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Alternator type dynamometer system for aeroengine

A technology of alternators and aero-engines, which is applied in the field of measuring the power extraction of aero-engines, and achieves the effect of wide working range and wide application range

Inactive Publication Date: 2019-05-03
中国航发贵阳发动机设计研究所
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

No domestic and foreign technical literature on measuring the output power of aeroengines using alternators based on suspended test benches was found

Method used

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  • Alternator type dynamometer system for aeroengine
  • Alternator type dynamometer system for aeroengine
  • Alternator type dynamometer system for aeroengine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0036] Design and manufacture of alternators for aero-engines: the operating speed of the alternator needs to meet the engine output speed of 19000rpm, and the maximum loading power needs to meet the alternator loading requirements of various types of aero-engines. First of all, statistically analyze the loaded operating speed and load power of the alternators of various types of aero-engines, and integrate the maximum value. After calculation, the maximum power output of a single alternator is 100kW, so the output power of the alternator is required to reach 2000rpm 100kW. Combined with the installation environment of the test bench, the technical conditions of the alternator are put forward. Due to the strict requirements on the installation space of the alternator, the outer diameter of the alternator is not greater than φ210mm, and the total length is not greater than 430mm (the end face of the adapter seat to the end of the alternator does not exceed 600mm) .

[0037] De...

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Abstract

The invention discloses an alternator type dynamometer system for an aeroengine. The system includes an alternator, an aeroengine accessory shaft power adjusting control system and a motor efficiencytest platform, wherein the alternator is driven by an aeroengine for power generation, the amount of power generated is controlled and measured by the aeroengine accessory shaft power adjusting control system, the energy is ultimately consumed by the resistive load heat, and the motor efficiency measurement platform provides motor efficiency for the system. The system is characterized in that thealternator mounted in a high speed suspension mode is utilized to set and measure the aeroengine accessory output shaft power by motor loading, the power of the aircraft accessory output shaft can beset and measured, in combination with an accessory efficiency value, the real power of the engine output is completely transmitted, a problem of evaluation distortion under the engine power extractioncondition caused by increase of the engine working load due to decrease of an efficiency factor in the long-term operation of the accessory is solved. The system is advantaged in that the system belongs to the field of military and civilian general-purposes and the aeroengine accessory loading test technology, and the research technology can be applied to the aeroengine power extraction test.

Description

technical field [0001] The invention belongs to the technical field of power extraction test of an aero-engine ground bench, and relates to the research on a method for measuring the power extraction of an aero-engine. Background technique [0002] Aeroengine power extraction assessment test is an important research project in the development process of aeroengine. The power extraction of the engine mainly transmits the power to the aircraft through the work of the aircraft accessories, and provides power for the aircraft's avionics, hydraulic and other systems. The power extraction test of the aero-engine on the suspension test bench is very important for the aero-engine finalization and batch production. However, in the actual engine test, there are often problems such as long development cycle and high development cost of aircraft accessories. In the test, due to the different power extraction requirements, the aircraft accessories are replaced repeatedly and the loadin...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/00G01R31/34G01R19/165G01K1/02G01F23/00G01L3/00G01R21/06G01P3/00G01K1/024
Inventor 许柯王洪斌刘江范启华
Owner 中国航发贵阳发动机设计研究所
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