METHOD AND APPARATUS FOR OBSERVING A GAP

Abstract: The assessment of clearance conditions in an operating turbine structure has provide difficult to achieve. The invention provides apparatus which enables the clearance between seal fins on rotating blades and adjacent fixed structure, to be observed during rotation, and comprises refracting prisms (30, 32) on the fixed structure arranged so as to straddle sealing fins (14) on the blades. The stage of blades on their associated disc are moved towards the fixed structure and light which is refracted through the prisms is obscured by the fins. In one embodiment, the ratio of obscured to unobscured light is utilised to generate electrical signals, which are then manipulated so as to indicate the magnitude of the clearance.

Description: METHOD AND APPARATUS FOR OBSERVING A GAP This invention relates to the observing of the magnitude of an axial gap between relatively rotating parts in eg a fluid flow engine. The invention has particular eff cacy when used to observe the running clearance between, say, fixed stators and rotating turbine blades and between blade shroud fins and a casing surrounding them. According to the present invention a method of observing a gap between relatively rotating parts comprises connecting a pair of radiation refracting members to the fixed part so as to protrude towards an opposing face of the rotable part and in refracting alignment with each other, positioning a projection on said opposing face so as to ensure passage thereof between the refracting members during rotation of the rotatable part and during said rotation refracting a beam of radiation through the refractors and using the obscuring of the beam by the projection to generate electrical signals capable of manipulation so as to provide an indication of the magnitude of the gap. The invention further provides apparatus for effecting the method, comprising a "fixed part and a rotatable part arranged for adjacent, coaxial relative rotation, a radiation source also fixed relative to the rotatable part and arranged to direct a beam of radiation radially between the opposing faces of the fixed and rotatable structure and means on the opposing face of the rotatable structure which during operation at least partially obscures the beam of radiation, and signal generating means for receiving unobscured portions thereof, and generating signals which may be manipulated so as to provide an indication of the axial spacing between the fixed and rotatable structure when the latter is rotating. The invention will now be described, by way of example and with reference to the accompanying drawings in which: Fig 1 is a diagrammatic, axial cross sectional view of an array of fixed stators and rotatable turbine blades, incorporating an embodiment of the present invention. Fig 2 is an exploded view of one embodiment of radiation beam refracting means in accordance with the present invention and Figs 3 to 7a inclusive depict various beam obscuring features which enable signals to be extracted when applied to the embodiments of Figs 1 and 2. Fig 8 depicts an alternative embodiment of the present invention. Referring to Fig 1. A turbine 2 includes a casing 4 in which two stages of stator blades 6 and 6a are fixed via their outer ends. A first stage of blades 8 lies immediately downstream of the stator stage 6 and a second stage of blades 8a lies immediately downstream of stator stage 6a. Both stages of blades 8 and 8a are carried in a drum 10 for rotation about an axis 12. The blades 8a have shrouds 12a at their outer ends in known manner. Each shroud 12a has an axially directed fin, 14a extending towards the opposing face of roots 16a at the outer ends of stators 6a. The fins 14a together provide an annular seal against massive egress of fluid from the turbine annulus 18. It is known to provide fins of the kind described herein for the stated purpose. Such arrangements however, have drawbacks, eg the fins can have their sealing efficiency destroyed as a result of excessive rubbing against the opposing face of the stator roots. In the present example therefore, the blades 8 are modified, which modification, in conjunction with a device 20 to be described hereinafter, enables the observation of the changes in the gap between the extremity of the fins 14 and the opposing face of the shroud of the stator 6 and therefore the gap between the fins 14a and the opposing face of the stator 6a, since the stages of blades 8 and 8a are joined via the drum 10. Each blade 8 has a radially spaced pair of fins 14 on the upstream face of a shroud 16. A device 22 which in the present example is a first housing 24 in which a pair of fibre optics 26, 27 are fitted, and a second housing 28 which contains a pair of radially spaced, elongate prisms 30 and 32, is carried in the root 17 of the stator 6. The specific example is more fully described hereinafter, with respect to Fig 2. Referring still to Fig 1. The prisms 30, 32 are arranged with their lengths parallel with the axis of rotation 12, and with their free ends projecting beyond the downstream face of the stator root 17 so as to just straddle the tip of the radially outer fin 14 when the turbine is inoperative. The radially outer prism 30 has its inner, chamfhered end aligned with the fibre optic 27, and the radially inner prism 32 has its inner chamfhered end, aligned with the fibre optic 26. The protruding champhered ends of the prisms 30, 32 are radially aligned with each other. A radiation source 34 which eg can be a light emitting diode, is connected to the fibre optic 27. The radiation is in the form of light. During operation of the turbine, the loads exerted on the blades 8 and 8a force them in a downstream