Honeywell International Inc.

Other

John Meier

Mark C Morris

Yogendra Y Sheoran

Nick A Nolcheff

Bernard Vollerin

Cristian E Anghel

Donald G Godfrey

Harry Lester Kington

Ardeshir Riahi

Daniel Cregg Crites

Charles S Lo

Mike S Koerner

Shakeel Nasir

Jeff Howe

Shezan Kanjiyani

John Schugardt

Henri Baumgartner

Daniel Aukland

James Laffan

Alan D Hemmingson

Andre Jacquemet

Yogendra Yogi Sheoran

A propulsion and electric power generation system includes a gas turbine propulsion engine, an electrical generator, an aircraft power distribution system, a plurality of auxiliary fans, and a controller. The gas turbine propulsion engine includes at least a low-pressure turbine coupled to a fan via a low-pressure spool, and the low-pressure turbine is configured to generate mechanical power. The electrical generator is directly connected to the low-pressure spool and generates a total amount of electrical power (Pe). The aircraft power distribution system receives a first fraction (Pa) of the total amount of electrical power. The auxiliary fans receive a second fraction (Pf) of the total amount of electrical power. The controller is configured to control a ratio of Pf to Pa (Pf/Pa) such that the ratio spans a range from less than 0.6 to at least 0.9.

Distributed propulsion and electric power generation system

A turbine engine incorporating a fine particle separation means includes a radial compressor that rotates about a longitudinal axis, a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal axis, from the radial compressor, and a flow path positioned downstream and radially outward, with respect to the longitudinal axis, from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc the redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the outer annular wall at a position downstream axially along the flow path from the arc.

Turbine engine designs for improved fine particle separation efficiency

A cooling arrangement is provided for a gas turbine engine with a turbine section. The cooling arrangement includes a first conduit to receive cooling air that includes particles; a separator system coupled to the first conduit to receive the cooling air and configured to remove at least a portion of the particles to result in relatively clean cooling air and scavenge air including the portion of the particles; and a second conduit coupled to the separator system and configured to direct the relatively clean cooling air to the turbine section.

Engine systems and methods for removing particles from turbine air

A heat exchange system includes a first flow passage and a second flow passage. The heat exchange system is configured to transfer heat between a first fluid flowing through the first flow passage and a second fluid flowing through the second flow passage. The first flow passage includes an inlet header, a plurality of tubes, and an outlet header. The inlet header includes a plurality of header-tube transition portions configured to allow the first fluid to flow from the inlet header and into the tubes, the plurality of header-tube transition portions each including a smoothly curved inlet portion and a tapered tube connection portion.

Tubular heat exchange systems

Formation of nitrogen oxides and/or soot is obviated by mixing recycled combustion gas with incoming comburant supplied to a burner via a distribution opening and controlling the mass flow rate of combustion gas being recycled with respect to the mass flow rate necessary for the gaseous comburant, the mixture being passed to the burner as a turbulent flow in which the ratio between the kinetic momentum flux of the mixture and the product of the radius of the said distribution opening times the axial movement quantity flux of the mixture has a value at least sufficient so that the said turbulent flow produces a recirculation of the said mixture within the combustion chamber in the form of a toroidal vortex. This is achieved by apparatus comprising a mixing enclosure having two inlets each provided with means for regulating the size of its aperture, and an outlet, inlets communicating respectively with the atmosphere and with a duct for combustion gases, the outlet being connected to the inlet of a ventilator whose outlet communicates with gas mixture supply means arranged coaxially to a fuel injection nozzle in order to impart a turbulent motion to the gas mixture emitted from the supply means.

Process and apparatus for controlled recycling of combustion gases

A fluid fuel boiler having a combustion chamber having an opening for introducing a combustion supporting gaseous fluid. A burner introduces a liquid fuel into the combustion chamber mixed with the gaseous fluid for combustion thereof. Water-heating flow paths are disposed circumferentially and axially of the combustion chamber. Axial hot gas flow paths deliver hot gases from a downstream portion of the combustion chamber to a plurality of nozzles for diverting some of the hot gases along axially spaced paths in a direction circumferentially of the combustion chamber. These latter hot gas flow paths are immersed in the flow paths of the water to improve heat transfer.

Boiler using combustible fluid

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Phoenix, AZ, United States of America

John Meier