WO2006125939A1 - An instrumentation arrangement - Google Patents

An instrumentation arrangement Download PDF

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Publication number
WO2006125939A1
WO2006125939A1 PCT/GB2006/001475 GB2006001475W WO2006125939A1 WO 2006125939 A1 WO2006125939 A1 WO 2006125939A1 GB 2006001475 W GB2006001475 W GB 2006001475W WO 2006125939 A1 WO2006125939 A1 WO 2006125939A1
Authority
WO
WIPO (PCT)
Prior art keywords
arrangement
baseplate
component
vane
engageable
Prior art date
Application number
PCT/GB2006/001475
Other languages
French (fr)
Inventor
Ian Graham Martindale
Robert Daniel Anthony
Original Assignee
Rolls-Royce Plc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls-Royce Plc filed Critical Rolls-Royce Plc
Priority to EP06726865.6A priority Critical patent/EP1883789B1/en
Priority to US11/920,729 priority patent/US8297136B2/en
Publication of WO2006125939A1 publication Critical patent/WO2006125939A1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
    • G01P5/14—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid
    • G01P5/16—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes, e.g. Machmeter
    • G01P5/165—Arrangements or constructions of Pitot tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics

Definitions

  • This invention relates to instrumentation, and particularly to measurement devices intended for use on stationary components of gas turbine engines.
  • the static structure of the gas turbine engine is commonly used to mount these measurement devices, and the airflow or signal is led from the compressor to measurement equipment by means of tubes and wires fixed to the structure .
  • An instrumentation arrangement for a component comprises a baseplate to which is attached at least one measurement device, characterised in that the baseplate comprises attachment features engageable in use with the component, to permit installation and removal without modification of the component .
  • the component may comprise a surface and the baseplate may be shaped to correspond to the surface.
  • the component may comprise a surface and the baseplate may be moulded in use to correspond to the surface.
  • the baseplate may be cured after moulding to ensure it retains its shape.
  • the attachment features may comprise hooks engageable with the component.
  • the attachment features may comprise fasteners engageable in holes in the component.
  • the holes may be manufacturing datum holes.
  • the baseplate may further comprise a tang engageable in use with structure associated with the component.
  • the structure may be a casing or a mounting ring.
  • the tang may provide location of the baseplate in at least a first direction
  • the attachment features may provide location of the baseplate in at least a second, different direction.
  • the first direction is radial and the second direction is axial.
  • the component may be a component of a gas turbine engine.
  • the component may be a vane of a gas turbine engine and the hooks may be engageable with the leading edge of the vane .
  • the arrangement may be at least partially secured to the component in use adhesively, magnetically or by suction.
  • the or each measurement device may be selected from the list consisting of: Pitot tube, thermocouple, miniature camera, laser sensor, densimeter, mass flow detector, particle detector. At least one measurement device may be protected by a shroud.
  • the or each measurement device may be attached to the baseplate by brazing or welding or adhesive bonding or mechanical fasteners.
  • the arrangement may further comprise at least one measurement device leadout tube or wire.
  • the or each leadout tube or wire may be secured to the baseplate.
  • the or each leadout tube or wire may be secured by clipping.
  • Figure 1 shows an instrumentation arrangement according to the invention, together with a vane of a gas turbine engine
  • Figure 2 shows a partial section on the line AA of Figure 1.
  • a fan outlet guide vane (OGV) 10 has a leading edge 12 and a trailing edge 14.
  • the vane 10 has a concave pressure surface 20 and, on its opposite side, a convex suction surface 22 (indicated in Figure 2) .
  • Two manufacturing datum holes 24 have been left in the pressure surface 20 by the vane manufacturing process.
  • a set of vanes 10 is mounted within an annular OGV mounting ring (the position of which is indicated by a dashed line 44) .
  • FIG. 1 also shows an instrumentation arrangement 30 according to the invention.
  • the arrangement 30 comprises a baseplate 32.
