Abstract: A system and method for ram air intake for pulse combustion systems is disclosed that improves the ability of pulse combustions to ingest air into the inlet pipe when the pulse combustion system is moving in a direction opposite the direction the open end of the inlet pipe is facing and the system and method includes the ability to increase the thrust output from the pulse combustion system.

Abstract: A system and method is disclosed for the start-up and control of pulsejet engines and this system includes an Electronic Fuel Injection (“EFI”) system that further includes one or more electrically controlled fuel injectors that can be selectively operated for start-up and control of such pulsejet engines. According to the system and method, the rate and/or pattern of fuel delivery to pulsejet engines can be varied not only by controlling the amount of time the fuel injectors are open versus closed to define a “duty cycle,” but also with the capability to selectively disable one or more fuel injectors in the programmed manner for start-up and control of such pulsejet engines.

Abstract: A rotating detonation combustor includes a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas and an air plenum configured to contain a volume of air. The rotating detonation combustor also includes a flow passage coupled in flow communication between the combustion chamber and the air plenum and configured to channel an airflow from the air plenum. The rotating detonation combustor also includes a fuel inlet coupled in flow communication with the flow passage and configured to channel a fuel flow into the flow passage. The flow passage includes a plurality of fuel mixing mechanisms configured to mix the airflow and the fuel flow within the combustion chamber.

Abstract: One embodiment of the present invention is a unique engine. Another embodiment of the present invention is a unique combustion system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: An acoustically dampened gas turbine engine having a gas turbine engine combustor with an acoustic damping resonator system is disclosed. The acoustic damping resonator system may be formed from one or more resonators positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor. The resonator may be positioned in a head region of the combustor basket. In one embodiment, the resonator may be positioned in close proximity to an intersection between the outer housing and an upstream wall defining at least a portion of the combustor. The acoustic damping resonator system may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions.

Abstract: One embodiment of the present invention is an engine. Another embodiment is a unique combustion system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: An acoustic resonance igniter uses gas expanding through a nozzle to form a sonic, or under-expanded supersonic, jet directed against the opening of a blind resonance cavity in a central body, setting up a high-frequency sonic resonance which heats the gas within the cavity. A pintle extends coaxially with the nozzle and injects liquid propellant into the jet. The liquid propellant ignites with the heated gas within the resonance cavity forming combustion gases. The combustion gases flow through openings in a flange which supports the resonance cavity into a combustion chamber in the same direction as the gas jet flows. The liquid propellant is injected from within the support flange in the direction of combustion gas flow to film cool the combustion chamber wall and the flange and the central body supported by the flange. The acoustic resonance igniter may form a rocket engine ignition torch or a RCS thruster.

Abstract: A millimeter-scale pulse jet engine comprises an engine body that defines a combustion chamber, a fuel, an air intake, and an exhaust. The fuel inlet is arranged to inject fuel directly into the combustion chamber. The air intake and the exhaust are in fluid communication with the combustion chamber, and the combustion chamber is configured such that air from the air intake and fuel from the fuel inlet cyclically combust in the combustion chamber to produce exhaust gases.

Abstract: An engine contains at least one pulse detonation combustor having a combustion chamber and an exit nozzle coupled to and downstream of the combustion chamber. During operation of the at least one pulse detonation combustor a detonation occurs within the combustion chamber and at least one of a fuel fill fraction and purge fraction of the at least one pulse detonation combustor are utilized to offset a temperature peak of said detonation from a pressure peak of said detonation. The fuel fill fraction is defined as 1?purge fraction, and the purge fraction is the ratio of the purge time of the at least one pulse detonation combustor to a sum of the purge time of the at least one pulse detonation combustor and a fuel fill time of the at least one pulse detonation combustor.

Abstract: The present specification generally relates to improvements to combustors such as burners and engines. In one aspect, the specification presents an acoustically enhanced ejector system which can be used as part of an intake system for a combustor. In another aspect, the specification teaches the use of a combustor combustion chamber as an oscillator to magnify a harmonic frequency of a pulsating frequency of the combustor. In still other aspects, the specification presents a combustion chamber having an inlet with a plurality of tangentially spaced apertures, and an in-line intake system connected to the apertures.

Abstract: A pulsed detonation combustor (PDC) is described. The PDC includes an outer casing defining a first hollow chamber configured to receive a flow and an inner liner. The inner liner includes at least one portion positioned within the first hollow chamber and configured to receive the flow from a plenum formed between the outer casing and inner liner. The PDC further includes a flow turning device with geometric features configured to direct the flow from the plenum to a second hollow chamber defined within the inner liner. The PDC also includes at least one fuel injection port located downstream of an inlet to the outer casing and an ignition device located downstream of the at least one fuel injection port and configured to periodically ignite fuel.

Abstract: Pulse detonation combustors of valveless construction. One valveless pulse detonation combustor, having a tube with a closed end and an open end, is constructed with a flame accelerator within the tube, adjacent the open end. A valveless, apertured flow restrictor is positioned between the flame accelerator and the closed end of the tube. A sparking device is positioned within the tube, between the flow restrictor and the flame accelerator. Valveless fuel and air ports are positioned between the flow restrictor and the closed end of the tube. Substantially right-angle manifold passageways are in communication with each of the ports.

