GAS TURBINE ENGINE FUEL SCHEDULING

Abstract

A method of controlling fuel flow for combustion in a gas turbine engine comprising a low pressure spool, a high pressure spool and a fuel metering valve is disclosed. The method comprises scheduling the fuel metering valve in dependence upon the speed of the high pressure spool.

Claims

1. A method of controlling fuel flow for combustion in a gas turbine engine comprising a low pressure spool, a high pressure spool and a fuel metering valve, the method comprising scheduling the fuel metering valve in dependence upon the speed of the high pressure spool.

2. The method according to claim 1 further comprising scheduling the fuel metering valve to an over-fuelling position with respect to a fuel flow necessary for ignition of the engine prior to an attempted ignition during an engine in-flight windmill start procedure.

3. The method according to claim 2 where the scheduling of the fuel metering valve to an over-fuelling position is employed following a failed ignition attempt during the in-flight engine windmill start procedure.

4. The method according to claim 2 where the position of the fuel metering valve is scheduled such that the degree of over-fuelling corresponding thereto is increased over time.

5. The method according to claim 1 where the scheduling in dependence upon the speed of the high pressure spool is employed during engine acceleration.

6. The method according to claim 1 where the scheduling in dependence upon the speed of the high pressure spool is employed during engine acceleration from ignition.

7. The method according to claim 1 where the scheduling in dependence upon the speed of the high pressure spool is employed during engine acceleration from ignition occurring during an in-flight engine windmill start procedure.

8. The method according to claim 1 where the scheduling of the fuel metering valve in dependence upon the speed of the high pressure spool is more specifically in dependence upon the rate of change of the high pressure spool speed.

9. The method in accordance with claim 1 where scheduling of the fuel metering valve in dependence upon the rate of change of the high pressure spool speed is more specifically in dependence upon a lagged rate of change of the high pressure spool speed.

10. The method according to claim 9 where the fuel metering valve is scheduled to move from a more open position to a more closed position, whereby the extent and/or rate of its closing is dependent on the lagged rate of change of the high pressure spool speed.

11. The method according to claim 9 where scheduling the fuel metering valve such that there is a decreased or zero rate of closing where the lagged rate of change of the high pressure spool speed is below a threshold and an increased rate of closing when it is above the threshold.

12. A gas turbine engine comprising a low pressure spool, a high pressure spool, a fuel metering valve and a fuel flow controller, the controller being arranged in use to schedule the fuel metering valve in dependence upon the speed of the high pressure spool.

13. A gas turbine engine fuel flow controller arranged for use in a gas turbine engine having a low pressure spool, a high pressure spool and a fuel metering valve, the controller being arranged in use to schedule the fuel metering valve in dependence upon the speed of the high pressure spool.

Description

[0021] Embodiments of the invention will now be described by way of example only, with reference to the Figures, in which:

[0022] FIG. 1 is a sectional side view of a gas turbine engine;

[0023] FIG. 2 is a schematic view of a gas turbine engine fuel system;

[0024] FIG. 3 is flow diagram showing an engine in-flight windmill start procedure in accordance with an embodiment of the invention;

[0025] FIG. 4 is an exemplary fuel metering valve ramp opening schedule in accordance with an embodiment of the invention;

[0026] FIG. 5 is an exemplary fuel metering pull-off schedule in accordance with an embodiment of the invention.

[0027] With reference to FIG. 1, a gas turbine engine is generally indicated at 10, having a principal and rotational axis 11. The engine 10 comprises, in axial flow series, an air intake 12, a propulsive fan 13, an intermediate pressure compressor 14, a high-pressure compressor 15, combustion equipment 16, a high-pressure turbine 17, an intermediate pressure turbine 18, a low-pressure turbine 19 and an exhaust nozzles 20. A nacelle 21 generally surrounds the engine 10 and defines both the intake 12 and the exhaust nozzles 20.

[0028] The gas turbine engine 10 works in the conventional manner so that air entering the intake 12 is accelerated by the fan 13 to produce two air flows: a first air flow into the intermediate pressure compressor 14 and a second air flow which passes through a bypass duct 22 to provide propulsive thrust. The intermediate pressure compressor 14 compresses the air flow directed into it before delivering that air to the high pressure compressor 15 where further compression takes place.