  • the baseplate is shaped to correspond to the contour of the pressure surface 20 of the vane 10.
  • the baseplate is extended at one end, to form a tang 33 with an end face 35.
  • a number of shrouded Pitot tubes 34 are welded to the baseplate. In this embodiment, twelve shrouded Pitot tubes 34 are provided. Leadout tubes 36 from the Pitot tubes 34 are clipped to the baseplate 32, and led out to measuring equipment 38 (not shown) .
  • the baseplate 32 has hooks 40 along one edge, which in use are engageable with the leading edge 12 of the vane 10. In this embodiment, twelve hooks 40 are used.
  • the rake 30 is located by the hooks 40 on the pressure surface 20 of the vane 10, approximately in the position indicated by the dashed lines 26. This provides a positive axial location for the baseplate.
  • the end face 35 of the baseplate tang 33 locates against the inner surface of the OGV mounting ring 44. This provides a positive radial location for the baseplate. Because the baseplate 32 is contoured to conform closely to the surface 20 of the vane 10, the combination of these three features (hooks 40, end face 35 and contoured baseplate) provides accurate and repeatable location of the baseplate 32 on the vane 10.
  • Suitable fasteners such as bolts, pass through holes 42 in the baseplate 32 and engage with the datum holes 24 in the vane 10, to secure the rake 30 to the vane 10.
  • Figure 2 shows a section through the line A-A of Figure 1, with the arrangement 30 installed on the vane 10.
  • One of the hooks 40 is visible, and a shrouded Pitot tube 34 can also be seen adjacent the leading edge 12 of the vane 10.
  • the previously described fasteners (not shown) pass through the holes 42 to secure the baseplate 32 to the vane 10.
  • the surface of the vane 10 may be worn or damaged.
  • the contour of the baseplate 32 may not then correspond precisely to the contour of the vane surface 20.
  • the baseplate 32 is partly or wholly made from a mouldable, curable material.
  • the baseplate 32 can be moulded exactly to the contour of the vane surface 20, taking account of any wear or damage. Once cured, the contour of the baseplate 32 will then be maintained throughout the subsequent testing.
  • Such an instrumentation arrangement incorporating a mouldable baseplate, could be arranged to fit to a number of different vanes or to a number of different gas turbine engines. This would advantageously reduce the inventory- needed at service locations in the field, because a small number of rakes could be adapted to serve all purposes.
  • shrouded or unshrouded measuring devices may be installed.
  • suitable devices are Pitot tubes, thermocouples, miniature cameras, laser sensors, densimeters, mass flow detectors and particle detectors, but the skilled reader will appreciate that this list is not exhaustive and that the invention could be applied to any measuring device of a suitable size.
  • a single rake may comprise several measurement devices of different types.
  • the measurement devices may be attached to the baseplate by means other than welding, for example by brazing, by adhesive bonding or by mechanical fasteners.
  • the leadout tubes or wires may be secured to the baseplate by alternative means.
  • the baseplate may be secured to the vane surface by adhesive bonding or by any other suitable means. If the vane is of suitable material the baseplate may be secured magnetically. With the addition of a seal around the outside of the baseplate, it may be secured by suction. Such alternative securing methods may be used instead of, or in addition to, the mechanical fasteners described in the specific description.
  • the invention thus provides an instrumentation arrangement that can be readily attached to and removed from a component of an engine, without the need for any modification of the component.
  • the component is left undamaged after the rake is removed. Because the baseplate is shaped to correspond to the component to which it is mounted in use, the effect on the aerodynamic behaviour of the component is minimised, and the measurements will be more accurate and representative.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Measuring Volume Flow (AREA)

Abstract

An instrumentation arrangement for a component comprises a plurality of measurement devices mounted on a baseplate. The baseplate is shaped to correspond to the surface of the component in use, and has attachment features engageable with features of the component, so that the rake can be easily installed and removed without modification of the component.

