GAS TURBINE ENGINE WITH INTERCOOLED COOLING AIR AND TURBINE DRIVE

A gas turbine engine (100) has a compressor section with a downstream most end (113) and a cooling air tap (114) at a location spaced upstream from the downstream most end (113). The cooling air tap (114) is passed through at least one boost compressor (124) and at least one heat exchanger (122,128)...

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Bibliographic Details
Main Author SNAPE, Nathan
Format Patent
LanguageEnglish
French
German
Published 18.12.2019
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:A gas turbine engine (100) has a compressor section with a downstream most end (113) and a cooling air tap (114) at a location spaced upstream from the downstream most end (113). The cooling air tap (114) is passed through at least one boost compressor (124) and at least one heat exchanger (122,128), and then passed to a turbine section to cool the turbine section. The boost compressor (124) is driven by a driveshaft (127) which is driven by the turbine section. A boost turbine (138) selectively drives the boost compressor (124).
Bibliography:Application Number: EP20190190401