Raytheon Technologies Corporation

United Technologies Corporation

Taryn Narrow

Frederick M Schwarz

Paul R Hanrahan

Jorn Axel Glahn

Francis Parnin

Gregory E Reinhardt

Matthew E Bintz

Lisa I Brilliant

Christopher M Valva

Daniel S Rogers

Yuan Dong

Steven D Roberts

Jonathan Ortiz

John H Mosley

Andrew J Murphy

Anthony Spagnoletti

Justin W Heiss

Jordan T Wall

Zachary Mott

Daniel J Monahan

Collin P Fitzgerald

Leonard Kolshak

Lucas D Sorensen

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

This disclosure relates to a buffer system for a gas turbine engine. An exemplary gas turbine engine includes, among other features, a buffer manifold in an intershaft region. The buffer manifold is configured to direct a flow of air between a first air seal and a first oil seal, and to direct another flow of air between a second air seal and a second oil seal.

Buffer system for gas turbine engine

A tap is connected to a location upstream of a downstream most location in a compressor to a heat exchanger. Downstream of the heat exchanger is a shut off valve and a cooling compressor. The cooling compressor is connected to a chamber provided with a check valve configured to selectively allow flow directly from a downstream location in the compressor. There is a system for stopping operation of the cooling compressor, and a control for closing the shut off valve. The cooling compressor is configured to compress air to a greater pressure than the higher pressure, such that the check valve is configured to maintain a closed position, but when said cooling compressor is not providing compressed air, the at least one check valve is configured to allow said higher pressure flow into the chamber. A method is also disclosed.

Intercooled cooling air with advanced cooling system

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 bearing assembly for a gas turbine engine includes, among other things, a bearing housing extending along an axis to define a bearing compartment, a lubricant seal assembly adjacent to the bearing housing to bound the bearing compartment, an air seal assembly defining a vent cavity along the bearing housing, wherein a mixing cavity is defined between the lubricant seal assembly and the air seal assembly, and wherein the bearing housing defines an airflow supply passage, an airflow vent passage and a scupper passage having respective fluid ports at different circumferential positions relative to the axis, the fluid port of the airflow vent passage fluidly coupled to the vent cavity, and the fluid ports of the airflow supply and scupper passages fluidly coupled to the mixing cavity. A method of sealing for a gas turbine engine is also disclosed.

Bearing compartment oil auto-ignition mitigation

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Glastonbury, CT, United States of America

Taryn Narrow