A gas turbine engine is provided that includes a compressor section, a combustor section, a
diffuser case module, and a manifold. The diffuser case module includes a multiple of struts …

A gas turbine engine includes a buffer system that communicates a buffer cooling air to at
least one bearing structure and at least one shaft of the gas turbine engine. The buffer …

BACKGROUND Turbine engines are used as the primary power source for many types of
aircraft. The engines are also auxiliary power Sources that drive air compressors, hydraulic …

US8840375B2 - Component lock for a gas turbine engine - Google Patents US8840375B2 -
Component lock for a gas turbine engine - Google Patents Component lock for a gas turbine …

BACKGROUND The present disclosure relates to a thermal management system used in a
gas turbine engine, in particular in a com pressor section of the engine. Gas turbine engines …

US10018116B2 - Gas turbine engine buffer system providing zoned ventilation - Google
Patents US10018116B2 - Gas turbine engine buffer system providing zoned ventilation …

A rotor disk assembly for a gas turbine engine includes a rotor disk with a circumferentially
intermittent slot structure that extends radially outward relative to an axis of rotation. A heat …

A gas turbine engine is provided that includes a compressor section, a combustor section
with a multiple of pre-swirlers, a diffuser case module, and a manifold. The diffuser case …

(57) ABSTRACT A tube-type vortex reducer for the conduction of cooling air in a compressor
(1) of a gas turbine, having radial secondary air tubes (2) arranged in a disk interspace (5) …

A tube-type vortex reducer conducts cooling air in a compressor (1) of a gas turbine. Radial
secondary air tubes (2) are arranged in a disk interspace (5) and attached to a compressor …