This disclosure provides systems, methods, and storage medium for storing code related to controlling turbine shroud clearance for operational protection. The disclosure includes a multi-stage turbine and a protection system. The multi-stage turbine includes a stage of airfoils with a distal shroud, a casing adjacent the distal shroud and defining a clearance distance between the distal shroud and the casing, and a clearance control mechanism that controllably adjusts the clearance distance based upon receiving a clearance control signal. The protection system has an operational limit value related to a failure mode and provides the clearance control signal to the clearance control mechanism. The protection system receives operational data related to the multi-stage turbine and modifies the clearance control signal based on the operational limit value to increase the clearance distance.

A propulsion system includes at least two propulsors. The at least two propulsors each comprising a fan having a plurality of fan blades. A controller includes memory and one or more processors. The memory stores instructions that when executed by the one or more processors cause the system to perform the following: determine a pairwise phase difference between one propulsor of the at least two propulsors and another propulsor of the at least two propulsors; generate a reference phase angle; determine a target phase shift for each propulsor of the at least two propulsors; and adjust a speed of each propulsor of the at least two propulsors based on the target phase shift until the pairwise phase difference is equal to the reference phase angle.

A system for neural network compensated aero-thermodynamic gas turbine engine parameter/inlet condition synthesis. The system includes an aero-thermodynamic engine model configured to produce a real-time model-based estimate of engine parameters, a machine learning model configured to generate model correction errors indicating the difference between the real-time model-based estimate of engine parameters and sensed values of the engine parameters, and a comparator configured to produce residuals indicating a difference between the real-time model-based estimate of engine parameters and the sensed values of the engine parameters. The system also includes an inlet condition estimator configured to iteratively adjust an estimate of inlet conditions based on the residuals and adaptive control laws configured to produce engine control parameters for control of gas turbine engine actuators based on the inlet conditions.

Turbines and associated equipment are normally cleaned via water or chemical pressure washing via a mist, spray systems. However, these systems fail to reach deep across the gas path to remove fouling materials. Various embodiments herein pertain to apparatus and methods that utilize the water and exiting chemicals to generate a foam. The foam can be introduced at that gas-path entrance of the equipment, where it contacts the stages and internal surfaces. In one embodiment, the method can include: forming a first foam with a liquid cleaning agent and pressurized gas; flowing the first foam over a member or matrix and increasing the size of the cells of the first foam to form a second foam; and flowing the second foam through a structure such as a mesh or one or more apertured plates and decreasing the size of the cells of the second foam to form a third foam.

The present application relates to a fuel supply device for a gas turbine, which can supply a first fuel and a second fuel having a high combustion speed to a combustor of the gas turbine. In the present device, a first fuel supply line and a second fuel supply line are merged at a merging portion and are connected to the combustor via a mixing line. The second fuel supply line is provided with a first shutoff valve serving as a controlled object when the combustion state is switched from a single fuel combustion state to a mixed fuel combustion state, and a flow meter provided upstream of the first shutoff valve. The flow meter can output a detection value of a flow rate of the second fuel in order to calculate a mixing ratio of the first fuel and the second fuel for monitoring an operating state of the gas turbine.

A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (r) along the radial direction, a total volume (V), and a normalized radius (r). The normalized radius (r) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation:
0.1(r).sup.1<r/r<K(r).sup.4/3,
wherein the normalized radius (r) is between 1.25 and 8 and K is equal to 40%, or the normalized radius (r) is between 2.75 and 4.5 and K is equal to 65%.

The gas turbine system has: a gas turbine having a compressor, a combustor, and a turbine; a fuel supply mechanism for supplying fuel to the combustor; a composition detection unit for detecting the composition of the fuel; and a controller for controlling the flow rate of the fuel supplied from the fuel supply mechanism to the combustor, on the basis of a function of the exhaust temperature of exhaust gas passing through the turbine and either air pressure of air expelled from the compressor to the combustor or an expansion ratio of the turbine. The controller calculates the specific heat ratio of the combustion gas from the composition of the fuel detected by the composition detection unit, corrects the function on the basis of the calculated specific heat ratio, and controls the flow rate of the fuel on the basis of the corrected function.

A control system for a gas turbine includes a controller. The controller includes a processor configured to access an operational parameter associated with the gas turbine. The processor is configured to receive a plurality of signals from sensors disposed in a turbine system, wherein the turbine system comprises a compressor system. The processor is further configured to derive a compressor efficiency and a turbine heat rate based on the plurality of signals. The processor is additionally configured to determine if an online water wash, an offline water wash, or a combination thereof, should be executed. If the processor determines that the online water wash, the offline water wash, or the combination thereof, should be executed, then the processor is configured to execute the online water wash, the offline water wash, or the combination thereof.

The present invention discloses a novel modular system and methods of operating an increased air supply to a gas turbine engine such that the upon supplying a source of external air to the system, a bias is added to the exhaust temperature such that a firing temperature with air injection is substantially equivalent to the firing temperature without air injection.

A method of monitoring turbine blade creep in a gas turbine engine is provided. The method includes: receiving stereo images of a turbine blade of a row of turbine blades, the images having been obtained using a stereo borescope located in the engine adjacent the row of turbine blades; identifying same features of the blade in each of the stereo images; mapping each of the identified features by triangulation onto a 3D space to produce a 3D depth map of at least part of the blade; providing a 3D reference model of the blade; and comparing the 3D reference model with the 3D depth map to measure one or more deviations in shape of the blade to determine an amount of creep-induced distortion of the blade.