scholarly journals Temperature Estimation Based on Microstructural Change of Coatings for a Gas Turbine — Influence of Deposition Process on Microstructural Change and Estimated Temperature —

2009 ◽  
Vol 58 (4) ◽  
pp. 323-330 ◽  
Author(s):  
Mitsutoshi OKADA ◽  
Tohru HISAMATSU ◽  
Terutaka FUJIOKA ◽  
Takayuki KITAMURA
Keyword(s):  
Gas Turbine ◽  
Deposition Process ◽  
Microstructural Change ◽  
Temperature Estimation

scholarly journals Service Temperature Estimation for Gas Turbine Buckets Based on Microstructure Change.

1996 ◽  
Vol 45 (6) ◽  
pp. 699-704 ◽  
Author(s):  
Yomei YOSHIOKA ◽  
Nagatoshi OKABE ◽  
Daizo SAITO ◽  
Kazunari FUJIYAMA ◽  
Takanari OKAMURA
Keyword(s):  
Gas Turbine ◽  
Service Temperature ◽  
Temperature Estimation ◽  
Microstructure Change

Development of Temperature Estimation Method for a Gas Turbine Transition Piece

2016 ◽  
Author(s):  
Mitsutoshi Okada ◽  
Toshihiko Takahashi ◽  
Susumu Yamada ◽  
Takayuki Ozeki ◽  
Tomoharu Fujii
Keyword(s):  
Heat Transfer ◽  
Temperature Distribution ◽  
Gas Turbine ◽  
Estimation Method ◽  
Life Assessment ◽  
Estimation Methods ◽  
Test Time ◽  
Internal Cooling ◽  
Temperature Estimation ◽  
Transition Piece

Temperature estimation methods for a transition piece of a gas turbine are developed in terms of microstructural changes and computational fluid dynamics (CFD) for life assessment. Temperature is estimated to be low around the center of the component where thermal barrier coating (TBC) is deposited on the Ni-base superalloy and a combination of internal cooling and film cooling is also applied. Test specimens are prepared from the above area for a high-temperature heating test in air. The microstructure in the superalloy and TBC is investigated after the test. The thermally grown oxide (TGO) formed on the bondcoat surface increases with the square root of the test time, and on the basis of this relation, a temperature-estimation equation is obtained. The estimated temperature distribution is compared with a numerical heat transfer simulation by means of CFD. The geometry of the transition piece with internal cooling structure is acquired using an X-ray computerized radiography and a laser digitizer, and it is modeled for the numerical simulation. The heat conduction analysis is applied to the transition piece, and the convection and radiation heat transfer analyses are applied to the gas path and internal cooling flow. These analyses are conjugated to estimate the temperature distribution. The simulation result agrees well with the estimation using TGO thickness.

Spectroscopic monitoring and melt pool temperature estimation during the laser metal deposition process

2016 ◽  
Vol 28 (2) ◽  
pp. 022303 ◽  
Author(s):  
Dieter De Baere ◽  
Wim Devesse ◽  
Ben De Pauw ◽  
Lien Smeesters ◽  
Hugo Thienpont ◽  
...  
Keyword(s):  
Deposition Process ◽  
Metal Deposition ◽  
Laser Metal Deposition ◽  
Temperature Estimation ◽  
Spectroscopic Monitoring ◽  
Melt Pool ◽  
Melt Pool Temperature

Sodium Sulphate Formation and Deposition in Marine Gas Turbines

1974 ◽  
Vol 96 (2) ◽  
pp. 129-133 ◽  
Author(s):  
V. I. Hanby
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Blades ◽  
Deposition Process ◽  
Sodium Sulphate ◽  
Time Range ◽  
Significant Variable ◽  
Gas Temperature ◽  
Salt Particle ◽  
Gas Turbine Combustion

The rate of formation of gaseous sodium sulphate from sodium chloride and the combustion of a sulphur-bearing fuel has been investigated in a controlled mixing history combustor. The reaction was studied in the residence time range 0–16 millisec to simulate conditions resembling those in a gas turbine combustion chamber. The results show that under the conditions investigated, gas temperature was the most significant variable affecting the reaction rate. Gas phase formation of sodium sulphate proceeds too slowly to contribute to sulphatic corrosion in the short residence times which occur in gas turbine combustion chambers. The results obtained, in conjunction with predictions of salt particle behavior in the gas turbine engine indicate that the deposition process on turbine blades occurs via passage of transient high concentrations of particles through the engine.

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