Abstract: A rotary engine having an insert in a peripheral wall of the stator body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the stator body and having a tip communicating with the cavity at a location spaced apart from the insert. The subchamber has a volume corresponding to from 5% to 25% of a sum of the minimum volume and the volume of the subchamber. A method of injecting heavy fuel into a Wankel engine is also discussed.

Abstract: The present invention relates to cooling additives for middle distillates, containing A) at least one polyester of formula (A1) wherein one of the radicals R1 to R4 represents a linear C16-C40 alkyl or alkenyl radical and the remainder of the radicals R1 to R4 represent, independently of one another, hydrogen or an alkyl radical having 1 to 3 C atoms, R5 is a C—C bond or an alkylene radical having 1 to 6 C atoms, R16 is a hydrocarbon group having 2 to 10 carbon atoms, n is an integer from 1 to 100, m is an integer from 3 to 250, p is 0 or 1, and q is 0 or 1, B) at least one copolymer of ethylene and of at least one ethylenically unsaturated ester, the copolymer having a melt viscosity, measured at 140 DEG C., of at most 5000 mPas, and C) at least one organic solvent.

Abstract: Process of producing power comprising:providing a turbine adapted to generate shaft work, said turbine having a combustor; and a rocket engine having a nozzle and a compressor means;feeding fuel and oxidant to the rocket engine and the rocket engine compressor means;feeding carbonaceous matter and steam into the rocket engine nozzle;processing the output of the rocket engine nozzle into fuel for the turbine;introducing said fuel and oxidant for the turbine to the turbine combustor; andrecycling a substantial portion of the hot exhaust from the turbine to the rocket engine compressor means; andcontrolling the inlet temperature to the turbine.Apparatus for producing power comprising a rocket engine and a turbine adapted to generate shaft work is also disclosed.

Abstract: A method for accelerating a vehicle in the atmosphere, space or aerospace includes the steps of supplying a propellant having silicone hydride compounds into a combustion chamber, compressing air and delivering compressed air into a ring formed with a plurality of circumferential orifices which open into the combustion chamber, reaching thereby temperatures of about 3000.degree. C., cracking nitrogen molecules present in the air at the temperature which attack the silicon atoms to generate great mass.

Abstract: A reduction in the emission of infrared radiation by the engine of a jet aircraft can be achieved by employing a low molecular weight monohydric alcohol, having a luminometer number of at least about 200 as at least a portion of the fuel. Additional reduction in emission of infrared radiation can be achieved by passing a low molecular weight monohydric alcohol in indirect heat exchange relationship with the hot exhaust nozzle prior to its introduction to the combustion chamber of the engine.

Abstract: The present invention provides an improved emissions reduction system for lowering the emissions of NO.sub.x generated by the combustion of hydrocarbons. The present invention further provides a method for lowering the emissions of NO.sub.x generated by the combustion of hydrocarbons.

Abstract: Solid fuel gas generator compositions for use in ducted rockets, in which fullerenes or substituted fullerenes are used. Fullerene compounds in which easily oxidizable groups, oxidizing groups, or salts of oxidizing acids are attached to the spherical carbon skeleton of the fullerene.

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.