Description

AN INSTRUMENTATION ARRANGEMENT
This invention relates to instrumentation, and particularly to measurement devices intended for use on stationary components of gas turbine engines.
It is a requirement when developing gas turbine engines that the airflow conditions at various positions in the gas duct are measured, to assess the performance of the engine's components and to compare it with theoretical calculations. This usually takes the form of air pressure and temperature measurement collected by Pitot tubes, thermocouples or other devices at convenient places in the compressor. The performance of such a measurement device may be improved by shrouding it. This makes the device less sensitive to changes in yaw angle, and thus improves the measurement accuracy. One such device, a shrouded Pitot tube, is sometimes referred to as a Kiel® probe.
The static structure of the gas turbine engine is commonly used to mount these measurement devices, and the airflow or signal is led from the compressor to measurement equipment by means of tubes and wires fixed to the structure .
Conventionally, Pitot tubes, thermocouples or other measurement devices are individually fixed to the structure, for example to a static aerofoil or vane, by drilling holes in the vane and welding in fixing pins to which the devices are welded. The leadouts from the devices are fixed to the vane aerofoil surface by welded-on sheet metal shim clips. This method is expensive and time- consuming, and has the further disadvantage that the drilling and welding irreparably damage the vane.
Because the airflow conditions vary across the duct, it is usual to mount several measurement devices at one position in the engine, radially spaced across the duct. Such an arrangement of measuring devices is commonly referred to as a rake.
As well as measuring the airflow conditions in an engine during its development, it would also be desirable to measure these airflow conditions when a gas turbine engine is being overhauled or repaired. Such measurements could allow damage or wear in the engine to be detected without the need to dismantle the engine. Unfortunately, because the mounting of the measurement devices damages the engine components (as explained above) it is rarely- possible to make such measurements on engines in service, and instead the engine must be stripped or dismantled for its condition to be assessed. This is, of course, very costly in time and money. It is therefore an object of this invention to provide the measurement capability of an instrumented vane, without the time-consuming preparation required in known techniques, and without causing damage to the vane. The resulting savings in time and cost will permit wider use of instrumentation during engine development, so that measurements may be made on more engine tests. It will also permit the use of such instrumentation as a diagnostic tool on engines in service.
According to the invention, An instrumentation arrangement for a component comprises a baseplate to which is attached at least one measurement device, characterised in that the baseplate comprises attachment features engageable in use with the component, to permit installation and removal without modification of the component .
The component may comprise a surface and the baseplate may be shaped to correspond to the surface.
Alternatively, the component may comprise a surface and the baseplate may be moulded in use to correspond to the surface. The baseplate may be cured after moulding to ensure it retains its shape.
The attachment features may comprise hooks engageable with the component. The attachment features may comprise fasteners engageable in holes in the component. The holes may be manufacturing datum holes.
The baseplate may further comprise a tang engageable in use with structure associated with the component. The structure may be a casing or a mounting ring.
The tang may provide location of the baseplate in at least a first direction, and the attachment features may provide location of the baseplate in at least a second, different direction. Preferably, the first direction is radial and the second direction is axial.
The component may be a component of a gas turbine engine. The component may be a vane of a gas turbine engine and the hooks may be engageable with the leading edge of the vane . The arrangement may be at least partially secured to the component in use adhesively, magnetically or by suction.
The or each measurement device may be selected from the list consisting of: Pitot tube, thermocouple, miniature camera, laser sensor, densimeter, mass flow detector, particle detector. At least one measurement device may be protected by a shroud.
The or each measurement device may be attached to the baseplate by brazing or welding or adhesive bonding or mechanical fasteners.
The arrangement may further comprise at least one measurement device leadout tube or wire. The or each leadout tube or wire may be secured to the baseplate. The or each leadout tube or wire may be secured by clipping. The invention will now be described, by way of example, making reference to the attached drawings in which
Figure 1 shows an instrumentation arrangement according to the invention, together with a vane of a gas turbine engine; and
Figure 2 shows a partial section on the line AA of Figure 1.
