Method for the adaption of the operation of a staged combustion chamber for gas turbines

US7003939B1 · kind B1 · utility

Assignee

• ROLLS-ROYCE DEUTSCHLAND LTD & CO KG · DE

Inventors

• Leif Rackwitz · Rangsdorf, DE
• Klaus Schmidt · Schwieberdingen, DE

Key dates

• Filing date: Aug 21, 2000
• Grant date: Feb 28, 2006
• Expiry date: Aug 21, 2020

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F23N2237/02
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

This invention relates to a fuel injection system for a staged combustion chamber (1) of a gas turbine aero-engine, in which a certain quantity of fuel is permanently supplied to the pilot burner(s) (3) and in which fuel is apportioned to the main burner(s) (4) only at higher engine performance, whereby a staging valve unit (7) which variably splits the total fuel mass flow (WF) to the pilot burners (3) and to the main burners (4) is provided downstream of a control valve unit (6) which controls the entire fuel mass flow, with both valve units being actuated by an engine control unit (8) and with the actuation of the staging valve unit (7) being accomplished on the basis of the desired engine performance, characterized in that the engine performance is described by way of a staging parameter (SP) reflecting the load of the gas turbine combustion chamber (1) and actuating the staging control unit (7) according to a switching line, in that the staging parameter (SP) is derived from a functional relationship, in that a downstream summation point is provided for the computation of the difference between an actual value of the staging point and a value of the nominal staging point, and …