東華大學圖書館 |

Language: English

Help

回圖書館首頁

手機版館藏查詢

Back

Switch To: Labeled | MARC Mode | ISBD

Temperature Measurement of Model Gas...

Haidar, Rifat.

Linked to FindBook

Google Book

Amazon

博客來

Temperature Measurement of Model Gas Turbine Combustor Using a Multi-Wavelength Pyrometry in Visible and Near Infrared Spectrum.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Temperature Measurement of Model Gas Turbine Combustor Using a Multi-Wavelength Pyrometry in Visible and Near Infrared Spectrum./
Author:	Haidar, Rifat.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2024,
Description:	146 p.
Notes:	Source: Dissertations Abstracts International, Volume: 86-01, Section: B.
Contained By:	Dissertations Abstracts International86-01B.
Subject:	Aerospace engineering. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31480159
ISBN:	9798382833958

Temperature Measurement of Model Gas Turbine Combustor Using a Multi-Wavelength Pyrometry in Visible and Near Infrared Spectrum.
Haidar, Rifat.

Temperature Measurement of Model Gas Turbine Combustor Using a Multi-Wavelength Pyrometry in Visible and Near Infrared Spectrum. - Ann Arbor : ProQuest Dissertations & Theses, 2024 - 146 p.

Source: Dissertations Abstracts International, Volume: 86-01, Section: B.

Thesis (Ph.D.)--University of Cincinnati, 2024.

Continuous control and monitoring of the gas turbine combustor wall is essential for preventing combustor liner from overheating which may significantly damage structural integrity and reduce overall lifespan. In the past half century combustor outlet temperature has risen from 1100 to 1850 K. The continuous increase of severity of operating conditions inside combustor demands for a temperature determination method whose operation and accuracy are not affected by ever rising temperature. Conventional methods such as thermocouples and thermographic phosphor are not only intrusive, but their operation is also either restricted by an upper temperature limit (thermocouple) or measurement accuracy significantly decreases with increasing temperature beyond a certain threshold (thermographic phosphor). In this paper a multi-wavelength pyrometry system is developed which provides a fast, minimally intrusive temperature determination of the combustor wall. This method does not require any prior knowledge of exact emissivity but of the functional relationship between emissivity and wavelength over the spectral region of interest. One of major problems of wall temperature measurement using a pyrometry in combustor is that the emission from the combustor wall is interfered by the emissions from molecular radicals existing in the flame such as CH* (~431nm), OH* (~308nm), CO2* (400-600 nm) in the visible range and major species such as H2O (1.4,1.9,2.7,6.3 um) and CO2 (2.7,4.3,15 um) in the infrared region. In this report, a combustor that is made of stainless steel and runs on natural gas and the spectrum of flame emission is measured to identify a proper wavelength range (650-800 nm) over which there exists minimal or no interference from flame emission with thermal radiation. Thermal radiation is measured within the mentioned spectral range with a spectrometer and camera assembly from the target spot on the combustor wall with temperatures ranging from 1000 to 1300K. Thermal radiation spectra from both bare stainless steel and YSZ thermal barrier-coated steel were measured for temperature determination. Measured spectra were transformed into a straight line and corresponding temperatures were measured from the slope of those lines. The slope method is only valid when reflected radiation from the target spot is minimal or non-existent and spectral emissivity of target spot is inversely proportional to the wavelength. A separate algorithm was formulated to compensate for reflected radiation when it constitutes a good portion of the total (thermal and reflected) measured radiation. It was found that the addition of YSZ TBC thickness increased the hot gas side temperature although it reduced the temperature of the base metal underneath. A steep temperature gradient was found to exist across the thickness of the non-isothermal thermal barrier coating. Measured temperatures are found to be in good agreement with temperatures measured with thermocouple with absolute error being always within 5% or less.

