3D computation of hydrogen-fueled combustion around turbine blade-effect of arrangement of injector holes-

Abstract

Recently, a number of environmental problems caused from fossil fuel combustion have been focused on. In addition, with the eventual depletion of fossil energy resources, hydrogen gas is expected to be an alternative energy resource in the near future. It is characterized by high energy per unit weight, high reaction rate, wide range of flammability and the low emission property. On the other hand, many researches have been underway in several countries to improve a propulsion system for an advanced aircraft. The system is required to have higher power, lighter weight and lower emissions than existing ones. In such a future propulsion system, hydrogen gas would be one of the promising fuels for realizing the requirements. Considering these backgrounds, our group has proposed a new cycle concept for hydrogen-fueled aircraft propulsion system. In the present study, we perform 3 dimensional computations of turbulent flow fields with hydrogen-fueled combustion around a turbine blade. The main objective is to clarify the influence of arrangement of hydrogen injector holes. Changing the chordwise and spanwise spacings of the holes, the 3 dimensional nature of the flow and thermal fields is numerically studied.

Comparative Investigation of Lean Effect of Stator Vane in Hydrogen-Fueled Combustion Turbine

“…The diameter of the injector hole is 3.0(mm) and the pitch of the holes is 3.0mm. This layout of injector holes has the highest feasibility among 5 cases studied in the previous study [5].…”

“…They concluded that this concept has the highest possibility by employing the hydrogen injection rate of 2H 2 /O 2 =0.25. Yamamoto et al [5] studied the interaction between the secondary flow and the endwall in a linear vane cascade. They found that the surface temperature on the endwall becomes extremely high (about 3000K) because of the secondary flow pattern.…”