Abstract: A blower compressor assembly comprises: a flow modifier comprising an array of nozzle guide vanes and an array of diffuser vanes, wherein the flow modifier is movable relative to a rotor between a turbine configuration and a compressor configuration; and an actuator assembly for moving the flow modifier relative to the rotor between the turbine configuration and the compressor configuration, wherein the actuator assembly comprises: a first actuator comprising a first chamber, a first valve configured to selectively supply pressurised air to the first chamber or vent pressurised air from the first chamber, and a piston arranged to one side of the first chamber and coupled to the flow modifier such that the flow modifier is moved into the turbine configuration or the compressor configuration based on the pressure of air within the first chamber.

Abstract: There is provided an air pressurisation system for an aircraft, the air pressurisation system comprising: a transmission for driving a rotor of a blower compressor for the air pressurisation system, wherein the transmission comprises: a first input configured to receive drive from a spool of a gas turbine engine; a second input; and an output configured to drive to the rotor of the blower compressor, wherein a speed of the output is determined by a function of speeds of the first and second inputs; and a brake coupled to the second input, wherein the brake is operable to engage and brake the transmission at the second input, in order to fix a transmission ratio of the transmission between the first input and the output.

Abstract: A blower system for supplying pressurized air to an airframe of an aircraft comprises: an air inlet for receiving air from an air source; an air outlet for supplying pressurized air to an airframe; a blower compressor in fluid communication with the air inlet and the air outlet, the blower compressor comprising a first rotor and a second rotor, wherein the first and second rotors are independently rotatable in order to compress air received from the air inlet and deliver the compressed air to the air outlet; a variable transmission comprising a first output for driving the first rotor, a second output for driving the second rotor, and first, second and third inputs; and first and second electrical machines, each comprising an electric rotor and an electric stator, wherein: the first input of the variable transmission is configured to be mechanically coupled to a spool of a gas turbine engine; the second input of the transmission is mechanically coupled to the electric rotor of the first electrical machine; th

Abstract: A guide vane assembly includes a guide vane and a sealing assembly slidable along a span of the guide vane relative to the guide vane and extending along a chordal axis and the span of the guide vane. The sealing assembly includes a plate configured to be disposed around at least a portion of an external surface of the guide vane. The sealing assembly further includes a manifold coupled to the plate and configured to receive pressurized fluid therein. The manifold is disposed around the plate. The sealing assembly further includes a plurality of flow tubes extending between the manifold and the plate. Each of the plurality of flow tubes are configured to receive the pressurized fluid from the manifold.

Abstract: A blower system for a gas turbine engine comprising: a rotor assembly, an airframe port and a routing-control valve. The rotor assembly is configured to be mechanically coupled to a spool of the gas turbine engine. The airframe port is configured to receive and discharge air to an airframe system. The routing-control valve comprises: a primary channel for bidirectional flow between the rotor assembly and the airframe port; a primary valve member configured to open and close the primary channel; and an auxiliary channel branched from the primary channel. The auxiliary channel is configured to bypass the primary valve member for: a first auxiliary flow from the airframe port to the rotor assembly; or a second auxiliary flow for purging air from the rotor assembly to a discharge port. The blower system is configured to operate in an engine drive mode and in a blower mode.

Abstract: There is provided an air pressurisation system for an aircraft. The air pressurisation system comprises a blower compressor configured to be mechanically coupled to a spool of a gas turbine engine and configured to receive a first inlet flow of air from a bypass duct of the gas turbine engine; a delivery line configured to convey air compressed by the blower compressor to a cabin pressurisation system of the aircraft; a core bleed line configured to selectively provide a second inlet flow of gases from a compressor of the gas turbine engine 10 to the delivery line in an augmented air supply mode of the air pressurisation system; and an air/oil separator arranged in the core bleed line for removing contaminating oil and oil mist from the second inlet flow of gases before the second inlet flow of gases is provided to the delivery line.

Abstract: A rotary assembly of a pressurized air system for an aircraft with a rotor configured to be mechanically coupled to a spool of a gas turbine engine and a flow modifier with a first section and a second section. The first section defining a plurality of first flow channels configured to receive flow from the rotor. The second section defining a plurality of second flow channels configured to direct flow towards the rotor. The rotary assembly is configured to permit relative movement between the rotor and the flow modifier to move between a turbine configuration in which the rotor is configured to receive air from an external air source to drive the spool to rotate and a compressor configuration in which the rotor is configured to be driven to rotate by the spool and to receive and compress air from the gas turbine engine.

