Flow and thermal field measurements in a combustor simulator relevant to a gas turbine aeroengine

S. S. Vakil, K. A. Thole

Research output: Contribution to journalArticle

34 Citations (Scopus)

Abstract

The current demands for high performance gas turbine engines can be reached by raising combustion temperatures to increase power output. Predicting the performance of a combustor is quite challenging, particularly the turbulence levels that are generated as a result of injection from high momentum dilution jets. Prior to predicting reactions in a combustor, it is imperative that these turbulence levels can be accurately predicted. The measurements presented in this paper are of flow and thermal fields produced in a largescale combustor simulator, which is representative of an aeroengine. Three-component laser Doppler velocimeter measurements were made to quantify the velocity field while a rake of thermocouples was used to quantify the thermal field. The results indicate large penetration depths for the high momentum dilution jets, which result in a highly turbulent flow field. As these dilution jets interact with the mainstream flow, kidney-shaped thermal fields result due to counter-rotating vortices that develop.

Original languageEnglish (US)
Pages (from-to)257-267
Number of pages11
JournalJournal of Engineering for Gas Turbines and Power
Volume127
Issue number2
DOIs
StatePublished - Apr 1 2005

Fingerprint

Combustors
Dilution
Gas turbines
Simulators
Momentum
Turbulence
Laser Doppler velocimeters
Thermocouples
Turbulent flow
Flow fields
Vortex flow
Turbines
Hot Temperature
Temperature

All Science Journal Classification (ASJC) codes

  • Nuclear Energy and Engineering
  • Fuel Technology
  • Aerospace Engineering
  • Energy Engineering and Power Technology
  • Mechanical Engineering

Cite this

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Flow and thermal field measurements in a combustor simulator relevant to a gas turbine aeroengine. / Vakil, S. S.; Thole, K. A.

In: Journal of Engineering for Gas Turbines and Power, Vol. 127, No. 2, 01.04.2005, p. 257-267.

Research output: Contribution to journalArticle

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