Apparatus for reducing combustor exit duct cooling

F - Mech Eng,Light,Heat,Weapons – 01 – D

Patent

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F01D 9/04 (2006.01) F01D 9/02 (2006.01)

Patent

CA 2374753

The present invention is directed to gas turbine engines in which distinct components are integrally cast so as to increase resistance to thermal stress and thus decrease the amount of cooling airflow required to maintain the structural integrity of the components. The inner duct wall (34) of a reverse airflow duct is integrally cast with a circumferentially extending shroud (42) surrounding the stator vanes (38) forming the turbine nozzle. The integral casting permits the inner duct wall (34) to withstand greater degrees of thermal stress and thus require less cooling (47).

La présente invention concerne des moteurs de turbine à gaz dans lesquels différents composants sont entièrement coulés, de manière à augmenter la résistance à la contrainte thermique et réduisant ainsi la quantité de circulation d'air de refroidissement nécessaire pour maintenir l'intégrité structurale des composants. La paroi intérieure (34) d'une gaine de circulation d'air inversée est entièrement coulée avec un anneau de renforcement s'étendant circulairement (42) autour des aubes de stator (38) formant le distributeur de turbine. Le moulage intégral permet à la paroi intérieure (34) de la gaine de résister à des degrés plus élevés de contrainte thermique, nécessitant ainsi un refroidissement (47) moindre.

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