Turbine engine cooling

It is known there is ingestion of hot gas flow 35 from an annular flow 36 in gas turbine engines. This flow 35 is prevented from attaching to the disc by coolant flow 32 passing through gaps in lock plates 28, 29 by creation of a barrier layer. In order to regulate and enhance this effect spacer pro...

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Bibliographische Detailangaben
Hauptverfasser:	SCANLON TIMOTHY J, SNOWSILL GUY D, DIXON JEFFREY A, BRUNTON IVAN L
Format:	Patent
Sprache:	eng
Schlagworte:	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 INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 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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Beschreibung
Zusammenfassung:	It is known there is ingestion of hot gas flow 35 from an annular flow 36 in gas turbine engines. This flow 35 is prevented from attaching to the disc by coolant flow 32 passing through gaps in lock plates 28, 29 by creation of a barrier layer. In order to regulate and enhance this effect spacer protrusions 31 are provided between ends of lock plates 28, 29 . In such circumstances the gap 30 is controlled and therefore the rate of leakage flow 32 regulated for best cooling effect. This cooling effect and cooling flow 32 can be further enhanced by providing chutes 39 for presentation of the coolant flow 32.