A gas turbine engine integrated turbine guide with thermal deformation compensation structure

Abstract

The invention provides a gas turbine engine integral turbine guide device with a heat deformation compensating structure. The heat deformation compensating structure is characterized in that a plurality of circumferential cuts are cut in an inner ring and / or outer ring of the guide device, and the direction of the circumferential cuts is basically the same as the blade type chord length direction of a blade root section. The heat deformation compensation structure is creatively designed, and compared with a segmented turbine guide device, the guide device with the heat deformation compensation structure can effectively reduce circumferential leakage of the inner ring of high pressure gas, and performance of an engine is ensured, and meanwhile, the number of parts is reduced; compared with a conventional whole-ring type guide device, the guide device with the heat deformation compensation structure can effectively reduce heat stress generated by discordance of inner ring heat deformation and outer ring heat deformation, and therefore the service life of the guide device is prolonged, so that the reliability of the guide device is improved; and the technical problem that inner ring heating deformation and outer ring heating deformation of the turbine guide device are not matched, and the circumferential direction of a wing plate is sealed tightly is well solved.

Description

technical field [0001] The invention relates to the technical field of turbines, more specifically, to an integrated turbine guide for a gas turbine engine or a guide for a high-pressure turbine of a ground combustion engine with a thermal deformation compensation structure. Background technique [0002] The high-pressure turbine guide of the gas turbine engine and the ground gas turbine is one of the main parts forming the airflow channel, which consists of a certain number of guide vanes and inner and outer rings. The inner and outer rings form an annular channel, and the blades are evenly distributed between the inner and outer rings along the circumference. The high-temperature and high-pressure gas from the combustion chamber flows through the space between the inner and outer rings of the guide and the blades. Depending on the advanced level of the engine, the temperature and pressure of the gas are also different. The pressure can reach 10 to 20 pressures or even hig...

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is to overcome the problems of the heat deformation mismatch between the inner and outer rings of the existing gas turbine engine turbine integrated guide or the high-pressure turbine guide of the ground gas turbine and the circumferential sealing of the edge plate, and provide a A gas turbine engine turbine integrated guide or a high-pressure turbine guide for a ground gas turbine with a thermal deformation compensation structure that can reduce the thermal stress on the inner and outer rings of the guide and ensure that the guide is sealed in the circumferential direction. After the thermal deformation compensation structure, the thermal stress of the edge plate of the guide can be well compensated, and the service life and reliability of the guide structure can be improved

Images