Thermal characteristics of gas turbine combustor in high temperature operation
Abstract
Atention is given to the development status of a silicon carbide gas turbine can-type combustor of 2 mm material cross section and 85 mm diameter, for which thermal resistance and thermal cycle tests have been conducted under conditions of 900 C air inlet temperature and an outlet gas temperature of 1350 C. It has been determined that sharp temperature gradients generated by carbon deposits must be eliminated through careful design; the fuels that may be used, while various, must also be such as to generate minimum carbon deposits.
- Publication:
-
1983 Tokyo International Gas Turbine Congress
- Pub Date:
- 1984
- Bibcode:
- 1984gatu....1..175A
- Keywords:
-
- Ceramics;
- Combustion Chambers;
- Gas Turbine Engines;
- High Temperature Tests;
- Research And Development;
- Thermal Resistance;
- Cyclic Loads;
- Engine Tests;
- Fuel Consumption;
- Fuel Tests;
- Inlet Temperature;
- Silicon Carbides;
- Silicon Nitrides;
- Test Stands;
- Thermal Stresses;
- Fluid Mechanics and Heat Transfer