Abstract: A method of assembling a gas turbine engine is disclosed herein. The method comprises providing a set of standard turbine stages. Each turbine stage included in the set of standard turbine stages includes a single turbine rotor having a plurality of blades configured to rotate about an axis and a subset of standard turbine vane rings associated with the single turbine rotor.

Abstract: A method of assembling a gas turbine engine is disclosed herein. The method comprises providing a set of standard turbine stages. Each turbine stage included in the set of standard turbine stages includes a single turbine rotor having a plurality of blades configured to rotate about an axis and a subset of standard turbine vane rings associated with the single turbine rotor.

Abstract: A method of assembling a gas turbine engine is disclosed herein. The method comprises providing a set of standard axial compressor stages. Each axial compressor stage included in the set of standard axial compressor stages includes a rotor having a plurality of blades configured to rotate about an axis and a stator having a plurality of stator vanes.

Abstract: A method of assembling a gas turbine engine is disclosed herein. The method comprises providing a set of standard axial compressor stages. Each axial compressor stage included in the set of standard axial compressor stages includes a rotor having a plurality of blades configured to rotate about an axis and a stator having a plurality of stator vanes.

Abstract: A sensor simultaneously determines a maximum rub depth and running clearance of a plurality of blade tips in a jet engine. The sensor includes an inductive component (e.g. inductor) and a resistive component comprising resistor portions each indicative of a depth into a layer of abradable material near the blade tips. When the blade tips move in proximity to the inductor, eddy currents in the blades generates a magnetic field that interact with the magnetic field generated by the inductor, which appears as an AC component in the current. When the blade tips abrade the abradable material, the resistor portions are severed and the DC current changes due to a change in resistance at the resistive component. An amplitude of the AC component indicates a running clearance as the blades move in proximity to the inductor. The frequency of the AC component indicates the rotational speed of the blades.

Abstract: A sensor simultaneously determines a maximum rub depth and running clearance of a plurality of blade tips in a jet engine. The sensor includes an inductive component (e.g. inductor) and a resistive component comprising resistor portions each indicative of a depth into a layer of abradable material near the blade tips. When the blade tips move in proximity to the inductor, eddy currents in the blades generates a magnetic field that interact with the magnetic field generated by the inductor, which appears as an AC component in the current. When the blade tips abrade the abradable material, the resistor portions are severed and the DC current changes due to a change in resistance at the resistive component. An amplitude of the AC component indicates a running clearance as the blades move in proximity to the inductor. The frequency of the AC component indicates the rotational speed of the blades.

Abstract: A gas turbine engine system includes a drive shaft and a compressor located in a compressor case. The compressor has a number of rotors. Each rotor includes a number of blades radially extending from a rotor wheel and terminating in a blade tip. The blade tip terminates in close proximity to the case and defines a tip clearance. An air flow control system is coupled to the compressor. The air flow system includes inductive coils and plasma actuators coupled to the case and magnets coupled to the blade. The plasma actuators induce air flows in order to, for example, mitigate air flow leakage around the tip of the blade.

Abstract: A turbofan gas turbine engine according to the present disclosure includes an engine core, a variable pitch fan, and a fan flow bifurcation with a flow path splitter ring that divides a bypass duct from an engine core inlet. The variable pitch fan is driven by the engine core and has movable fan blades that are reconfigurable to provide forward or reverse thrust. The fan flow bifurcation is arranged between the variable pitch fan and the engine core and is configured to interact with air flow when the fan blades are set to forward or reverse thrust.

Abstract: A gas turbine engine system includes a drive shaft and a compressor located in a compressor case. The compressor has a number of rotors. Each rotor includes a number of blades radially extending from a rotor wheel and terminating in a blade tip. The blade tip terminates in close proximity to the case and defines a tip clearance. An air flow control system is coupled to the compressor. The air flow system includes inductive coils and plasma actuators coupled to the case and magnets coupled to the blade. The plasma actuators induce air flows in order to, for example, mitigate air flow leakage around the tip of the blade.

Abstract: A gas turbine engine system includes a compressor drive shaft and a compressor. The compressor includes a number of rotors. Each rotor includes a number of blades radially extending from a rotor wheel. The rotor wheels are concentric with the compressor drive shaft and separated from the compressor drive shaft by a gap. The rotors wheels are electromagnetically coupled to the compressor drive shaft so as to rotate with or about the compressor drive shaft at variable speeds.