A compressor variable angle measurement system for guiding the positioning variable vanes supported on a penny of a compressor of a gas turbine engine. The system comprising a gauge assembly that is connectable to a computing device. the gauge assembly comprises a base plate and a clamp arm. The gauge assembly is configured to removably grip a variable vane between three vane contact portions of the baseplate and the vane contact portion of the clamp arm and on the leading edge vane engaging portion and the trailing edge vane engaging portion of the base plate, the stagger angle of the variable vane with respect to the radial setting pin being determined by the computing device from measurements made by an inertial measurement unit.

An oil system for a gas turbine engine and a method of supplying oil to the system. The oil system includes a main oil tank connected by oil lines with a supplementary oil storage tank, which has an actuator, and that are connected to one oil pump for supplying oil to the gas turbine engine. The supplementary oil storage tank is equal in size or larger than a steady state oil gulp of the system. The method includes supplying oil from a main oil tank through a pipe line using an oil pump, detecting the oil level in the oil system and determining if additional oil is required or requires removing using a sensor and an electronic controller, and transmitting a signal to an actuator to supply or remove oil to and from the pipe lines in the oil system from or into a supplementary oil storage tank.

A measurement system for a gas turbine engine is provided. The measurement system comprises a sensor assembly. The measurement system also includes multiple sensors coupled to the sensor assembly. The sensor assembly is configured to be removably inserted within a space defined by a circumferential track embedded within an inner diameter of a casing of the gas turbine engine without having to disassemble the casing.

A probe includes a probe head, a probe tip extending from the probe head and having a sensor in fluidic communication with a first fluid stream, a pressure channel extending into the probe tip through the sensor face with a pressure sensor that senses pressure in the pressure channel, and a temperature channel extending into the probe tip through the sensor face. The temperature channel including a temperature orifice disposed on the sensor face and at least one exit port distal from the sensor face. The temperature channel is parallel to and fluidly separate from the pressure channel and includes a temperature sensor that senses temperature in the temperature channel. The temperature channel directs fluid flow from the temperature orifice to the at least one exit port, thereby discharging fluid flow into a second fluid stream.

An emissions control system for a gas turbine system includes a reducing agent supply, at least one sensor, at least one valve, and a controller. The reducing agent supply has one or more conduits configured to couple to one or more fluid pathways of the gas turbine system, which are fluidly coupled to a flow path of an exhaust gas from a combustor through a turbine of the gas turbine system. The at least one sensor is configured to obtain a feedback of one or more parameters of the gas turbine system, which are indicative of a visibility of emissions of the exhaust gas. The at least one valve is coupled to the reducing agent supply. The controller is communicatively coupled to the at least one sensor and the at least one valve, such that, in response to the feedback, the controller adjusts the at least one valve to adjust a flow of the reducing agent to reduce the visibility of the emissions of the exhaust gas.

A method of optimizing probe placement in a turbomachine is disclosed which includes determining wavenumber (Wn) of N dominant wavelets generated by upstream and downstream stators and blade row interactions formed around an annulus, establishing a design matrix A utilized in developing flow properties around the annulus having a dimension of m×(2N+1), iteratively modifying probe positions placed around the annulus and determining a condition number of the design matrix A for each set of probe positions until a predetermined threshold is achieved for the condition number representing optimal probe position, wherein the condition number is defined as norm A.Math.norm A+, wherein A+ represents inverse of A for a square matrix and a Moore-Penrose pseudoinverse of A for a rectangular matrix.

Apparatus and associated methods relate to a system for detecting foreign object debris ingested into an aircraft engine. The system detects such foreign object debris by projecting a beam of light over an inlet of the aircraft engine. When foreign object debris is ingested into the aircraft engine, it intercepts the beam of light and scatters a back-scattered portion of the intercepted beam of light. An optical detector is configured to detect the back-scattered portion of the intercepted beam of light. A processor is configured to determine whether foreign object debris is ingested by the aircraft engine based on a comparison of a threshold value with a signal indicative of the back-scattered portion generated by the optical detector.

A gas turbine engine of an aircraft includes an engine control configured to monitor and control operation of the gas turbine engine in real-time and a communication adapter that includes a housing and a plurality of antennas in the housing. The communication adapter is configured to establish communication with the engine control and wireless communication with an offboard system external to the aircraft through at least one of the antennas of the communication adapter. The housing includes a metal chassis with a non-conductive substrate between the metal chassis and the antennas. The antennas are partitioned into two or more portions. A communication interface of the communication adapter is configured to establish wireless communication through the antennas using two or more different wireless communication protocols.

A method of controlling a gas turbine engine includes the steps of: detecting a shaft break event in a shaft connecting a compressor of the gas turbine engine to a turbine of the gas turbine engine; and in response to this detection, activating a shaft break mitigation system which introduces a fluid into a gas flow of the gas turbine engine downstream of the turbine, or increases an amount of a fluid being provided into the gas flow of the gas turbine engine downstream of the turbine, whereby the fluid reduces an effective area of a nozzle for the gas flow so as to reduce the mass flow rate of the gas flow through the turbine.

A gas turbine engine includes, among other things, a fan, a fan drive gear system that is coupled with the fan and a fan drive input shaft, a compressor section that includes a first compressor and a second compressor, and a turbine section. The turbine section includes a first turbine coupled with a first shaft and a second turbine coupled through a second shaft to the second compressor. A bearing supports the fan drive input shaft. The bearing is located proximal to, and radially spaced from, a forward end of the first shaft. The bearing includes a speed sensor target that is rotatable with the forward end and that defines a rotation path. A speed sensor probe is situated proximal to the rotation path and is operable to read the speed sensor target.