Abstract: A guide vane assembly includes a guide vane and a sealing assembly slidable along a span of the guide vane relative to the guide vane and extending along a chordal axis and the span of the guide vane. The sealing assembly includes a plate configured to be disposed around at least a portion of an external surface of the guide vane. The sealing assembly further includes a manifold coupled to the plate and configured to receive pressurized fluid therein. The manifold is disposed around the plate. The sealing assembly further includes a plurality of flow tubes extending between the manifold and the plate. Each of the plurality of flow tubes are configured to receive the pressurized fluid from the manifold.

Abstract: There is provided a gas turbine engine comprising a blower system for supplying pressurised air to an airframe via an airframe port. The blower system comprises a compressor configured to receive air from a bypass duct or a core of the gas turbine engine and to discharge compressed air into a delivery line extending from the compressor to the airframe port. The blower system also comprises a heat exchanger configured to transfer heat from the compressed air to a coolant and a valve arrangement configured to switch between operation of the blower system in a baseline mode and a cooling mode, the valve arrangement being configured to: selectively divert the compressed air within the delivery line to the heat exchanger for operation in the cooling mode; and/or selectively provide the coolant to the heat exchanger for operation in the cooling mode.

Abstract: There is provided an air pressurisation system comprising: a blower compressor coupled to a spool of a gas turbine engine and configured to receive inlet air from a bypass duct of the gas turbine engine; an air treatment apparatus to mix air from the air cycle line with air from the bypass line to control a temperature of air for discharge to an airframe system; and a core bleed line configured to provide a second inlet flow of air from a compressor of the gas turbine engine to the air treatment apparatus in an augmented air supply mode of the air pressurisation system; wherein the core bleed line is configured to provide the second inlet flow of air directly to the bypass line or mix the second inlet flow of air with air from the blower compressor upstream of the bypass line.

Abstract: A power electronics cooling assembly with a housing for power electronics. The housing is mountable to a bulkhead for separating a fire zone from a non-fire zone of a gas turbine engine. In the non-fire zone, one or more ducts extend from the bulkhead to the housing. A fluid supply and return pipes extend through the one or more ducts from the bulkhead to the housing. The fluid supply and return pipes are for carrying an ignitable fluid coolant. A heat exchange structure arranged within the housing is configured to receive the ignitable fluid coolant from the fluid supply pipe, facilitate transfer of heat from the power electronics within the housing to the ignitable fluid coolant, and output the ignitable fluid coolant to the fluid return pipe. A system, gas turbine engine assembly and an aircraft comprising the power electronics cooling assembly are also provided.

Abstract: There is provided an air pressurisation system for an aircraft, the air pressurisation system comprising: a transmission for driving a rotor of a blower compressor for the air pressurisation system, wherein the transmission comprises: a first input configured to receive drive from a spool of a gas turbine engine; a second input; and an output configured to drive to the rotor of the blower compressor, wherein a speed of the output is determined by a function of speeds of the first and second inputs; and a brake coupled to the second input, wherein the brake is operable to engage and brake the transmission at the second input, in order to fix a transmission ratio of the transmission between the first input and the output.

Abstract: The present disclosure provides a computing device (100) for classification of an aspirating/dispensing operation in an automated analyzer (50). The computing device (100) comprises a memory (22) storing a neural network model (24). The neural network model 24 sequentially comprises a plurality of convolution blocks (202-1, 202-2 . . . 202-N). The computing device (100) further comprises a processor (20) communicably coupled to the memory (22) and at least one measurement sensor (106) associated with a pipetting probe (104) of a pipetting device (102). The processor (20) is capable of executing the neural network model (24). The processor (20) is further capable of executing instructions (26) to classify the aspirating/dispensing operation into at least one correct class or at least one incorrect class.

Abstract: There is provided a blower system for providing air to an airframe system, comprising a rotor configured to be mechanically coupled to a spool 440 of a gas turbine engine, wherein the rotor is configured to: in a blower mode, be driven to rotate by the spool to discharge air to an airframe discharge port for supply to an airframe system; and, in an engine drive mode, receive air from an external air source via an impingement port that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool to.

