| 摘要 |
A gas turbine engine is provided with a plurality of compressors and a plurality of turbines. The compressors supply less than half of the oxygen received to the combustor chamber and thus fuel rich combustion occurs in the combustion means. A number of combustion ducts are positioned between adjacent turbines and oxygen is supplied to each of the combustion ducts from the respective compressor via the cooling passages of the respective turbine. Unburned fuel in the exhaust gases of the combustion means is mixed with cooling air in the turbines and is then burnt in the combustion ducts.
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