Rocket fuels, such as liquid hydrogen, kerosene (RP-1), or hydrazine, have much higher energy densities compared to conventional jet fuels used in gas turbine engines. This means they can provide more energy per unit mass or volume.
However, rocket propellants often have different ignition and combustion properties than jet fuels. Rocket propellants are designed to burn at extremely high temperatures and pressures, whereas gas turbine engines operate at lower temperatures and pressures.
The combustion characteristics and flame temperatures of rocket propellants may not be suitable or optimized for the design and materials used in gas turbine engines. Using incompatible fuels can lead to incomplete combustion, increased exhaust emissions, higher thermal loads on engine components, and reduced engine efficiency.
Furthermore, the handling, storage, and safety requirements for rocket fuels can be more complex and hazardous compared to jet fuels. Rocket propellants often require specialized equipment and infrastructure for safe handling and storage.
Overall, while rocket fuels may have higher energy content, their suitability for use in gas turbine engines requires careful assessment, modifications to engine design and materials, and comprehensive testing to ensure compatibility, safety, and optimal performance.
