Abstract: Bearing apparatus including: a first bearing; a second bearing; and a pivot member including a first part contacting the first bearing, a second part contacting the second bearing, and a fulcrum between the first part and the second part. The pivot member is arranged to pivot about the fulcrum to distribute load between the first bearing and the second bearing.

Abstract: A fluid conduit for a gas turbine engine. The conduit includes a superelastic material such as TNTZ or Ti2448. The conduit is installed such that at least part of the conduit is subject to a stress which lies in one of a superelastic and a plastic region of the material in use.

Abstract: A method including initiating, by a processing device, a transaction including a plurality of data items in one or more data stores to cause a change to at least a data item of the plurality of data items. The transaction includes a transaction identifier (ID). The method further includes for at least a data item of the plurality of data items, generating transactional data usable to undo the change to each data item associated with the transaction. The method further includes intercepting data items. The method further includes adding the transactional ID and the transactional data to each data item. The method further includes providing the data items to a data store of the one or more data stores.

Abstract: A gas turbine engine provides mechanical shaft power. Two parameters relating to engine operation are sensed that are representative of two different pressures, two different temperatures, or a pressure and a temperature associated with the engine. A value representative of the shaft power is determined during engine operation as a function of these two parameters. This value may be used for engine monitoring including making one or more adjustments to operational aspects of the engine, regulating/controlling engine function, and/or providing one or more power indicators.

Abstract: A gas turbine engine (20) comprising a variable geometry engine compressor (24), a variable geometry engine turbine (30) coupled to the engine compressor (24) and a combustor (28). The combustor (28) has an inlet (34) arranged to receive air from a first engine compressor outlet (34), and an outlet arranged to deliver combustion products to the engine turbine (30); a combustor bypass passage (50) having an inlet (53) arranged to receive air from a second engine compressor outlet (53), and an outlet (54) in fluid communication with a main fluid flow path downstream of a combustion zone (46, 48) of the combustor (28), and upstream of a turbine inlet (31); wherein the combustor bypass passage (50) comprises a bypass control valve (52) configured to selectively modulate the ratio of air flowing to the combustor inlet (34) to air flowing through the bypass passage (50).

Abstract: A gas turbine engine has in flow series: a compressor section, a combustor, and a turbine section. The engine further has a steam generator, and a water and steam delivery system. During an engine start-up period, the delivery system delivers liquid water to the combustor and mixes the delivered water in its liquid state with working gas in the combustor. After the start-up period, the delivery system accepts steam from the steam generator, delivers the steam to the combustor and mixes the delivered steam in its gaseous state with the working gas in the combustor.

Abstract: The invention concerns an aircraft propulsion control system in which a gas turbine engine has an actuable flow opening for control of flow to or from a portion of the engine. One or more sensor is arranged to sense a condition indicative of vapour trail formation by the exhaust flow from the engine. A controller is arranged to control actuation of the flow opening so as to reduce the efficiency of the engine upon sensing of said condition by the one or more sensor. In one example, the flow opening is a variable area fan nozzle.

Abstract: A bearing arrangement comprises: first and second thrust bearings, each including an inner race which is disposed on a shaft and an outer race which is supported by at least one resilient element. Applying a shaft thrust load elastically deforms the resilient elements so as to axially displace the respective outer races in order that the thrust load is shared between the first and second thrust bearings.

Abstract: A duct arrangement 18 for a waterjet propulsor 10. The duct arrangement 18 comprises a main duct 30 having an inlet 20. The inlet 20 has an elongate main portion 32 extending along a principal axis 34, and at least one lateral portion 36 in fluid communication with the main portion 34. The at least one lateral portion 36 extends part way only along the length of the main portion 34.

Abstract: This invention provides for tracking and rewarding commuters according to their contribution to unclogging roads by opting for alternative transport forms and improving their health and the health of the environment. In particular, the invention relates to commuters who travel under human power to and from their place of work and who sign up as subscribers to a managed system that tracks their travel events, compares data gathered about the event with other events and determines whether or not the event qualifies as a commute, in which case an account of the user is credited. When the accumulated credit in the account reaches a threshold amount, the user qualifies for receiving a reward such as by means of a value token.

Abstract: A method of compressing a gas, which uses a compressor train having a plurality of discrete portions and including at least an upstream portion, a mid-stream portion and a downstream portion arranged successively in flow series. The method includes: (i) performing a first compression step by directing a flow of said gas into the upstream compressor portion and driving the upstream compressor portion to compress the gas; (ii) performing a second compression step by directing the compressed flow from the upstream compressor portion into the mid-stream compressor portion and driving the mid-stream compressor portion to further compress the gas; and (iii) performing a third compression step by directing the compressed flow from the mid-stream compressor portion into the downstream compressor portion and driving the downstream compressor portion to further compress the gas.

