Honeywell International Inc.

Shailesh Kumar

Mahmoud Mansour

Jyotichandra Jingade

Yogendra Y Sheoran

Shakeel Nasir

David Richard Hanson

William B Schuster

Tirumala Rao Koka

Mohammed Qizar

Swarna Sinha Srinath

Karthik Narayanasamy

Michael Barton

John Gunaraj

A gas turbine engine includes a rotatable component, and an engine casing disposed about the rotatable component. The engine casing includes a casing treatment having a plurality of grooves and a plurality of acoustic chambers. Each of the plurality of grooves is defined in the engine casing with a groove depth, and each of the plurality of acoustic chambers has an acoustic chamber depth based on the groove depth. Two of the plurality of grooves are associated with one of the plurality of acoustic chambers, one of the plurality of grooves is associated with a second one of the plurality of acoustic chambers, and the one of the plurality of acoustic chambers has an acoustic configuration that is different than the second one of the plurality of acoustic chambers.

Acoustic engine casing for gas turbine engine

An impeller associated with a compressor of a gas turbine engine includes a plurality of impeller blades. Each impeller blade of the plurality of impeller blades has a leading edge and a trailing edge opposite the leading edge in a streamwise direction. Each impeller blade of the plurality of impeller blades extends in a spanwise direction from a hub at 0% span to a tip at 100% span, and each impeller blade of the plurality of impeller blades has a plurality of mean camber lines that each extend from the leading edge to the trailing edge at a respective spanwise location. The leading edge includes a partially swept leading edge surface defined between 70% span to 100% span that extends in the streamwise direction between 3% to 15% of a mean camber line at 100% span.

Compressor impeller with partially swept leading edge surface

An inlet particle separator system for a gas turbine engine includes a separator manifold. The separator manifold includes an inlet upstream from an outlet. The inlet is to receive an incoming airflow, and the outlet is to be fluidly coupled to an inlet of the gas turbine engine. The inlet particle separator system includes at least one dry fog nozzle coupled proximate the inlet so as to face at least partially away from the inlet. The dry fog nozzle is external to the separator manifold, and the dry fog nozzle is to direct a spray of dry fog in a direction transverse to the incoming airflow to agglomerate with fine particles in the incoming airflow to form agglomerated particles. The inlet particle separator system includes a scavenging system coupled to the separator manifold downstream from the inlet, and the scavenging system removes the agglomerated particles from the separator manifold.

Systems and methods for dry fog inlet particle separator

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Uttter pradesh, India

Shailesh Kumar