Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Simulation test device for rotor blade loss of aero-engine

An aero-engine, simulation test technology, applied in jet engine testing, gas turbine engine testing, etc., can solve the problems of inability to realize the simulation of the vibration response of the whole machine, insufficient control accuracy of the fly-off speed, and difficulty in the fly-off of the blades, and achieve the structural The effect of high similarity, high security and strong operability

Active Publication Date: 2020-12-01
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
View PDF9 Cites 5 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In previous studies, the simulation of rotor blade loss generally adopts the scheme that the mass block overcomes the friction force of the clamp under the action of centrifugal force. If the flying speed is high, it is difficult for the blades to fly off. If the friction force is small, the blades may fly off at low speeds; the second is that the rotor blade loss test device does not include the casing and the stator structure, and it cannot realize the actual aeroengine blade loss failure. Simulation of the Vibration Response of the Whole Machine

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Simulation test device for rotor blade loss of aero-engine
  • Simulation test device for rotor blade loss of aero-engine
  • Simulation test device for rotor blade loss of aero-engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0032] In order to clearly illustrate the technical characteristics of this patent, the following describes this patent in detail through specific implementation methods and in conjunction with the accompanying drawings. The structure of the aero-engine rotor tester and the installation stand recorded in this case is similar to the structure recorded in the article "Analysis of the Influence of Mounting Joint Stiffness on the Coupled Vibration of the Engine Whole Machine" in the Journal of Aerodynamics, Volume 32, Issue 7, July 2017 .

[0033] The present invention as Figure 1-4 As shown, it includes an installation stand 102 for installing the aero-engine rotor tester 1, a rotary drive assembly for driving and installing the aero-engine rotor tester 1, an L-shaped blade 201 for simulating blades, and an L-shaped blade for impacting. Impact system 4 of 201;

[0034] The L-shaped blade 201 is fixedly connected to the output shaft of the aero-engine rotor tester 1, and the ro...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention discloses a simulation test device for rotor blade loss of an aero-engine and relates to the technical field of the blade loss tests of aero-engines. According to the simulation test device for the rotor blade loss of the aero-engine, the situation that a rotor blade flies out after being broken can be effectively simulated, the flying-off rotating speed of the blade can be effectively controlled, and therefore a rotor blade loss simulation test can be conveniently conducted. The device comprises a mounting rack 102 used for mounting an aero-engine rotor tester 1, a rotation driving assembly used for driving the aero-engine rotor tester 1, an L-shaped blade 201 used for simulating the blade, and an impact system 4 used for impacting the L-shaped blade 201. The device has theadvantages of wide blade loss rotating speed control range, high precision, high structural similarity, high operability, good repeatability, high safety and the like on the whole.

Description

technical field [0001] The invention relates to the technical field of aeroengine blade loss testing. Background technique [0002] Aeronautical gas turbine engine (referred to as "aero engine") is a high-speed rotating complex thermodynamic machinery. With the improvement of modern aero-engine's comprehensive requirements for high thrust-to-weight ratio and high performance, its speed and workload are constantly increasing and increasing. Presenting the mechanical characteristics of "softness" and "heavy load", the challenges faced by structural and dynamic design have increased significantly. In addition to satisfying the strength design under normal loads, it is also necessary to realize the safety design of the whole machine under extreme severe load conditions . [0003] Blade loss is a typical severe load condition that an aero-engine may encounter. It refers to a part or the entire rotor blade that breaks and flies out. It can be caused by bird strikes or other forei...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/14
CPCG01M15/14
Inventor 杨默晗陈果于平超张凯勇
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com