Abstract: A compressor of an aircraft air pressurization system comprises: a rotor configured to be mechanically coupled to a spool of a gas turbine engine; and a housing, wherein the rotor is supported for rotation within the housing about a rotor axis, wherein the rotor and housing define a primary air channel extending between an inlet of the blower compressor for receiving the inlet flow of air and an outlet from which the blower compressor is configured to output pressurized air to a delivery line. The housing further comprises a bleed opening in a wall of the housing between the inlet and the outlet, the bleed opening extending circumferentially about the rotor axis, wherein the bleed opening is for contaminants within the inlet flow of air, which have been driven outward due to the rotation of the rotor, to be bled out of the blower compressor.

Abstract: A compressor of an aircraft air pressurization system comprises: a rotor configured to be mechanically coupled to a spool of a gas turbine engine; an oil-lubricated bearing for supporting rotation of the rotor, wherein the oil-lubricated bearing is disposed within a bearing chamber; and a seal assembly for restricting oil from the bearing chamber from reaching an inlet of the blower compressor, wherein the seal assembly comprises: a seal disposed between the bearing chamber and an air buffer chamber; an air buffer inlet configured to receive a flow of pressurized air into the air buffer chamber; and an air buffer outlet configured to allow the flow of pressurized air to be exhausted from the air buffer chamber together with oil from the bearing chamber that has passed through the seal and become entrained within the flow of pressurized air.

Abstract: There is provided a dynamic sealing assembly for a rotary machine, comprising a primary sandwich plate, a secondary sandwich plate and a bristle pack. The primary sandwich plate comprises a plurality of primary vane openings, and the secondary sandwich plate comprises a plurality of secondary vane openings. The bristle pack comprises a plurality of bristles and is disposed between the primary sandwich plate and the secondary sandwich plate. Each of the plurality of primary vane openings overlies and aligns with a respective secondary vane opening to form a vane channel for receiving a vane along a longitudinal axis of the dynamic sealing assembly. The bristle pack is configured to: provide a brush seal between each vane received within the respective vane channels and the dynamic sealing assembly; and allow relative movement between the dynamic sealing assembly and the vane received within each vane channel along the longitudinal axis.

Abstract: There is provided an air pressurisation system for an aircraft. The air pressurisation system comprises a blower compressor, a delivery line and a catalyst material. The blower compressor is configured to be mechanically coupled to a spool of a gas turbine engine and configured to receive an inlet flow of gases from a bypass duct of the gas turbine engine. The delivery line is configured to convey gases received from the blower compressor to an airframe port for supply to an airframe system. The catalyst material is disposed along the delivery line and configured to catalyse a reaction of volatile organic compounds within gases conveyed by the delivery line.

Abstract: There is provided a dynamic sealing assembly for a rotary machine, comprising a primary sandwich plate, a secondary sandwich plate and a bristle pack. The primary sandwich plate comprises a plurality of primary vane openings, and the secondary sandwich plate comprises a plurality of secondary vane openings. The bristle pack comprises a plurality of bristles and is disposed between the primary sandwich plate and the secondary sandwich plate. Each of the plurality of primary vane openings overlies and aligns with a respective secondary vane opening to form a vane channel for receiving a vane along a longitudinal axis of the dynamic sealing assembly. The bristle pack is configured to: provide a brush seal between each vane received within the respective vane channels and the dynamic sealing assembly; and allow relative movement between the dynamic sealing assembly and the vane received within each vane channel along the longitudinal axis.

Abstract: There is provided an air pressurisation system comprising: a blower compressor coupled to a spool of a gas turbine engine and configured to receive inlet air from a bypass duct of the gas turbine engine; an air treatment apparatus to mix air from the air cycle line with air from the bypass line to control a temperature of air for discharge to an airframe system; and a core bleed line configured to provide a second inlet flow of air from a compressor of the gas turbine engine to the air treatment apparatus in an augmented air supply mode of the air pressurisation system; wherein the core bleed line is configured to provide the second inlet flow of air directly to the bypass line or mix the second inlet flow of air with air from the blower compressor upstream of the bypass line.