In Figure 1, a fan outlet guide vane (OGV) 10 has a leading edge 12 and a trailing edge 14. The vane 10 has a concave pressure surface 20 and, on its opposite side, a convex suction surface 22 (indicated in Figure 2) . Two manufacturing datum holes 24 have been left in the pressure surface 20 by the vane manufacturing process. In use, a set of vanes 10 is mounted within an annular OGV mounting ring (the position of which is indicated by a dashed line 44) .
Figure 1 also shows an instrumentation arrangement 30 according to the invention. The arrangement 30 comprises a baseplate 32. The baseplate is shaped to correspond to the contour of the pressure surface 20 of the vane 10. The baseplate is extended at one end, to form a tang 33 with an end face 35. A number of shrouded Pitot tubes 34 are welded to the baseplate. In this embodiment, twelve shrouded Pitot tubes 34 are provided. Leadout tubes 36 from the Pitot tubes 34 are clipped to the baseplate 32, and led out to measuring equipment 38 (not shown) .
The baseplate 32 has hooks 40 along one edge, which in use are engageable with the leading edge 12 of the vane 10. In this embodiment, twelve hooks 40 are used. The rake 30 is located by the hooks 40 on the pressure surface 20 of the vane 10, approximately in the position indicated by the dashed lines 26. This provides a positive axial location for the baseplate. At the same time, the end face 35 of the baseplate tang 33 locates against the inner surface of the OGV mounting ring 44. This provides a positive radial location for the baseplate. Because the baseplate 32 is contoured to conform closely to the surface 20 of the vane 10, the combination of these three features (hooks 40, end face 35 and contoured baseplate) provides accurate and repeatable location of the baseplate 32 on the vane 10. Consequently, the locations of the shrouded Pitot tubes 34 relative to the vane 10 are accurately known. Suitable fasteners (not shown) , such as bolts, pass through holes 42 in the baseplate 32 and engage with the datum holes 24 in the vane 10, to secure the rake 30 to the vane 10.
Because the shape of the baseplate 32 corresponds to the contour of the pressure surface 20 of the vane 10, it fits closely in use and causes the minimum disturbance to the aerodynamic behaviour of the vane 10. Figure 2 shows a section through the line A-A of Figure 1, with the arrangement 30 installed on the vane 10. One of the hooks 40 is visible, and a shrouded Pitot tube 34 can also be seen adjacent the leading edge 12 of the vane 10. The previously described fasteners (not shown) pass through the holes 42 to secure the baseplate 32 to the vane 10.
When the invention is to be used on a service engine, the surface of the vane 10 may be worn or damaged. The contour of the baseplate 32 may not then correspond precisely to the contour of the vane surface 20. In an alternative aspect of this invention, the baseplate 32 is partly or wholly made from a mouldable, curable material. The baseplate 32 can be moulded exactly to the contour of the vane surface 20, taking account of any wear or damage. Once cured, the contour of the baseplate 32 will then be maintained throughout the subsequent testing.
Such an instrumentation arrangement, incorporating a mouldable baseplate, could be arranged to fit to a number of different vanes or to a number of different gas turbine engines. This would advantageously reduce the inventory- needed at service locations in the field, because a small number of rakes could be adapted to serve all purposes.
It will be appreciated that various modifications may be made to the embodiment described in this specification, without departing from the scope of the invention claimed.
As mentioned in the introductory part of this specification, other types of shrouded or unshrouded measuring devices may be installed. Examples of suitable devices are Pitot tubes, thermocouples, miniature cameras, laser sensors, densimeters, mass flow detectors and particle detectors, but the skilled reader will appreciate that this list is not exhaustive and that the invention could be applied to any measuring device of a suitable size. A single rake may comprise several measurement devices of different types.
The measurement devices may be attached to the baseplate by means other than welding, for example by brazing, by adhesive bonding or by mechanical fasteners. Likewise, the leadout tubes or wires may be secured to the baseplate by alternative means.
Lesser or greater numbers of measurement devices and hooks may be employed, to suit the particular vane and the required measurements. The baseplate may be secured to the vane surface by adhesive bonding or by any other suitable means. If the vane is of suitable material the baseplate may be secured magnetically. With the addition of a seal around the outside of the baseplate, it may be secured by suction. Such alternative securing methods may be used instead of, or in addition to, the mechanical fasteners described in the specific description.
The invention thus provides an instrumentation arrangement that can be readily attached to and removed from a component of an engine, without the need for any modification of the component. The component is left undamaged after the rake is removed. Because the baseplate is shaped to correspond to the component to which it is mounted in use, the effect on the aerodynamic behaviour of the component is minimised, and the measurements will be more accurate and representative.

