United Technologies Corporation

Raytheon Technologies Corporation

Wyatt S Daentl

Matthew D Teicholz

Stewart B Hatch

William G Tempelman

John R Gendron

Paul H Spiesman

Glenn D Bartkowski

Sean D J Blake

Kerri A Wojcik

Sean Dj Blake

An example gas turbine engine compressor includes a first compressor section. The first compressor section includes a rotating stage that includes rotating blades and a stationary stage upstream thereof that includes stationary guide vanes. The stationary vanes controllably pivot about respective pivot axes for providing flow control into the rotating stage.

Low compressor having variable vanes

A control system for a gas turbine engine includes a processing system operable to control a speed of the gas turbine engine and a memory system. The memory system is operable to store instructions executable by the processing system to determine at least one performance parameter associated with a stall condition of the gas turbine engine and to incrementally adjust an acceleration rate of the gas turbine engine based on detecting a degraded stall line limit according to the at least one performance parameter.

Gas turbine engine with progressive stall recovery

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Stafford, CT, United States of America

Wyatt S Daentl