direction, as indicated by the arrow 36. Thus, the gaps between fin tips and stator root surfaces increase and need to be adjusted. This is achieved by applying an axial force to the shaft (not shown) to which the drum 10 is connected, in an upstream direction. Presently, contact between fins .and root surfaces is the only indication of relative positions of the stator roots and fins. Thus, initial wear by friction is generated. The present invention obviates friction in the following manner; on start up of the turbine, a light from source 34 is passed down fibre optic 27, to the chamfered inner end of the prism 30, which refracts the light along its length and then refracts it further from its outer end, onto the outer end of the radially inner prism 32. The light is further refracted by the prism 32, to the fibre optic 26 which in turn guides the light to a black box 36. A transducer (not shown) in the black box 36 converts the light to an electrical signal, which is then passed to sample and hold, dividing and ratioing circuitry within the box 36. The circuitry itself is not inventive and can be devised by a competent electronics engineer. Immediately after start up, the turbine is forced by known means (not shown) in an upstream direction, thus causing the radially outer annular fin 14 on the shroud 16 to penetrate the beam of light which extends from prism 27 to prism 26. The transducer (not shown) senses the reduced exposure and changes its output to the circuitry (not shown). In consequence of this, further signals are generated and passed to a display 38 which will display, preferably in digital form, the magnitude of the gap between the tip of the fins 14 and the opposing face of the stator root 17. As the turbine moves further, so the gap reduces, and the circuitry in the black box 36 changes its output to the display 38, as appropriate. Thus throughout the manoeuvre, the magnitude of the gap is known and when the display indicates the achievement of a pre selected gap size, movement of the turbine can be stayed. Referring to Fig 2. The fibre optics which are gold jacketed, are brazed into respective fibre tubes 40, 42. The tubes 40, 42 in turn, are a sliding fit in respective lens tubes 29, 31 which in turn fit in bores in the housing 24. A pair of sapphire lenses 44, 46 are fixed in the ends of the bores and the tubes 40, 42 are moved therein, until light beams passing through them are collinated by the lenses 44, 46. Grub screws 48 are then screwed into the housing 24, to trap the tubes 40, 42 against further movement. The housing 28 is recessed to accept the end of the housing 24 which contains the lenses 44, 46 and is further recessed so as to accept the prisms 30, 32. Leaf springs 48, 50 and 52, 54 resiliently locate the prisms 30, 32 in their appropriate positions in the housing 28. After the leaf springs and prisms have been fitted in the housing 28, a corer 56 is fitted and held by a screw 58. Referring to Fig 3. This shows the obscuring of the refracted light beam by the radially out fin 14, and the refraction of the non obscured portion 60 through the prism 32. Fig 3a depicts the ratio of obscured beam area, to an non obscured beam area, as achieved by the fin 14 of Fig 3. Fig 4 includes a local notch 62 formed in the fin 14. As is more clearly seen in Fig 4a, the notch 62 is deep enough to ensure that the whole beam passes through it, to the prism 32, each time the notch 62 passes the beam during rotation of the turbine. By this means the obtaining of the ratio of the full beam to obscured beam is enabled, rather than merely relying on a beam of reducing cross sectional area. Fig 5 depicts a slot 64 in the fin 14 and masking 66 applied to the prism 30, so as to form two refracted beams. The beam spacing is such that they both are totally embracable by the slot 64, one at each end thereof. The arrangement provides a clear indication of the direction of axial movement of the turbine. Thus if the turbine starts from the position indicated in Fig 5a with respect to the beams and moves towards the face of the stator root 17, the fin will obscure only the beam 68. If the turbine withdraws, it will only obscure the other beam 70. The arrangement further provides the opportunity to pre-set an optimum position of the turbine, and enable observing of movement of the turbine relative thereto, in either direction with respect to the opposing face of the stator root 17. Fig 6 and 6a depict a notch 72 which has one sloping side 74. In this arrangement, the sloping side 74 starts to obscure the beam at an increasing rate as the turbine moves towards the stator roof 17, and a decreasing rate, as the turbine retreats therefrom. Thus, the arrangement is a mark/space sensor, which also provides an indication of direction of movement. Figs 7 and 7a illustrate the ability of the device, to provide signals by sensing the change in wave length of the light, as the beam becomes more or less obscured. Referring back to Fig 1. The radially inner fin 14 is provided so as to shield the prisms 30, 32 from the hot fluids passing through the turbine. Referring now to Fig 8. An alternative embodiment of the present invention utilises the device 20 for the purpose of observing tip clearance between the tips of fins 76 in the shrouds 78 of turbine blades 80. The device 20 is rotated through 90° and fitted within the turbine casing 82. Only the prisms 30 and 32 are shown, and they straddle the fin 76. Thus, as the blade extends under centrifugal force towards the casing wall, the refracted light beam is obscured. Apart from location and orientation, the embodiment of Fig 8 is exactly the same in content and operation, as that described with respect to Figs 1 to 7a.

