Novel turbine disc cavity heat insulation structure with heat insulation plate and air interlayer

Abstract

The novel turbine disc cavity heat insulation structure comprises a turbine guide vane, a turbine heat insulation plate is arranged on one side of the turbine guide vane, a turbine movable vane is arranged at one end of the turbine guide vane, a boss is arranged at the position, opposite to the turbine guide vane, of the turbine heat insulation plate, and the air interlayer is arranged on the boss. The device has the beneficial effects that the long screws are in threaded connection with the mechanical seal shell and the motor shell, so that the effects of fixing the turbine disc heat insulation plate and preventing large-amplitude vibration caused by too large cantilever distance of the heat insulation plate are achieved; meanwhile, the turbine disc heat insulation plate is close to the turbine disc, a small disc cavity gap is formed between the turbine disc heat insulation plate and the turbine disc, a large vortex system can be prevented from being generated, turbine disc resonance is avoided, and operation safety is guaranteed; and compared with large vortex system flow, the convection heat transfer coefficient of flow in the narrow disc cavity space is small, and the heat exchange amount from the turbine disc to the heat shielding plate is reduced.

Description

Technical field: [0001] The invention belongs to the technical field of turbine disc cavity heat insulation, in particular to a novel turbine disc cavity heat insulation structure with a heat shield plate and an air interlayer. Background technique: [0002] The flight speed of a hypersonic vehicle is usually above Mach 5, and the flight at a high Mach number leads to an increase in the stagnation temperature of the incoming air. When the Mach number of the aircraft reaches 4, the stagnation temperature is about 860K, and when the Mach number reaches 6, the stagnation temperature can reach 1600K. On the one hand, the aircraft is facing more and more serious thermal protection problems. On the other hand, it can be considered to use part of the aerodynamic heat to push the turbine components to expand and do work to achieve thermoelectric conversion, so as to solve the power supply problem of hypersonic aircraft and reduce the thermal protection system. work pressure. In re...

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Problems solved by technology

Secondly, the turbine power generation device usually adopts a compact design scheme to reduce the impact on the aerodynamic shape design of the aircraft, which will inevitably cause a sudden increase in the heat transfer between the components, which will reduce the life of the bearing and sealing device near the turbine end or even fail.

In the traditional turbine disk heat shielding scheme, the large cavity between the turbine disk and the heat shield will generate a large vortex flow, which will easily cause the resonance of the turbine disk and enhance the flow and heat transfer of the turbine disk cavity, weakening the heat insulation effect of the heat shield , endangering the operation safety of the turbine disk

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