GAS TURBINE ENGINE CONTROL SYSTEM Russian patent published in 2008 - IPC F02C9/00 

FIELD: engines and pumps.

SUBSTANCE: invention relates to area aviation engine engineering and can be used in electronic-hydro mechanical systems of automatic control (ACS) of gas turbine engines (GTE). The invention consists in that the fuel pressure controller (FPC) is incorporated additionally in the hydro mechanical part of the system, the said controller being made up of a rod with a slider and a adjuster spring arranged inside the two-piston mechanism (TPM), the FPC control cavity communicating via the rod hole with the line feeding fuel to the inlet of fuel distribution mechanism (FDM). Here, note that the TPM inner space communicates via a cut-off slide valve (COS) with the line feeding fuel into the high-pressure pump inlet (HPP) and with the control space of shut-off-drain valve (SODV). Also, the COS control space communicates with selector, the TPM first outer space communicates via a throttling assemble with the SODV control space, while the second TDM outer space communicates with the line feeding fuel into the FDM inlet.

EFFECT: higher reliability fighting capacity.

1 dwg