Abstract: A rotary engine includes a rotor having one or more combustion chambers connected to an exhaust passageway extending radially outward from the combustion chamber to an exhaust port adjacent a peripheral edge of the rotor. The exhaust gas is expelled at an angle to thereby generate cause the rotor to rotate. The housing may include reflective surfaces that reflect shockwaves from the exhaust gas back towards vanes on the rotor to thereby capture additional energy from the exhaust gas. The housing may also include stators that capture additional energy from the exhaust gas and rotate the rotor. An intake port fluidly connected to the combustion chamber is aligned with an opening in the housing as the rotor rotates to thereby allow comprised air to flow into the combustion chamber. As the combustion chamber rotates, it is closed off by a closed portion of the housing, fuel is injected, and ignited, to thereby generate exhaust gases and generate power.

Abstract: A two-stage pulse detonation system includes a pre-combustor and a geometric resonator connected via a converging-diverging nozzle to the pre-combustor to create a high temperature and high pressure conditions in the resonator in order to create optimal conditions for detonation initiation. A mixture of a fuel and a gas is burned in the pre-combustor and is passed through the nozzle into the geometric resonator, where the burned mixture is detonated. The detonation propagates through the resonator exit nozzle thus generating thrust.

Abstract: A method for monitoring and diagnosing the combustion dynamics of a gas turbine engine system includes mounting at least one sensor on an external surface of at least one combustor can, receiving a signal from the sensor mounted to the combustor can, validating an accuracy of the signal from the sensors, determining the combustion dynamics of the can based on the received signals, and generating an indication when a combustion dynamic threshold has been exceeded.

Abstract: Provided is a combustion chamber for producing a pressurized gas containing: a wall structure defining an interior chamber; a first reflecting surface for reflecting a pressure wave within said interior chamber; a second reflecting surface for reflecting said pressure wave within said interior chamber, wherein said first and second reflecting surfaces being constructed and arranged to resonate said pressure wave in said interior chamber; at least one first inlet for introducing a first gas into said interior chamber; and at least one outlet from said interior chamber for drawing off a pressurized gas from said interior chamber. Also provided is a turbine engine containing the combustion chamber, and an electrical generating power plant containing the turbine engine.

Abstract: Provided is a combustion chamber for producing a pressurized gas containing:

Abstract: Provided is a combustion chamber for producing a pressurized gas containing: a wall structure defining an interior chamber; a first reflecting surface for reflecting a pressure wave within said interior chamber; a second reflecting surface for reflecting said pressure wave within said interior chamber, wherein said first and second reflecting surfaces being constructed and arranged to resonate said pressure wave in said interior chamber; at least one first inlet for introducing a first gas into said interior chamber; and at least one outlet from said interior chamber for drawing off a pressurized gas from said interior chamber. Also provided is a turbine engine containing the combustion chamber, and an electrical generating power plant containing the turbine engine.

Abstract: A pulsating combustor has a plurality of annular plate elements (12), which are stacked in spaced vertical alignment so as to define a central space (14). There is a plurality of slot-like passages (18), one such passage between each adjacent pair of elements. There is at least one combustion chamber (21) in communication with at least one slot-like passage. Fuel and combustion air are fed into the combustion chambers. There is a spark plug for igniting a fuel-air mixture in the combustion chamber. Preferably there is a first housing (24) defining the combustion chamber and another housing defining a collection chamber for combustion gases emerging from the passages.

Abstract: In a method for burning a liquid fuel in a combustion system (10) which comprises a combustion chamber (11) and at least one injection nozzle (13) through which liquid fuel is injected into the combustion chamber (11) in the form of a fuel spray (16) and is burnt there with combustion air being added, disturbance-free operation in a simple manner is distinguished in that, in order to actively suppress hydrodynamic instabilities in the combustion chamber (11), the injected fuel spray (16) is modulated by having an electrical voltage applied to it during the injection process, governed by a selected time function.

Abstract: Provided is a combustion chamber for producing a pressurized gas having a wall structure defining an interior chamber, an explosion chamber disposed within the interior chamber, an annular chamber connected to the explosion chamber, a first reflecting surface for reflecting a pressure wave within the interior chamber, a second reflecting surface for reflecting the pressure wave within the interior chamber, at least one inlet for introducing a first gas into the interior chamber, and at least one outlet from the interior chamber for drawing off a pressurized gas from the interior chamber.

Abstract: Provided is a combustion chamber for producing a pressurized gas containing: a wall structure defining an interior chamber; an explosion chamber disposed within the interior chamber and arranged such that compressed air can contact an exterior surface of the explosion chamber to cool it, a first reflecting surface for reflecting a pressure wave within the interior chamber; a second reflecting surface for reflecting the pressure wave within the interior chamber, wherein the first and the second reflecting surfaces are constructed and arranged to resonate the pressure wave in the interior chamber; at least one first inlet for introducing a first gas into the interior chamber; and at least one outlet from the interior chamber for drawing off a pressurized gas from the interior chamber.