Transition section structure of high-pressure and low-pressure turbines

Abstract

The invention discloses an ultra-compact transition section structure of high-pressure and low-pressure turbines, which can realize the weight reduction and the performance improvement of an engine. The ultra-compact transition section structure is characterized in that a long vane of a supporting plate of a transition section and a short vane of a guiding device of a low-pressure turbine adopt an integrated structural layout with one large vane and one small vane, the long vane is used for realizing the function of the supporting plate and the short vane is used for realizing the function of the guiding device of the low-pressure turbine. The ultra-compact transition section structure can be directly used for a high-performance aviation gas turbine engine; compared with a conventional structural layout with the supporting plate and the transition section structure of the guiding device of the low-pressure turbine, for the structure disclosed by the invention, the transition section with the layout with the one large vane and one small vane of the supporting plate and the guiding device of the low-pressure turbine is adopted, so that the compactness of the transition section of the high-pressure and low-pressure turbines is improved greatly and the aerodynamic performance of the transition section is improved.

Description

technical field [0001] The present invention relates to an ultra-compact high and low pressure turbine transition section structure, in particular to a high and low pressure turbine transition section structure in which the long blades of the support plate and the short and large blades of the low pressure turbine guider are integrated, which can greatly improve the transition between high and low pressure turbines. The compactness and aerodynamic performance of the segment are especially suitable for large bypass ratio aviation gas turbine engines. Background technique [0002] In order to pursue higher economy (high efficiency, low fuel consumption rate, etc.) and environmental friendliness (low emission, low noise, etc.), modern high-performance civil turbofan engines usually use a higher bypass ratio. Coaxial, limited by the fan strength and tangential velocity (inlet shock wave and noise), the low-pressure rotor rotates at a low speed, making the radial span between the...

AI Technical Summary

Problems solved by technology

However, while improving the performance of the high-low pressure turbine transition section, the above-mentioned flow control methods inevitably bring about problems such as complex structure and installation, which greatly limit their application in actual engine models

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