Method of efficiently operating an engine and a generator for increased load

Abstract

Method of operating an engine and electricity generator powered by torque from the engine is provided. The engine has a working-line which is a locus of engine operating points as the engine is throttled. The method includes increasing electrical-load on the generator. Repeatedly performing steps of: (i) detecting the engine working-line position; (ii) determining if the detected working-line position is sufficient for the engine to provide additional torque to power the generator while maintaining engine operation within range of acceptable engine operating conditions relative to the detected working-line position; (iii) when determination at step (ii) is that the engine operating condition is insufficient, modifying engine operational parameters to adjust the working-line position for the engine to provide additional torque while maintaining engine operation within the range of acceptable engine operating conditions; and (iv) increasing electrical-output from the generator by an amount so the engine provides additional torque. Repeating steps until the generator electrical-output matches electrical-load.

Claims

1. A method of operating a gas-turbine engine and an electricity generator powered by torque from the engine, the engine having a working line which is a locus of operating points of a compressor of the engine as the engine is throttled, the method comprising: increasing an electrical load on the generator; and repeatedly performing the steps of: (i) detecting a working line position of the engine; (ii) determining if the detected working line position is sufficient or insufficient to allow the engine to provide additional torque to power the generator while maintaining engine operation within a predetermined range of acceptable engine operating conditions relative to the detected working line position; (iii) when the determination at step (ii) is that the detected working line position is insufficient, modifying operational parameters of the engine to adjust a position of the working line to allow the engine to provide the additional torque while maintaining engine operation within the predetermined range of acceptable engine operating conditions; and (iv) increasing an electrical output from the generator by an amount such that the engine provides the additional torque, wherein the steps (i)-(iv) are repeated until the electrical output of the generator matches the increased electrical load.

2. The method of claim 1, wherein in step (iv) a pulse width modulator controls the electrical output from the generator by modifying a mark-to-space ratio of a control signal of the pulse width modulator.

3. The method of claim 1, wherein the generator is a switched reluctance generator.

4. The method of claim 1, wherein the predetermined range of acceptable engine operating conditions include a condition of a minimum acceptable surge margin of the gas-turbine engine.

5. The method of claim 4, wherein in step (iv) the electrical output from the generator is increased by an amount which is determined by a function of the minimum acceptable surge margin.

6. The method of claim 1, wherein the operational parameters which are modified are adjustment settings of one or more variable stator vanes and/or one or more bleed valves.

7. The method of claim 1, wherein the generator receives the torque from an interconnecting shaft of the gas-turbine engine.

8. The method of claim 1, wherein the steps (i)-(iv) are repeatedly performed by an electronic engine controller.

9. An electronic engine controller, operably connectable to a gas-turbine engine and an electricity generator powered by torque from the engine, the engine having a working line which is a locus of operating points of a compressor of the engine as the engine is throttled, wherein the controller is configured such that, in response to an increase in an electrical load on the generator, the controller repeatedly performs the steps of: (i) detecting a working line position of the engine; (ii) determining if the detected working line position is sufficient or insufficient to allow the engine to provide additional torque to power the generator while maintaining engine operation within a predetermined range of acceptable engine operating conditions relative to the detected working line position; (iii) when the determination at step (ii) is that the detected working line position is insufficient, modifying operational parameters of the engine to adjust a position of the working line to allow the engine to provide additional torque while maintaining engine operation within the predetermined range of acceptable engine operating conditions; and (iv) increasing an electrical output from the generator by an amount such that the engine provides the additional torque, wherein the steps (i)-(iv) are repeated until the electrical output of the generator matches the increased electrical load.

10. An arrangement of the gas turbine engine, the electricity generator powered by the torque from the engine, and the electronic engine controller according to claim 9, the engine having the working line which is the locus of operating points of the compressor of the engine as the engine is throttled, and the engine and the generator being controlled by the electronic engine controller in response to an increase in the electrical load on the generator.

11. A non-transitory computer readable medium storing a computer program comprising code which, when run on a computer, causes the computer to perform a method of operating a gas turbine engine and an electricity generator powered by torque from the engine, the engine having a working line which is a locus of operating points of a compressor of the engine as the engine is throttled, wherein, in response to an increase in an electrical load on the generator, the computer performs the method which comprises: repeatedly performing the steps of: (i) detecting a working line position of the engine; (ii) determining if the detected working line position is sufficient or insufficient to allow the engine to provide additional torque to power the generator while maintaining engine operation within a predetermined range of acceptable engine operating conditions relative to the detected working line position; (iii) when the determination at step (ii) is that the detected working line position is insufficient, modifying operational parameters of the engine to adjust a position of the working line to allow the engine to provide additional torque while maintaining engine operation within the predetermined range of acceptable engine operating conditions; and (iv) increasing an electrical output from the generator by an amount such that the engine provides the additional torque, wherein the steps (i)-(iv) are repeated until the electrical output of the generator matches the increased electrical load.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Embodiments of the invention will now be described by way of example with reference to the accompanying drawings in which:

(2) FIG. 1 shows a longitudinal cross-section through a ducted fan gas turbine engine;

(3) FIG. 2 shows a system schematic for managing an engine and generator;

(4) FIG. 3 shows gate drive signals provided by the PWM to the generator in FIG. 2;

(5) FIG. 4 shows schematically the relation between an EEC and a PWM of the system of FIG. 2;

(6) FIG. 5 shows an electrical circuit diagram for controlling the output from the generator;

(7) FIG. 6 shows a flow-diagram illustrating the control of the generator and engine; and

(8) FIG. 7 shows another system schematic for managing an engine and generator.

DETAILED DESCRIPTION AND FURTHER OPTIONAL FEATURES

(9) With reference to FIG. 1, a ducted fan gas turbine engine incorporating the invention is generally indicated at 10 and has a principal and rotational axis X-X. The engine comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, an intermediate pressure turbine 17, a low-pressure turbine 18 and a core engine exhaust nozzle 19. A nacelle 21 generally surrounds the engine 10 and defines the intake 11, a bypass duct 22 and a bypass exhaust nozzle 23.

(10) During operation, air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate-pressure compressor 13 and a second air flow B which passes through the bypass duct 22 to provide propulsive thrust. The intermediate-pressure compressor 13 compresses the air flow A directed into it before delivering that air to the high-pressure compressor 14 where further compression takes place.

(11) The compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 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 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust. The high, intermediate and low-pressure turbines respectively drive the high and intermediate-pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.

(12) The interconnecting shaft for the intermediate-pressure turbine 17 and compressor 13 is connected to an auxiliary gearbox 24 via a radial drive (not shown). The auxiliary gearbox in turn powers a starter/generator. Therefore as the gas-turbine engine operates it generates a torque which allows the starter/generator to produce electricity for powering aircraft systems. As discussed above, however, there is a risk that, by taking too much torque from the engine, the operating conditions of the intermediate-pressure compressor could deteriorate. For example the surge margin of the compressor could be reduced, resulting in distorted/unpredictable airflow through the compressor. This can lead to power fluctuations or engine stall, either of which is undesirable.

(13) FIG. 2 shows a system schematic for control of the engine and electrical generator. An electronic engine controller (EEC) 201, is operably connected to both the gas turbine engine 204 and the starter/generator 206. The EEC receives as an input 203 the engine's current position on a working line of a compressor map 202, as well as the current electrical output 208, e.g. phase current, of the generator. The electrical output of the generator is provided to aircraft electrical loads 209, such as electrical fuel pumps and cabin environmental controls.

(14) The compressor map 202 is a predetermined operating map which is specific to the variant of gas-turbine engine in question, and is generally a plot of flow against pressure ratio for the intermediate-pressure compressor. The working line indicates a locus of operating points as the engine is throttled. Generally it is preferred that the engine be operated along the working line. The compressor map also indicates a minimum acceptable surge margin, a region of operating conditions of the compressor which is unsuitable for engine operation. The EEC operates to ensure that the engine operation takes place with a surge margin of at least a given size e.g. at an appropriate remove from the surge line.

(15) Increasing the electrical output of the generator 206, without modifying the engine 204 operating parameters, could cause the engine's position on the compressor map 202 to encroach on the surge line, i.e. to operate with an inadequate surge margin. To avoid this, the EEC 201 outputs a control signal 205 to a pulse width modulator (PWM) 207 connected to the generator. The PWM in turn controls the output of the generator, and so ensures that the engine maintains an adequate surge margin. For example, if the generator is a switched reluctance generator, the PWM controls the coupling and de-coupling of the flux in the generator. The gain on the PWM control signal 205 from the EEC can be modified by reference to the current electrical output 208. The current electrical output can either be measured in each of the generated phases within the generator, or at the output of the generator i.e. in series with the electrical load.