ISBN: 9798382833958Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Heat transfer

Temperature Measurement of Model Gas Turbine Combustor Using a Multi-Wavelength Pyrometry in Visible and Near Infrared Spectrum.
LDR:04286nmm a2200397 4500 001 2428183
005 20241210085427.5
006 m o d
007 cr#unu||||||||
008 261011s2024 ||||||||||||||||| ||eng d
020 $a 9798382833958
035 $a (MiAaPQ)AAI31480159
035 $a (MiAaPQ)OhioLINKucin1712917096247453
035 $a AAI31480159
040 $a MiAaPQ $c MiAaPQ
100 1 $a Haidar, Rifat. $3 3815222
245 1 0 $a Temperature Measurement of Model Gas Turbine Combustor Using a Multi-Wavelength Pyrometry in Visible and Near Infrared Spectrum.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2024
300 $a 146 p.
500 $a Source: Dissertations Abstracts International, Volume: 86-01, Section: B.
500 $a Advisor: Lee, Jongguen.
502 $a Thesis (Ph.D.)--University of Cincinnati, 2024.
520 $a Continuous control and monitoring of the gas turbine combustor wall is essential for preventing combustor liner from overheating which may significantly damage structural integrity and reduce overall lifespan. In the past half century combustor outlet temperature has risen from 1100 to 1850 K. The continuous increase of severity of operating conditions inside combustor demands for a temperature determination method whose operation and accuracy are not affected by ever rising temperature. Conventional methods such as thermocouples and thermographic phosphor are not only intrusive, but their operation is also either restricted by an upper temperature limit (thermocouple) or measurement accuracy significantly decreases with increasing temperature beyond a certain threshold (thermographic phosphor). In this paper a multi-wavelength pyrometry system is developed which provides a fast, minimally intrusive temperature determination of the combustor wall. This method does not require any prior knowledge of exact emissivity but of the functional relationship between emissivity and wavelength over the spectral region of interest. One of major problems of wall temperature measurement using a pyrometry in combustor is that the emission from the combustor wall is interfered by the emissions from molecular radicals existing in the flame such as CH* (~431nm), OH* (~308nm), CO2* (400-600 nm) in the visible range and major species such as H2O (1.4,1.9,2.7,6.3 um) and CO2 (2.7,4.3,15 um) in the infrared region. In this report, a combustor that is made of stainless steel and runs on natural gas and the spectrum of flame emission is measured to identify a proper wavelength range (650-800 nm) over which there exists minimal or no interference from flame emission with thermal radiation. Thermal radiation is measured within the mentioned spectral range with a spectrometer and camera assembly from the target spot on the combustor wall with temperatures ranging from 1000 to 1300K. Thermal radiation spectra from both bare stainless steel and YSZ thermal barrier-coated steel were measured for temperature determination. Measured spectra were transformed into a straight line and corresponding temperatures were measured from the slope of those lines. The slope method is only valid when reflected radiation from the target spot is minimal or non-existent and spectral emissivity of target spot is inversely proportional to the wavelength. A separate algorithm was formulated to compensate for reflected radiation when it constitutes a good portion of the total (thermal and reflected) measured radiation. It was found that the addition of YSZ TBC thickness increased the hot gas side temperature although it reduced the temperature of the base metal underneath. A steep temperature gradient was found to exist across the thickness of the non-isothermal thermal barrier coating. Measured temperatures are found to be in good agreement with temperatures measured with thermocouple with absolute error being always within 5% or less.
590 $a School code: 0045.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Thermodynamics. $3 517304
650 4 $a Mechanical engineering. $3 649730
653 $a Heat transfer
653 $a Radiation
653 $a Thermal barrier coating
653 $a Pyrometry
653 $a Flame emission
690 $a 0538
690 $a 0548
690 $a 0348
710 2 $a University of Cincinnati. $b Engineering and Applied Science: Aerospace Engineering. $3 3277533
773 0 $t Dissertations Abstracts International $g 86-01B.
790 $a 0045
791 $a Ph.D.
792 $a 2024
793 $a English
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31480159