INTERTURBINE VANE WITH MULTIPLE AIR CHAMBERS

A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear...

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Bibliographic Details
Main Authors DUROCHER, ERIC, GRIVAS, NICOLAS
Format Patent
LanguageEnglish
French
Published 26.09.2017
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
ENGINE PLANTS IN GENERAL
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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Summary:A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil. Une turbine à gaz possède un châssis de turbine intermédiaire placé entre des ensembles de rotor de turbine. Le cadre de turbine intermédiaire comprend des surfaces portantes creuses sétendant radialement à travers une conduite de trajet de gaz annulaire. Les conduites de trajet de gaz comprennent chacune une structure de bord dattaque à paroi double pour définir une chambre avant séparée dune chambre arrière définie dans lespace restant à lintérieur de la surface portante.
Bibliography:Application Number: CA20102715594