United Technologies Corporation

Raytheon Technologies Corporation

Daniel J Monahan

Jonathan D Little

Matthew E Bintz

Lisa I Brilliant

Yuan Dong

Steven D Roberts

David Maliniak

Kevin J Cummings

Herbert L Walker

Andrew J Murphy

Taryn Narrow

Jordan T Wall

Arun Kumar Jayasingh

Paul S Schweiger

Lucas D Sorensen

Veerachari J Mayachari

Rakesh Sharma N Dumavath

A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.

Rotor blade for a gas turbine engine

A gas turbine engine includes a compressor section and a nosecone assembly. The compressor section includes an inlet guide vane assembly including an inner shroud, an outer shroud, and an inlet guide vane extending from the inner shroud to the outer shroud. The nosecone assembly is attached to the inner shroud.

Gas turbine engine with attached nosecone

An air bleed system for a gas turbine engine includes an annular bleed case with a manifold therein. The annular bleed case has a forward section and an aft section and ligaments connecting the two sections. The forward section, the aft section and the ligaments define bleed ports. The manifold is disposed radially outward of the ligaments and communicates with the series of bleed ports.

Aerodynamic intercompressor bleed ports

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Cromwell, CT, United States of America

Daniel J Monahan