NOZZLE SINGLET FOR MANUFACTURING NOZZLE SEGMENT USED IN TURBINE ENGINE, AND GAS TURBINE ENGINE

PROBLEM TO BE SOLVED: To provide a nozzle singlet 32 for a turbine engine 10. SOLUTION: The nozzle singlet 32 includes an inner band 40, an outer band 38, at least one wing-shaped part 36 extending therebetween, at least one first row 100 of cooling holes 60 oriented at an angle with respect to at l...

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Bibliographische Detailangaben
Hauptverfasser:	GUENTERT JOSEPH M, HEYWARD JOHN P, HEFFRON TODD S
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 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To provide a nozzle singlet 32 for a turbine engine 10. SOLUTION: The nozzle singlet 32 includes an inner band 40, an outer band 38, at least one wing-shaped part 36 extending therebetween, at least one first row 100 of cooling holes 60 oriented at an angle with respect to at least one second row 110 of cooling holes 120, wherein the orientation of the at least one first row and the at least one second row forms a cooling hole pattern that accommodates to a change in an angle of the wing-shaped part without reorienting it. COPYRIGHT: (C)2008,JPO&INPIT