Patent ID: 8307661
Filing Date: 2012-11-13
Classification: F01D,F02C,F05D,F23R

Abstract:
1. A process for operating a gas turbine engine, the gas turbine engine comprising a compressor to supply compressed air to a combustion chamber of a combustor, a rotor shaft and a turbine to produce power from a hot gas stream produced in the combustor, the process comprising the steps of: forming a primary burn zone in the combustion chamber; forming a second burn zone in the combustion chamber located downstream from the primary burn zone; injecting a fuel and the compressed air into the primary burn zone a from a first rotary cup surface of a rotary cup that extends from the rotor shaft into the combustion chamber; and, injecting a fuel and the compressed air into the secondary burn zone from a second rotary cup surface of the rotary cup.