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Turbine rotor blade

A technology of turbine rotors and blades, which is applied to the supporting elements of blades, engine elements, machines/engines, etc., can solve the problems of inability to meet the needs of engine use, short lasting life of high-pressure turbine rotor blades, etc., to improve maturity and service life. improved effect

Inactive Publication Date: 2019-11-19
中国航发贵阳发动机设计研究所
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Problems solved by technology

[0004] The purpose of the present invention is to aim at the higher overall technical index requirements of the existing aviation gas turbofan engine, and to invent a turbine rotor blade by using DD32 single crystal material, so as to solve the problem of the high-pressure turbine rotor blade durability of the existing aviation gas turbofan engine. The service life is short and cannot meet the needs of the engine

Method used

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Embodiment Construction

[0019] Below, combine figure 1 , figure 2 , image 3 , the present invention will be further described in detail through specific embodiments. The following implementations are only descriptive, not restrictive, and cannot limit the protection scope of the present invention.

[0020] Depend on figure 1 It can be seen that a turbine rotor blade made of DD32 single crystal alloy according to the present invention includes a blade body 1, an edge plate 2, and a tenon 3, and is a hollow cast blade, and the blade body part is divided into a blade basin 4, an inner cavity 5, a blade The back is 6, and the trailing edge is in the form of opening splits. The present invention has taken following technical scheme:

[0021] Among them, in order to improve the long-lasting life of the blade, the material of the blade is designed with DD32 single-crystal alloy, which utilizes the characteristics of high-temperature resistance and long-lasting creep strength of DD32 single-crystal al...

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Abstract

The invention belongs to the technical field of turbomachinery, and particularly relates to a turbine rotor blade. The blade is a hollow blade without crown integrally formed by a blade body, a flangeplate and a tenon; and the blade body is designed as an airfoil like hollow structure, and a partition wall and a plurality of disturbing columns are distributed in an inner cavity of the blade body.According to the turbine rotor blade, the service life of the turbine rotor blade is prolonged by at least 4 times to meet the service demand of the whole life of an existing aviation gas turbine fanengine; and at the same time, the situation that a DD32 single crystal alloy material is applied to the blade is proposed, and the deformation resistance is further improved under the condition of large load, so that the high temperature resistance of the blade is greatly improved, and the service life of the blade is greatly prolonged.

Description

technical field [0001] The invention belongs to the technical field of turbomachinery, and in particular relates to a turbine rotor blade; in particular, it relates to a turbine rotor blade using domestic newly developed DD32 single crystal material. Background technique [0002] Turbine is one of the key core components of aviation gas turbine fan engine. Its function is to convert the thermal energy and kinetic energy of the engine into mechanical energy. The turbine rotor blade is a core part of energy conversion in turbine components. Its working environment is very harsh and long-term The working temperature is above 1000°C and the speed is above 10000r / min. It bears huge centrifugal force, thermal stress and aerodynamic bending moment load, is scoured and corroded by high-temperature gas, and is also affected by high and low frequency vibration stress, and the load occurs periodically Changes, therefore, require turbine rotor blades to be resistant to high temperature,...

Claims

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Application Information

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IPC IPC(8): F01D5/18F01D5/28
CPCF01D5/188F01D5/28
Inventor 李义平杨升林亚靳福来林垲梁湘华张溯朱培模石伟蒋竞升
Owner 中国航发贵阳发动机设计研究所
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