Claims

1. An instrumentation arrangement (30) for a component, the arrangement comprising a baseplate (32) to which is attached at least one measurement device (34), characterised in that the baseplate comprises attachment features engageable in use with the component, to permit installation and removal without modification of the component .
2. An arrangement as in claim 1, in which the component comprises a surface (20) and the baseplate (32) is shaped to correspond to the surface (20) .
3. An arrangement as in claim 1, in which the component comprises a surface (20) and the baseplate (32) is moulded in use to correspond to the surface (20) .
4. An arrangement as in claim 3, in which the baseplate (32) is cured after moulding to ensure it retains its shape .
5. An arrangement as in any of claims 1 to 4, in which the attachment features comprise hooks (40) engageable with the component .
6. An arrangement as in any of claims 1 to 4, in which the attachment features comprise fasteners engageable in holes (24) in the component.
7. An arrangement as in claim 6, in which the holes (24) are manufacturing datum holes.
8. An arrangement as in any preceding claim, in which the baseplate (32) further comprises a tang (33) engageable in use with structure associated with the component.
9. An arrangement as in claim 8, in which the structure is a casing or a mounting ring (44) .
10. An arrangement as in claim 8 or claim 9, in which in use the tang (33) provides location of the baseplate (32) in at least a first direction, and the attachment features (40) provide location of the baseplate in at least a second, different direction.
11. An arrangement as in claim 10, in which the first direction is radial and the second direction is axial.
12. An arrangement as in any preceding claim, in which the component is a component of a gas turbine engine.
13. An arrangement as in claim 5, in which the component is a vane (10) of a gas turbine engine and the hooks (40) are engageable with the leading edge (12) of the vane (10).
14. An arrangement as in any preceding claim, which in use is at least partially secured to the component adhesively, magnetically or by suction.
15. An arrangement as in any preceding claim, in which the or each measurement device is selected from the list consisting of: Pitot tube, thermocouple, miniature camera, laser sensor, densimeter, mass flow detector, particle detector.
16. An arrangement as in any preceding claim, in which at least one measurement device is protected by a shroud.
17. An arrangement as in any preceding claim, in which the or each measurement device is attached to the baseplate by brazing or welding or adhesive bonding or mechanical fasteners .
18. An arrangement as in any preceding claim, and further comprising at least one measurement device leadout tube or wire (36) .
19. An arrangement as in claim 18, in which the or each leadout tube or wire (36) is secured to the baseplate.
20. An arrangement as in claim 19, in which the or each leadout tube or wire (36) is secured by clipping.
21. An instrumentation arrangement for a vane (10) of a gas turbine engine, comprising a baseplate (32) and a plurality of shrouded Pitot tubes (34), the baseplate (32) being shaped to correspond to the pressure surface (20) of the vane (10) , the baseplate (32) having hooks (40) engageable in use with the leading edge (12) of the vane (10) and a tang (33) engageable in use with a mounting ring (44) associated with the vane (10), the baseplate (32) being secured in use to the vane surface (20) by fasteners engageable in holes (24) in the vane surface (20) .
PCT/GB2006/001475 2005-05-21 2006-04-21 An instrumentation arrangement WO2006125939A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP06726865.6A EP1883789B1 (en) 2005-05-21 2006-04-21 An instrumentation arrangement
US11/920,729 US8297136B2 (en) 2005-05-21 2006-04-21 Instrumentation arrangement

