Honeywell International Inc.

Timothy Darling

Jason Smoke

Harry Lester Kington

Courtney Murphy

William Weiss

Nick A Nolcheff

Bruce David Reynolds

Mahmoud Mansour

Jeffrey J Aitchison

Ernest Kurschat

Costantinos Vogiatzis

Jeffrey Aitchison

A shroud system for a gas turbine engine. The shroud system includes a support structure defining two stages. One shroud is disposed at one stage and another shroud is disposed at the other stage. A retention and positioning assembly is disposed on the support structure and positions and holds both shrouds relative to the support structure. A load transfer pin is located radially outward from each of the shrouds. A spring is coupled to the support structure and engages both load transfer pins. The spring applies forces on the load transfer pins toward their respective shroud. A retainer is coupled with the support structure and extends over both stages.

Shroud system with two-stage spring and retainer system for gas turbine engine shroud

A system for coupling a shroud to a case associated with a gas turbine engine includes the case having a mounting pad, and the shroud having a surface that faces the case. The system includes a load spreader having a spreader surface in contact with the surface of the shroud and a locator pin coupled to the mounting pad and the load spreader to couple the shroud to the case. The system includes a load spreader retainer coupled to the load spreader. The load spreader retainer is to distribute a force to the load spreader. The system includes a biasing system coupled about the mounting pad that includes a spring arm configured to apply the force to the load spreader retainer to maintain the spreader surface of the load spreader in contact with the surface of the shroud.

Spring biased shroud retention system for gas turbine engine

A gas turbine engine includes a combustor having a combustor air inlet, an axial-centrifugal compressor, a shroud, a secondary flow duct, and a valve. The shroud surrounds at least a portion of the axial-centrifugal compressor and has a surge bleed plenum defined therein that is in fluid communication with, and receives compressed air from, the axial compressor outlet. The secondary airflow duct has a duct inlet that is in fluid communication with the surge bleed plenum, and a duct outlet that is in fluid communication with the combustor air inlet. The valve is mounted on the secondary airflow duct and is movable between a closed position, in which the secondary airflow duct does not provide fluid communication between the surge bleed plenum and the combustor air inlet, and an open position, in which the secondary airflow duct provides fluid communication between the surge bleed plenum and the combustor air inlet.

Gas turbine engine with compressor bleed system for combustor start assist

Gas turbine engine (GTE) compressor sections and compressor intake ducts are provided having Soft Foreign Object debris (SFOD) endwall treatments, which reduce peak damage to GTE components in the event of SFOD ingestion. In embodiments, the GTE compressor section includes a compressor rotor and a compressor intake duct. The compressor intake duct includes an intake flow passage, which extends through compressor intake duct to the compressor rotor. A first duct endwall extends around a centerline of the flow passage to bound a peripheral portion of the intake flow passage. An SFOD endwall treatment includes topological features formed in or otherwise provided on the first duct endwall. The topological features of the SFOD endwall treatment are configured such that SFOD impacting the topological features is directed in a radially inward direction toward the flow passage centerline prior discharge of the SFOD from the intake flow passage and into the compressor rotor.

Gas turbine engine compressor sections and intake ducts including soft foreign object debris endwall treatments

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Phoenix, AZ, United States of America

Timothy Darling