Base-movable aeroengine dual-rotor system model experiment platform

A technology of aero-engine and system model, which is applied in the field of aero-engine and can solve problems such as single function and inability to effectively simulate rotor system.

Active Publication Date: 2013-09-18
TIANJIN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In the research on the dynamics of the high and low pressure dual rotor system of the aero-engine, in order to overcome the shortcomings of the existing rotor system experimental device with single function and the inability to effectively simulate the actual r

Method used

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  • Base-movable aeroengine dual-rotor system model experiment platform
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  • Base-movable aeroengine dual-rotor system model experiment platform

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[0033] The present invention will be further described in detail below in conjunction with specific embodiments.

[0034] Such as figure 1 with figure 2 As shown, a basic sports aero-engine dual-rotor system model test bed of the present invention includes a basic turntable base 1 fixed on the ground, and a coaxial pitch drive shaft A3 and a pitch drive shaft are provided on the basic turntable base 1 B22, a basic turntable support 24 is supported between the pitch drive shaft A3 and the pitch drive shaft B22, the basic turntable support 24 is provided with a main drive shaft 5, and a basic turntable 6 is fixed on the main drive shaft 5.

[0035] It also includes internal and external dual rotor systems, such as figure 2 As shown, the inner and outer dual-rotor system includes a dual-rotor system experimental platform base 7 fixed to the basic turntable 6, an inner rotor 12, an outer rotor 17, a bearing seat A, a bearing seat B, a bearing seat C, and an inner rotor low pressure ai...

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Abstract

The invention discloses a base-movable aeroengine dual-rotor system model experiment platform, which comprises a base rotary table seat, a transmission shaft A, a transmission shaft B, a base rotary table and an inner rotor and outer rotor subsystem, and the transmission shaft A and the transmission shaft B can synchronously rotate; the inner rotor and outer rotor subsystem mainly comprises an inner rotor, an outer rotor, an inner rotor low-pressure compressor rotary table, an inner rotor low-pressure turbine rotary table, an outer rotor high-pressure compressor rotary table, an outer rotor high-pressure turbine rotary table, three bearing blocks (A, B, C) and a rotor system base fixedly connected with the base rotary table; the inner rotor is inserted in an outer rotor and supported on the bearing blocks (A, B), the bearing block A is a damping-adjustable support, and the bearing block B is a flexible support; one end of the outer rotor is supported on the inner rotor by ball bearings, and the other end of the outer rotor is supported on the bearing block C, which is a flexible support; and infrared optical sensors and eddy current sensors are arranged on both the inner rotor and the outer rotor to test the vibration signal of the system. The base-movable aeroengine dual-rotor system model experiment platform can effectively simulate the dynamic experiment of a dual-rotor system of an aeroengine under actual working conditions.

Description

technical field [0001] The invention belongs to the technical field of aero-engines, and in particular relates to a comprehensive dynamic experiment device composed of a two-axis basic turntable providing basic motion and an aero-engine double-rotor model test bench. Background technique [0002] At present, most of the rotor system dynamics experimental devices used by scientific research institutions are single-span or multi-span (serial and parallel) single-rotor dynamics test benches, a few are dual-rotor experimental devices, and all rotor dynamics test benches have no Considering the factors of basic motion, the use of such experimental devices for dynamic experiments must not reflect the real dynamics of the high-low pressure dual-rotor system of the aero-engine under maneuvering flight conditions. [0003] For any dynamic experimental device of rotating machinery, the principles of structural similarity, kinematics similarity and dynamics similarity must be satisfied...

Claims

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Application Information

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IPC IPC(8): G01M15/00G01M13/02
Inventor 曹树谦杨蛟白雪川陈予恕
Owner TIANJIN UNIV
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