Honeywell International Inc.

Mario Scaini

Russell W Johnson

Rodolphe Dudebout

Frank Joseph Zupanc

Eric Blumer

Bijan F Hagh

Daguang Zheng

Mukund Acharya

Terrel Kuhn

Sunil James

Victor Reyes

David H Edmonds

Veeraraghave Raju Hasti

Roger J DeRudder

Audie Mak

Veeraraghava Raju Hasti

Victor M Reyes

A system is provided for inerting a fuel tank of an aircraft. The system includes a first compressor fluidly coupled to the fuel tank for removing an air and fuel vapor mixture from an ullage of the fuel tank. The system further includes a fuel processor fluidly coupled to the first compressor and configured to receive the air and fuel vapor mixture and to generate hydrogen from the air and fuel vapor mixture. The system further includes a fuel cell fluidly coupled to the fuel processor and configured to receive the hydrogen as anode fuel to produce electricity. The system further includes a combustor fluidly coupled to the fuel cell and configured to combust the exhaust product to produce combustion gas, and a first heat exchanger fluidly coupled to the combustor and configured to cool the combustion gas into inerting gas for the fuel tank.

Aircraft systems and methods with integrated tank inerting and power generation

A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.

Reverse-flow annular combustor for reduced emissions

An auxiliary power unit (APU) includes a rotary fuel slinger, and a single-spool, two-stage turbine. The rotary fuel slinger receives a rotational drive force from the turbine, and a supply of fuel from a fuel source. The rotary fuel slinger injects the fuel into a combustor as a continuous 'fuel sheet.' As a result, fuel mixing and atomization inside the combustor is improved, which reduces emissions and pattern factor, which in turn increases turbine life.

Auxiliary power unit having a rotary fuel slinger

Growing community of inventors

Phoenix, AZ, United States of America

Mario Scaini