Engine turbine disc cavity structure with pre-rotation nozzle and flow guiding disc

Abstract

The invention discloses an engine turbine disc cavity structure with a pre-rotation nozzle and a flow guiding disc. The engine turbine disc cavity structure comprises a turbine disc and further comprises the flow guiding disc and a pre-rotation nozzle ring which are arranged in front of the turbine disc. High-pressure low-temperature two-strand airflow is divided into two strands after entering apre-rotation airflow cavity through the pre-rotation nozzle ring. One strand of airflow passes through pre-rotation cool air receiving holes evenly distributed in the circumferential direction of theflow guiding disc and enters an axial ventilation hole in the bottom of a turbine disc mortise along a radial flow guiding plate on the rear side of the flow guiding disc. The other strand of airflowpasses through a sealed grid tooth ring on the flow guiding disc, and after the other strand of airflow is pre-rotated and pressurized through an inclined flow guiding plate above the front side of the flow guiding disc and is converged with cool air from cool air impact holes evenly distributed in the circumferential direction of the installing edge of a guiding device, the other strand of airflow enters a main runner through a turbine rotor and stator gap. By means of the engine turbine disc cavity structure, the relative total temperature of cool air can be reduced, convection heat exchangeof cool air and the turbine disc is enhanced, pre-rotation pressurizing is conducted on the wheel edge seal gas, the seal effect is improved, and seal gas and main flow mixing losses are reduced.

Description

technical field [0001] The invention belongs to the technical field of aero-engines and gas turbines, and relates to a cooling and sealing structure for a secondary air system of a turbine component disc cavity, in particular to an engine turbine disc cavity structure with a pre-swirling nozzle and a deflector plate. By rationally designing the geometry of the pre-swirling nozzle Parameters, different forms of deflectors are arranged at different positions of the deflector plate, which can reduce the relative total temperature of the cooling air, reduce the flow loss, and pre-swirl and pressurize the sealing gas of the rim, improve the sealing effect and reduce the sealing effect. Strict gas and mainstream mixing loss. At the same time, the structure is simple, and the processing, assembly and disassembly are convenient, so as to meet the requirements of high-performance turbines. Background technique [0002] With the increase of thrust-to-weight ratio requirements of aero...

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Problems solved by technology

[0003] In the design of traditional gas turbine and aero-engine turbine disc cavity structures, there are often the following four problems: ①The flow of cold air along the above-mentioned flow path often develops through irregular disc cavity, grate teeth and other sealing structures, and the temperature rise and pressure along the process The loss is large, which greatly affects the cooling and sealing effect; ②The friction pump effect caused by the rotation of the turbine disc continuously pumps the air in the disc cavity, reducing the pressure in the cavity. When the pumping flow is greater than the cooling air supply flow, Gas backflow occurs at the rim of the turbine disk; ③The mutual interference of the rotor and stator in the main channel causes the circumferential pressure fluctuation of the main gas, which will form gas backflow at the rim of the turbine disk; The blade load, secondary flow distribution and aerodynamic performance of the main flow area have a significant impact, and the greater the sealing flow, the more obvious the effect

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