Controlling fuel supply to a combustor of a gas turbine engine

Details Controlling fuel supply to a combustor of a gas turbine engine Controlling fuel supply to a combustor of a gas turbine engine

2007-07-06

2010-12-14

McCall, Eric S (Department: 2855)

Measuring and testing

Turbine engine

Reexamination Certificate

active

07849732

ABSTRACT:
The minimum fuel flow to a combustor of a gas turbine engine is limited in response to the engine inlet temperature T1and x, an exponent dependent on engine configuration and engine entry pressure P1, in order to provide a fuel air ratio (FAR) limit which responds to both factors. This enables the fuel flow to be limited such that the FAR is set to avoid unintentionally extinguishing the combustor flame and the rate of deceleration is maximised, regardless of ambient temperature and engine altitude.

REFERENCES:
patent: 5596871 (1997-01-01), Lenertz
patent: 2 397 395 (2004-07-01), None
patent: A 03-249337 (1991-11-01), None

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