The physical modeling embodied in the computational fluid dynamics codes is discussed. The objectives were to identify shortcomings in the models and to provide a program plan to improve the quantitative accuracy. The physical models studied were for: turbulent mass and momentum transport, heat release, liquid fuel spray, and gaseous radiation. The approach adopted was to test the models against appropriate benchmark-quality test cases from experiments in the literature for the constituent flows that together make up the combustor real flow
The Turbine Engine Hot Section Technology Combustion Program is briefly described. The overall objec...
The use of numerical simulations with combustion for predicting the flow field in a gas turbine comb...
Presented is a collection of papers on research activities carried out during the funding period of ...
Aerothermal submodels used in analytical combustor models are analyzed. The models described include...
The main objectives of the Aerothermal Modeling Program, Phase 2 are: to develop an improved numeric...
The experimental test effort is discussed. The test data are presented. The compilation is divided i...
Some significant features of the approach adopted for the combustor aerothermal modeling program are...
Phase 1 was conducted as part of the overall NASA Hot Section Technology (HOST) Program. The purpose...
The overall objective of the Turbine Engine Hot Section Technology Combustion Project is to develop ...
Research was performed in the area of computational modeling and application of hypersonic, high-ent...
Critical issues concerning the modeling of low-density hypervelocity flows where thermochemical none...
One of the significant ways in which the performance level of aircraft turbine engines has been impr...
The overall objective of the Turbine Engine Hot Section Technology Combustion Project was to develop...
The goal of this research is to bring computational fluid dynamics to a state of practical applicati...
The main objective of the NASA sponsored Aerothermal Modeling Program, Phase 2--Element A, is to dev...
The Turbine Engine Hot Section Technology Combustion Program is briefly described. The overall objec...
The use of numerical simulations with combustion for predicting the flow field in a gas turbine comb...
Presented is a collection of papers on research activities carried out during the funding period of ...
Aerothermal submodels used in analytical combustor models are analyzed. The models described include...
The main objectives of the Aerothermal Modeling Program, Phase 2 are: to develop an improved numeric...
The experimental test effort is discussed. The test data are presented. The compilation is divided i...
Some significant features of the approach adopted for the combustor aerothermal modeling program are...
Phase 1 was conducted as part of the overall NASA Hot Section Technology (HOST) Program. The purpose...
The overall objective of the Turbine Engine Hot Section Technology Combustion Project is to develop ...
Research was performed in the area of computational modeling and application of hypersonic, high-ent...
Critical issues concerning the modeling of low-density hypervelocity flows where thermochemical none...
One of the significant ways in which the performance level of aircraft turbine engines has been impr...
The overall objective of the Turbine Engine Hot Section Technology Combustion Project was to develop...
The goal of this research is to bring computational fluid dynamics to a state of practical applicati...
The main objective of the NASA sponsored Aerothermal Modeling Program, Phase 2--Element A, is to dev...
The Turbine Engine Hot Section Technology Combustion Program is briefly described. The overall objec...
The use of numerical simulations with combustion for predicting the flow field in a gas turbine comb...
Presented is a collection of papers on research activities carried out during the funding period of ...