Abstract: An inflatable probe for testing a component. The inflatable probe has a balloon formed of a dielectric material, the balloon having a neck and at least one electrode pair comprising an inner electrode and an outer electrode, the inner electrode being positioned on an internal surface of the balloon and the outer electrode being positioned on an external surface of the balloon. The inflatable probe also has a sealing plug that forms an air tight seal with neck of the balloon to retain a fluid within the balloon, the sealing plug at least having a seal electrode to connect to the inner electrode within the balloon, the sealing plug supporting a first wire to connect to a first seal electrode. The inflatable probe also has at least one tool that is connected to the balloon.

Abstract: A method of monitoring a fuel system in a gas turbine engine. The method may comprise pumping fuel to a combustor from a fuel tank with a pump. The method may comprise controlling a flow of the fuel to the combustor with a metering valve disposed downstream of the pump and closing a spill valve disposed downstream of the pump, wherein the spill valve is closed in fixed increments and closing the spill valve increases a pressure in the fuel system. The method may comprise opening a pressure valve in response to the pressure in the fuel system being equal to or greater than a predetermined value, and capturing a degree of closing of the spill valve when the pressure valve opens.

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: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

Abstract: A method of mitigating uncommanded or uncontrollable high thrust in a gas turbine engine is provided. The method may comprise pumping fuel to a combustor from a fuel tank, controlling a flow rate of the fuel to the combustor with a metering valve, spilling a portion of the fuel pumped by the pump with a primary spill valve, controlling a pressure of the fuel flowing to the combustor via a pressure valve, detecting a pressure differential across the pressure valve with a pressure transducer, determining the flow rate of the fuel based on the detected pressure differential and the positional feedback of the pressure valve opening, comparing the determined flow rate with a demand flow rate, and opening a secondary spill valve when the determined flow rate exceeds the demand flow rate.

Abstract: A tile for a gas turbine engine combustor. The tile has a base that has a hot-side surface, a cold-side surface, a first circumferential extremity, a second circumferential extremity and a local radial axis. The tile also has a plurality of cooling channels that have inlets on the cold-side surface and outlets on the hot-side surface, and one or more rail structure attached to the cold-side surface of the base.

Abstract: A fuel system for a hydrogen fueled gas turbine engine comprises a main hydrogen fuel storage unit configured to store liquid hydrogen. The main fuel storage unit comprises an ullage space configured to store ullage fluid comprising gaseous or supercritical hydrogen. The system further comprises a liquid hydrogen drain line configured to provide liquid hydrogen from the main hydrogen fuel storage unit to a fuel conduit, the fuel conduit being configured to supply hydrogen fuel to a combustor of the gas turbine engine. A priming line is provided, which is configured to provide ullage fluid to the fuel conduit, and a priming valve is configured to selectively control flow through the priming line.

Abstract: An example system includes an electrical machine electrically configured to generate electrical energy used by one or more components of a gas-turbine engine; an energy storage system; and a controller electrically connected to the energy storage system and configured to receive electrical energy from the energy storage system, wherein, in response to the gas-turbine engine being shut off, the controller is configured to cause the electrical machine to rotate a rotor of the gas-turbine engine using the energy received from the energy storage system.

Abstract: Methods of reducing dry crack formation in ceramic matrix composite green bodies are provided. Some of the methods expose the green body to a gaseous atmosphere at a relatively high humidity for a first period, and then slowly lower the humidity over a second period, where the gaseous atmosphere is at room temperature for both periods. Other methods start the gaseous atmosphere at room temperature and then raise the temperature to a higher temperature while the humidity is relatively high, and hold that temperature even as the humidity is lowered in the second period.

Abstract: A system includes a plurality of forming roller sets comprising an inner forming roller and an outer forming roller, each inner forming roller rotatable about an inner forming roller axis, each outer forming roller rotatable about an outer forming roller axis, each forming roller set being adjustable between an engagement configuration and a disengagement configuration, each forming roller set forming a profile on the ring component based on a forming roller set profile of the forming roller set, the system also including an actuating unit which controls the engagement and a disengagement of the forming roller sets with the ring component.

