Abblassystem für ein Bläsertriebwerk mit vereinfachter Regelung

The double flow turbojet comprises an intermediate structural casing (9) between the primary (2) and secondary (3) ducts which is located axially between low pressure (5) and high pressure (7) compressors. Discharge means allowing diversion of a part of the gas flow delivered by the low pressure com...

Full description

Saved in:
Bibliographic Details
Main Authors BROSSIER, PASCAL NOEL, BRAULT, MICHEL GILBERT
Format Patent
LanguageGerman
Published 06.03.2008
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
JET-PROPULSION PLANTS
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
NON-POSITIVE DISPLACEMENT PUMPS
POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS
PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
STEAM ENGINES
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:The double flow turbojet comprises an intermediate structural casing (9) between the primary (2) and secondary (3) ducts which is located axially between low pressure (5) and high pressure (7) compressors. Discharge means allowing diversion of a part of the gas flow delivered by the low pressure compressor to the secondary duct comprise an annular cavity (16) forming a manifold located upstream of the intermediate casing in the external wall of the primary duct. Several axial conduits (18) in the intermediate casing and connected to the manifold are in permanent communication with the primary duct. Several tubes (20), located around the high pressure compressor, fitted with flow regulation valves (22) put the axial conduits in communication with the secondary duct.
Bibliography:Application Number: DE20026020737T