ADVANCED BOOSTER SYSTEM

A compression stage [8] having a plurality of stator vanes [40] and rotor blades [ 14] coaxial with a longitudinal centerline axis [15], each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade...

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Bibliographic Details
Main Authors WOOD, PETER JOHN, DAILEY, LYLE D, FALK, ERIC ANDREW
Format Patent
LanguageEnglish
French
Published 05.04.2016
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 compression stage [8] having a plurality of stator vanes [40] and rotor blades [ 14] coaxial with a longitudinal centerline axis [15], each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.
Bibliography:Application Number: CA20072611336