首页> 外国专利> Integral bladed gas turbine rotor for gas turbine aircraft engine, has shrouding band designed as closed ring, and resting against outside sections of rotor blades in resting condition and in operation of rotor by compression stress

Integral bladed gas turbine rotor for gas turbine aircraft engine, has shrouding band designed as closed ring, and resting against outside sections of rotor blades in resting condition and in operation of rotor by compression stress

机译：用于燃气轮机发动机的整体叶片式燃气轮机转子，具有设计成封闭环的覆盖带，并在静止状态下以及在转子工作时因压缩应力而抵靠在转子叶片的外侧部分上

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摘要

The rotor (10) has a rotor base body (11) with multiple rotor blades (12) and a shrouding band (13) attached radially external to the rotor blades. The shrouding band is designed as closed ring, and rests against the outside sections of the rotor blades in a resting condition and in the operation of the gas turbine rotor by compression stress. The rotor blades are welded to the rotor base body. The shrouding band is made of a material e.g. metal matrix composite (MMC) material, carbon fiber reinforced plastic and cemented carbide.

机译：转子（10）具有转子基体（11），该转子基体具有多个转子叶片（12）和在径向上安装在转子叶片外部的覆盖带（13）。覆盖带设计为封闭环，并且在静止状态下以及在燃气轮机转子的运行中由于压缩应力而贴靠在转子叶片的外部上。转子叶片被焊接到转子基体上。覆盖带由例如铝的材料制成。金属基复合材料（MMC），碳纤维增强塑料和硬质合金。

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公开/公告号DE102006025883A1

专利类型
公开/公告日2007-12-06

原文格式PDF
申请/专利权人 MTU AERO ENGINES GMBH;
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申请/专利号DE20061025883
发明设计人 BAYER ERWIN;
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申请日2006-06-02
分类号F01D5/22;F01D5/34;
国家 DE
入库时间 2022-08-21 19:49:56

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