| 摘要 |
The minimum fuel flow to a combustor of a gas turbine engine is limited in response to the engine inlet temperature T1 and 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. |
