Advanced Combustor Liner Cooling Concepts
Abstract
Small gas turbine liner cooling is especially difficult due to the low combustor air flow and relatively large flame tube areas. Therefore, it is desirable to increase the cooling potential of the cooling air by application of combined convective-film cooling. Its advantage must be balanced carefully against the disadvantage of increased weight and production cost. The large number of variable parameters of a combined cooling configuration requires a computer model which allows the simulation of different cooling approaches. To verify this, model tests with various configurations were conducted in a 2D- cooling rig. Good agreement between measured and calculated liner temperatures could be achieved. Thus, the model is suitable to show under which conditions a marked decrease of wall temperature can be reached compared with the case of straight film cooling under the same conditions.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1984
- Accession Number
- ADP003148
Entities
People
- B. Simon
- D. Schubert
- U. Basler