Matches 1 - 36 out of 36


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US20120047873 DUPLEX TAB OBSTACLES FOR ENHANCEMENT OF DEFLAGRATION-TO-DETONATION TRANSITION  
A detonation chamber for a pulse detonation combustor including: a plurality of duplex tab obstacles disposed on at least a portion of an inner surface of the detonation chamber wherein the...
US20150184860 SPIRAL PULSE DETONATION TUBE CONFIGURATION  
An engine includes an elongated pulse detonation combustor tube having an arcuate combustion path over a majority of an entire length of the combustor tube, and an elongated portion of the...
US20090241507 GROUND BASED PULSE DETONATION COMBUSTOR FOR POWER GENERATION  
A ground based power generation system contains at least two compressor stages, a combustion stage and a turbine stage. An intercooler is positioned between the two compressor stages and a...
US20130263569 HELICAL CROSS FLOW (HCF) PULSE DETONATION ENGINE  
A helical cross flow pulse detonation engine.
US20050109010 Pulse detonation power system and plant with fuel preconditioning  
A power system includes a fuel preconditioner adapted to convert a fuel to at least one conditioned fuel, a pulse detonation combustor, and a turbine. The pulse detonation combustor is adapted to...
US20080115480 PULSE DETONATION ENGINE BYPASS AND COOLING FLOW WITH DOWNSTREAM MIXING VOLUME  
An engine contains at least one pulse detonation combustor which is surrounded by a bypass flow air duct, through which bypass air flow is directed. The bypass air duct contains at least one...
US20070256426 TRIGGERED PULSED IGNITION SYSTEM AND METHOD  
The ignition system is for use in a gas turbine engine. It comprises an ignition plug having a triggered spark gap therein.
US20090266047 MULTI-TUBE, CAN-ANNULAR PULSE DETONATION COMBUSTOR BASED ENGINE WITH TANGENTIALLY AND LONGITUDINALLY ANGLED PULSE DETONATION COMBUSTORS  
An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an...
US20110056182 VALVELESS PULSE COMBUSTOR  
A valveless pulse combustor having a combustion chamber with a closed first end and an open second end, the combustor also having a tailpipe in fluid communication with the open second end of the...
US20070180833 Methods and apparatus for controlling air flow within a pulse detonation engine  
A flow control device for use with a pulse detonation chamber including an inlet coupled in flow communication with a source of compressed air. The inlet extends at least partially into the...
US20120131899 INTEGRATED DEFLAGRATION-TO-DETONATION OBSTACLES AND COOLING FLUID FLOW  
A detonation chamber and a pulse detonation combustor including a detonation chamber, wherein the detonation chamber includes a plurality of initiation obstacles and at least one injector in fluid...
US20090165438 Pulse detonation engine  
The invention provides a liquid fueled pulse detonation air breathing engine. The invention also provides an embodiment of an engine which has an axial flow compressor final stage configured for...
US20090000266 Pneumatic Operating Driving Device  
A pneumatic operating driving device, comprising at least one rotor (1) being connected to a rotatable supported shaft (3) and being brought into rotation by means of air. Near the circumference...
US20120324860 GAS TURBINE ENGINE AND PULSE DETONATION COMBUSTION SYSTEM  
One embodiment of the present invention is a unique pulse detonation combustion system. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices,...
US20070137172 Geometric configuration and confinement for deflagration to detonation transition enhancement  
A pulse detonation combustor is provided with a fuel-air mixer located upstream from a detonation chamber. A fuel-air mixture exits the fuel-air mixer and enters the detonation chamber, where it...
US20080155959 DETONATION COMBUSTOR TO TURBINE TRANSITION PIECE FOR HYBRID ENGINE  
A transition piece for use within a gas turbine engine provides a path between the exhaust from one or more pressure-rise combustors and a downstream turbine for the extraction of work from the...
US20060254252 Pulse detonation assembly and hybrid engine  
A pulse detonation (PD) assembly includes a number of PD chambers adapted to expel respective detonation product streams and a number of barriers disposed between respective pairs of PD chambers....
US20090065652 Aircraft combination engines exhaust thrust recovery  
A gas turbine engine with a turbine with an exhaust manifold thereabout from which fluids can be transferred to the turbine and an air compressor having an air transfer duct extending therefrom so...
