GB1104322A - Gas turbine engine - Google Patents
Gas turbine engineInfo
- Publication number
- GB1104322A GB1104322A GB2199965A GB2199965A GB1104322A GB 1104322 A GB1104322 A GB 1104322A GB 2199965 A GB2199965 A GB 2199965A GB 2199965 A GB2199965 A GB 2199965A GB 1104322 A GB1104322 A GB 1104322A
- Authority
- GB
- United Kingdom
- Prior art keywords
- radiation
- laser
- blade
- emissivity
- temperature
- 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.)
- Expired
Links
- 230000005855 radiation Effects 0.000 abstract 7
- 238000004616 Pyrometry Methods 0.000 abstract 1
- 238000009529 body temperature measurement Methods 0.000 abstract 1
- CPBQJMYROZQQJC-UHFFFAOYSA-N helium neon Chemical compound [He].[Ne] CPBQJMYROZQQJC-UHFFFAOYSA-N 0.000 abstract 1
- 238000002310 reflectometry Methods 0.000 abstract 1
- 239000007787 solid Substances 0.000 abstract 1
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
- G01J5/0022—Radiation pyrometry, e.g. infrared or optical thermometry for sensing the radiation of moving bodies
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Spectroscopy & Molecular Physics (AREA)
- Radiation Pyrometers (AREA)
Abstract
1,104,322. Radiation pyrometry. ROLLSROYCE Ltd. May 17, 1966 [May 24, 1965], No. 21999/65. Heading G1A, A pyrometric temperature measurement of a turbine blade in a gas turbine engine compensates for changes in emissivity of the turbine blade with temperature by arranging for the pyrometer to receive also radiation which has been reflected off the surface of the blade a change in emissivity then being off-set by a change in reflectivity. Radiation from a laser is directed on to the blade and the reflected radiation and radiation emitted by the blade is received, preferably, upon a single solid-state detector in the pyrometer. The intensity of the laser is made equal to that of a black-body radiator at the temperature of the blade in order to effect the compensation. The laser intensity is either maintained constant at this value or small permitted changes are monitored by a second detector which corrects the signal from the first. The path lengths from the laser to the first and second detectors are made the same. Filters may be inserted in the radiation paths to select a particular wavelength in the infrared at which the apparatus is most sensitive to temperature changes. The laser beam may be modulated and a further detector sensitive to the modulation can then distinguish the reflected laser beam from the emitted radiation in order to make compensation for the change in emissivity. A helium-neon gas or solid state laser may be used.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2199965A GB1104322A (en) | 1965-05-24 | 1965-05-24 | Gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2199965A GB1104322A (en) | 1965-05-24 | 1965-05-24 | Gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1104322A true GB1104322A (en) | 1968-02-21 |
Family
ID=10172305
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2199965A Expired GB1104322A (en) | 1965-05-24 | 1965-05-24 | Gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1104322A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2133877A (en) * | 1982-12-24 | 1984-08-01 | Rolls Royce | Generation of a signal dependent upon temperature of gas turbine rotor blades |
-
1965
- 1965-05-24 GB GB2199965A patent/GB1104322A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2133877A (en) * | 1982-12-24 | 1984-08-01 | Rolls Royce | Generation of a signal dependent upon temperature of gas turbine rotor blades |
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