PUMP

Abstract

A pump has a brushless electrical motor including a stator assembly and a rotor ring arranged externally of the stator assembly. The pump further has a centrifugal impeller operatively connected to the rotor ring such that the electrical motor rotates the impeller. The impeller is configured to raise the pressure of a fluid which flows through the impeller between an inlet and an outlet thereof. The pump is configured such that a portion of the raised pressure fluid flow is diverted to form a recirculation flow which circulates through and cools the electrical motor before being returned to the impeller for re-pressurisation thereby.

Claims

1. A fuel pumping unit for an aero-engine, the unit having a low pressure pump and a high pressure pump, the low pressure pump supplying fuel at a raised pressure to the high pressure pump for onward supply to a fuel metering unit of the engine, wherein the low pressure pump has: a brushless electrical motor including a stator assembly and a rotor ring arranged externally of the stator assembly; and a centrifugal impeller operatively connected to the rotor ring such that the electrical motor rotates the impeller, the impeller being configured to raise the pressure of a fluid which flows through the impeller between an inlet and an outlet thereof; wherein the low pressure pump is configured such that a portion of the raised pressure fluid flow is diverted to form a recirculation flow which circulates through and cools the electrical motor before being returned to the impeller for re-pressurisation thereby.

2. A fuel pumping unit according to claim 1, wherein the centrifugal impeller is coaxial with the motor.

3. A fuel pumping unit according to claim 1, wherein the electrical motor is fully immersed in the pumped fluid.

4. A fuel pumping unit according to claim 1, wherein the centrifugal impeller has an inducer section which extends from an inlet for the fluid flow towards an outlet for the fluid flow.

5. A fuel pumping unit according to claim 4, wherein the centrifugal impeller further has an exducer section located in flow series between the inducer section and the outlet.

6. A fuel pumping unit according to claim 1, wherein the rotor ring is located within the centrifugal impeller such that the raised pressure fluid flow passes radially outwardly of the rotor ring towards the outlet.

7. An aero-engine having a fuel pumping unit according to claim 1.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Embodiments of the invention will now be described by way of example with reference to the accompanying drawings in which:

[0026] FIG. 1 shows a longitudinal cross-section through a ducted fan gas turbine engine;

[0027] FIG. 2 shows schematically a longitudinal cross-section through an LP pump of a fuel pumping unit;

[0028] FIG. 3 shows schematically the rotor motor within the volume of the impeller in an end view of the pump of FIG. 2 from direction A;

[0029] FIG. 4 shows a recirculation flow super-imposed on the cross-section of FIG. 2;

[0030] FIG. 5 shows schematically a longitudinal cross-section through a variant LP pump;

[0031] FIG. 6 shows schematically an end view of the pump of FIG. 5 from direction B;

[0032] FIG. 7 shows an example flow chart for a start-up test for the LP pump;

[0033] FIG. 8 shows an example flow chart for measurement of supplied power;

[0034] FIG. 9 shows an example flow chart of a continuous multi-phase flow check, where the measured power for a given pump speed is compared against a reference power derived from a stored motor driven pump characteristic; and

[0035] FIG. 10 shows an example flow chart of a threshold-based multi-phase flow check;

DETAILED DESCRIPTION AND FURTHER OPTIONAL FEATURES

[0036] 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.

[0037] 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.

[0038] 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.

[0039] The engine has a fuel pumping unit (not shown in FIG. 1) which receives fuel from one or more local pumps associated with respective aircraft wing fuel tanks, and supplies pressurised fuel to a fuel metering unit of the engine. The metered fuel is then sent to the burners of the combustion equipment 15.

[0040] The pumping unit has an LP and an HP pump. The HP pump can be a positive displacement (e.g. twin pinion gear) pump driven from a shaft on an engine accessory gearbox and having a fixed speed relationship with engine running speed.

[0041] The LP pump, by contrast, is a centrifugal pump, as shown schematically in the longitudinal cross-section of FIG. 2. The LP pump is suitable for pumping a multi-phase fluid and has a centrifugal impeller driven by a brushless electrical motor having an inner stator assembly 30 and an external rotor ring 32. The impeller is coaxial with the motor and has an inducer section 34 located within a housing 36 of the pump. The inducer section expands from an axially-located inlet 38 in the housing towards an annular outlet 40. The stator and rotor are arranged to be substantially located within the inducer section such that further containment of the rotor magnetic elements is unnecessary, and a compact pump can be achieved. The pump may have a volute (not shown) at the annular outlet to collect the raised pressure fluid flow therefrom. FIG. 3 shows schematically an end view of the pump of FIG. 2 from direction A.

[0042] The pumped fuel flow passes radially outwardly of the rotor ring 32 en route to the outlet 40. However, as shown in FIG. 4, a portion of this flow (indicated by dotted, arrowed lines) is allowed to recirculate back to the impeller through the electrical motor, thus cooling the motor. In particular, the recirculation flow can flow through gaps in the motor, such as between coil windings 42 of the stator assembly and/or the gap between the stator assembly and the rotor ring. The recirculation flow can either be returned to the inlet 38 through an interior passage of the inducer section 34, or exit the interior of the inducer section 34 at an axial location between the inlet and the outlet as shown in FIG. 4. The recirculation flow can enable higher power applications than would otherwise be possible though natural convection cooling of the motor.