(16) FIG. 3 illustrates an example of gate drive signal(s) by which, in response to the PWM control signal 205 from the EEC 201, the PWM controls the generator. More particularly, the generator 206 produces a three-phase electrical output with phases A, B, and C, and therefore three gate drive signals 301-303 are provided by the PWMone for each phase. Each signal has two components: a mark 304 where the signal is high and the generator provides electrical output, and a space 305 where the signal is low and the generator does not provide electrical output. By modifying the time during which the signal is high relative to the time during which the signal is low (i.e. the mark-to-space ratio) the total electrical output of the generator can be modified. The signals may start at a mark-to-space ratio on the order of 10% of a final mark-to-space ratio, i.e. 10% of the mark-to-space ratio which ultimately meets the electrical demand. Another option is for the signal(s) to start at a mark-to-space ratio determined by the current position of the engine on the working line.

(17) As shown schematically in FIG. 4, the PWM control signal 205 from the EEC 201 is effectively a ramp limiter on the PWM which ensures that the PWM does not increase the mark-to-space ratio at a rate that could cause the engine to have too small a surge margin.

(18) FIG. 5 is circuit diagram showing how the three phase electrical output is generated by respective inductors: phase A inductor 501, phase B inductor 502, phase C inductor 503. The currents generated by these inductors are measured by respective ammeters 504, 505, 506, before being applied to the aircraft load 507. A capacitor 508 is included to smooth the current generated by the inductors. Each inductor is situated between a pair of gates 509a, 509b which are driven by the PWM. When a high signal is provided by the PWM, the gates allow the flow of current through the respective ammeter and to the aircraft load. When a low signal is provided by the PWM, the gates do not allow current to flow through them. Respective diodes 510a and 510b are provided providing a return path from the aircraft load through the respective inductors. This allows for power to be provided from the aircraft load to the generator, such that torque is provideable to the engine. For example during engine start-up, a source of power could be provided such that the generator operates as a starter motor.

(19) FIG. 6 shows a flow diagram describing the control of the engine and generator. In a first step 601, an electrical load is applied to the generator. This step can be under the control of the EEC, or may be performed by a system external thereto. The increase in the electrical load stimulates a second step 602, in which the electrical current supplied by the generator is increased at a rate controlled by the PWM (the PWM being controlled in turn by the EEC) as discussed below. The ramp rate is selected such that the electrical output from the generator is initially lower than required by the load in order to avoid any risk that the engine may be pushed into an unacceptable operating condition. After step 602, the EEC, in step 603, reads the generator phase current which is being provided. At this stage, the EEC enters a repeat loop in which it initially determines (step 604) whether there is sufficient surge margin to deliver an additional increment in output torque, e.g. can the engine provide additional electrical output without encroaching on the surge line. More particularly, the determination of the surge margin involves detecting the working line position of the engine, and then determining if the detected position is sufficient or insufficient to allow the engine to provide the additional torque needed to provide the additional electrical output while maintaining an adequate surge margin. If not, in step 605 the EEC orders the modification of certain engine operation parameters. For example, the EEC may modify one or more variable stator vanes and/or bleed valves to thereby provide a larger surge margin and/or increase the available engine torque. These modifications move the working line of the engine relative to the surge line to increase the surge margin.

(20) If there is a sufficient surge margin to deliver the additional torque to the generator, then in step 606 the gate drive PWM signal mark-to-space ratio begins to increase to match the increased electrical demand. The EEC then determines in step 607 whether the current gate drive PWM signal is causing the output of the generator to meet the increased electrical demand. If so, the demand is met as shown in step 608 and the loop stops. If not, the loop returns to step 604 to so as to determine if the surge margin can facilitate a further increase in electrical output.

(21) As a result of this method, the size of the load being applied does not need to be known in advance. The control of the engine and generator is dynamic, i.e. when an electrical load is applied the PWM control of the generator ramps up and the current delivered to the electrical load is monitored and fed into engine control laws in the EEC. This is achieved by closing the loop between the control of the PWM and the detected working line position.

(22) FIG. 7 shows a more specific version of the system of FIG. 2. In the more specific system, the electrical output 208 of the generator 206 is provided to an aircraft load 209 comprising a motor controller 701 (such as a multi-phase PWM inverter) and an electric motor 702 controlled and powered by the motor controller (e.g. under the guidance of the EEC 201). This motor then has further loads, an example of which can be one or more propulsive fans of the aircraft. The system is this suitable for controlling an all-electric aircraft propulsion system, such as the E-Thrust concept developed by Airbus SE and Rolls-Royce plc. That is, the system manages the power drawn from the generator by the electric motor 702 until the gas turbine 204 is providing sufficient output torque to deliver the required electric power.

(23) While the invention has been described in conjunction with the exemplary embodiments described above, many equivalent modifications and variations will be apparent to those skilled in the art when given this disclosure. Accordingly, the exemplary embodiments of the invention set forth above are considered to be illustrative and not limiting. Various changes to the described embodiments may be made without departing from the spirit and scope of the invention.