GB2109472A - Pyrometer for gas turbine - Google Patents

Pyrometer for gas turbine Download PDF

Info

Publication number
GB2109472A
GB2109472A GB08133205A GB8133205A GB2109472A GB 2109472 A GB2109472 A GB 2109472A GB 08133205 A GB08133205 A GB 08133205A GB 8133205 A GB8133205 A GB 8133205A GB 2109472 A GB2109472 A GB 2109472A
Authority
GB
United Kingdom
Prior art keywords
pyrometer
rotor
sensing portion
mirror
window
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
GB08133205A
Inventor
John Frederick Gray
Ronald Edwin Fineman
Joseph Douglas
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
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 GB08133205A priority Critical patent/GB2109472A/en
Publication of GB2109472A publication Critical patent/GB2109472A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/05—Means for preventing contamination of the components of the optical system; Means for preventing obstruction of the radiation path
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/0022—Radiation pyrometry, e.g. infrared or optical thermometry for sensing the radiation of moving bodies
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/0088—Radiation pyrometry, e.g. infrared or optical thermometry in turbines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/04—Casings
    • G01J5/041—Mountings in enclosures or in a particular environment
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/05—Means for preventing contamination of the components of the optical system; Means for preventing obstruction of the radiation path
    • G01J5/051—Means for preventing contamination of the components of the optical system; Means for preventing obstruction of the radiation path using a gas purge
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/08—Optical arrangements
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/08—Optical arrangements
    • G01J5/0806—Focusing or collimating elements, e.g. lenses or concave mirrors
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/08—Optical arrangements
    • G01J5/0808—Convex mirrors
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/08—Optical arrangements
    • G01J5/0813—Planar mirrors; Parallel phase plates
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/08—Optical arrangements
    • G01J5/0818—Waveguides
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/08—Optical arrangements
    • G01J5/0818—Waveguides
    • G01J5/0821—Optical fibres
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/08—Optical arrangements
    • G01J5/084—Adjustable or slidable
    • G01J5/0843—Manually adjustable
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/04—Casings
    • G01J5/046—Materials; Selection of thermal materials

Landscapes

  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Spectroscopy & Molecular Physics (AREA)
  • Radiation Pyrometers (AREA)

Abstract

A pyrometer for use in a gas turbine engine to monitor the temperature of turbine blades 14 has a portion 20 which can be moved by arrangement 46 in a direction radially within the engine and also rotationally about its longitudinal axis so as to enable one to scan the length and chord of each blade. Portion 20 includes a rhodium mirror 26 and a sapphire lens for transmitting radiation from the blades to measuring apparatus 32 via fibre optic guide 28. Air from inlet 44 cleans mirror 26 before passing through viewing aperture 24. <IMAGE>

