Gas turbine engines connected in series

Details Gas turbine engines connected in series Gas turbine engines connected in series

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 6/02 (2006.01) F02C 3/34 (2006.01)

Patent

CA 2316875

A high temperature compression and reheat gas turbine system (10), and method for operating the system, is disclosed. The system includes a high temperature compressor (12), a combustor (14), a high pressure turbine (16), a high temperature compressor (20), a reheat combustor (24), and a low pressure turbine (26). High pressure turbine (16) only partially expands the process gas. High pressure compressor (20), compresses the high pressure turbine exit gas stream (6b) before reheat combustor (24) raises the process gas stream enthalpy h1 to a point approximately equal to the enthalpy of the gas stream entering the high pressure turbine (16).

L'invention concerne un système (10) de turbine à gaz à compression et postcombustion haute température, ainsi qu'un procédé de fonctionnement de ce système. Ce système comprend un compresseur (12) haute température, une chambre de combustion (14), une turbine (16) haute pression, un compresseur (20) haute température, une chambre (24) de postcombustion et une turbine (26) basse pression. La turbine (16) haute pression ne dilate que partiellement le gaz utilisé. Le compresseur (20) haute pression comprime le flux (6b) de gaz de sortie de la turbine haute pression avant que la chambre (24) de postcombustion n'augmente l'enthalpie h1 du flux de gaz utilisé jusqu'à un point environ équivalent à l'enthalpie du flux gazeux entrant la turbine (16) haute pression.

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