Claims: Claims:- 1. A method of observing a gap between relatively rotating parts characterised by connecting a pair of radiation refracting members (30,32) to the fixed part (6) so as to protrude towards an opposing face of the rotatable part (8) and in refracting alignment with each other, positioning a projection (14) on said opposing face so as to ensure passage thereof between the refracting members (30,32) during rotation of the rotatable part (8) and during said rotation, refracting a beam of radiation through the refractors (30,32) to a transducer (36) and using the obscuring of the beam by the projection (14) to generate electrical signals capable of manipulation so as to provide an indication of the magnitude of the gap. 2 A method of observing a gap as claimed in claim 1 characterised by the step of refracting a beam of light through the refractors (30,32) to the transducer (36). 3. A method as claimed in claim 1 or claim 2 characterised by including the step of providing a notch (62) in the projection, said notch (62) allowing the whole cross sectional area of the beam to pass through, so as to intermittently enable comparison of obscured and non obscured radiation. 4. A method of observing a gap as claimed in claim 3 characterised in that said notch (62) is *v' shaped and is orientated such that one side thereof is parallel with the axis of rotation so as to provide a mark/space sensor. 5. A method of observing a gap as claimed in claim 1 or claim 2 and characterised by including the step of providing a slot (64) in the projection and masking that refractor (30) which refracts the beam to the other refractor (32), so that that refractor (32) refracts two beams thereto, the spacing of which is such that both simultaneously may pass through the slot (64). 6. A method of observing a gap as claimed in claim 1 or claim 2 characterised by including the step of utilising changes in wavelength of the beam to generate said signals. 7. A method of observing a gap as claimed in any previous claim characterised in that the gap is defined by a stage of stator vanes (6) and an annular array of sealing fins (14) on an adjacent stage of turbine blades(8). 8. A method of observing a gap as claimed in any of claims 1 to 7 characterised in that the gap is defined by the inner wall of a turbine casing (82) and an array of sealing fins (76) each of which is radially upstanding from the shroud (78) of an associated turbine blade (80) in a stage of turbine blades. 9. Apparatus for measuring a gap between relatively rotating parts, characterised by a pair of refracting prisms (30,32) located in spaced relationships in a housing (28) with common ends protruding therefrom in refracting alignment, their other ends being non aligned so as to enable during operation input to one of a beam to be refracted and output from the other of the refracted beam to a beam receiving source (36). 10. Apparatus as claimed in claim 9 characterised in that the fixed part is a stator blade (6) in a stage of stator blades the housing (28) being supported in a root (17) thereof, and the spacing of the prisms (30,32) is in the radial sense with respect to the axis of rotation of the rotatable part (8). 11. Apparatus as claimed in claim 9 characterised in that the fixed part is a turbine casing (82) the housing (28) being supported thereby, the rotatable part (80) is a stage of turbine blades and the spacing of the prisms (30,32) is in the axial sense, with respect to the axis of rotation of the rotatable turbine blades (80). 12. Apparatus as claimed in any of claims 9 to 11 characterised by including a radiation source (34) and a transducer (36) for receiving a refracted radiation beam and converting it to electrical signals for manipulation into visual signals. 13. Apparatus as claimed in any of claims 9 to 12 wherein the radiation source and the transducer are located in or on the fixed part. 14. Apparatus as claimed in any of claims. 