specific volumetric increase of about 20,000:1.

Abstract: A compound having the following formula: ##STR1## wherein R.sup.1 is --N.sup.+ H.sub.3 as found in claim 1 and R.sup.2 is either the same as F.sup.1 or hydrogen. "A" is an oxidizing anion, and X is selected to provide a neutral charge balance for the compound. A method of making a compound of the indicated structure from a compound of similar structure by an anion exchange process is also disclosed. Finally, propellant formulations incorporating the novel compounds of the present invention as fuels and oxidizers are disclosed.

Abstract: Disclosed is a single control thruster having the expanded capability of operating at various thrust levels and more than one propellant fluid so that the number of control thrusters for a maneuvering vehicle can be reduced to one third from that now required for appropriate maneuverability in space, resulting in large cost savings and improved reliability. Also disclosed is a "plug in" package with control thruster which can be removed from the vehicle and replaced to make the vehicle easily maintainable.

Abstract: In a solid fuel ramjet in which a fluid flow boundary layer extends along a urning fuel grain and receives combustible material liberated from the grain, exciting oscillations in air flowing toward the grain so that oscillations continue in the boundary layer and promote vortices in the layer to mix the air and the combustible material.