GAS-TURBINE BLADE WITH COOLING LOOPS

FIELD: mechanical engineering; gas turbines. ^ SUBSTANCE: proposed gas turbine blade for gas-turbine engine has feather overlapped in blade head area by cross wall and radially projecting beyond said wall to form bath. Blade contains also first cooling loop arranged in central part of blade with at...

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Bibliographische Detailangaben
Hauptverfasser:	BOTREL' EHRVAN, EHNO PATRIS
Format:	Patent
Sprache:	eng ; rus
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS 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 STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	FIELD: mechanical engineering; gas turbines. ^ SUBSTANCE: proposed gas turbine blade for gas-turbine engine has feather overlapped in blade head area by cross wall and radially projecting beyond said wall to form bath. Blade contains also first cooling loop arranged in central part of blade with at least one outer space adjoining suction face of blade feather, at least one inner space, adjoining blade pressure surface, at least one central space arranged in central part of blade between inner space and outer space. Blade has also second cooling loop independent from first cooling loop. Said second cooling loop has at least one rear space arranged close to trailing edge of blade. Cross wall of blade has at least one outlet hole opening into rear space of second cooling loop and onto head of blade. ^ EFFECT: reduced average temperature of blade, prevention of formation of temperature gradients. ^ 12 cl, 5 dwg