Abstract: A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A blade splitter (shroud) on the fan partially spans the fan blade thus separating the core and bypass streams downstream while leaving a gap upstream for communication between the flows. The communication gap expands the operational range of the fan over fans without the communication gap.

Abstract: A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A blade splitter (shroud) on the fan partially spans the fan blade thus separating the core and bypass streams downstream while leaving a gap upstream for communication between the flows. The communication gap expands the operational range of the fan over fans without the communication gap.

Abstract: A system includes a housing for a gas turbine engine, and a fan disposed in the housing to rotate coaxially with a gas turbine included in the housing. The system also includes an inlet guide vane disposed in the housing in axial alignment with the fan and configured to have an open position where a first flow of air is received by the fan through the inlet guide vane, and a closed position where airflow through the inlet guide vane is obstructed. The system further includes a heat exchanger disposed in a supply passage in fluid communication with a second flow of air received by the fan. The second flow of air is received by the fan via the supply passage with the inlet guide vane in the open position or in the closed position.

Abstract: A system includes a housing for a gas turbine engine, and a fan disposed in the housing to rotate coaxially with a gas turbine included in the housing. The system also includes an inlet guide vane disposed in the housing in axial alignment with the fan and configured to have an open position where a first flow of air is received by the fan through the inlet guide vane, and a closed position where airflow through the inlet guide vane is obstructed. The system further includes a heat exchanger disposed in a supply passage in fluid communication with a second flow of air received by the fan. The second flow of air is received by the fan via the supply passage with the inlet guide vane in the open position or in the closed position.

Abstract: A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A blade splitter (shroud) on the fan partially spans the fan blade thus separating the core and bypass streams downstream while leaving a gap upstream for communication between the flows. The communication gap expands the operational range of the fan over fans without the communication gap.

Abstract: A system and method for meeting take off noise requirements in a gas turbine engine with a multi-stage fan, comprising an inlet passage, a core passage, a bypass passage and a mid-stage offtake passage; the core passage comprising a core inlet, high pressure compressor, combustor, high pressure turbine, low pressure turbine and a core exhaust; the bypass passage comprising a primary bypass inlet and a primary bypass exit; the mid-stage offtake passage comprising an offtake inlet and offtake exit; a first stage comprising a first rotor, and a second stage comprising a second rotor; and a variable guide vane located axially between the first rotor and the second rotor; an actuator coupled to and selectively varying the variable guide vane between two or more orientations; a variable offtake exit thrust nozzle; and, wherein a gas stream exiting the inlet passage enters one of the core, bypass or mid-stage off take passages as a function of the two or more orientations.

Abstract: An apparatus for the control of fluid flow in a gas turbine engine comprises a first plurality of inlet guide vanes disposed upstream of a fan, a compressor, a combustor, and a turbine; at least one airflow splitter adapted to split air admitted through the first plurality of inlet guide vanes into a core airflow which flows through the fan, the compressor, the combustor, and the turbine and a bypass airflow which flows through the fan; wherein the first plurality of inlet guide vanes comprise a radially-inward first portion adapted to direct air admitted through the first plurality of inlet guide vanes to the core airflow and a radially-outward second portion adapted to direct air admitted through the first plurality of inlet guide vanes to the bypass airflow, and wherein the first portion comprises a fixed vane and the second portion comprises a variable vane.

Abstract: A gas turbine engine axial compressor vane is disclosed having an aperture capable of flowing a relatively high pressure working fluid to change a direction of a flow vector downstream of the vane. The relatively high pressure working fluid can originate from a compressor discharge. The vane may have any number of apertures.

Abstract: A gas turbine engine axial compressor vane is disclosed having an aperture capable of flowing a relatively high pressure working fluid to change a direction of a flow vector downstream of the vane. The relatively high pressure working fluid can originate from a compressor discharge. The vane may have any number of apertures.

Abstract: The present invention includes a supersonic inlet having a converging portion and a diverging portion operable to diffuse engine airflow from supersonic speeds to subsonic speeds. A physical throat includes a fixed flow area at a fixed location is between the converging and diverging portions of the inlet. A fluidic injector injects pressurized fluid into the inlet to form a variable effective throat within the inlet and improve the off design efficiency of the inlet.

Abstract: The present invention relates to a system and method for managing the operation of a turbocharger and is responsible for controlling the turbocharger to cause a desired air mass flow to be provided to the engine and for protecting the turbocharger from excessive shaft speed and excessive turbine inlet temperature. The protection modes have higher priority than the performance control. First, turbocharger shaft speed is checked against a programmable limit, and the turbocharger is adjusted to bring the speed under control if its speed exceeds this limit. If the speed is not above the limit, the turbine inlet temperature is checked against a second programmable limit. If the turbocharger inlet temperature is above the predetermined limit, the turbocharger is adjusted to bring the inlet temperature under control.