Description

SPECIFICATION Pyrometer This invention relates to pyrometers, and in particuiar to pyrometers for measuring the temperature of rotors in gas turbine engines.
A known form of pyrometer for measuring the temperature of a rotor in a gas turbine engine comprises a sensing portion having a cylindrical body with a window at one end thereof. In use of the pyrometer the sensing portion is inserted through an aperture in the engine casing so as to point to a predetermined radial position on a rotor whose temperature is to be measured, thereby to cause radiation from that position on the rotor to pass through the window and along the body to measuring apparatus external to the engine.
With such a pyrometer a single radial position on the rotor must be selected before insertion of the sensing portion when making the aperture in the engine casing and the temperature at this position must be assumed to be representative of the temperature of the whole rotor. In certain circumstances this assumption may not be valid and the pyrometer output will then become unrepresentative and may result in unreliable engine control.
It is an object of the present invention to provide a pyrometer in which the above disadvantage may be overcome.
In accordance with the present invention a pyrometer for use in measuring the temperature of a rotor of a gas turbine engine comprises: a sensing portion insertable through the engine casing to a position adjacent the rotor whose temperature is to be measured; and traversing means for moving the sensing portion to sense different radial positions on the rotor.
Also, in the known form of pyrometer described above, since the sensing portion must point directly to the position of interest on the rotor, access for the sensing portion may be difficult.
This may necessitate the positioning of the casing aperture at some point remote from the rotor whose temperature is to be measured and so cause the sensing portion to be undesirably long and heavy.
It is a further object of this invention to provide a pyrometer in which the immediately preceding disadvantage may be overcome.
In accordance with this further object the sensing portion comprises a hollow, elongate body having therein a window which, in use of the pyrometer, faces the rotor and a mirror arranged within the body adjacent the window to reflect along the body radiation emitted from the rotor and entering the window.
One pyrometer in accordance with the invention will now be described, by way of example only, with reference to the accompanying drawings, in which: Figure 1 shows a cross-sectional view of part of a gas turbine engine including the pyrometer; and Figure 2 shows in greater detail part of the pyrometer; and Figure 3 shows a cross-sectional view on the line 111-Ill in Figure 2.
Referring firstly to Figure 1, a gas turbine engine 2 (of which only part is shown) has outer and inner engine casings, 4 and 6 respectively, containing a high-pressure turbine rotor 8 and inlet guide vanes 10 thereto. The rotor 8 comprises a central disc 12 from which extend a multiplicity of similar radially extending blades 14.
Radiaily aligned apertures are provided in the inner and outer engine casings and in the aperture of the inner casing is brazed a cylindrical sleeve 1 6.
Through the apertures in the inner and outer casings and into the sleeve 1 6 is inserted a sensing portion 20 of a pyrometer 22. The sensing portion 20 may extend into the gas flow path between adjacent guide vanes 10 or a guide vane may be cut away to allow the sensing portion to be positioned so as not to disturb the gas flow.
Referring now also to Figure 2 the sensing portion 20 comprises a hollow cylindrical body having in its side at an end a window in the form of an opening 24. The opening 24 faces onto the blades 14 of the rotor 8. A rhodium mirror 26 is positioned in the sensing portion 20 adjacent the opening 24 and is angled at approximately 450 to the length of the sensing portion.
When the engine is operating, the blades 14 of the high pressure turbine rotor 6 become heated to such a temperature that they emit radiation, characteristic of their temperature, such radiation from a particular radial position on the turbine blades which the opening 24 faces enters the opening and is reflected by the mirror 26 radially outwardly along the body of the sensing portion.
The radiation then enters a fibre optic waveguide 28 via a sapphire lens 30 to focus the optical system onto the rotor blades 14. The radiation is transmitted by the waveguide 28 out of the sensing portion 20 to measuring apparatus 32.
The measuring apparatus 32 measures the temperature from the radiation received and passes a signal representative of this temperature to the engine control system (not shown) to control the running of the engine.
Referring now also to Figure 3 the mirror 26 is of substantially rectangular shape and is mounted in a slot 34 in a hollow, open-ended, cylindrical insert 36 having an opening 38 therein. The insert 36 has external lugs 40 which allow the insert 36 to fit closely within the body of the sensing portion and the mirror 26 is sized and has its ends rounded so that the mirror is located accurately within the body of the sensing portion adjacent the opening 24 therein. The annular passage 42 formed between the body of the sensing portion 20 and the body of the insert 36 is used to condct air entering the sensing portion at an inlet 44 to the mirror 26.In this way the mirror 26 is cooled and kept clean by the air passing over the mirror 26 and exhausting through the opening 24 Radiation received by the measuring apparatus is determined by the radial position on the rotor blades towards which the opening 24 faces. In order to allow this position to be varied, as desired, in use of the pyrometer, a traversing arrangement 46 is connected to the sensing portion 20 via a connecting rod 48. The traversing arrangement 46 moves the sensing portion 20 both radially so as to move along the sleeve 1 6 and rotationally so as to twist about its own axis within the sleeve. In this way a large proportion of the surface of the rotor blades 14 may be traversed. Rotating the sensing-portion 20 about its own axis enables temperatures along the chord of the blade 14 (i.e. at different axial positions) to be sensed (although at decreased resolutions since the focal length of the system is fixed).
Radially traversing the sensing portion 20 enables the entire radial length of the blade 14 to be sensed (without change of resolution).
It will be appreciated that such a pyrometer, by allowing the temperature of a large proportion of the surface of the rotor blades to be measured, enables more accurate and reliable control of engine operation.

Claims (8)