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0510440.1 2005-05-21
GBGB0510440.1A GB0510440D0 (en) 2005-05-21 2005-05-21 An instrumentation rake

Publications (1)

Publication Number Publication Date
WO2006125939A1 true WO2006125939A1 (en) 2006-11-30

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2006/001475 WO2006125939A1 (en) 2005-05-21 2006-04-21 An instrumentation arrangement

Country Status (4)

Country Link
US (1) US8297136B2 (en)
EP (1) EP1883789B1 (en)
GB (1) GB0510440D0 (en)
WO (1) WO2006125939A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2008759A1 (en) * 2007-06-28 2008-12-31 United Technologies Corporation Tool alignment fixture
CN102906555A (en) * 2010-02-13 2013-01-30 麦卡利斯特技术有限责任公司 Methods, devices, and systems for detecting properties of target samples
FR3077135A1 (en) * 2018-01-23 2019-07-26 Safran Aircraft Engines DEVICE FOR MEASURING PARAMETERS OF A MINIMIZED INTRUSIVITY AERODYNAMIC FLOW, TURBOMACHINE VEIN FOR SUCH A DEVICE AND TURBOMACHINE EQUIPPED WITH SUCH A VEIN
US11193854B2 (en) 2018-06-20 2021-12-07 Rolls-Royce Plc Estimating fluid parameter

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9010198B2 (en) * 2011-07-29 2015-04-21 United Technologies Corporation Aircraft debris monitoring sensor assembly
FR3017459B1 (en) * 2014-02-07 2017-07-21 Snecma AUBE INSTRUMENTEE A TUBE REPORTED IN A GROOVE
DE102015109416A1 (en) * 2015-06-12 2016-12-15 Rolls-Royce Deutschland Ltd & Co Kg Measuring device and device with such a measuring device
FR3066779B1 (en) * 2017-05-26 2020-04-03 Safran Aircraft Engines DEVICE FOR MEASURING PARAMETERS OF AN AERODYNAMIC FLOW FOR A TURBOMACHINE BLADE, BLADE AND A TURBOMACHINE BLADE EQUIPPED WITH SAID MEASUREMENT DEVICE
US10684183B2 (en) * 2018-04-24 2020-06-16 The Boeing Company Powered total pressure measurement rake with telemetry

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1059465A (en) * 1964-05-15 1967-02-22 United Aircraft Corp Control system for the variable aperture air inlet of an air breathing engine
GB1183198A (en) * 1966-08-15 1970-03-04 Rolls Royce Controlling Supersonic Air Intakes
GB2293923A (en) * 1994-09-20 1996-04-10 Frank Richard Lee A thermocouple electrical wiring harness
US5563510A (en) * 1995-04-11 1996-10-08 Component Sales & Consultants, Inc. Variable reluctance sensor having hermetically sealed housing and damping element
US5612497A (en) * 1992-08-10 1997-03-18 Dow Deutschland Inc. Adaptor for monitoring a pressure sensor to a gas turbine housing
GB2314164A (en) * 1996-06-10 1997-12-17 Secr Defence A method and device to measure fluid parameters
GB2318873A (en) * 1996-11-02 1998-05-06 Asea Brown Boveri Method and device for measuring rotor blade vibrations
US6354153B1 (en) * 1999-06-24 2002-03-12 Robert Bosch Gmbh Pressure sensor connection device
US6518565B1 (en) 2000-09-20 2003-02-11 Eaton Corporation Sensor assembly
WO2004051194A1 (en) * 2002-12-05 2004-06-17 Penny & Giles Controls Limited Transducer
DE202004009112U1 (en) * 2004-06-09 2004-08-19 Loh, Ko-Chin Housing for an ultrasound detector, especially for mounting in a vehicle bumper for use in a distance measurement system, has a mounting arrangement that allows simple mounting or replacement of a whole detector unit
US20040211875A1 (en) * 2003-04-28 2004-10-28 Wisniewski Andrew J. Method for mounting non-acceleration based sensor

