SENSOR SYSTEM

Abstract

A sensor system is disclosed comprising a sensor and a mast on which the sensor is mounted. The mast comprises a core body and a shroud, whereby the shroud is provided about the core body and the shroud is rotatable with respect to the core body under the influence, in use, of a fluid flow flowing past the shroud. The shroud is shaped so as, from at least one fluid flow direction, it presents a different flow resistance in dependence upon its rotational orientation. The rotational orientation of the shroud adjusts to reduce the flow resistance produced by the shroud to the fluid flow in response to the commencement of, or a change in the fluid flow direction to, one of the at least one fluid flow directions.

Claims

1. A sensor system comprising a sensor and a mast on which the sensor is mounted, the mast comprising a core body and a shroud, whereby the shroud is provided about the core body and the shroud is rotatable with respect to the core body under the influence, in use, of a fluid flow flowing past the shroud, and where further the shroud is shaped so as, from at least one fluid flow direction, it presents a different flow resistance in dependence upon its rotational orientation, such that the rotational orientation of the shroud adjusts to reduce the flow resistance produced by the shroud to the fluid flow in response to the commencement of, or a change in the fluid flow direction to, one of the at least one fluid flow directions.

2. A sensor system in accordance with claim 1 further comprising a duct in which the sensor is positioned and through which in use the fluid flow is passed.

3. A sensor system in accordance with claim 2 where the largest dimension of the mast extends in a longitudinal direction between proximal and distal ends thereof the mast being adapted to be secured to the duct at or adjacent its proximal end.

4. A sensor system according to claim 3 where the sensor is provided at or adjacent the distal end.

5. A sensor system according to claim 3 where the distal end of the mast is free.

6. A sensor system according to claim 3 where the axis of rotation of the shroud is parallel to the longitudinal direction.

7. A sensor according to claim 1 where the shroud has an aerofoil shape.

8. A sensor according to claim 1 where a chord of the shroud is substantially perpendicular to its axis of rotation.

9. A sensor according to claim 1 where a bearing is provided between the core body and the shroud.

10. A sensor according to claim 1 where the shroud extends for substantially the full length of the mast.

11. A sensor according to claim 1 where the mast comprises a plurality of the shrouds that are independently rotatable.

12. A sensor according to claim 1 where the sensor is mounted on the core body.

13. A gas turbine engine comprising the sensor system according to claim 1.

14. A test rig comprising the sensor system of claim 1.

Description

[0029] Embodiments will now be described by way of example only, with reference to the Figures, in which:

[0030] FIG. 1 is a sectional side view of a gas turbine engine;

[0031] FIG. 2 is a cross-sectional top view of a mast in accordance with embodiments of the invention;

[0032] FIG. 3 is a perspective view showing the mast of FIG. 2;

[0033] FIG. 4 is a cross-sectional view showing a test rig in accordance with an embodiment of the invention;

[0034] FIG. 5 is a cross-sectional view showing a test rig in accordance with an embodiment of the invention;

[0035] FIG. 6 is a perspective view showing an alternative mast of a sensor system in accordance with embodiments of the invention;

[0036] FIG. 7 provides views of a shroud alignment system in accordance with embodiments of the invention.

[0037] 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 nozzle 20. A nacelle 21 generally surrounds the engine 10 and defines both the intake 12 and the exhaust nozzle 20.

[0038] 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.

[0039] 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 nozzle 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.

[0040] Other gas turbine engines to which the present disclosure may be applied may have alternative configurations. By way of example such engines may have an alternative number of interconnecting shafts (e.g. two) and/or an alternative number of compressors and/or turbines. Further the engine may comprise a gearbox provided in the drive train from a turbine to a compressor and/or fan.

[0041] Referring now to FIGS. 2 to 4, sensor system arrangements suitable for use in the gas turbine engine 10 are discussed. Such sensor systems may for instance be employed to measure air flow velocity and turbulence in the bypass duct 22 behind the fan 13.

[0042] Referring first to FIGS. 2 and 3 a mast 30 of a sensor system 32 is shown. The mast 30 is elongate, with its largest dimension extending in a longitudinal direction between proximal 34 and distal 36 ends of the mast 30. In use a sensor, in this case a hot wire anemometer (not shown), is provided at the distal end 36 of the mast 30 attached to a core body 38 of the mast 30. The core body 38 is formed as a cylindrical rod which acts as a skeleton of the mast 30 and extends for its full length. Embedded within the core body 38 are wires 40 forming part of an electrical circuit by which current is passed through the hot wire anemometer.

[0043] Surrounding the core body 38 and extending for substantially the full length of the mast 30 is a shroud 42. The shroud 42 is shaped as a symmetrical aerofoil having a leading edge 44 and a trailing edge 46. The leading edge 44 has a curved arc shape.

[0044] Between the core body 38 and shroud 42 is a bearing 48 arranged to allow free rotation of the shroud 42 about the core body 38. The cylinder axis of the core body 38 and axis of rotation of the shroud 42 are common. Further a chord of the shroud 42 between its leading 44 and trailing 46 edges is perpendicular to its axis of rotation.

[0045] In use the mast 30 is inserted into the bypass duct 22 through an access opening (not shown) in a fan case 50 of the gas turbine engine 10. The mast 30 is inserted so that it extends radially inwards across the bypass duct 22 and immediately downstream of the fan 13. The mast 30 does not span the full radial extent of the bypass duct 22 and so its distal end 36 is free. The mast 30 is secured to the fan case 50 at its proximal end 34 via a suitable fixing (not shown). When the fan 13 is operated a current is passed through the wires 40 and hot wire anemometer (not shown). As air flow forced by the fan 13 passes the hot-wire, the resistance of the wire changes due to the convection heat transfer by the flow. The variations in current flow allow measurement of the flow velocity and of the turbulence (i.e. flow velocity fluctuation).

