Gas turbine engine

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F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/18 (2006.01) F01D 5/08 (2006.01) F01D 5/18 (2006.01) F01D 9/02 (2006.01) F01D 9/04 (2006.01) F01D 9/06 (2006.01) F02C 3/10 (2006.01) F02C 3/36 (2006.01) F04D 27/02 (2006.01)

Patent

CA 2345293

A gas turbine engine includes a compressor driven by a compression turbine, a combustor (116) receiving a part (A) of the compressed air, a compression turbine rotor disc (118), and a power turbine rotor disc (114). A minor part of the compressor air is fed to the combuster (116) through ports (123). The fuel is provided through port (117) and the exhaust gases (D) flow through the power turbine and then through the compression turbine. A major part (B) of the compressor air is bled from the compressor and directly bypassed successively through a zone (122 and 124), to a zone (128) of the power turbine rotor disc (114). The air (B) is fed for driving the power turbine rotor disc (114) into passages (126) of the power turbine blades (115), thereby cooling them, and is consequently ejected and mixed into the main exhaust gas stream (D).

Une turbomachine comprend une partie d'écoulement pour aube de turbine située entre un bord d'entrée d'aube et un bord de sortie, et un compresseur qui fournit un écoulement de fluide comportant une partie substantielle de la sortie du fluide du compresseur le long de la surface externe de la partie d'écoulement d'aube, ceci produisant une couche limite d'isolation thermique pour les aubes de turbine au-dessus de laquelle s'écoule le fluide provenant de la chambre de combustion.e fluide chauffé formé dans la chambre de combustion s'écoule sans se refroidir directement sur les aubes de turbine, ceci réduisant les pertes associées au refroidissement.

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