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3348414A (en) * 1964-10-09 1967-10-24 Gen Electric Gas turbine temperature measuring apparatus
GB2036363A (en) * 1978-12-04 1980-06-25 United Technologies Corp Inspecting Stator Vanes
US4298312A (en) * 1979-07-24 1981-11-03 Purex Corporation Damaged vane locating method and apparatus
US4605315A (en) * 1984-12-13 1986-08-12 United Technologies Corporation Temperature probe for rotating machinery
US4902139A (en) * 1988-04-13 1990-02-20 General Electric Company Apparatus and method for measuring the thermal performance of a heated or cooled component
US4916715A (en) * 1988-04-13 1990-04-10 General Electric Company Method and apparatus for measuring the distribution of heat flux and heat transfer coefficients on the surface of a cooled component used in a high temperature environment

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1059465A (en) * 1964-05-15 1967-02-22 United Aircraft Corp Control system for the variable aperture air inlet of an air breathing engine
GB1183198A (en) * 1966-08-15 1970-03-04 Rolls Royce Controlling Supersonic Air Intakes
US5612497A (en) * 1992-08-10 1997-03-18 Dow Deutschland Inc. Adaptor for monitoring a pressure sensor to a gas turbine housing
GB2293923A (en) * 1994-09-20 1996-04-10 Frank Richard Lee A thermocouple electrical wiring harness
US5563510A (en) * 1995-04-11 1996-10-08 Component Sales & Consultants, Inc. Variable reluctance sensor having hermetically sealed housing and damping element
GB2314164A (en) * 1996-06-10 1997-12-17 Secr Defence A method and device to measure fluid parameters
GB2318873A (en) * 1996-11-02 1998-05-06 Asea Brown Boveri Method and device for measuring rotor blade vibrations
US6354153B1 (en) * 1999-06-24 2002-03-12 Robert Bosch Gmbh Pressure sensor connection device
US6518565B1 (en) 2000-09-20 2003-02-11 Eaton Corporation Sensor assembly
WO2004051194A1 (en) * 2002-12-05 2004-06-17 Penny & Giles Controls Limited Transducer
US20040211875A1 (en) * 2003-04-28 2004-10-28 Wisniewski Andrew J. Method for mounting non-acceleration based sensor
DE202004009112U1 (en) * 2004-06-09 2004-08-19 Loh, Ko-Chin Housing for an ultrasound detector, especially for mounting in a vehicle bumper for use in a distance measurement system, has a mounting arrangement that allows simple mounting or replacement of a whole detector unit

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2008759A1 (en) * 2007-06-28 2008-12-31 United Technologies Corporation Tool alignment fixture
US8764000B2 (en) 2007-06-28 2014-07-01 United Technologies Corporation Tool alignment fixture
CN102906555A (en) * 2010-02-13 2013-01-30 麦卡利斯特技术有限责任公司 Methods, devices, and systems for detecting properties of target samples
CN102906555B (en) * 2010-02-13 2015-07-08 麦卡利斯特技术有限责任公司 Methods, devices, and systems for detecting properties of target samples
FR3077135A1 (en) * 2018-01-23 2019-07-26 Safran Aircraft Engines DEVICE FOR MEASURING PARAMETERS OF A MINIMIZED INTRUSIVITY AERODYNAMIC FLOW, TURBOMACHINE VEIN FOR SUCH A DEVICE AND TURBOMACHINE EQUIPPED WITH SUCH A VEIN
US11193854B2 (en) 2018-06-20 2021-12-07 Rolls-Royce Plc Estimating fluid parameter
US11236683B2 (en) 2018-06-20 2022-02-01 Rolls-Royce Plc Control system

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GB0510440D0 (en) 2005-06-29

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