Control structure and method used for reducing separation loss of low-pressure turbine blades

Abstract

The invention discloses a control structure and method used for reducing the separation loss of low-pressure turbine blades. The ultrahigh load low-pressure turbine blades are designed for reducing the weight of an engine and solving the problems that at the cruise state of the aero-engine, the incoming flow air density is low, suction faces of low-pressure turbine blades are prone to separating, the adverse pressure gradient of a diffuser of a blade lattice channel is intensified, the separating loss becomes more serious, and the turbine efficiency is reduced sharply. The control structure and method used for reducing the separation loss of the low-pressure turbine blades are suitable for the high-load and ultrahigh-load low-pressure turbine blades of the aero-engine. Air guiding holes are formed in the appropriate positions of the suction faces of turbine blades, spraying holes are formed in the downstream positions of the air guiding holes, and communicating pipelines are arranged between the air guiding holes and the corresponding spraying holes. According to the structure, air guiding is achieved through the air guiding holes in the upstream wake, the airflow is sprayed to the main flow at the spraying holes at the downstream positions, the airflow energy of an attaching face layer is increased, downstream separating of the spraying holes is eliminated, and therefore the working efficiency of a low-pressure turbine is improved, and the working margin of the low-pressure turbine is enlarged.

Description

technical field [0001] The invention relates to a control structure and method for reducing the separation loss of low-pressure turbine blades, which is suitable for aero-engines and can effectively reduce the separation loss of turbine blades and improve engine efficiency. Background technique [0002] The high bypass ratio turbofan engine has the advantages of low fuel consumption, low pollution and high thrust, and has become the preferred power for civil aircraft today. For an engine with a large bypass ratio, 80% of its thrust comes from the fan part, which is driven by the low-pressure turbine, which results in more stages of the low-pressure turbine and higher weight; at the same time, because the turbine is a hot-end part, the turbine blades are usually The use of denser nickel-based alloys with better high-temperature performance rather than lower-density titanium alloys further increases the weight of the low-pressure turbine. According to statistics, the weight o...

AI Technical Summary

Problems solved by technology

But like all active control schemes, VGJ requires a complex control mechanism and air source supply system, which greatly reduces its applicability

Images