A fuel injector system includes an outer support and an inner support, with a feed arm extending radially between the inner support and the outer support. A plurality of outlet openings extend in an axial direction from the feed arm for feeding respective injection nozzles. The outer support and feed arm define a plurality of fuel passages therethrough to convey fluid from an external source through the outer support and feed arm to the outlet openings. A heat shield extends around the feed arm from the outer support to the inner support. The heat shield is spaced apart from the feed arm with an insulative gap therebetween.

A method for operating a gas turbine plant having a compressor and a turbine, where a limit value of a guide blade adjustment for the compressor of the gas turbine is identified depending on at least one drive shaft speed of the gas turbine plant. For the at least one drive shaft speed, a maximum allowable turbine entry temperature corresponding to the limit value of the guide vane adjustment for the compressor or a maximum allowable temperature for the turbine of the gas turbine, which is dependent on the turbine entry temperature, is identified. The gas turbine is operated in consideration of the identified maximum allowable turbine entry temperature or the identified maximum allowable temperature.

A method of managing over-temperature excursions in an electronic control unit of a control system having failed-fixed capability and an operationally independent temperature monitoring and power enable function. The method includes receiving a temperature signal indicative of a temperature associated with an electronic control unit, determining if the temperature associated with the electronic control unit exceeds a first selected threshold, determining if the temperature associated with the electronic control unit exceeds a second selected threshold, and ascertaining if an engine associated with the control system is operational. The method also includes that if the engine is not operational and the temperature exceeds the first selected threshold, then disabling an actuator associated with the control system. In addition, the method also includes that if the temperature associated with the electronic control unit exceeds the second selected threshold, then disabling an actuator associated with the control system.

A method for non-destructively testing the heating of a determined zone of a part made of a polymer material, the method comprising the following steps: a) taking at least one colorimetric measurement on said determined zone to be tested and obtaining the value a.sub.p of the parameter a of the CIELAB colorimetric space; b) taking at least one colorimetric measurement on said reference zone of said part and obtaining the value a.sub.p/ref of the parameter a of the CIELAB colorimetric space; c) calculating a.sub.p=a.sub.pa.sub.p/ref; and d) establishing a risk of heating said determined zone to be tested if a.sub.p is higher than a threshold value A1.

An integrally bladed rotor (IBR) for a gas turbine engine and method is provided. The IBR is configured for use in blade off testing and includes a hub, a plurality of rotor blades, a central passage, and first and second lateral cavities. The hub has forward and aft ends and a circumferentially extending exterior surface. The central passage is disposed in the hub radially below a test rotor blade, extending along a path between an inlet at or forward of the test blade leading edge and an outlet at or aft of the test blade trailing edge. The first and second lateral cavities are disposed in the hub, extending generally parallel to the central passage path, on opposite circumferential sides. The first lateral cavity is disposed a distance (MSD1) from the central passage and the second lateral cavity is disposed a distance (MSD2) from the central passage.

In an aircraft, a fuel return valve (FRV) controls a flow of fuel, used to cool an oil feeding a propulsion engine and an oil of an integrated drive generator (IDG). A first sensor supplies measurements of the oil temperature at an output port of the IDG and a second sensor supplies measurements of oil temperature of the propulsion engine. An FRV operation monitoring system: determines, for each flight of the aircraft, an oil temperature maximum at an output port of the IDG and/or a maximum oil temperature of the propulsion engine; assesses a trend of one and/or the other of the oil temperature maxima over several flights; and generates an alarm when the trend of one and/or the other of the oil temperature maxima shows that a predetermined threshold has been exceeded.

The present invention relates to a fuel metering unit for an aircraft engine, comprising: a metering member configured to receive a position control signal and to meter the feed of fuel to the engine depending on said position control; a cutting member configured to cut the feed of fuel to the engine; and characterized in that the fuel metering unit also has a computer for protecting and cutting the engine, said protecting and cutting computer being configured todetect an overspeeding state of the engine speed andin response to the detection of an overspeeding state, to transmit a cutting control signal to a cutting control member contained in the cutting member.

An aeroderivative gas turbine provided with a casing, a compressor including a rotor mounted on a generator shaft supported for rotation in the casing, a high pressure turbine arranged in the casing and with a rotor mounted on the generator shaft for co-rotation with the compressor rotor, a combustor, a power turbine arranged in the casing and including a rotor mounted on a turbine shaft to drive a load, wherein a thermal insulation coating is present to reduce heat dispersion through the casing.

A method of mitigating thermal rotor bow in a rotor assembly of a turbine engine may include performing a plurality of motoring cycles. The plurality of motoring cycles may include receiving feedback on a temperature within a turbine engine in a post-shutdown state, actuating a starter motor when the temperature is greater than a predetermined threshold, operating the starter motor for a motoring time to exhaust some residual heat from the turbine engine, and shutting down the starter motor after the motoring time.

A vacuum pump and a control device are capable of accurately determining timing of rotor blade replacement by creating an index which allows a degree of fatigue of a rotor blade to be determined quantitatively and easily. A motor current value output from a motor drive control portion is input to a time count processing portion, and time in which a current value of a rotating body remains in a range of a stage is totalized for each stage of the current value in the time count processing portion. A rotor blade temperature value output from a rotor blade temperature measurement portion is also input to the time count processing portion. A one-minute average value of the rotor blade temperature value acquired by sampling is calculated. For each stage of the rotor blade temperature value, time in which the average value remains in a range of the stage is totalized.