Gas turbine engine comprising three rotary bodies

A technology for gas turbines and engines, applied in gas turbine installations, engine components, machines/engines, etc., can solve the problems of heavy engine weight, limit fuel saving, etc., and achieve the effect of weight and size optimization, length and weight reduction
CN103562518AInactive Publication Date: 2014-02-05SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
Publication Date
2014-02-05
Estimated Expiration
Not applicable · inactive patent

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Abstract

The invention relates to a gas turbine engine for propelling an aircraft, comprising: a low-pressure rotary body (10) having mobile low-pressure turbine blades (10T), an intermediary rotary body (20) having mobile intermediary turbine blades (20T), a high-pressure rotary body (30) having mobile high-pressure turbine blades (30T), a flow of air flowing through the engine from upstream to downstream. According to the invention, at least one mobile intermediary turbine blade (20T) is followed directly downstream by a mobile low-pressure turbine blade (10T) such as to straighten the flow of air deflected by the mobile intermediary turbine blade (20T).
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Description

technical field

[0001] This invention relates to the field of gas turbine engines used to propel aircraft. Background technique

[0002] Hereinafter, the terms "upstream" and "downstream" are defined according to the flow direction of the airflow in the engine. Generally, a gas turbine engine includes, from upstream to downstream, a low-pressure compressor, a high-pressure compressor, a combustor, a high-pressure turbine, and a low-pressure turbine. To this end, the engine includes a low pressure mandrel supporting the compressor and turbine rotor blades and a high pressure mandrel supporting the compressor and turbine rotor blades. Upstream, the low-pressure compressor comprises, in a known manner, large rotor blades called "fans" by those skilled in the art.

[0003] One of the ways to limit the fuel consumption of the engine is to reduce the speed of the fan blades to increase the bypass ratio of the engine, that is, the air mass of the bypass flow (air mass that is exp...

Claims

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