Honeywell International Inc.

David G Walhood

Ian L Critchley

Jurgen C Schumacher

Cristopher Frost

Gregory O Woodcock

Stony Kujala

Robert B Sumegi

Barry J Kingery

Hiroshi Kawamura

Mark A Kuper

Mark Lai

Albert K Wong

Stony W Kujala

An engine assembly includes a combustor having a combustion chamber in which an air and fuel mixture is combusted to produce combustion gases. The engine assembly further includes a transition scroll coupled to the combustor for receiving the combustion gases. The transition scroll includes an interior surface, an exterior surface, and effusion cooling holes for providing cooling air to the interior surface. The engine assembly further includes a turbine coupled to the transition scroll for receiving and extracting energy from the combustion gases.

Transition scrolls for use in turbine engine assemblies

A gas turbine engine assembly includes a combustor configured to combust an air-fuel mixture to produce combustion gases in a first direction; a transition liner coupled to the combustor and adapted to receive the combustion gases from the combustor and to redirect the combustion gases in a second direction; and a turbine coupled to the transition liner and adapted to receive the combustion gases from the transition liner. The transition liner has a plurality of effusion holes that include a first group that extend at least partially in a tangential direction.

Systems and methods for cooling gas turbine engine transition liners

A variable penetration dilution jet array for a single can and scroll assembly includes a plurality of differentially sized dilution openings around the circumference of the combustor can. The alternating smaller and larger openings provide for circumferential and radial mixing uniformity with the smaller openings giving shallow penetration and the larger openings enabling deep core penetration. The larger openings provide dilution air to the hot gas flow core without the need for an increase in combustor pressure drop. The smaller openings provide a film cooling flow to the downstream scroll, reducing dedicated scroll cooling requirements.

Temperature variance reduction using variable penetration dilution jets

A gas turbine engine integrates the functions of an auxiliary power unit (APU) with one or more functions of an ECS, and that is capable of operating in both an unfired mode and a fired mode. The gas turbine engine includes a combustor system that is configured to allow the gas turbine to quickly transition from the unfired mode to the fired mode, by bypassing a portion of the air flowing to the combustor system around the combustor.

Dual mode power unit having a combustor bypass system

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Scottsdale, AZ, United States of America

David G Walhood