9 to 13 characterised in that the protruding ends of the prisms (30,32) straddle a projecting sealing fin (14) (76) on the rotating part (8) (80). AMENDED CLAIMS [received by the International Bureau on 9 July 1993 (09.07.93); original claims 1-14 replaced by amended claims 1-14 (3 pages)] 1. A method of observing a gap between relatively rotating parts of a turbine characterised by connecting a pair of radiation refracting members (30,32) to a fixed part (6) of the turbine (2) so as to protrude towards an opposing face of the rotatable part (8) of the turbine (2) and in refracting alignment with each other, positioning a projection (14) on said opposing • face so as to ensure passage thereof between the refracting members (30,32) during rotation of the rotatable part (8) and during said rotation, refracting a beam of radiation through the refractors (30,32) to a transducer (36) and using the obscuring of the beam by the projection (14) to generate electrical signals capable of manipulation so as to provide an indication of the magnitude of the gap. 2 A method of observing a gap as claimed in claim 1 including the step of refracting a beam of light through the refractors (30,32) to the transducer (36). 3. A method as claimed in claim 1 or claim 2 characterised by including the step of providing a notch (62) in the projection, said notch (62) allowing the whole cross sectional area of the beam to pass through, so as to intermittently enable comparison of obscured and non obscured radiation. 4. A method of observing a gap as claimed in claim 3 characterised in that said notch (62) is 'v 1 shaped and is orientated such that one side thereof is parallel with the axis of rotation so as to provide a mark/space sensor. 5. A method of observing a gap as claimed in claim 1 or claim 2 and characterised by including the step of providing a slot (64) in the projection and masking that refractor (30) which refracts the beam to the other refractor (32), so that that refractor (32) refracts two beams thereto, the spacing of which is such that both simultaneously may pass through the slot (64). 6. A method of observing a gap as claimed in claim 1 or claim 2 characterised by including the step of utilising changes in wavelength of the beam to generate said signals. 7. A method of observing a gap as claimed in any previous claim characterised in that the gap is defined by a stage of stator vanes (6) of the turbine (2) and an annular array of sealing fins (14) on an adjacent stage of turbine blades (8) of the turbine (2). 8. A method of observing a gap as claimed in any of claims 1 to 6 wherein the gap is defined by the inner wall of the turbine casing (82) and an array of sealing fins (76) each of which is radially upstanding from the shroud (78) of an associated turbine blade (80) in a stage of turbine blades of the turbine (2). 9. Apparatus fixed in a turbine so as to enable measuring a gap between relatively rotating turbine parts, comprising a pair of refracting prisms (30,32) located in spaced relationships in a housing (28) with common ends protruding therefrom in refracting alignment, their other ends being non aligned so as to enable during operation input to one of a beam to be refracted and output from the other of the refracted beam to a beam receiving source (36). 10. Apparatus as claimed in claim 9 characterised in that the fixed part is a stator blade (6) in a stage of stator blades in said turbine (2), the housing (28) being supported in a root (17) thereof, and the spacing of the prisms (30,32) is in the radial sense with respect to the axis of rotation of the rotatable part (8). 11. Apparatus as claimed in claim 9 characterised in that the fixed part is a turbine casing (82) the housing (28) being supported thereby, the rotatable part (80) is a stage of turbine blades of the turbine (2) and the spacing of the prisms (30,32) in the axial sense, with respect to the axis of rotation of the rotatable turbine blades (80). 12. Apparatus as claimed in any of claims 9 to 11 characterised by including a radiation source (34) and a transducer (36) for receiving a refracted radiation beam and converting it to electrical signals for manipulation into visual signals. 13. Apparatus as claimed in any of claims 9 to 12 wherein the radiation source and the transducer are located in or on the fixed part (6) (82). 14. Apparatus as claimed in any of claims 9 to 13 wherein the protruding ends of the prisms (30,32) straddle a projecting sealing fin (14) (76) on the rotating part (8) (80) of the turbine (2).

Inventors: JENKINS MICHAEL PAUL, SWEENEY MICHAEL, JENKINS, MICHAEL, PAUL, SWEENEY, MICHAEL
Applicants: NORTHERN ENG IND, NORTHERN ENGINEERING INDUSTRIES PLC
Application year: 1993
Main classification: F01D21
IPC codes: F01D21, G01B11, G01D5