US 4,998,949 AGranted

Overspeed limiter for gas turbine aeroengine

AssigneeROLLS-ROYCE plc

InventorHugh F. Cantwell

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Abstract

A fuel control system for a three spool gas turbine aeroengine has a fuel contorl unit incorporating an intermediate pressure spool overspeed limiter. A fuel control signal is produced which drives a fuel metering unit to meter the flow of fuel to the engine in accordance with control and sensor inputs as acted upon by predetermined control laws incorporated in the fuel control unit. The engine has variable inlet guide vanes (VIGV's) in one or more of its compressor stages and a safety problem arises in that if the VIGV's fail at an angle for low engine speed while the engine is accelerating to a high speed, the rotational speed of the intermediate pressure spool can increase very quickly. This can lead to overshooting of maximum acceptable levels of spool speed before known overspeed limiters have time to regain control. The problem is solved by incorporating an overspeed limiter function for the intermediate pressure spool whose speed limit setting is not just an upper limit as previously, but which varies between lower and upper limits as a function of at least one other internal working parameter of the engine such as the speed of the high pressure spool. The arrangement is such that whenever actual spool speed exceeds the variable limit, a signal is generated which is proportional to the difference between actual spool speed and the variable limit and which is used to reduce the fuel flow to the engine.

Claims7

Dependent claims

A fuel control system for a gas turbine aeroengine having at least one spool, the engine having a normal working characteristic defined by the normal working relationship between the rotational speed of the spool and at least one other internal working parameter of the engine, the fuel control system including:

controller means for receiving engine control commands form a flight station and sensor signals from sensors in the engine, the sensor signals representing working parameters of the engine, the controller means incorporating predetermined control laws for acting upon the control commands and sensor signals to produce a fuel control signal;
fuel metering means for receiving the fuel control signal and controlling fuel flow to the engine in accordance therewith;
and
overspeed limiter means comprising means for defining a variable speed limit for the spool as a function of said at least one other internal working parameter, which speed limit varies in correlation with said normal working characteristic up to a predetermined maximum acceptable limit of spool speed in a manner which avoids interference with normal operation of the engine, and means for overriding the effect of the fuel control signal on fuel flow such that fuel flow to the engine is trimmed whenever the spool speed exceeds the variable speed limit, thereby to avoid substantial overshooting of the predetermined maximum acceptable limit of spool speed;
said gas turbine aeroengine having at least a high pressure spool and a relatively lower pressure spool, said normal working characteristic being defined by the normal working relationship between the rotational speed of said lower pressure spool and said at least one other internal working parameter of the engine, said variable speed limit being defined for said lower pressure spool.

2 more elements

Dependencies are inferred from the claim text.