[0029] The compressed air exhausted from the high-pressure compressor 15 is directed into the combustion equipment 16 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 17, 18, 19 before being exhausted through the nozzles 20 to provide additional propulsive thrust. The high 17, intermediate 18 and low 19 pressure turbines drive respectively the high pressure compressor 15, intermediate pressure compressor 14 and fan 13, each by suitable interconnecting shaft. The high pressure compressor 15, turbine 17 and interconnecting shaft form a high pressure spool, the intermediate pressure compressor 14, turbine 18 and interconnecting shaft form an intermediate pressure spool and the fan 13, low pressure turbine 19 and interconnecting shaft form a low pressure spool.

[0030] Referring now to FIG. 2, parts of a fuel system for the engine 10, generally shown at 30, are discussed. The fuel system 30 comprises a fuel tank 32, a fuel pump 34, a fuel metering valve 36, a fuel flow controller (in this case an engine electronic controller (EEC) 38 of a full authority digital engine control (FADEC)) and combustor fuel spray nozzles 40. The fuel tank 32, fuel pump 34, fuel metering valve 36 and nozzles 40 are connected in series by fuel conduits 42. A fuel return loop 43 is also provided to spill excess fuel back to the fuel tank 32. Additional fueldraulic conduit loops (not shown) branch off from the fuel conduits 42 upstream of the fuel metering valve 36 for delivery of fuel for use in additional engine 10 components. The fuel pump 34 is connected to and in use is driven by the intermediate pressure spool (although in alternative embodiments the fuel pump is connected to and in use is driven by the high pressure spool). The connection between the fuel pump 34 and intermediate pressure spool is via an ancillary gearbox (not shown). In use of the fuel system 30, the fuel pump 34, driven by the intermediate pressure spool, delivers fuel from the fuel tank 32 to the fueldraulic conduit loops as well as to the nozzles 40 via the fuel metering valve 36. The EEC 38 controls the fuel metering valve 36 position (and so fuel delivery to the nozzles 40) in accordance with a thrust demand (selected for example via a cockpit power lever) and one or more fuel metering schedules. Fuel metering schedules are used to trim fuel metering, particularly where the engine is operating under certain conditions and/or in certain regimes.

[0031] Referring now to FIG. 3, an engine in-flight windmill start procedure suitable for an engine as previously discussed with respect to FIGS. 1 and 2 is explained. Under windmill conditions the engine 10 is not running. Nonetheless on-rushing air passing through the engine 10 turns the low, intermediate and high pressure spools. As a consequence of this windmill turning of the intermediate pressure spool, the fuel pump 34 is operated and can deliver fuel to the nozzles 40 under the control of the fuel metering valve 36 as well as to the fueldraulic conduit loops. As will be appreciated however the fuel deliverable by the pump 34 is relatively low as a consequence of the relatively slow windmill speed of the intermediate pressure spool. Furthermore as ambient air pressure increases (associated with lower altitude operation) and/or engine 10 airspeed drops, the windmill speed of the intermediate pressure spool will decrease, reducing further the fuel deliverable by the fuel pump 34 to the nozzles 40.

[0032] With sufficient altitude and/or airspeed, sufficient fuel may be deliverable to the nozzles 40 for ignition and initial acceleration of the engine 10 without additional fuel delivery assistance. Thus as an initial step 50 of the engine in-flight windmill start procedure, the EEC 38 initiates an engine ignition attempt. The EEC 38 then monitors the engine to detect whether the ignition attempt has been successful and the engine is running. If within ten seconds of the ignition attempt the EEC 38 confirms successful ignition (step 52), normal engine acceleration is scheduled up to an idle speed before the engine in-flight windmill start procedure is ended (step 54) and normal engine running is resumed including standard fuel metering. If, on the other hand, the EEC 38 fails to confirm successful ignition within 10 seconds of the ignition attempt (step 56) a fuel metering valve ramp opening schedule is initiated (step 58).

[0033] An exemplary fuel metering valve ramp opening schedule employed here is shown in FIG. 4. The schedule demands a continuous opening of the fuel metering valve 36 over time. The opening of the valve gives rise to an ever increasing over-fuelling fuel metering valve 36 position with respect to a fuel flow necessary for ignition of the engine 10. Because relatively slow operation of the fuel pump 34 is the principle limiting factor in the fuel deliverable to the nozzles 40, the ever greater opening of the fuel metering valve 36 is unlikely to give rise to a corresponding and proportional increase in fuel delivered to the nozzles 40. Nonetheless the ever greater opening of the fuel metering valve 36 tends to reduce the pressure in the fuel system 30 and consequently correspondingly reduce fuel losses to the fueldraulic conduit loops. This in turn increases the proportion of the fuel pumped by the fuel pump 34 that is delivered to the nozzles 40. As the fuel metering ramp opening schedule is invoked, successive engine ignition attempts are initiated at intervals until successful ignition is confirmed by the EEC 38 (step 60). It may therefore be that anywhere from one to several additional engine ignition attempts are necessary.