[0046] As will be appreciated the flow of air generated by the fan is substantially and predominantly perpendicular to the axis of rotation of the shroud 42 and substantially parallel to chords thereof. Thus the air flow tends to flow over the shroud 42 from its leading edge 44 to its trailing edge 46. If at any given time the shroud 42 is misaligned with the air flow direction so as it has an angle of attack with respect thereto, the symmetric aerofoil shape of the shroud 42 means that its resistance to that flow will be increased. Because however the shroud 42 is free to rotate about the core body 38, it will rotate in order to reduce its resistance to the flow direction such that it is substantially aligned therewith. With specific reference to FIG. 2 a first air flow direction is indicated by arrow 52, with the rotational orientation consequently adopted by the shroud 42 shown in solid lines. A second air flow direction is indicated by arrow 54, with the consequent and different rotational orientation adopted by the shroud 42 shown in broken lines. As will be appreciated the second air flow direction 54 might for example prevail after the first air flow direction 52. In view of the shroud 42 presenting a different flow resistance in dependence upon its rotational orientation and its freedom to rotate to reduce its flow resistance, the change to the second air flow direction 52 will elicit the rotation of the shroud 42 so that it is aligned therewith, thereby reducing its resistance to the prevailing air flow direction. Furthermore, because the shroud is aerofoil shaped, flow shedding is reduced by comparison with alternative shroud shapes.

[0047] The combination of the reduction in flow shedding and the reduction in flow resistance produced by the aerofoil shape of the shroud and its alignment with the prevailing air flow direction reduces vibration and buffeting of the mast 30. This in turn may lead to more accurate measurements in terms of flow velocity and turbulence recorded by the hot-wire anemometer.

[0048] Where measurement of the flow velocity and turbulence is desired at an alternative radial position, the mast may be extended or retracted as appropriate.

[0049] Whilst the embodiment of FIGS. 2 and 3 has been described in the context of use in a fully assembled gas turbine engine 10, it will be appreciated that the embodiment might equally be used in the same manner in the context of a rig test for a fan suitable for use in a gas turbine engine. By way of example FIG. 4 shows a rig 55 arranged for testing a gas turbine engine fan 56. The sensor system 32 is provided as part of the rig 55, with the mast 30 positioning the sensor in a duct 57 of the rig 55 at a position immediately downstream of the fan 56. By way of further example FIG. 5 shows a rig 58 arranged for testing a gas turbine engine turbine. Two sensor systems 32 are provided as part of the rig 58, with each mast 30 of each sensor system 32 positioning a sensor immediately downstream of the rotors 59 of respective turbine stages.

[0050] Referring now to FIG. 6 an alternative mast 60 of another sensor system 62 is shown. The difference between the mast 60 and the mast 30 is in the configuration of the shroud. In the mast 60 a plurality of disc like shrouds 64 are provided instead of one single shroud. The shrouds 64 surround a core body 66 of the mast 60 and between them extend for substantially the full length of the mast 60. Each shroud 64 is shaped as a symmetrical aerofoil having a leading edge 44 and a trailing edge 46. The leading edge 44 has a curved arc shape.

[0051] Between the core body 66 and each shroud 64 is a bearing (not shown) arranged to allow free rotation of the shroud 64 about the core body 66. Each shroud 64 is independently rotatable with respect to the other shrouds 64. A cylinder axis of the core body 66 and axis of rotation of each shroud 64 is common. Further a chord of each shroud 64 between a leading 68 and trailing 70 edge thereof is perpendicular to its axis of rotation.

[0052] In use the shrouds 64 function in the same way as the shroud 42, to reduce vibration and buffeting which might otherwise adversely impact on the measurement accuracy produced by the hot wire anemometer. Because however each of the shrouds 64 are independently rotatable, they are better able to align with the air flow direction local to them. As will be appreciated the prevailing air flow may vary somewhat along the length of the mast 60 and the shrouds 64 may therefore produce improved vibration and buffeting reduction by comparison with the embodiment of FIGS. 2 and 3.

[0053] Referring now to FIG. 7 an exemplary shroud alignment system is described in the context of implementation in a sensor system similar to sensor system 32. As will be appreciated however a similar system 72 may also be applied to sensor system 62. The shroud alignment system 72 is pneumatically based and comprises a gas delivery passage 74 passing through a core body 76 of a sensor system 78. An outlet 80 from the fluid delivery passage 74 passes through an exterior wall 82 of the core body 76 and provides fluid communication between the gas delivery passage 74 and a chamber 84 inside of a shroud 86 of the sensor system 78. The outlet 80 is centred around one circumferential location about the core body 76 and has a limited circumferential extent. In use, the sensor system 78 of the shroud 86 (and therefore the centre of its chamber 84) may, through rotation of the shroud 86 about the core body 76, become somewhat misaligned with the centre of the outlet 80. In this case, it is possible to re-align the shroud 86 with respect to the core body 76 by delivering pressurised gas to the chamber via the gas delivery passage 74 and outlet 80. This will bring the shroud 86 into a known orientation relative to the core body 76, which may have been selected to allow removal of the whole sensor system 78 from a duct through an aperture in the duct that is shaped to accommodate the shroud 86 in only one or a narrow range of orientations.

[0054] Where the system 72 is to be applied to a sensor system in the style of that shown in FIG. 6, each shroud may be provided with a chamber, and there may be a series of circumferentially aligned outlets from the gas delivery passage one or more such outlet being provided at a location corresponding to the axial location of a respective chamber. Alternatively one or more extended outlets may be provided having portions respectively corresponding to a plurality of the chamber axial locations.

[0055] 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.