United Technologies Corporation

Raytheon Technologies Corporation

Zachary Mott

Ross Wilson

David Richard Griffin

Michael G McCaffrey

Paul R Hanrahan

Christopher Corcoran

Jonathan Ortiz

Theodore W Hall

John H Mosley

Jason D Himes

Dwayne K Mecklenburg

David R Griffin

Taryn Narrow

Michael Lastrina

Jonathan Oritz

A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine comprising a plurality of turbine blades. The gas turbine engine includes a tap for tapping air that is compressed by the compressor, to be passed through a heat exchanger to cool the air, the cooled air to be passed to the plurality of turbine blades. A sensor is located downstream of a leading edge of the combustor, and is configured to measure a characteristic of the cooled air. A controller is configured to compare the measured characteristic to a threshold and control an operating condition of the gas turbine engine based on the comparison.

Gas turbine engine control based on characteristic of cooled air

A turbine section of a gas turbine engine includes a seal that extends between a vane platform and a Blade Outer Air Seal.

Inner stage turbine seal for gas turbine engine

A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.

Disk lug cooling flow trenches

A retaining ring for a turbomachine disk and coverplate assembly includes a ring body defining a coverplate interface side and an opposed disk lip interface side. A flow feature is defined by the ring body on the coverplate interface side to allow airflow between the turbomachine disk coverplate and the ring body such that a pocket defined between the coverplate and the turbomachine disk is in fluid communication with a conditioning flow pathway through the retaining ring.

Retaining rings for turbomachine disk and coverplate assemblies

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Glastonbury, CT, United States of America

Zachary Mott