US20070180832 Compact, low pressure-drop shock-driven combustor  
A system for efficiently creating cyclic detonations is provided. The system includes at least a first initiator chamber configured to generate an initial wave, at least one main chamber coupled...
US20140216045 GAS TURBINE WITH IMPROVED POWER OUTPUT  
The application provides an apparatus for augmenting the power produced by a Brayton-cycle gas turbine system of the type having an air compressor for producing compressed air, a combustor for...
US20070180811 Multiple tube pulse detonation engine turbine apparatus and system  
A pulse detonation combustor (PDC) assembly includes an upstream chamber forming an inlet plenum, a downstream chamber including a downstream portion of at least one PDC tube, and an integrated...
US20100192536 GROUND-BASED SIMPLE CYCLE PULSE DETONATION COMBUSTOR BASED HYBRID ENGINE FOR POWER GENERATION  
An engine contains a compressor stage, a compressor plenum, an inlet valving stage, a PDC stage, a PDC exit nozzle stage, a transition stage, a high pressure turbine stage, a turbine plenum, and a...
US20130139487 VARIABLE INITIATION LOCATION SYSTEM FOR PULSE DETONATION COMBUSTOR  
A pulse detonation combustor (PDC) includes a combustion tube, an inlet located on an upstream end of the combustion tube which receives a flow of a fuel/air mixture, an enhanced DDT region...
US20130139486 VARIABLE INITIATION LOCATION SYSTEM FOR PULSE DETONATION COMBUSTOR  
A pulse detonation combustor (PDC) includes a combustion tube, an inlet located on an upstream end of the combustion tube which receives a flow of a fuel/air mixture, an enhanced DDT region...
US20060260291 Pulse detonation assembly with cooling enhancements  
A pulse detonation (PD) assembly includes at least one PD chamber having a wall, which defines cooling holes arranged along at least a portion of the PD chamber. A manifold extends around the PD...
US20140216000 Indexed Positive Displacement Rotary Motion Device  
Disclosed herein is an indexing system for a rotor assembly where in one example the indexing system regulates the rotational location of drive rotors. In one example the rotors are configured to...
US20120151896 HOT GAS PATH COMPONENT COOLING FOR HYBRID PULSE DETONATION COMBUSTION SYSTEMS  
The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass...
US20050138933 Pulse detonation engine and method for initiating detonations  
The invention relates to a pulse detonation engine and a method for initiating detonations in a pulse detonation engine. The pulse detonation engine (1) comprises a combustion chamber (2), an...
US20140083077 ENVIRONMENTALLY SEALED COMBUSTION POWERED LINEAR ACTUATOR  
A combustion powered linear actuator features an actuator body having a first chamber therein and a power piston mounted in the first chamber movable between retracted and extended positions. The...
US20120151895 HOT GAS PATH COMPONENT COOLING FOR HYBRID PULSE DETONATION COMBUSTION SYSTEMS  
The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass...
US20070180810 Pulse detonation combustor with folded flow path  
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...
US20120017563 JET ENGINE, IN PARTICULAR A JET ENGINE FOR AN AIRCRAFT  
The invention relates to a jet engine (1), in particular an aircraft jet engine, including at least one combustion chamber (3). The combustion chamber (3) is connected to at least one compressed...
US20120216504 ENGINE AND COMBUSTION SYSTEM  
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...
US20100275404 ON-LINE CLEANING OF TURBINE HOT GAS PATH DEPOSITS VIA PRESSURE PULSATIONS  
A method for removing hot gas deposits from a system via pressure pulses is provided. The method includes regulating a flow of a mixture of detonation fluid and oxidizer into an expansion chamber;...
US20160326956 INLET MANIFOLD FOR MULTI-TUBE PULSE DETONATION ENGINE  
An inlet manifold for a multi-tube pulse detonation engine includes a vaneless diffuser disposed in a first zone to collect an air discharged from a compressor; a vaned diffuser including a...
US20160102609 PULSE DETONATION COMBUSTOR  
A pulse detonation combustor may include a valve and a tubular combustor wall, which forms an airflow inlet and a combustion chamber. The valve may be configured to selectively fluidly couple the...

Matches 1 - 36 out of 36