Abstract: In examples, a clutch assembly includes a first clutch member disposed near a first end of a first shaft. The first clutch member defines a first surface. The first shaft includes a starter motor coupled to a second end of the first shaft. The clutch assembly includes a second clutch member disposed near a first end of a second shaft. The second clutch member defines a second surface opposing the first surface, and the second shaft includes an accessory gearbox of a gas turbine engine coupled to a second end of the second shaft. The surfaces of the first and second clutch member engage such that rotational motion is transferred between the first clutch member and the second clutch member. The first clutch member and the second clutch member are configured to passively disengage from each other and actively reengage with each other.

Abstract: The invention relates to a component of a gas turbine engine which has a fiber-composite material having a multiplicity of rovings, wherein at least one roving of the fiber-composite material along the spatial extent thereof has a variable cross section, at least two rovings have in each case a dissimilar cross section and/or the at least one roving follows a variable direction and the at least one roving is deposited by means of tailored fiber placement. The invention also relates to a method of a component.

Abstract: The disclosure describes a fluid plate assembly that includes a plurality of fluid plates and one or more seals between the plurality of fluid plates. The plurality of fluid plates are coupled together to form a fluid passage. At least one fluid plate of the plurality of fluid plates includes a plurality of holes and one or more fluid channels. The plurality of holes are configured to spray pressurized fluid on at least a portion of one or more components of a rotary machine. The one or more fluid channels that form the fluid passage are configured to direct the pressurized fluid to the plurality of holes.

Abstract: The invention relates to a method for training machine learning models, having the steps of: detecting data in the form of time series data using one or more computers, said data being obtained by means of one or more measuring devices (60-62), in each case in the form of a sensor for measuring a physical variable; receiving multiple classification data units relating to the data using the one or more computers; receiving a selected part of the data using the one or more computers for each of the classification data units; and training multiple machine learning models using the one or more computers, in each case on the basis of at least one of the classification data units and the at least one corresponding selected part of the data, wherein the multiple machine learning models represent multiple instances of the same machine learning model.

Abstract: In some examples, a technique including positioning supports such that the supports are between a first metallic substrate and a second metallic substrate, wherein an undulating member is located between the first metallic substrate and the second metallic substrate, the undulating member defining a plurality of first peaks adjacent to a first surface of the first metallic substrate and a plurality of second peaks adjacent to a second surface of the second metallic substrate, wherein a first support of the supports is positioned such that the first support extends between a first peak of the plurality of first peaks and the second surface of the second metallic substrate; welding the first peak to the first surface of the first metallic substrate in an area of the first support; and removing the first support by at least one of a thermal removal process or a chemical removal process.

Abstract: An example system includes one or more heaters configured and positioned to add thermal energy to one or more portions of a gas turbine engine after the gas turbine engine was in operation, wherein the thermal energy minimizes or prevents undesired contact or seizing of a rotor of the gas turbine engine with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The system further includes a controller configured to control operation of the one or more heaters.

Abstract: There is disclosed a gas turbine engine comprising: an electrically-powered motor configured to rotate a driven spool of the gas turbine engine; a primary controller configured to conduct a primary function using the motor; and a bow controller configured to selectively control the motor to perform a rotor bow mitigation operation in which the motor drives the driven spool to rotate to mitigate a non-uniform thermal distribution in a rotor of a spool of the gas turbine engine.

Abstract: A gas turbine engine includes a bypass duct including an outer wall, a heat exchanger arranged within the bypass duct, and a turnbuckle assembly. The outer wall includes a main body and an access panel removably coupled to the main body. The turnbuckle assembly couples the heat exchanger to the access panel, and includes a first rod coupled to the access panel and a second rod coupled to the first rod and to the heat exchanger. The outer end of the first rod is threadably received in a socket of a socket housing removably coupled to the access panel such that the first rod is fixedly coupled to the socket housing to increase lateral stiffness of the heat exchanger and the turnbuckle assembly such that the lateral dynamic mode is outside of a fan rotor operating range.

Abstract: A techniques for improved guiding of hyper-redundant manipulator probes into a constrained space which make use of the known characteristics of the space into which the probe is being inserted to increase the efficiency of the computation of the path of the probe. Embodiments of the invention achieve this through an optimisation function which determined a new orientation which minimises the deviation between each of: a) the point on the probe where the probe starts to follow a defined curve within the constrained space and a predetermined initial point, and b) the distal end of the probe and said defined curve.

Abstract: The present application discloses a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft, the method comprising: determining a mass of a fuel being loaded, or which has been loaded, onto the aircraft; determining a corresponding volume of the fuel; determining one or more fuel characteristics of the fuel based on the determined mass and volume. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.