Kompressor- und Turbinenmantel

The compressor section of a gas turbine engine contains a insert (24) installed around the compressor blades that includes cells (28) in a honeycomb configuration. Each cell is at a compound angle to the blade tip to energize the tip air flow as the tip passes over the cell as the blade rotates, imp...

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Bibliographic Details
Main Author KHALID, SYED J
Format Patent
LanguageGerman
Published 12.10.2000
Edition7
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
NON-POSITIVE DISPLACEMENT PUMPS
POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS
PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
STEAM ENGINES
WEAPONS
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Summary:The compressor section of a gas turbine engine contains a insert (24) installed around the compressor blades that includes cells (28) in a honeycomb configuration. Each cell is at a compound angle to the blade tip to energize the tip air flow as the tip passes over the cell as the blade rotates, improving the stall margin. Each cell is oriented in the direction of the blade chord and facing the advancing blades. As the blade rotates it sweeps by each cell and high pressure airflow is first captured in the cell from the high pressure side of the blade and released to the low pressure side as the blade passes the cell, creating a energizing jet of high velocity flow in the direction of the airflow across the blade.
Bibliography:Application Number: DE19956015814T