Novel high-pressure turbine of aircraft engine

Abstract

The invention discloses a novel high-pressure turbine of an aircraft engine. The novel high-pressure turbine comprises a plurality of turbine blades and a turbine disc, wherein a plurality of wedged grooves are formed in an outer side of the turbine disc at intervals; each wedged groove is internally provided with a wedged key, and a gap is formed between each wedged groove and the corresponding wedged key; the outer side of each wedged key is connected with two turbine blades; the outer side of each turbine blade is fixedly connected with an inner side of a turbine hoop and is limited by the turbine hoop. The turbine blades are connected with the inner side of the turbine hoop and the turbine blades are not connected with the turbine disc. In a working process, a centrifugal force of the turbine blades falls onto the turbine hoop and the turbine blades completely bear compressive stress, so that a situation that turbine blades of a traditional turbine only bear tensile stress is changed; sufficient condition guarantees are provided for popularization and application of a full-ceramic turbine blade. A combination form of the turbine blades and the turbine disc provides a sufficient free expansion space for heating of the turbine blades and heat stress of the turbine blades is reduced at maximum; impact, caused by vibration, on a turbine shaft can also be alleviated and the service life of the aircraft engine is prolonged.

Description

[0001] 1. Technical field [0002] The invention belongs to the technical field of turbines, and in particular relates to a novel aero-engine high-pressure turbine. [0003] 2. Background technology [0004] The turbine blades of aero-engines are one of the key components in the development of high thrust-to-weight ratio aeroengines. After years of hard work, although my country has made a lot of progress in the materials and casting process of turbine blades, there is still a big gap compared with the international level. For traditional aviation turbines, the turbine blades are inlaid or welded on the turbine disk. When the engine is working normally, the speed exceeds 10,000 rpm, and the turbine blades are subjected to a huge centrifugal load, high temperature oxidation and gas corrosion when they are close to the temperature limit of the material (less than 200°C from the melting point of the alloy). etc. composite effect. The existence of tensile stress corrosion and hi...

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Problems solved by technology

However, ceramics are brittle materials, which are not compressive but not tensi

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