[0043] As the fuel is at a raised pressure any undissolved air (in the case of multi-phase flow) within the fuel air mix is forced back into solution and therefore the windings of the motor are not exposed to air. This reduces the possibility of electrical breakdown within the windings and avoids a need for full encapsulation of the windings. Moreover, the pump can avoid a need to seal the rotor ring from the impeller. Indeed, the electrical motor can be fully immersed in the pumped fuel.

[0044] The electrical motor allows the pump to be run at speeds independent of engine running speed. Thus to provide a pressure rise to force any undissolved air in the fuel back into solution, the pump can simply be run at a higher speed.

[0045] FIG. 5 shows schematically a longitudinal cross-section through a variant of the LP pump. In this variant, the rotor ring 32 is located axially within an extension 44 from an exducer section 46 of the impeller. Thus only the recirculation flow passes radially outwardly of the rotor ring 32. The major part of the raised pressure flow passes from the inducer section 34 to the exducer section 46 before exiting through the annular outlet 40. However, the same motor cooling principal of recirculating outlet flow back towards the inlet is applicable to this variant. FIG. 6 shows schematically an end view of the pump of FIG. 5 from direction B.

[0046] The LP pump may have a variable frequency motor drive, which typically comprises inverter power electronics and may be used to vary the speed of the impeller. The variable frequency drive measures the current supplied to the motor windings (known as the phase current) to allow the motor to be successfully controlled. In addition, the variable frequency drive measures the phase voltage. This allows a control unit associated with the drive to calculate the power supplied to the motor, For example, the instantaneous voltage and current can be measured, and the resultant calculated instantaneous power can then be integrated across a defined period, such as a number of drive output cycles (typically a minimum of two).

[0047] Conveniently, the voltage and current measurement may be synchronised to the motor pulse width modulation frequency as this defines the fastest rate that the system can adjust the phase voltage, and therefore motor phase current. This synchronisation may also help to reduce processing overheads as computation can be synchronised around a common timing.

[0048] As the fluid mass flow through the pump is proportional to the power consumed, it is possible for the control unit to determine, through the power measurement described above, if the density of the fluid flowing in the pump has changed in a way that is indicative of multi-phase flow. In particular, the control unit can compare the measured electrical power to a reference power, and, when the measured electrical power is less than the reference power by a predetermined amount suitable action can be taken, such as restoring pump performance to its previous pressure rise by controlling the motor drive to increase the speed of the pumping mechanism until the power consumed is comparable to that prior to the multi-phase flow being detected. The reference power can be determined from a stored model of pump performance, or from one or more previous power measurements. Both approaches allow the comparison to be performed by the control unit as cyclic check.

[0049] In this way sufficient inlet pressure to the HP pump can be ensured without needing to oversize the LP pump to handle (generally infrequent) multi-phase flow events. The ability to increase the pump speed in the event of a failure in the wing tank pumps allows the LP pump to be smaller and better optimised for normal operating modes. The ability to detect multi-phase flow can also be used by the control unit to monitor the condition of the aircraft wing tank pumps. Thus the measured power can be used as both a detection and a control parameter.

[0050] FIG. 7 shows an example flow chart for a start-up test for the LP pump, which shows the pump acting as a health monitoring system for wing fuel tank pumps. In this test the pump speed is increased from zero to a defined percentage of full speed, a power measurement is made, and the value compared against a stored motor driven pump characteristic. If the measured pump power is less than the expected (reference) value by the predetermined amount (Y %), then a suspected wing tank pump failure is flagged by the control unit.

[0051] FIG. 8 shows an example flow chart for measurement, by the variable frequency motor drive and the control unit, of the supplied power using parameters available in the drive. In this example, the instantaneous measured power is integrated across plural drive output cycles.

[0052] FIG. 9 shows an example flow chart of a continuous multi-phase flow check, where the measured power for a given pump speed is compared against a reference power derived from a stored motor driven pump characteristic. If the measured power is less than a defined percentage of the characteristic the speed of the motor is increased and a fault counter incremented. A threshold on the fault counter can be used to flag an external fault. A second check is performed in the event of the measured power being greater than the characteristic. This can be used to decrease the motor speed should the presence of multi-phase flow cease due to external factors, such as a drop in altitude increasing the partial pressure in the aircraft wing tanks.

[0053] FIG. 10 shows an example flow chart of a threshold-based multi-phase flow check in which the reference power is a previous power measurement at a time when the pump was operating under the same engine fuel demand and known to be operating without multi-phase flow. An initial check is performed against a defined motor driven pump characteristic in a similar way as the example of FIG. 4. If the check against the characteristic is successful, a value of the required power is stored and used for subsequent threshold detection. A check is included that the demanded speed (i.e. engine fuel demand) has not decreased. If it has decreased, then the initial check is repeated. Again a fault counter, with an optional threshold to flag an external fault, can be included in the same manner as shown as the example of FIG. 9.

[0054] 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. For example, although descried above in relation to a low pressure pump of an aero-engine fuel pumping unit, the pump may have other (e.g. non-aerospace) applications. 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.