Automated daily process for global ionospheric total electron content maps and satellite ocean altimeter ionospheric calibration based on Global Positioning System data

A method for operating a gas turbine engine includes channeling compressed air from the gas turbine engine to a noise suppression system, and selectively operating the noise suppression system such that air discharged from the noise suppression system generates a plurality of flow control mechanisms in the gas turbine exhaust flowpath

Methods and apparatus for operating gas turbine engines

A structural turbine exhaust case of a gas turbine engine, comprises inner and outer case portions; a bearing housing connected to the inner case portion for supporting a main spool of the gas turbine engine; and a plurality of airfoils extending between the inner and outer case portions, airfoils structurally connecting the inner case portion to the outer case portion.

Turbine exhaust case and method of making

A tailcone mixer for an engine, as well as a jet engine assembly, an airplane, and methods of repairing, improving operation, and retrofitting an engine. The tailcone mixer may include a main body and a plurality of lobes. The main body may include a wider forwar end and a more narrow rear end and a mid-portion extending between the forward end and the rear end. The forward end is structured and arranged for attachment to an inner duct case. The rear end is closed, and the mid-portion has a first sloping contour from the forward end to the rear end. The lobes are rigidly secured to the mid-portion. Each of the lobes has an inner section and an outer section that extend from a forward section, with the forward section being adjacent the mid-portion of the main body.

Jet nozzle mixer

A thermal management system includes at least two of a multiple of heat exchangers arranged in an at least partial-series relationship.

Shared flow thermal management system

A noise reduction kit for modifying a two (2) spool axial flow turbofan engine with multi-stage compressors and fan driven by multi-stage reaction turbines, and a thrust of at least about 18,000 lbs. at sea level. There is a fan at the upstream end of the core engine for generating axial fan air flow through bypass ducts terminating at a common nozzle, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches. A target thrust reverser includes opposing doors rotatable into position to block and divert the flow of exhaust gas for generating reverse thrust. Mixing means for radially diverting fan air and permitting radially outward expansion of exhaust gas is provided coaxially downstream to the core engine. An acoustically dampened light bulb-shaped nose cone is provided for coaxial attachment to an upstream end of the core engine. The axial flow front fan is axially separated from the inlet guide vane is extended relatively forwardly. A bleed air valve, selectively operational to bleed air from the core engine when the valve is open, is ducted for directing bleed air to the vicinity of the common nozzle.

Turbofan engine with reduced noise

In a noise reduction kit for modifying a two spool axial flow turbofan engine (20) with multi-stage compressors and fan driven by multi-stage reaction turbines, and a thrust of at least about 18,000 lbs. at sea level, there is a fan (21,22) at the upstream end (66) of the core engine (20) for generating axial fan air flow through bypass ducts (26a,26b,26c;27a,27b,27c) terminating at a common nozzle (28), the common nozzle (28) having a mixing plane area (29) for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches. A target thrust reverser (41) includes opposing doors (43,44) rotatable into position to block and divert the flow of exhaust gas for generating reverse thrust. A material layer (300) is located in a spacing between a tip of blades (302) for at least some of the fans (21) and a duct for the fans, thereby to reduce a normal clearance between the tip of blades (302) for a fan (21) and the duct (305). Mixing means for radially diverting fan air and permitting radially outward expansion of exhaust gas is provided coaxially downstream to the core engine (20). An acoustically dampened light bulb-shaped nose cone (51) is provided for coaxial attachment to an upstream end of the core engine (20). The axial flow front fan is axially separated from the inlet guide vane which is extended relatively forwardle. A bleed air valve (202), selectively operational to bleed air from the core engine (20) when the valve (202) is open, is ducted for directing bleed air to the vicinity of the common nozzle (28).

Kenneth R. Mcguire

Papers

Turbofan engine with reduced noise

Noise reduction kit for turbofan engine

Ensemble amortisseur de bruit pour turbosoufflante