Abstract: A combustor nozzle is provided. The combustor nozzle includes a first fuel system configured to introduce a syngas fuel into a combustion chamber to enable lean premixed combustion within the combustion chamber and a second fuel system configured to introduce the syngas fuel, or a hydrocarbon fuel, or diluents, or combinations thereof into the combustion chamber to enable diffusion combustion within the combustion chamber.

Abstract: A pulse detonation engine contains a mechanically driven timing device coupled with a stator device, where the timing device has both an opening portion and a blocking portion. The opening and blocking portions open and close air flow access to a detonation chamber of the pulse detonation engine at appropriate times during the pulse detonation cycle.

Abstract: A valve (50) comprising a first part (401) defining a first array of apertures and a second part (2) defining a second array of apertures, the first part (401) being moveable laterally relative to the second part (2) between a closed configuration in which the first and second arrays of apertures are not registered to substantially prevent passage of a fluid through the valve and an open configuration in which the first and second arrays of apertures are registered to allow passage of fluid, wherein the first and second parts (401, 2) are configured to lock in the closed configuration in response to a pressure differential across the valve (50). In one embodiment, the first part (401) is configured to be sealed against the second part (2) by a pressure differential across the valve when the first and second parts (401,2) are locked in the closed configuration.

Abstract: A valve comprising a first pan (10?) defining a first array of apertures (20?) and a second part (50) defining a second array of apertures (60?), the first pan (10?) being moveable relative to the second part (50) between a first configuration in which passage of a fluid through the valve is substantially prevented and a second configuration in which passage of fluid is allowed. In one embodiment, the first pan (10?) comprises a flexible plate-like member configured to engage a sealing face of the second part (50) when in the second configuration and lock in the second configuration in response to a pressure differential across the valve. The plate-like member is sufficiently flexible to conform to a profile of the sealing face in response to a pressure differential across the valve.

Abstract: A vessel (10) for traveling on water comprises a hull (20) and a keel (30) comprising a member (34) depending from the hull, the member (34) comprising two limbs (44) each depending from a respective lateral side of the hull (20), the two limbs (44) defining at least in part an enclosed flow path extending in a bow to stern direction, the enclosed flow path being configured to allow water incident on the vessel to flow over inner and outer surfaces of the limbs (44a, 44b). The limbs (44) each have a zero-lift surface which is angled to generate in use a component of hydrodynamic force directed away from the enclosed flow path when there is a net flow of water along the enclosed flow path.

Abstract: Apparatus (10) for storing energy, comprising: compression chamber means (24) for receiving a gas; compression piston means (25) for compressing gas contained in the compression chamber means; first heat storage means (50) for receiving and storing thermal energy from gas compressed by the compression piston means; expansion chamber means (28) for receiving gas after exposure to the first heat storage means; expansion piston means (29) for expanding gas received in the expansion chamber means; and second heat storage means (60) for transferring thermal energy to gas expanded by the expansion piston means. The cycle used by apparatus (10) has two different stages that can be split into separate devices or combined into one device.

Abstract: An apparatus for storing energy includes a compression chamber for receiving a gas, a compression piston for compressing gas contained in the compression chamber, a first heat store for receiving and storing thermal energy from gas compressed by the compression piston, an expansion chamber for receiving gas after exposure to the first heat store, an expansion piston for expanding gas received in the expansion chamber, and a second heat store for transferring thermal energy to gas expanded by the expansion piston. The cycle used by the apparatus has two different stages that can be split into separate devices or combined into one device.

Abstract: A supersonic propulsion system is provided. The supersonic propulsion system includes a plurality of systems for efficiently creating cyclic detonations and at least one rocket booster device. Each of the systems include at least a first initiator chamber configured to generate an initial wave, at least one main chamber coupled to the first initiator chamber. The main chamber is configured to generate a main wave and to output products of supersonic combustion. The products are generated within the main chamber. The main chamber is configured to enable the main wave to travel upstream and downstream within the main chamber when the first initiator chamber is located outside the main chamber. The system further includes an initial connection section located between the first initiator chamber and the main chamber that enhances a combustion process via shock focusing and shock reflection.

Abstract: A method of providing resistance to intergranular stress corrosion cracking in an alloy material, the method comprising sensitizing the alloy to form carbides, allowing the carbides to precipitate, and applying a heat treatment to replenish a chromium-depleted zone.

Abstract: Apparatus (10?) for use as a heat pump comprising: compression chamber means (40?); inlet means (30?) for allowing gas to enter the compression chamber means; compression means (60?) for compressing gas contained in the compression chamber means; heat exchanger means for receiving thermal energy from gas compressed by the compression means; expansion chamber means (124?) for receiving gas after exposure to the heat exchange means; expansion means (120?) for expanding gas received in the expansion chamber means; and exhaust means (100?) for venting gas from the expansion chamber means after expansion thereof.

Abstract: A vessel (10) for travelling on water comprises a hull means (20) and a keel (30) comprising a member (34) depending from the hull means, the member (34) comprising two limbs (44) each depending from a respective lateral side of the hull means (20), the two limbs (44) defining at least in part an enclosed flow path extending in a bow to stem direction, the enclosed flow path being configured to allow water incident on the vessel to flow over inner and outer surfaces of the limbs (44a, 44b). The limbs (44) each have a zero-lift surface which is angled to generate in use a component of hydrodynamic force directed away from the enclosed flow path when there is a net flow of water along the enclosed flow path.

Abstract: A pulse detonation engine contains a mechanically driven timing device coupled with a stator device, where the timing device has both an opening portion and a blocking portion. The opening and blocking portions open and close air flow access to a detonation chamber of the pulse detonation engine at appropriate times during the pulse detonation cycle.

Abstract: A combustor nozzle is provided. The combustor nozzle includes a first fuel system configured to introduce a syngas fuel into a combustion chamber to enable lean premixed combustion within the combustion chamber and a second fuel system configured to introduce the syngas fuel, or a hydrocarbon fuel, or diluents, or combinations thereof into the combustion chamber to enable diffusion combustion within the combustion chamber.

Abstract: A preform includes an airfoil stub and a dovetail hub. The hub first undergoes electrochemical discharge machining to form a rough dovetail. The airfoil stub undergoes electrochemical machining to form an airfoil. The rough dovetail then undergoes electrochemical discharge machining to form a rough tang. The rough tang is finish machined to form a dovetail extending from the airfoil in a unitary rotor blade.