[0034] The steady ramping of the opening of the fuel metering valve 36 and periodic ignition attempts may mean that the extent of the over-fuelling position is only as substantially great as is necessary in order to provide a sufficient increase in fuel for successful engine 10 ignition. This may be preferable to a rapid and complete opening of the fuel metering valve 36 followed by an engine ignition attempt, as this may unnecessarily increase the degree of over-fuelling subsequent to ignition.

[0035] The shape of the fuel metering valve ramp opening schedule may have a fixed predetermined shape or may be variable. In the event that the fuel metering valve ramp opening schedule is variable, its shape and particularly its gradient may be determined in accordance with the particular operating conditions of the engine 10. It may be for example that where the engine 10 has a slower airspeed and/or lower altitude, a fuel metering valve ramp opening schedule is calculated by the EEC 38 that requires a more rapid over-fuelling position increase in recognition of the greater likely extent of any shortfall in fuel necessary for ignition.

[0036] Once the EEC 38 has confirmed successful engine 10 ignition a fuel metering pull-off schedule is invoked (step 62) in place of the fuel metering valve ramp opening schedule. An exemplary fuel metering pull-off schedule employed here is shown in FIG. 5. The fuel metering pull-off schedule determines the extent of the closing of the fuel metering valve 36 throughout the remainder of the engine in-flight windmill start procedure via EEC 38 control of the fuel metering valve 36.

[0037] The fuel metering pull-off schedule varies the position of the fuel metering valve 36 in dependence upon a lagged rate of change of the high pressure spool speed. The lagged rate of change of the high pressure spool speed is calculated from measured high pressure spool speed, which is then lagged with an appropriate time constant, before finally being differentiated. The lag is a convenient way to remove noise on the input signal and therefore provides some damping to avoid large oscillatory behaviour.

[0038] The fuel metering pull-off schedule generally reduces fuel delivered as the lagged rate of change of the high pressure spool speed increases. Nonetheless where the lagged rate of change of the high pressure spool speed indicates a relatively slow acceleration of the engine 10 the fuel delivery reduction in accordance with the schedule is lower than where it indicates a relatively rapid acceleration. The action of the fuel metering pull-off schedule tends to counteract an over-fuelling condition otherwise tending to result from the over-fuelling position of the fuel metering valve 36 brought about by step 58. Such over-fuelling might otherwise give rise to rapid acceleration of the engine 10, potentially causing a high pressure compressor 15 stall. By linking the fuel metering valve 36 position during initial acceleration to the rate of change of the high pressure spool speed, high pressure compressor stall may be avoided whilst allowing the engine 10 to accelerate following ignition. Furthermore the relatively restrained closing of the fuel metering valve 36 dictated by the fuel metering pull-off schedule where the engine 10 is accelerating relatively slowly (e.g. immediately after ignition) may allow fuel delivered to reach more quickly a nominal delivery expected for the engine windmill rate had the engine 10 been running normally at that rate.

[0039] The use of the lagged rate of change of the high pressure spool speed rather than simply the rate of change of the high pressure spool speed has the advantage that the impact of signal noise is reduced before differentiation of the signal is undertaken. The differentiation tends to amplify any oscillatory behaviour, so the pre-lagging of the signal is particularly advantageous.

[0040] The end of the engine in-flight windmill start procedure (step 64) occurs when the engine has accelerated to an idle speed. Thereafter scheduling in dependence upon the lagged rate of change of the high pressure spool speed is ceased (i.e. a delta associated with the fuel metering pull-off scheduling is removed) and standard scheduling is performed.

[0041] It will be understood that the invention is not limited to the embodiments above-described and various modifications and improvements can be made without departing from the concepts described herein. Except where mutually exclusive, any of the features may be employed separately or in combination with any other features and the disclosure extends to and includes all combinations and sub-combinations of one or more features described herein.