United Technologies Corporation

Nicola Laudadio

John C Szillat

Teresa Chin

Leon Krukoski

Stephen P Doherty, Jr

Merrill L Kratz

A control system for operating a compressor bleed valve in a gas turbine engine to prevent compressor operation in surge region determines engine stability in response to a plurality of sensed engine parameters, and calculates and stores engine parameters to estimate compressor performance relative to a stability limit which is indicative of a surge operation. The control system further maintains a rolling average of the estimate of compressor performance for up to a predetermined number of engine flights. This rolling average of the estimate of compressor performance is indicative of engine usage and associated engine degradation. The control system determines a bias for the bleed valve in response to calculated engine parameters and adjusts the operation of the bleed valve in response to the compressor performance so as not to exceed the stability limit.

Control system for modulating bleed in response to engine usage

A fuel control system for a gas turbine engine having a staged combustor includes apparatus and methods to operate the combustor during pilot operation, staged operation, and transition between the two modes of operation. Various construction details are developed which provide a fuel control having a switch with built in hysteresis for determining the transition points between operating modes. In one embodiment, the combustor is switched from pilot to staged operation at a thrust level greater than the thrust level at which the combustor is switched from staged to pilot operation. During transitions between operating modes, the changes in fuel flows are limited by a plurality of rate limits to prevent combustor fuel spikes and blow-outs from occurring. During engine starts, the fuel lines to the main combustor are pre-filled to provide responsiveness during the transition from pilot to staged operation.

Starting fuel control system for a staged combustor

Fuel control system for a staged combustor

In a twin spool gas turbine engine the electronic engine control modulates the open area of the compressor bleed valves during engine transients as a function of a ratio of the actual rate of change of the compressor speed to a maximum scheduled rate of change such that the bleeds are opened more as the actual rate of change approaches the scheduled maximum rate. This continuous modulation provides smooth thrust transition from one steady state condition to another while maintaining a proper safety margin relative to the engine surge line.

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Rockville, CT, United States of America

Nicola Laudadio