Gas turbine engine with increased fuel efficiency and method for accomplishing the same

A method of improving engine efficiency in an engine comprising a compressor, a first combustion chamber, a second combustion chamber, and a turbine at least a portion of which is downstream of the first and second combustion chambers, the method comprising the steps of:

• passing gas through the compressor to generate compressed gas;
• passing a first portion of the compressed gas to a first combustion chamber;
• passing a second portion of the compressed gas to a second combustion chamber;
• adding fuel to the first portion of compressed gas in the first combustion chamber to form a first mixture;
• igniting the first mixture to generate a first portion of exhaust gases;
• adding fuel to the second portion of compressed gas in the second combustion chamber to form a second mixture;
• igniting the second mixture to generate a second portion of exhaust gases;
• and
• directing the first portion of exhaust gases to an inner annular area of the turbine.

An engine comprising:

• a casing having an inlet and an outlet downstream of the inlet;
• a compressor rotatably disposed within the casing generating compressed gas;
• a primary combustion chamber disposed within the casing downstream of the compressor receiving a primary portion of the compressed gas and generating primary exhaust gases;
• a secondary combustion chamber disposed within the casing downstream of the compressor receiving a secondary portion of the compressed gas and generating secondary exhaust gases;
• a first turbine downstream from the first combustion chamber receiving only the primary exhaust gases;
• and
• a second turbine downstream of the first and second combustion chambers, the second turbine having a plurality of turbine blades, wherein the primary exhaust gases are directed along a first path toward an inner annular area of the turbine blades and the secondary exhaust gases are directed along a second path different from the first path toward an outer annular area of the turbine blades.

A method of improving engine efficiency in an engine comprising the steps of:

• passing gas through a compressor to generate compressed gas;
• dividing the compressed gas into a first portion and a second portion;
• passing the first portion of the compressed gas to a first combustion chamber;
• passing a second portion of the compressed gas to a second combustion chamber;
• adding fuel to the first portion of compressed gas in the first combustion chamber to form a first mixture;
• igniting the first mixture to generate first combustion chamber exhaust gases;
• adding fuel to the second portion of compressed gas in the second combustion chamber to form a second mixture;
• igniting the second mixture to generate second combustion chamber exhaust gases, said second combustion chamber exhaust gases being exhausted downstream of the first combustion chamber;
• directing the first combustion chamber exhaust gases along a first path toward an inner annular area of a turbine;
• and
• directing the second combustion chamber exhaust gases along a second path different from the first path toward an outer annular area of the turbine.

An engine comprising:

• a casing having an inlet and an outlet downstream of the inlet;
• a first compressor rotatably disposed within the casing generating compressed gas;
• a second compressor upstream of the first compressor;
• a first turbine downstream of the first compressor and coupled to the first compressor;
• a second turbine downstream of the first turbine and coupled to the second compressor, wherein the second turbine comprises a plurality of turbine blades;
• a primary combustion chamber disposed within the casing downstream of the first compressor receiving a first portion of the compressed gas and generating primary exhaust gases, said primary exhaust gases being guided to the first turbine and to an inner annular area of second turbine blades along a first path;
• and
• a secondary combustion chamber disposed within the casing downstream of the first compressor and receiving a second portion of the compressed gas and generating secondary exhaust gases, wherein the secondary exhaust gases are exhausted downstream of the primary combustion chamber and the first turbine, and wherein the secondary exhaust gases are guided along a second path different from the first path to an outer annular area of the second turbine blades.