Abstract: This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.

Abstract: A heating unit includes a housing defining a thermal cavity and has a first longitudinal edge and an opposing second longitudinal edge, a reflector assembly disposed within the thermal cavity, a heating element, and a lighting element. The housing defines a vent positioned at least one of laterally between a central longitudinal plane of the housing and the first longitudinal edge and laterally between the central longitudinal plane and the opposing second longitudinal edge. The reflector assembly is coupled to an interior surface of the housing. A spacer is positioned between the reflector assembly and the interior surface forming an air gap therebetween. The heating element extends within the central longitudinal plane and is at least partially surrounded by the reflector assembly. The lighting element is positioned along at least one of the first longitudinal edge and the opposing second longitudinal edge such that the vent is positioned laterally between the lighting element and the heating element.

Abstract: A temperature regulation unit includes a housing, a conduit, a fan, and a thermal element. The housing has a sidewall with an upper end and a lower end. The sidewall defines an internal cavity. The conduit is disposed within the internal cavity of the housing and defines a passage. The conduit has a first end and an opposing second end. The fan is positioned within the internal cavity of the housing at the first end of the conduit. The fan is configured to provide an airflow to the passage of the conduit. The thermal element is positioned within the passage of the conduit. The thermal element is configured to thermally regulate a temperature of the airflow flowing past the thermal element and out of the opposing second end of the conduit.

Abstract: A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energize the first and second plasma generators at an energizing frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component.

Abstract: A fuel system for a gas turbine engine, the gas turbine engine including a combustor having a pilot fuel injector and a main fuel injector, the fuel system including first and second variable flow fuel pumps configured to provide metered fuel flow to the pilot injector, and the main injector respectively; first and second variable speed electric motors configured to drive respective first and second fuel pumps; wherein each of the electric motors includes a polyphase motor including a stator having concentrated windings.

Abstract: This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.

Abstract: A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energise the first and second plasma generators at an energising frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component.

Abstract: Loss reduction apparatus for a fluid transfer system includes a fluid device. The fluid device defines a first fluid path along which a greater part of a fluid flows in a first condition, and a second fluid path along which a greater part of the fluid flows in a second condition. The apparatus is arranged so that when a leak occurs at a location in the system, the leak causes a relative reduction in fluid pressure at the location, which moves the device from the first condition to the second condition.

Abstract: It is known there is ingestion of hot gas flow 35 from an annular flow 36 in gas turbine engines. This flow 35 is prevented from attaching to the disc by coolant flow 32 passing through gaps in lock plates 28, 29 by creation of a barrier layer. In order to regulate and enhance this effect spacer protrusions 31 are provided between ends of lock plates 28, 29. In such circumstances the gap 30 is controlled and therefore the rate of leakage flow 32 regulated for best cooling effect. This cooling effect and cooling flow 32 can be further enhanced by providing chutes 39 for presentation of the coolant flow 32.

Abstract: A seal arrangement 32 between a turbine shroud seal segments 38,40 in a gas turbine engine. The arrangement 32 comprises facing slots 34, 36 provided respectively in the segments 38,40 with offset spaces 42, 44 provided between the segments 38,40. A strip 46 is cemented into the slot 36 such that the flow path 50 passes through the space 42, around the free end of the strip 46, and out through the offset space 44, thereby providing a longer flow path.

Abstract: The present invention is a more durable expanded material that enables thinner wall thicknesses and a more flexible reinforcement suitable for stenting. The present invention is especially useful in the construction of grafts, stents, and stent-grafts which are used, for example, in repairing or replacing blood vessels that are narrowed or occluded by disease, aneurismal blood vessels, or other medical treatments. The inventive material and configurations allow expansion or contraction in size or adjustment in size in an incremental manner so that the optimum size, shape, and fit with other objects can be obtained. The present invention is also optionally capable of more accurately delivering one or more active ingredients such as drugs over longer periods of time. The present invention optionally includes surface modifications and additives that increase the surface adhesion of active ingredients, coatings, or combinations thereof.

Abstract: The present invention relates to decoys for heat-seeking missiles and methods of producing and using the same. The decoys are designed to be kinematic or pseudo-kinematic, producing one or more infra-red radiation emitting clouds that give the appearance of a moving infra-red target in the airspace in which the decoy has been released.

Abstract: A gas-fired water heater is provided with a combustion shutoff system which precludes further combustion within the water heater's combustion chamber in response to a combustion temperature therein reaching a predetermined level correlated to and indicative of a predetermined, undesirably high concentration of carbon monoxide present in the combustion chamber. In various illustrated embodiments thereof, the combustion shutoff system is operative to terminate further combustion air inflow to the combustion chamber, or terminate further fuel flow to the burner portion of the water heater.

Abstract: A gas-fired water heater is provided with a combustion shutoff system which precludes further combustion within the water heater's combustion chamber in response to a combustion temperature therein reaching a predetermined level correlated to and indicative of a predetermined, undesirably high concentration of carbon monoxide present in the combustion chamber. In various illustrated embodiments thereof, the combustion shutoff system is operative to terminate further combustion air inflow to the combustion chamber, or terminate further fuel flow to the burner portion of the water heater.

Abstract: A method for the identification of agents which modulate sterol biosynthesis which method comprises contacting a test compound with a host cell comprising a DNA sequence which controls expression of a yeast acetoacetyl CoA thiolase gene operably linked to a reporter system such that modulation of sterol biosynthesis in the host cell leads to a detectable change in cell phenotype, and determining whether any such detectable change has occurred.