Abstract: A fuel controller for a combustion system in a gas turbine having a combustion system, a fuel supply, a pressure control valve proximate the combustion system and a first pressure sensor proximate the pressure control valve, the fuel controller including: a proportional-integrated (PI) logic unit generating a control command for the pressure control valve and receiving input signals representing a desired fuel pressure at the pressure control valve and an input signal from the first pressure sensor representing an actual fuel pressure at the pressure control valve, and a plurality of control gains stored in electronic memory of the controller, wherein each control gain is applicable to a predefined operating condition of the gas turbine, and wherein the controller determines which set of control gains is to be applied by the PI logic unit based on an actual operating condition of the gas turbine.

Abstract: A fuel controller for a combustion system in a gas turbine having a combustion system, a fuel supply, a pressure control valve proximate the combustion system and a first pressure sensor proximate the pressure control valve, the fuel controller including: a proportional-integrated (PI) logic unit generating a control command for the pressure control valve and receiving input signals representing a desired fuel pressure at the pressure control valve and an input signal from the first pressure sensor representing an actual fuel pressure at the pressure control valve, and a plurality of control gains stored in electronic memory of the controller, wherein each control gain is applicable to a predefined operating condition of the gas turbine, and wherein the controller determines which set of control gains is to be applied by the PI logic unit based on an actual operating condition of the gas turbine.

Abstract: Damages to load supporting structures in an aircraft or spacecraft resulting from an explosive decompression are minimized or avoided by rapidly making available at least one relatively large flow-cross-sectional area. This is accomplished by mounting a decompression panel with a plurality of releasable mounting locks to a frame. The locks are so constructed that the panel along can be blown out in one direction and the panel with the frame and the locks can be blown out in the opposite direction in response to a rapid pressure increase which shears off shearing pins normally holding locking levers in a clamp-down or hold-down position. The frame has support flanges against which the panel and a wall section rest. The locks rest on and are secured to the frame and respond to defined release pressure ratios between the inside and outside in either direction. Each lock has at least one locking or clamp-down lever for the panel and one for a wall section.