Patent ID: 6745571
Filing Date: 2004-06-08
Classification: F02C,F05D,F23R

Abstract:
A method of providing a gas turbine engine selectively operable in at least a simple configuration and a heat-recuperated configuration, the method comprising the steps of:providing a generic gas turbine engine assembly having a combustor; determining a first geometry for an airflow path in the gas turbine engine assembly, the airflow path having a branch for externally cooling the combustor and a branch for providing combustion air, the first geometry for use when the gas turbine engine is operated in a first one of said engine configurations; determining a second geometry for the airflow path of the generic gas turbine engine assembly, the second geometry for use when the gas turbine engine is operated in a second one of said engine configurations different from said first configuration, wherein the second geometry affects a distribution of a total air mass flow in the engine between an air mass flow used for combustion and an air mass flow used for said cooling, wherein said distribution results in a flame temperature in a primary combustion zone of the combustor when the gas turbine engine is operated in the second configuration, and wherein said flame temperature is substantially the same as a flame temperature in a primary combustion zone of the combustor when the gas turbine engine is operated in the first configuration with the first geometry and has a modified cooling air flow path; selecting one of said at least first and second geometries for use in said gas turbine engine assembly based on whether the gas turbine engine is to be operated in said first or second engine configurations.