A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.

Late lean injection with adjustable air splits

A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.

Actuation system for a translating variable area fan nozzle

A gas turbine engine includes a buffer system that can communicate buffer supply air to a portion of the gas turbine engine The buffer system can include a first circuit and a second circuit The first circuit selects between a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to render a first buffer supply air having an intermediate pressure The second circuit selects between a third bleed air supply and a fourth bleed air supply to communicate a second buffer supply air

Gas turbine engine buffer system

A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.

Late lean injection system configuration

A gas turbine engine is provided and includes a fuel circuit, including multiple fuel circuit branches, a combustor having a first interior in which a first fuel supplied thereto by any one of the multiple fuel circuit branches is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by any one of the multiple fuel circuit branches, the second fuel including gas receivable by the fuel circuit from an external source, and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors which supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.

Late lean injection with expanded fuel flexibility

A turbofan engine (10) employs a flow control device (41) that changes an effective exit nozzle area (40) associated with a bypass flow path (B) of the turbofan engine. A spool (14) couples a fan (20) to a generator (52). The turbofan emergency power system includes a controller (50) that communicates with the flow control device (41). Upon sensing an emergency condition, the controller manipulates the flow control device to reduce the effective nozzle exit area (40) of the bypass flow path, which chokes the flow through the bypass flow path thereby increasing the rotational speed of the fan. In this manner, the generator is driven at a higher rotational speed than if the flow through the bypass flow path was not choked, which enables a smaller generator to be utilized.

Turbofan engine with variable area fan nozzle and low spool generator for emergency power generation and method for providing emergency power.

An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being an air transfer duct connected from a compressor in the gas turbine engine to the air intake to transfer compressed air thereto.

Combination engines for aircraft

A power generation system for propelling, and generating electrical power in, an aircraft, having a gas turbine engine in an engine compartment in the aircraft with an air inlet in the aircraft that is curved along its extent in leading to an air compressor in the gas turbine engine having a compressor air transfer duct extending therefrom to an internal combustion engine provided as an intermittent combustion engine at an air intake thereof. An inlet duct manifold is positioned against the duct wall of the inlet duct to cover a perforated portion thereof on the air compressor side of a curve therein with the inlet duct manifold having an inlet air transfer duct extending therefrom that is coupled to the intermittent combustion engine air intake.

Aircraft combination engines inlet airflow control system

Temperature-dependent partial discharge characteristics of high temperature materials at DC voltage for hybrid propulsion systems

Development of electric, hybrid and turboelectric propulsion technologies for electrified aircraft propulsion system is essential for improving fuel consumption, reducing emissions and noise pollution, lowering maintenance costs and improving reliability of the air transportation systems. The future needs and key benefits of aircraft electrification has made it a highly persuaded common technology trend across the aerospace industry ranging from very large airplanes to small aircrafts, all alike. For very high power (20MW) propulsion system, with the inadequacies of current and near future state-of-the art of electric energy storage technologies, all electric aircraft solution faces enormous technology gaps that needs to be bridged. Advanced turbo-electric technology offers potential solutions towards successful realization of the benefits of electrification of aircrafts. However, this represent a grand challenge in many fronts to realize electric drivetrain (EDT) designs that would significantly improve fuel burn reduction, design flexibility, and operational improvements in next generation of aircrafts. This work focuses on the underlying technological elements to enable such high power turbo-electric aircraft. A preliminary study is carried out to find that to achieve the key benefits of electrifications, the ETD system efficiency has to be > 93% and the specific power density of the system is required to be > 7.5 kW/kg. Furthermore, it is found that that to achieve such system level performances, the EDT components is required to be ≥ 99% and with specific power densities > 40 kW/kg to achieve the 7.5 kW/kg target. These necessitates orders of magnitude of improvements at all technological fronts and requires radical improvement in design and integration methodologies. Major technologies and design trades for various components and system architectures are presented to provide guidelines and framework to address this grand challenge. Key results are provided to support the design study.

Charles E. Lents

Papers

Turbofan engine with variable area fan nozzle and low spool generator for emergency power generation and method for providing emergency power.

Combination engines for aircraft

Aircraft combination engines inlet airflow control system

Temperature-dependent partial discharge characteristics of high temperature materials at DC voltage for hybrid propulsion systems

Anatomy of a 20 MW Electrified Aircraft: Metrics and Technology Drivers