Numerical investigation of enhanced dilution zone mixing in a reverse flow gas turbine combustor
- CFD Research Corp., Huntsville, AL (United States)
An advanced method for dilution zone mixing in a reverse flow gas turbine combustor was numerically investigated. For long mixing lengths associated with reverse flow combustors (X/H > 2.0), pattern factor was found to be mainly driven by nozzle-to-nozzle fuel flow and/or circumferential airflow variations; conventional radially injected dilution jets could not effectively mix out circumferential nonuniformities. To enhance circumferential mixing, dilution jets were angled in the opposite direction, thus enhancing turbulent shear at the expense of jet penetration. Three-dimensional CFD calculations were performed on a three-nozzle (90 deg) sector, with different fuel flow from each nozzle (90, 100, 110 percent of design fuel flow). The computations showed that the optimum configuration of angled jets reduced the pattern factor by 60 percent compared to an existing conventional dilution hole configuration. The radial average temperature profile was adequately controlled by the inner-to-outer liner dilution flow split.
- Sponsoring Organization:
- USDOE
- OSTI ID:
- 78172
- Report Number(s):
- CONF-930502-; ISSN 0742-4795; TRN: IM9531%%223
- Journal Information:
- Journal of Engineering for Gas Turbines and Power, Vol. 117, Issue 2; Conference: 38. ASME international gas turbine and aeroengine congress and exhibition, Cincinnati, OH (United States), 24-27 May 1993; Other Information: PBD: Apr 1995
- Country of Publication:
- United States
- Language:
- English
Similar Records
Introducing the VRT gas turbine combustor
Combustor bulkhead heat shield assembly