1. A pyrometer for use in measuring the temperature of a rotor of a gas turbine engine, the pyrometer comprising: a sensing portion insertable through the engine casing to a position adjacent the rotor whose temperature is to be measured; and traversing means for moving the sensing portion to sense different positions on the rotor.
2. A pyrometer according to claim 1, wherein the traversing means is arranged to rotate the sensing portion so to enable it to sense different axial positions on the rotor.
3. A pyrometer according to claim 1 wherein the traversing means is arranged to move the sensing portion radially so as to sense different radial positions on the rotor.
4. A pyrometer according to claims 2 and 3.
5. A pyrometer according to claim 1,2, 3 or 4 wherein the sensing portion comprises a hollow, elongate body having therein a window which, in use of the pyrometer, faces the rotor and a mirror arranged within the body adjacent the window to reflect along the body radiation emitted from the rotor and entering the window.
6. A pyrometer according to claim 5 wherein the sensing portion includes an elongate locating member positioned in the body and locating the mirror therein, the locating member and the body defining therebetween a passage for cooling gas to cool the mirror and body.
7. A pyrometer according to claim 5 or 6 wherein the mirror is made of rhodium.
8. A pyrometer substantially as hereinbefore described with reference to the accompanying drawings.
GB08133205A 1981-11-04 1981-11-04 Pyrometer for gas turbine Withdrawn GB2109472A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB08133205A GB2109472A (en) 1981-11-04 1981-11-04 Pyrometer for gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB08133205A GB2109472A (en) 1981-11-04 1981-11-04 Pyrometer for gas turbine

Publications (1)

Publication Number Publication Date
GB2109472A true GB2109472A (en) 1983-06-02

Family

ID=10525616

Family Applications (1)

Application Number Title Priority Date Filing Date
GB08133205A Withdrawn GB2109472A (en) 1981-11-04 1981-11-04 Pyrometer for gas turbine

Country Status (1)

Country Link
GB (1) GB2109472A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0173548A2 (en) * 1984-08-22 1986-03-05 ROLLS-ROYCE plc Radiation probe and method of use
DE102004050906B3 (en) * 2004-10-19 2006-04-20 Siemens Ag Method for determining the temperature of a surface coating of blades of a turbomachine during operation and corresponding apparatus for carrying out the method
WO2009115520A1 (en) * 2008-03-20 2009-09-24 Siemens Aktiengesellschaft Pyrometer with spatial resolution
EP2565387A1 (en) * 2011-08-29 2013-03-06 Siemens Aktiengesellschaft Flow engine with a contactless temperature sensor
CN104964748A (en) * 2015-06-15 2015-10-07 中国航空工业集团公司上海航空测控技术研究所 Infrared wavelength acquisition apparatus
CN110231093A (en) * 2019-07-02 2019-09-13 电子科技大学 A kind of infrared radiation temperature meter reducing meter background radiation
WO2020159723A1 (en) * 2019-02-01 2020-08-06 Solar Turbines Incorporated Temperature measuring system

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0173548A2 (en) * 1984-08-22 1986-03-05 ROLLS-ROYCE plc Radiation probe and method of use
EP0173548A3 (en) * 1984-08-22 1987-09-02 Rolls-Royce Plc Radiation probe and method of use
DE102004050906B3 (en) * 2004-10-19 2006-04-20 Siemens Ag Method for determining the temperature of a surface coating of blades of a turbomachine during operation and corresponding apparatus for carrying out the method
US7517143B2 (en) 2004-10-19 2009-04-14 Siemens Aktiengesellschaft Method for determining the temperature of a surface coating
JP2011515671A (en) * 2008-03-20 2011-05-19 シーメンス アクチエンゲゼルシヤフト Optical measuring device and turbine
DE102008015205A1 (en) * 2008-03-20 2009-10-01 Siemens Aktiengesellschaft Pyrometer with spatial resolution
WO2009115520A1 (en) * 2008-03-20 2009-09-24 Siemens Aktiengesellschaft Pyrometer with spatial resolution
DE102008015205B4 (en) * 2008-03-20 2013-04-11 Siemens Aktiengesellschaft Pyrometer with spatial resolution
EP2565387A1 (en) * 2011-08-29 2013-03-06 Siemens Aktiengesellschaft Flow engine with a contactless temperature sensor
CN104964748A (en) * 2015-06-15 2015-10-07 中国航空工业集团公司上海航空测控技术研究所 Infrared wavelength acquisition apparatus
CN104964748B (en) * 2015-06-15 2018-07-27 中国航空工业集团公司上海航空测控技术研究所 A kind of infrared wavelength harvester
WO2020159723A1 (en) * 2019-02-01 2020-08-06 Solar Turbines Incorporated Temperature measuring system
US11215508B2 (en) 2019-02-01 2022-01-04 Solar Turbines Incorporated Temperature measuring system
CN110231093A (en) * 2019-07-02 2019-09-13 电子科技大学 A kind of infrared radiation temperature meter reducing meter background radiation
CN110231093B (en) * 2019-07-02 2021-03-30 电子科技大学 Infrared radiation thermometer capable of reducing background radiation

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Legal Events

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WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)