| abstract |
The invention provides a compact high-temperature fuel cracking gas power generation turbine sealing and cooling structure, which belongs to the technical field of power generation turbines. It solves the problem that the shaft end seal of the current high-pressure and high-speed turbine generally uses dry gas seal, which is expensive and complicated in structure, requires a large assembly space and an attached high-pressure nitrogen gas supply device, but can withstand low temperature due to material and technical limitations; Turbine working in a high temperature working medium generally uses water circulation to take away heat for cooling, but for hypersonic aircraft, the cooling source is limited, and the use of circulating water for cooling will greatly increase the volume of the power generation system. It includes motor housing, turbine shaft, front end cover, cooling and insulating cavity, axial seal, staggered labyrinth seal and motor cooling system. The invention meets the space and quality requirements of airborne equipment, has better sealing and cooling effect, simplifies the turbine sealing and heat insulation system, can effectively reduce the leakage of the turbine, and ensures the power generation of the turbine. |