Abstract: A tail section for an aerospace vehicle is provided. The tail section comprises a rudder which is movable about an axis to generate a yawing moment on the aerospace vehicle. The tail section further comprises a thruster having, in flow series, an air intake, an electrically powered device for accelerating the air received through the intake, and an air outlet which directs the accelerated air to increase the yawing moment generated by the rudder.

Abstract: The invention includes a process for reducing the amount of HCN discharged to atmosphere from a FCC unit, having a regenerator and a means for collecting and supporting catalyst particles. The process comprises adding a catalyst to the regenerator flue gas prior to entering the collecting means and precipitating the catalyst in the collecting means to form a catalyst bed. Ammonia or ammonia precursor is optionally added to the flue gas. The flue gas HCN is reacted in the presence of water and oxygen in the flue gas, and optional ammonia or ammonia precursor, at 200° C. to 800° C. in the presence of the catalyst bed to reduce the HCN amount, and the flue gas containing a reduced amount of HCN is discharged to atmosphere. The catalyst is one or more supported transition or lanthanide metal catalysts. The process can also be utilized in any combustion process.

Abstract: A bearing arrangement is disclosed. The bearing arrangement includes first and second bearings, with each bearing including a respective support element and a respective set of rolling elements and defining a respective load path extending through the respective support element and rolling elements. The support elements are coupled such that a load applied to either support element is transmitted through both the first and second load paths. The arrangement further includes a pair of superelastic titanium alloy elements located in the respective load paths to provide resilient movement between the bearings when a load is applied to the bearing arrangement.

Abstract: A heat exchange arrangement for a gas turbine engine. The arrangement includes a first conduit for an engine component cooling fluid and a second conduit for a second fluid. The arrangement further includes a heat exchange portion in which fluids flowing through the first and second conduits are in a heat exchange relationship. A valve is provided, which is configured to moderate the mass flow rate of one of the fluids through the heat exchange portion. The arrangement includes divert valve in the first conduit which diverts flow to the second conduit as the flow in the second conduit is moderated to reduce thermal shock in the heat exchange portion.

Abstract: A distribution pipeline power plant, comprising: an input, configured to receive a fluid that has been heated using energy derived from a geothermal field; an expander, configured to extract energy from the fluid that has been heated using energy derived from a geothermal field; and an output configured to transfer at least some of the energy extracted from the fluid that has been heated using energy derived from a geothermal field to a circulator to drive a further fluid along a distribution pipeline.

Abstract: A beverage preparation capsule containing a beverage preparation ingredient, having a body with side walls formed from one or more substantially air- and liquid-impermeable sheet materials defining a chamber containing a beverage preparation ingredient and further defining an outlet channel having an upstream end in fluid communication with the chamber for escape of beverage from the chamber. At least a region of the outlet channel is filled by a filtration material for filtering the beverage escaping from the chamber. Also provided is a clamp assembly for preparing a beverage from such a capsule, the clamp assembly comprising two or more clamp members, wherein an inner wall of at least one of the clamp members comprises a concave base surface for receiving the capsule and one or more pressure pads projecting from the concave base surface for selectively constricting a region of the capsule.

Abstract: A method of modulating the cooling of a gas turbine component is disclosed. The method includes determining a target component temperature at which the gas turbine component can be maintained without the gas turbine component experiencing a failure over the course of an indicated life of the gas turbine component; scheduling a cooling air value to the target component temperature; and determining one or more of a demanded cooling air temperature and a demanded cooling air mass flow rate based on the scheduled cooling air value.

Abstract: The invention includes a process for reducing the amount of HCN discharged to atmosphere from a FCC unit, having a regenerator and a means for collecting and supporting catalyst particles. The process comprises adding a catalyst to the regenerator flue gas prior to entering the collecting means and precipitating the catalyst in the collecting means to form a catalyst bed. Ammonia or ammonia precursor is optionally added to the flue gas. The flue gas HCN is reacted in the presence of water and oxygen in the flue gas, and optional ammonia or ammonia precursor, at 200° C. to 800° C. in the presence of the catalyst bed to reduce the HCN amount, and the flue gas containing a reduced amount of HCN is discharged to atmosphere. The catalyst is one or more supported transition or lanthanide metal catalysts. The process can also be utilized in any combustion process.

Abstract: A gas turbine engine has in flow series: a compressor section, a combustion chamber, and a turbine section. The engine further has a steam generator. The combustion chamber has a steam reservoir located at the upstream end thereof. The steam reservoir receives steam from the steam generator, and delivers the received steam into a combustion zone of the combustion chamber.