A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

Systems, assemblies, and methods to enhance the efficiency of operation of a gas turbine engine may include a turbine housing positioned to at least partially enclose the gas turbine engine, and a filtration assembly connected to the turbine housing to supply at least partially filtered intake air to an inlet assembly associated with the gas turbine engine. The filtration assembly may include a pre-cleaner including one or more inertial separators configured to separate a first portion of particles and/or liquid from ambient air supplied to the gas turbine engine, thereby to provide at least partially filtered intake air, and one or more filters positioned downstream of the pre-cleaner to separate a second portion of the particles and/or liquid from the at least partially filtered intake air.

A deflecting device for protecting a jet engine of an aircraft from damage caused by a bird strike. The bird strike deflection device attaches to an opening in the front of a cowling of the jet engine to shield an engine air intake from ingesting a bird that would otherwise damage the engine. A conically shaped screening portion having an open mesh pattern is attached to the cowling in a convex orientation. A perimeter of the screening portion terminates in a rim sized to fit the engine intake opening in the cowling. The rim may be directly attached to the cowling or an attachment flange may connect the rim to the cowling. The deflecting device may be completely removable from, hingedly attached to, or integrated directly into the cowling.

The present invention provides compartment(s) for a turbine engine, comprising a main compartment for receiving the turbine engine and an intake compartment disposed on a side of the main compartment. The intake compartment comprises: an intake compartment body, a gas filter device and a muffler device. The gas filter device and the muffler device are disposed outside the intake port of the intake compartment. The compartment unit is configured to have a first gas path which permits air for combustion in the turbine engine to pass from the external through the gas filter device and the first muffler device in turn into the intake compartment body, and then be delivered through the exhaust port of the intake compartment to the turbine engine in the main compartment.

A method for designing and/or controlling a filter assembly for the air supply to a turbomachine includes: calculating a current and/or an expected concentration of particles in air present at an inlet of at least one filter stage of the filter assembly as a function of a mean size of the particles; calculating a sensitivity spectrum that, depending on the mean size of the particles, indicates an extent to which a predetermined concentration of such particles has a negative effect on performance and/or on service life of the turbomachine; calculating, for at least one filter candidate usable in the filter stage and/or switchable on or off, a concentration of particles to be expected at an outlet of the filter from a concentration and filter properties of the at least one filter candidate; and calculating a quality rating from the concentration and a sensitivity spectrum.

A method for designing and/or controlling a filter assembly for the air supply to a turbomachine includes: calculating a current and/or an expected concentration of particles in air present at an inlet of at least one filter stage of the filter assembly as a function of a mean size of the particles; calculating a sensitivity spectrum that, depending on the mean size of the particles, indicates an extent to which a predetermined concentration of such particles has a negative effect on performance and/or on service life of the turbomachine; calculating, for at least one filter candidate usable in the filter stage and/or switchable on or off, a concentration of particles to be expected at an outlet of the filter from a concentration and filter properties of the at least one filter candidate; and calculating a quality rating from the concentration and a sensitivity spectrum.

A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.

A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

A core duct assembly for a gas turbine engine includes a core duct including an outer and an inner wall, the outer wall having an interior surface; a gas flow path member extending across the gas flow path at least partly between the inner and outer walls, the rotor blade having a radial span extending from a blade platform to a blade tip, wherein an upstream wall axis is defined as an axis tangential to a point on a first portion of the interior surface of the outer wall of the core duct extending downstream from the gas flow path member, the upstream wall axis lying in a longitudinal plane of the gas turbine engine containing the rotational axis of the engine, and wherein the upstream wall axis intersects the rotor blade at a point spaced radially inward from the blade tip of the rotor blade.